AIR VEHICLE

• US 20120267472A1
• Filed: 06/02/2010
• Published: 10/25/2012
• Est. Priority Date: 06/08/2009
• Status: Abandoned Application

• Current Assignee: ELTA Systems Limited (Government of Israel)
• Original Assignee: ELTA Systems Limited (Government of Israel)
• Inventors: Pratzovnick, Arie, Ron, Shmuel
• Application Number:
  US13/376,446
• Publication Number:
  US 20120267472A1
• Time in Patent Office: Days
• US Class Current: 244/13
• CPC Class Codes: B64C 1/26 Attaching the wing or tail units or stabilising surfaces
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: G01S 7/021 Auxiliary means for detecting or identifying radar signals or the like, e.g. radar jamming signals
• CPC Class Codes: G01S 7/38 Jamming means, e.g. producing false echoes
• CPC Class Codes: H04K 2203/22 for communication related to vehicles
• CPC Class Codes: H04K 2203/32 including a particular configuration of antennas
• CPC Class Codes: H04K 2203/34 involving multiple cooperating jammers
• CPC Class Codes: H04K 3/45 characterized by including monitoring of the target or target signal, e.g. in reactive jammers or follower jammers for example by means of an alternation of jamming phases and monitoring phases, called "look-through mode"
• CPC Class Codes: H04K 3/825 by jamming

Abstract

A sensor/emitter arrangement (M1-M3) is integrated into the fuselage (120) structure of a specially designed air vehicle (100), in which the air vehicle is configured for optimizing operation of the sensor/emitter arrangement (M1-M3) with respect to at least azimuthal lines of sight radiating along a azimuthal reference plane of the air vehicle (100). The azimuthal reference plane intersects the air vehicle fuselage (120). In at least some embodiments, the fuselage (120) is formed with a plurality of oblate cross-sections that facilitate maximizing the room available for a sensor/emitter array (172, 174, 176) that is elongated along an elongate axis that may be aligned with the azimuthal reference plane. In at least some embodiments one or more such elongate axes may be inclines to the longitudinal (roll) axis and the pitch axis of the air vehicle (100). In at least some embodiments, the air vehicle may have a blunt aft end incorporating an elongate aft-facing sensor/emitter array (172, 174, 176).

Claims

1. An air vehicle, comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

a sensor/emitter arrangement configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage;

wherein said sensor/emitter arrangement comprises at least one sensor/emitter array, the or each said sensor/emitter array comprising a sensing/emitting face configured for said at least one of sensing and emitting energy and that is elongated with respect to an elongation axis, and wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis; and

wherein said fuselage is configured for integrating said sensor/emitter arrangement therein for enabling optimizing operation of said sensor/emitter arrangement.

2. The air vehicle according to claim 1, wherein said elongation axis is generally aligned with said reference azimuthal plane of said air vehicle.

3. The air vehicle according to claim 1 or claim 2, wherein at least a part of said fuselage is formed having a generally oblate cross-section perpendicular to said longitudinal axis for accommodating therein at least a portion of said sensor/emitter arrangement, and wherein said vehicle comprises an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, greater than unity.

4. The air vehicle according to claim 3, wherein said inverse oblateness ratio is greater than about 1.5.

5. The air vehicle according to any one of claims 1 to 4, wherein said fuselage comprises a first fineness ratio, taken as a ratio of said fuselage length to said fuselage width, of less than about 5.0.

6. The air vehicle according to any one of claims 1 to 5, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

7. The air vehicle according to any one of claims 1 to 6, wherein said sensor/emitter arrangement comprises a plurality of said sensor/emitter arrays, each sensor/emitter array being configured for operating to at least one of provide sensor data and emit energy for a respective portion of a 360 degree azimuth volume with respect to the air vehicle referenced to said at least one azimuthal reference plane.

8. The air vehicle according to claim 7, wherein said sensor/emitter arrangement is configured for operating with respect to a substantially continuous 360 degree azimuth volume with respect to the air vehicle referenced to said azimuthal reference plane.

9. The air vehicle according to any one of claims 7 to 8, wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof facing one of said forward direction and said aft direction along the longitudinal axis.

10. The air vehicle according to any one of claims 7 to 9, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

11. The air vehicle according to claim 10, wherein said aft end comprises an aerodynamically blunt aft end.

12. The air vehicle according to claim 10, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

13. The air vehicle according to any one of claims 10 to 12, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

14. The air vehicle according to any one of claims 9 to 13, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

15. The air vehicle according to claim 14, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis, in plan view.

16. The air vehicle according to claim 15, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees or an angle of 60 degrees with respect to said longitudinal axis, in plan view.

17. The air vehicle according to any one of claims 9 to 17, comprising three said sensor/emitter arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

19. The air vehicle according to any one of claims 9 to 16, comprising four or more said sensor/emitter arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

20. The air vehicle according to any one of claims 9 to 19, wherein each sensor/emitter array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate axis, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

21. The air vehicle according to any one of claims 7 to 20, each said sensor/emitter array being further configured for providing said sensor data in elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

22. The air vehicle according to claim 21, wherein said sensor/emitter arrangement is configured for operating with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

23. The air vehicle according to any one of claims 7 to 22, each said sensor/emitter array being further configured operating with respect to elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

24. The air vehicle according to any one of claims 9 to 23, wherein said sensor/emitter arrays are configured for providing substantially similar sensor/emitter performance one to another, at least with respect to one of:

sensor maximum range, sensor/emitter field of view in azimuth, sensor/emitter field of view in elevation with respect to said azimuthal reference plane.

25. The air vehicle according to any one of claims 9 to 24, wherein said sensor/emitter arrangement comprises a radar arrangement, and each said sensor/emitter array comprise a respective radar array configured for at least detecting a target.

26. The air vehicle according to claim 25, wherein said radar arrays comprise phase radar arrays.

27. The air vehicle according to any one of claims 1 to 26, wherein said air vehicle comprises a propulsion system dorsally mounted on said fuselage.

28. The air vehicle according to any one of claims 1 to 27 wherein said air vehicle is configured as a UAV or as a manned air vehicle, and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

29. The air vehicle according to any one of claims 1 to 28, wherein the air vehicle is free of additional tail arrangement.

30. The air vehicle according to any one of claims 7 to 32, wherein each said sensor/emitter array is comprised in a respective compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

31. The air vehicle according to claim 30, wherein at least one said sensor/emitter array is a radar array, and the respective fairing thereof is made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array, and wherein said fairings each comprise a smooth rounded shape.

32. The air vehicle according to any one of claims 1 to 31, wherein said fuselage has an outer surface that is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor/emitter array, and which forms part of an external skin of said air vehicle.

33. The air vehicle according to any one of claims 1 to 32, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

34. The air vehicle according to any one of claims 1 to 33, wherein said wing arrangement comprises an integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

35. The air vehicle according to any one of claims 7 to 35, wherein in plan view or in bottom view at least a majority of each said sensor/emitter array is free from superposition by said wings.

36. The air vehicle according to any one of claims 7 to 35, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

37. The air vehicle according to any one of claims 7 to 36, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

38. The air vehicle according to any one of claims 7 to 39, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

39. The air vehicle according to claim 38, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

40. The air vehicle according to any one of claims 1 to 39, wherein sensor/emitter arrangement may include one or more of a radar jammer arrangement, a passive radar detector, a SIGINT module, an ELINT module, and a COMINT module, a guard antenna, IFF (identify friend or foe) elements, radio transmitting elements.

122. The air vehicle according to claim 1, wherein said elongation axis is generally aligned with said reference azimuthal plane of said air vehicle corresponding to said azimuthal volume.

18. The air vehicle according to claim 18, wherein said triangle is an equilateral triangle or an isosceles triangle.

41. An air vehicle comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

a sensor/emitter arrangement configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage;

said fuselage being configured for integrating said sensor/emitter arrangement therein for enabling optimizing operation of said sensor/emitter arrangement, and said fuselage comprising a fuselage fineness ratio including at least one of;

a first fineness ratio, taken as a ratio of said fuselage length to said fuselage height, wherein said first fineness ratio is less than about 5;

a second fineness ratio, taken as a ratio of said fuselage length to said fuselage width, wherein said first fineness ratio is less than about 6;

an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, wherein said inverse oblateness ratio is greater than 1.5.

42. The air vehicle according to claim 41, wherein the air vehicle is free of additional tail arrangement.

43. The air vehicle according to any one of claim 41 or 42, wherein at least a part of said fuselage is formed having a generally oblate cross-section perpendicular to said longitudinal axis for accommodating therein at least a portion of said sensor/emitter arrangement.

44. The air vehicle according to any one of claims 41 to 43, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array, the or each said sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

45. The air vehicle according to claim 44, wherein said elongation axis is generally aligned with the reference azimuthal plane of said air vehicle.

46. The air vehicle according to any one of claims 44 to 45, wherein said sensor/emitter arrangement comprises a plurality of said sensor/emitter arrays, each sensor/emitter array being configured for operating to at least one of provide said sensor data and emit energy for a respective portion of a 360 degree azimuth volume with respect to the air vehicle referenced to the azimuthal reference plane.

47. The air vehicle according to claim 46, wherein said sensor/emitter arrangement is configured for operating with respect to a substantially continuous 360 degree azimuth volume with respect to the air vehicle referenced to said azimuthal reference plane.

48. The air vehicle according to any one of claims 46 to 47, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

49. The air vehicle according to any one of claims 46 to 48, wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof facing one of said forward direction and said aft direction.

50. The air vehicle according to claim 49, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

51. The air vehicle according to claim 50, wherein said aft end comprises an aerodynamically blunt aft end.

52. The air vehicle according to any one of claims 50 and 51, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

53. The air vehicle according to any one of claims 50 to 52, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

54. The air vehicle according to any one of claims 46 to 53, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

55. The air vehicle according to claim 54, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis, in plan view.

56. The air vehicle according to claim 55, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees with respect to said longitudinal axis, and an angle of 60 degrees with respect to said longitudinal axis, in plan view.

57. The air vehicle according to any one of claims 46 to 56, comprising three said sensor/emitter arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

58. The air vehicle according to claim 57, wherein said triangle is an isosceles triangle or an equilateral triangle.

59. The air vehicle according to any one of claims 46 to 56, comprising four or more said sensor/emitter arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

60. The air vehicle according to any one of claims 46 to 59, wherein each sensor/emitter array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate axis, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

61. The air vehicle according to any one of claims 46 to 60, each said sensor/emitter array being further configured for operating with respect to elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

62. The air vehicle according to claim 61, wherein said sensor/emitter arrangement is configured for operating with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

63. The air vehicle according to any one of claims 46 to 62, each said sensor/emitter array being further configured for operating with respect to elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

64. The air vehicle according to any one of claims 46 to 64, wherein said sensor/emitter arrays are configured for providing substantially similar sensor/emitter performance one to another, at least with respect to one of:

sensor/emitter maximum range, sensor/emitter field of view in azimuth, sensor/emitter field of view in elevation with respect to said azimuthal reference plane.

65. The air vehicle according to any one of claims 41 to 64, wherein sensor/emitter arrangement may include one or more of:

a radar jammer arrangement, a passive radar detector, a SIGINT module, an ELINT module, and a COMINT module, a guard antenna, IFF (identify friend or foe) elements, radio transmitting elements.

66. The air vehicle according to any one of claims 46 to 65, wherein said sensor/emitter arrangement comprises a radar arrangement, and each said sensor/emitter array comprises a respective radar array for at least detecting a target.

67. The air vehicle according to claim 66, wherein said radar arrays comprise phase radar arrays.

68. The air vehicle according to any one of claims 41 to 67, wherein said air vehicle comprises a propulsion system dorsally mounted on said fuselage.

69. The air vehicle according to any one of claims 41 to 68 wherein said air vehicle is configured as a UAV or as a manned air vehicle and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

70. The air vehicle according to any one of claims 46 to 69, wherein each said sensor/emitter array is comprised in a respective compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

71. The air vehicle according to claim 70, wherein at least one said sensor/emitter array is a radar array, and the respective fairing thereof is made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array.

72. The air vehicle according to any one of claims 70 to 71, wherein said fairings each comprise a smooth rounded shape.

73. The air vehicle according to any one of claims 41 to 72, wherein said fuselage has an outer surface that is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor array, and which forms part of an external skin of said air vehicle.

74. The air vehicle according to any one of claims 41 to 73, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

75. The air vehicle according to any one of claims 41 to 74, wherein said wing arrangement comprises a integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the wing.

76. The air vehicle according to any one of claims 44 to 75, wherein in plan view or in bottom view at least a majority of each said sensor/emitter array is free from superposition by said wings

77. The air vehicle according to any one of claims 46 to 76, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

78. The air vehicle according to any one of claims 46 to 77, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

79. The air vehicle according to any one of claims 46 to 78, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

80. The air vehicle according to claim 79, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

87. The air vehicle according to claim 44, wherein said elongation axis is generally aligned with an azimuthal plane of said air vehicle.

81. An air vehicle comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

a sensor/emitter arrangement configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage;

the fuselage being configured for integrating said sensor/emitter arrangement therein for enabling optimizing operation of said sensor/emitter arrangement;

the air vehicle being free of additional tail arrangement.

82. The air vehicle according to claim 81, wherein at least a part of said fuselage is formed having a generally oblate cross-section perpendicular to said longitudinal axis for accommodating therein at least a portion of said sensor/emitter arrangement.

83. The air vehicle according to any one of claim 81 or 82, wherein said vehicle comprises an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, greater than unity, and wherein said inverse oblateness ratio is greater than about 1.5.

84. The air vehicle according to any one of claims 81 to 83, wherein said fuselage comprises a first fineness ratio, taken as a ratio of said fuselage length to said fuselage width, of less than about 5.0.

85. The air vehicle according to any one of claims 81 to 84, wherein sensor/emitter arrangement may include one or more of:

a radar jammer arrangement, a passive radar detector, a SIGINT module, an ELINT module, and a COMMIT module, a guard antenna, IFF (identify friend or foe) elements, radio transmitting elements.

86. The air vehicle according to any one of claims 81 to 85, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

88. The air vehicle according to any one of claims 86 to 87, wherein said sensor/emitter arrangement comprises a plurality of said sensor/emitter arrays, each said sensor/emitter array being configured for operating to at least one of provide sensor data and emit energy for a respective portion of a 360 degree azimuth volume with respect to the air vehicle referenced to said at least one azimuthal reference plane.

89. The air vehicle according to claim 88, wherein said sensor/emitter arrangement is configured for operating with respect to a substantially continuous 360 degree azimuth volume with respect to the air vehicle referenced to said azimuthal reference plane.

90. The air vehicle according to any one of claim 88 or 89, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

91. The air vehicle according to any one of claim 88 or 90, wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof facing one of said forward direction and said aft direction.

92. The air vehicle according to claim 91, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

93. The air vehicle according to claim 92, wherein said aft end comprises an aerodynamically blunt aft end.

94. The air vehicle according to claim 92, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

95. The air vehicle according to any one of claims 92 to 94, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

96. The air vehicle according to any one of claims 91 to 95, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

97. The air vehicle according to claim 96, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis.

98. The air vehicle according to claim 97, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees or an angle of 60 degrees with respect to said longitudinal axis.

99. The air vehicle according to any one of claims 88 to 98, comprising three said arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

100. The air vehicle according to claim 99, wherein said triangle is an equilateral triangle or an isosceles triangle.

101. The air vehicle according to any one of claims 88 to 98, comprising four or more said sensor/emitter arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

102. The air vehicle according to any one of claims 88 to 101, wherein each sensor/emitter array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate axis, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

103. The air vehicle according to any one of claims 88 to 102, each said sensor/emitter array being further configured operating with respect to elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

104. The air vehicle according to claim 103, wherein said sensor/emitter arrangement is configured for operating with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

105. The air vehicle according to any one of claims 88 to 104, each said sensor/emitter array being further configured operating with respect to elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

106. The air vehicle according to any one of claims 88 to 105, wherein said sensor/emitter arrays are configured for providing substantially similar sensor/emitter performance one to another, at least with respect to one of:

sensor/emitter maximum range, sensor/emitter field of view in azimuth, sensor/emitter field of view in elevation with respect to said azimuthal reference plane.

107. The air vehicle according to any one of claims 88 to 106, wherein said sensor/emitter arrangement comprises a radar arrangement, and each said sensor/emitter array comprise a respective radar array for at least detecting a target.

108. The air vehicle according to claim 107, wherein said radar arrays comprise phase radar arrays.

109. The air vehicle according to any one of claims 81 to 108 wherein said air vehicle is configured as a UAV or as a manned air vehicle, and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

110. The air vehicle according to any one of claims 88 to 109, wherein each said sensor/emitter array is comprised in a respective compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

111. The air vehicle according to claim 110, wherein at least one said sensor/emitter array is a radar array, and the respective fairing thereof is made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array.

112. The air vehicle according to any one of claims 110 to 111, wherein said fairings each comprise a smooth rounded shape.

113. The air vehicle according to any one of claims 88 to 115, wherein said fuselage has an outer surface that is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor array, and which forms part of an external skin of said air vehicle.

114. The air vehicle according to any one of claims 81 to 113, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

115. The air vehicle according to any one of claims 81 to 113, wherein said wing arrangement comprises a integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

116. The air vehicle according to any one of claims 86 to 119, wherein in plan view or in bottom view at least a majority of the or each said sensor/emitter array is free from superposition by said wings.

117. The air vehicle according to any one of claims 88 to 116, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

118. The air vehicle according to any one of claims 88 to 117, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

119. The air vehicle according to any one of claims 88 to 118, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

120. The air vehicle according to claim 119, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

121. An airborne radar system configured for providing surveillance coverage throughout at least a portion of a 360 degree azimuth volume, comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

a radar system comprising a plurality of antenna structures, each having a respective field of view;

the fuselage comprising a plurality of internal compartments peripherally disposed with respect thereto and each compartment configured for enabling integrating therein a respective said antenna structure;

wherein at least one said antenna structure comprises a respective sensing/emitting face that is elongated along an elongation axis and is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

123. The air vehicle according to any one of claim 121 or 122, wherein said vehicle comprises an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, greater than unity, and wherein said inverse oblateness ratio is greater than about 1.5.

124. The air vehicle according to any one of claims 121 to 124, wherein said fuselage comprises a first fineness ratio, taken as a ratio of said fuselage length to said fuselage width, of less than about 5.0.

125. The air vehicle according to any one of claims 121 to 126, wherein said antenna structures each comprises a radar array, each radar array being configured for providing radar data for a respective portion of said 360 degree azimuth volume with respect to the air vehicle.

126. The air vehicle according to claim 127, wherein said radar system is configured for providing said radar data for a substantially continuous 360 degree azimuth volume with respect to the air vehicle.

127. The air vehicle according to any one of claim 127 or 128, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

128. The air vehicle according to any one of claims 121 to 127, wherein at least one said antenna structure is arranged with the respective sensing/emitting face thereof facing one of said forward direction and said aft direction.

129. The air vehicle according to any one of claims 121 to 128, wherein at least one said radar array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

130. The air vehicle according to claim 129, wherein said aft end comprises an aerodynamically blunt aft end.

131. The air vehicle according to any one of claims 129 and 130, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

132. The air vehicle according to any one of claims 129 to 131, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

133. The air vehicle according to any one of claims 126 to 132, wherein at least one said radar array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

134. The air vehicle according to claim 133, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis, in plan view.

135. The air vehicle according to claim 134, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees or an angle of 60 degrees with respect to said longitudinal axis, in plan view.

136. The air vehicle according to any one of claims 126 to 135, comprising three said arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

137. The air vehicle according to claim 136, wherein said triangle is an equilateral triangle or an isosceles triangle.

138. The air vehicle according to any one of claims 126 to 134, comprising four or more said radar arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

139. The air vehicle according to any one of claims 126 to 138, wherein each radar array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate direction, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

140. The air vehicle according to any one of claims 126 to 139, each said radar array being further configured for providing said radar data in elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

141. The air vehicle according to claim 140, wherein said radar arrangement is configured for providing said radar data from a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

142. The air vehicle according to any one of claims 126 to 141, each said radar array being further configured for providing said radar data in elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

143. The air vehicle according to any one of claims 126 to 142, wherein said radar arrays are configured for providing substantially similar radar performance one to another, at least with respect to one of:

maximum range, field of view in azimuth, field of view in elevation with respect to said azimuthal reference plane.

144. The air vehicle according to any one of claims 126 to 143, wherein said radar arrays comprise phase radar arrays.

145. The air vehicle according to any one of claims 121 to 144, wherein said air vehicle comprises a propulsion system dorsally mounted on said fuselage.

146. The air vehicle according to any one of claims 121 to 145 wherein said air vehicle is configured as a UAV or as a manned air vehicle, and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

147. The air vehicle according to any one of claims 126 to 146, wherein each said radar array is mounted in a respective said compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

148. The air vehicle according to claim 147, wherein said fairings are made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array.

149. The air vehicle according to any one of claims 147 to 148, wherein said fairings each comprise a smooth rounded shape.

150. The air vehicle according to any one of claims 147 to 148, wherein said fuselage has an outer surface that is faceted, and wherein each said radar array comprises a respective said fairing that is substantially flat and spaced from the respective sensor array, and which forms part of an external skin of said air vehicle.

151. The air vehicle according to any one of claims 121 to 150, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

152. The air vehicle according to any one of claims 121 to 150, wherein said wing arrangement comprises a integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

153. The air vehicle according to any one of claims 126 to 152, wherein in plan view or in bottom view at least a majority of each said radar array is free from superposition by said wings.

154. The air vehicle according to any one of claims 121 to 153, the air vehicle being free of additional tail arrangement.

155. The air vehicle according to any one of claims 121 to 154, further comprising one or more additional sensors or transmitters accommodated in said compartments.

156. The air vehicle according to claim 155, wherein said additional sensors or transmitters may include one or more of a radar jammer arrangement, a passive radar detector, a SIGINT module, an ELINT module, and a COMINT module, a guard antenna, IFF (identify friend or foe) elements, radio transmitting elements.

157. The air vehicle according to any one of claims 121 to 156, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said radar arrays, wherein a majority of each said cross-section is occupied by the respective said array.

158. The air vehicle according to any one of claims 121 to 157, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said radar arrays.

159. The air vehicle according to any one of claims 121 to 158, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the radar arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

160. The air vehicle according to claim 159, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

161. An air vehicle, comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

the fuselage comprising a blunt aft end; and

the air vehicle being free of additional tail arrangement.

162. The air vehicle according to claim 161, wherein said fuselage is configured for integrating said sensor/emitter arrangement therein for enabling optimizing operation of said sensor/emitter arrangement, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array, the or each said sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and configured for enabling at least one said sensor/emitter array to be arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

163. The air vehicle according to claim 162, further comprising the sensor/emitter arrangement, wherein the sensor/emitter arrangement is configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage.

164. The air vehicle according to claim 163, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

165. The air vehicle according to claim 164, wherein said elongation axis is generally aligned with an azimuthal plane of said air vehicle.

166. The air vehicle according to any one of claims 162 to 165, wherein at least a part of said fuselage is formed having a generally oblate cross-section perpendicular to said longitudinal axis for accommodating therein at least a portion of the sensor/emitter arrangement, and wherein said inverse oblateness ratio is greater than about 1.5.

167. The air vehicle according to any one of claims 161 to 166, wherein said fuselage comprises a first fineness ratio, taken as a ratio of said fuselage length to said fuselage width, of less than about 5.0 or less than about 2.0.

168. The air vehicle according to any one of claims 162 to 167, wherein said sensor/emitter arrangement comprises a plurality of said sensor/emitter arrays, each sensor/emitter array being configured for operating to at least one of provide sensor data and emit energy for a respective portion of a 360 degree azimuth volume with respect to the air vehicle referenced to at least one azimuthal reference plane.

169. The air vehicle according to claim 168, wherein said sensor/emitter arrangement is configured for operating with respect to a substantially continuous 360 degree azimuth volume with respect to the air vehicle referenced to said azimuthal reference plane.

170. The air vehicle according to any one of claim 168 or 169, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

171. The air vehicle according to any one of claims 168 to 170, wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof facing one of said forward and said aft direction.

172. The air vehicle according to any one of claims 168 to 171, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

173. The air vehicle according to claim 172, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

174. The air vehicle according to any one of claims 161 to 173, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

175. The air vehicle according to any one of claims 168 to 174, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

176. The air vehicle according to claim 175, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis, in plan view.

177. The air vehicle according to claim 176, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees or an angle of 60 degrees with respect to said longitudinal axis, in plan view.

178. The air vehicle according to any one of claims 168 to 177, comprising three said arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

179. The air vehicle according to claim 178, wherein said triangle is an equilateral triangle or an isosceles triangle.

180. The air vehicle according to any one of claims 168 to 176, comprising four or more said sensor/emitter arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

181. The air vehicle according to any one of claims 168 to 180, wherein each sensor/emitter array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate direction, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

182. The air vehicle according to any one of claims 168 to 181, each said sensor/emitter array being further configured for operating with respect to elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

183. The air vehicle according to claim 182, wherein said sensor/emitter arrangement is configured for operating with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

184. The air vehicle according to any one of claims 168 to 183, each said sensor/emitter array being further configured for operating with respect to elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

185. The air vehicle according to any one of claims 168 to 184, wherein said sensor/emitter arrays are configured for providing substantially similar sensor/emitter performance one to another, at least with respect to one of:

sensor/emitter maximum range, sensor/emitter field of view in azimuth, sensor/emitter field of view in elevation with respect to said azimuthal reference plane.

186. The air vehicle according to any one of claims 168 to 185, wherein said sensor/emitter arrangement comprises a radar arrangement, and each said sensor/emitter array comprise a respective radar array for at least detecting a target.

187. The air vehicle according to claim 186, wherein said radar arrays comprise phase radar arrays.

188. The air vehicle according to any one of claims 161 to 187, wherein said air vehicle comprises a propulsion system dorsally mounted on said fuselage.

189. The air vehicle according to any one of claims 161 to 188 wherein said air vehicle is configured as a UAV or as a manned air vehicle, and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

190. The air vehicle according to any one of claims 168 to 189, wherein each said sensor/emitter array is comprised in a respective compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

191. The air vehicle according to claim 190, wherein at least one said sensor/emitter array is a radar array, and the respective fairing thereof is made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array.

192. The air vehicle according to any one of claims 190 to 191, wherein said fairings each comprise a smooth rounded shape.

193. The air vehicle according to any one of claims 161 to 195, wherein said fuselage has an outer surface that is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor array, and which forms part of an external skin of said air vehicle.

194. The air vehicle according to any one of claims 161 to 193, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

195. The air vehicle according to any one of claims 161 to 193, wherein said wing arrangement comprises a integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

196. The air vehicle according to any one of claims 168 to 195, wherein in plan view or in bottom view at least a majority of each said sensor/emitter array is free from superposition by said wings.

197. The air vehicle according to any one of claims 168 to 196, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

198. The air vehicle according to any one of claims 168 to 197, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

199. The air vehicle according to any one of claims 168 to 198, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

200. The air vehicle according to claim 199, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

201. An air vehicle, comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

said fuselage comprising a blunt aft end; and

said fuselage comprising a fuselage fineness ratio including at least one of;

a first fineness ratio, taken as a ratio of said fuselage length to said fuselage height, wherein said first fineness ratio is less than about 5;

a second fineness ratio, taken as a ratio of said fuselage length to said fuselage width, wherein said first fineness ratio is less than about 6;

an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, wherein said inverse oblateness ratio is greater than 1.5.

202. The air vehicle according to claim 201, wherein said fuselage is configured for integrating said sensor/emitter arrangement therein for enabling optimizing operation of said sensor/emitter arrangement, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array, the or each said sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and configured for enabling at least one said sensor/emitter array to be arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

203. The air vehicle according to claim 202, further comprising the sensor/emitter arrangement, wherein the sensor/emitter arrangement is configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage.

204. The air vehicle according to claim 203, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

205. The air vehicle according to claim 204, wherein said elongation axis is generally aligned with an azimuthal plane of said air vehicle.

206. The air vehicle according to any one of claims 201 to 205, wherein the air vehicle is free of additional tail arrangement.

207. The air vehicle according to any one of claims 202 to 206, wherein at least a part of said fuselage is formed having a generally oblate cross-section perpendicular to said longitudinal axis for accommodating therein at least a portion of said sensor/emitter arrangement.

208. The air vehicle according to any one of claims 203 to 207, wherein said sensor/emitter arrangement comprises a plurality of said sensor/emitter arrays, each sensor/emitter array being configured for operating to at least one of provide sensor data and emit energy for a respective portion of a 360 degree azimuth volume with respect to the air vehicle referenced to at least one azimuthal reference plane.

209. The air vehicle according to claim 208, wherein said sensor/emitter arrangement is configured for operating with respect to a substantially continuous 360 degree azimuth volume with respect to the air vehicle referenced to said azimuthal reference plane.

210. The air vehicle according to any one of claim 208 or 209, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

211. The air vehicle according to any one of claims 208 to 210, wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof facing one of said forward and said aft direction.

212. The air vehicle according to any one of claims 208 to 211, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

213. The air vehicle according to claim 212, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

214. The air vehicle according to any one of claims 201 to 213, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

215. The air vehicle according to any one of claims 208 to 214, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

216. The air vehicle according to claim 215, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis.

217. The air vehicle according to claim 216, wherein at least one said inclined elongation axis is inclined at an angle of about 30 degrees or 60 degrees with respect to said longitudinal axis.

218. The air vehicle according to any one of claims 208 to 217, comprising three said arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

219. The air vehicle according to claim 218, wherein said triangle is an equilateral triangle or an isosceles triangle.

220. The air vehicle according to any one of claims 208 to 219, comprising four or more said sensor/emitter arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

221. The air vehicle according to any one of claims 208 to 220, wherein each sensor/emitter array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate direction, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

222. The air vehicle according to any one of claims 208 to 221, each said sensor/emitter array being further configured operating with respect to elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

223. The air vehicle according to claim 222, wherein said sensor/emitter arrangement is configured for operating with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

224. The air vehicle according to any one of claims 208 to 223, each said sensor/emitter array being further configured for operating with respect to elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

225. The air vehicle according to any one of claims 208 to 224, wherein said sensor/emitter arrays are configured for providing substantially similar sensor/emitter performance one to another, at least with respect to one of:

sensor/emitter maximum range, sensor/emitter field of view in azimuth, sensor/emitter field of view in elevation with respect to said azimuthal reference plane.

226. The air vehicle according to any one of claims 208 to 225, wherein said sensor/emitter arrangement comprises a radar arrangement, and each said sensor/emitter array comprise a respective radar array for at least detecting a target.

227. The air vehicle according to claim 226, wherein said radar arrays comprise phase radar arrays.

228. The air vehicle according to any one of claims 201 to 227, wherein said air vehicle comprises a propulsion system dorsally mounted on said fuselage.

229. The air vehicle according to any one of claims 201 to 228 wherein said air vehicle is configured as a UAV or as a manned air vehicle, and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

230. The air vehicle according to any one of claims 208 to 229, wherein each said sensor/emitter array is comprised in a respective compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

231. The air vehicle according to claim 230, wherein at least one said sensor/emitter array is a radar array, and the respective fairing thereof is made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array.

232. The air vehicle according to any one of claims 230 to 231, wherein said fairings each comprise a smooth rounded shape.

233. The air vehicle according to any one of claims 201 to 232, wherein said fuselage has an outer surface that is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor array, and which forms part of an external skin of said air vehicle.

234. The air vehicle according to any one of claims 201 to 233, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

235. The air vehicle according to any one of claims 201 to 233, wherein said wing arrangement comprises a integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

236. The air vehicle according to any one of claims 208 to 235, wherein in plan view or in bottom view at least a majority of each said sensor/emitter array is free from superposition by said wings.

237. The air vehicle according to any one of claims 204 to 236, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

238. The air vehicle according to any one of claims 204 to 237, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

239. The air vehicle according to any one of claims 204 to 238, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

240. The air vehicle according to claim 239, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

241. An air vehicle, comprising:

a fuselage and a wing arrangement in fixed-wing configuration, said air vehicle having a longitudinal axis, and said fuselage having a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage;

the fuselage comprising a plurality of internal compartments peripherally disposed with respect thereto and configured for enabling integrating therein a sensor/emitter arrangement that is configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage;

said fuselage comprising a fuselage fineness ratio including at least one of;

a first fineness ratio, taken as a ratio of said fuselage length to said fuselage height, wherein said first fineness ratio is less than about 5;

a second fineness ratio, taken as a ratio of said fuselage length to said fuselage width, wherein said first fineness ratio is less than about 6;

an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, wherein said inverse oblateness ratio is greater than 1.5.

242. The air vehicle according to claim 241, wherein said fuselage is configured for integrating said sensor/emitter arrangement therein for enabling optimizing operation of said sensor/emitter arrangement, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array, the or each said sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and configured for enabling at least one said sensor/emitter array to be arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

243. The air vehicle according to claim 242, further comprising the sensor/emitter arrangement, wherein the sensor/emitter arrangement is configured for at least one of sensing and emitting energy in directions associated with a plurality of different lines of sight (LOS) with respect to said fuselage.

244. The air vehicle according to claim 243, wherein said sensor/emitter arrangement comprises at least one sensor/emitter array comprising a sensing/emitting face that is elongated with respect to an elongation axis, and wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.

245. The air vehicle according to claim 244, wherein said elongation axis is generally aligned with an azimuthal plane of said air vehicle.

246. The air vehicle according to any one of claims 241 to 245, wherein the air vehicle is free of additional tail arrangement.

247. The air vehicle according to any one of claims 243 to 246, wherein said sensor/emitter arrangement comprises a plurality of said sensor/emitter arrays, each sensor/emitter array being configured for operating to provide sensor data or emit energy for a respective portion of a 360 degree azimuth volume with respect to the air vehicle referenced to at least one azimuthal reference plane.

248. The air vehicle according to any one of claims 243 to 247, wherein sensor/emitter arrangement may include one or more of:

a radar jammer arrangement, a passive radar detector, a SIGINT module, an ELINT module, and a COMINT module, a guard antenna, IFF (identify friend or foe) elements, radio transmitting elements.

249. The air vehicle according to claim 247 or claim 248, wherein said sensor/emitter arrangement is configured for operating with respect to a substantially continuous 360 degree azimuth volume with respect to the air vehicle referenced to said azimuthal reference plane.

250. The air vehicle according to any one of claims 247 to 249, wherein said wing arrangement lacks any portions thereof that intersect with or that is below said azimuthal reference plane.

251. The air vehicle according to any one of claims 247 to 249, wherein at least one said sensor/emitter array is arranged with the respective sensing/emitting face thereof facing one of said forward and said aft direction

252. The air vehicle according to any one of claims 247 to 251, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and located at an aft end of said fuselage.

253. The air vehicle according to claim 252, wherein said aft end comprises an aerodynamically blunt aft end.

254. The air vehicle according to any one of claims 252 to 253, wherein at least a majority of said aft end is closed and lacks a streamlined configuration.

255. The air vehicle according to any one of claims 252 to 254, wherein said aft end comprises a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

256. The air vehicle according to any one of claims 247 to 255, wherein at least one said sensor/emitter array is arranged with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

257. The air vehicle according to claim 256, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis, in plan view.

258. The air vehicle according to claim 257, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees with respect to said longitudinal axis and an angle of 60 degrees with respect to said longitudinal axis, in plan view.

259. The air vehicle according to any one of claims 247 to 258, comprising three said arrays, arranged with the respective elongate axes along the sides of an imaginary triangle.

260. The air vehicle according to claim 259, wherein said triangle is an isosceles triangle or an equilateral triangle.

261. The air vehicle according to any one of claims 247 to 260, comprising four or more said sensor/emitter arrays, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

262. The air vehicle according to any one of claims 247 to 261, wherein each sensor/emitter array has an array height dimension and an array width dimension, taken orthogonal to and along with, respectively, the elongate direction, and an aspect ratio of array width to array height for at least one said array is between about 1.5 and about 10.

263. The air vehicle according to any one of claims 247 to 262, each said sensor/emitter array being further configured for operating with respect to elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume, and wherein said sensor/emitter arrangement is configured for operating with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

264. The air vehicle according to any one of claims 247 to 263, each said sensor/emitter array being further configured for operating with respect to elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

265. The air vehicle according to any one of claims 247 to 264, wherein said sensor/emitter arrays are configured for providing substantially similar sensor/emitter performance one to another, at least with respect to one of:

sensor/emitter maximum range, sensor/emitter field of view in azimuth, sensor/emitter field of view in elevation with respect to said azimuthal reference plane.

266. The air vehicle according to any one of claims 247 to 265, wherein said sensor/emitter arrangement comprises a radar arrangement, and each said sensor/emitter array comprise a respective radar array for at least detecting a target.

267. The air vehicle according to claim 266, wherein said radar arrays comprise phase radar arrays.

268. The air vehicle according to any one of claims 241 to 267, wherein said air vehicle comprises a propulsion system dorsally mounted on said fuselage.

269. The air vehicle according to any one of claims 241 to 268 wherein said air vehicle is configured as a UAV or as a manned air vehicle, and wherein said air vehicle is configured as a subsonic or a transonic air vehicle.

270. The air vehicle according to any one of claims 247 to 269, wherein each said radar array is mounted in a respective said compartment in said fuselage and facing a fairing that forms part of the outer skin of the air vehicle.

271. The air vehicle according to claim 270, wherein at least one said sensor/emitter array is a radar array, and the respective fairing thereof is made from a material that is substantially transparent to the radar beams transmitted from and/or received by the respective radar array.

272. The air vehicle according to any one of claims 270 to 271, wherein said fairings each comprise a smooth rounded shape.

273. The air vehicle according to any one of claims 241 to 272, wherein said fuselage has an outer surface that is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor array, and which forms part of an external skin of said air vehicle.

274. The air vehicle according to any one of claims 241 to 273, wherein said wing arrangement comprises a port wing and a starboard wing, each mounted to a corresponding side of said fuselage.

275. The air vehicle according to any one of claims 241 to 274, wherein said wing arrangement comprises a integral wing having a port wing part and a starboard wing part, and wherein said wing is mounted to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

276. The air vehicle according to any one of claims 247 to 275, wherein in plan view or in bottom view at least a majority of each said sensor/emitter array is free from superposition by said wings.

277. The air vehicle according to any one of claims 247 to 276, wherein said fuselage comprises cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

278. The air vehicle according to any one of claims 247 to 277, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

279. The air vehicle according to any one of claims 247 to 278, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

280. The air vehicle according to claim 279, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

323. The method according to any one of claims 280 to 322, wherein said fuselage is formed with cross-sections at planes corresponding to locations of respective said sensor/emitter arrays, wherein a majority of each said cross-section is occupied by the respective said array.

324. The method according to any one of claims 280 to 323, wherein said fuselage has a profile that is generally determined by the size, shape and locations of said sensor/emitter arrays.

325. The method according to any one of claims 280 to 324, wherein said sensor/emitter arrays are arranged in said fuselage around an imaginary center point, wherein the sensor/emitter arrays are spaced from said center point by respective spacings which are dimensionally similar to one another.

326. The method according to claim 325, wherein at least some of said spacings are not equal to one another, and wherein a maximum said spacing is larger than a minimum said spacing by less than a factor of 2 times said minimum spacing.

281. A method for generating an air vehicle configuration, comprising:

(a) providing geometrical specifications of a plurality of sensors/emitters;

(b) providing desired relative spatial relationships between said sensors/emitters;

(c) providing a fairing configuration for each sensor/emitter, the respective fairing configuration being configured for minimizing interference with sensor/emitter operation of the respective sensor/emitter via the respective fairing;

(d) generating a fuselage configuration including an outer fuselage skin enclosing a fuselage volume, wherein said sensors/emitters are integrated within said fuselage volume in said desired relative spatial relationships, wherein said fairing configurations form part of said fuselage skin, and optimizing said fuselage configuration to provide optimal aerodynamic performance according to predetermined criteria, while substantially maintaining minimal interference of said fairing configuration with said sensor/emitter operation;

(e) providing a wing arrangement in fixed-wing relationship to said fuselage.

282. The method according to claim 281, wherein said air vehicle comprises a longitudinal axis, and wherein said fuselage comprises a fuselage length in a direction parallel to said longitudinal axis, a fuselage width in a direction parallel to a pitch axis of the air vehicle, and a fuselage height in a direction parallel to a yaw axis of the air vehicle, the air vehicle further defining at least one azimuthal reference plane that intersects said fuselage.

283. The method according to claim 282, wherein at least a part of said fuselage is formed having a generally oblate cross-section perpendicular to said longitudinal axis for accommodating therein at least some of said sensors/emitters.

284. The method according to any one of claim 281 or 282, wherein said fuselage is formed with an inverse oblateness ratio, taken as a ratio of said fuselage width to said fuselage height, greater than unity.

285. The method according to claim 284, wherein said inverse oblateness ratio is greater than about 1.5.

286. The method according to any one of claims 281 to 285, wherein said fuselage is formed with a first fineness ratio, taken as a ratio of said fuselage length to said fuselage width, of less than about 5.0, or less than about 2.0.

287. The method according to any one of claims 281 to 286, wherein each said sensor/emitter comprises a planar sensor/emitter array.

288. The method according to any one of claims 281 to 287, comprising configuring said air vehicle as a tailless air vehicle.

289. The method according to any one of claims 281 to 288, wherein said wing arrangement is configured to lack any portions thereof that intersect with or that is below an azimuthal reference plane with respect to the air vehicle.

290. The method according to any one of claims 282 to 289, wherein each said sensor/emitter array comprises a sensing/emitting face that is elongated with respect to an elongation axis.

292. The method according to any one of claims 290 to 291, wherein said desired relative spatial relationships include arranging at least one said sensor/emitter array with the respective elongation axis thereof substantially parallel to said pitch axis of the air vehicle, and locating the respective array at an aft end of said fuselage.

293. The method according to claim 292, wherein said aft end is formed as an aerodynamically blunt aft end.

294. The method according to claim 292, wherein at least a majority of said aft end is closed and is formed lacking a streamlined configuration.

295. The method according to any one of claims 292 to 294, wherein said aft end is formed with a cross-section that is generally rounded in at least a majority of cross-sections taken perpendicular to the azimuthal reference plane and generally parallel to the longitudinal axis of the air vehicle.

296. The method according to any one of claims 287 to 295, wherein said desired relative spatial relationships include arranging at least one said sensor/emitter array with the respective elongation axis thereof substantially inclined to said pitch axis and to said longitudinal axis, in plan view.

297. The method according to claim 296, wherein at least one said inclined elongation axis is inclined at an angle between about 10 degrees and about 80 degrees with respect to said longitudinal axis, in plan view.

298. The method according to claim 295, wherein at least one said inclined elongation axis is inclined at one of an angle of about 30 degrees or an angle of 60 degrees with respect to said longitudinal axis, in plan view.

299. The method according to any one of claims 287 to 298, wherein three said sensor/emitter arrays are integrated in said fuselage volume, arranged with the respective elongate axes along the sides of an imaginary triangle.

300. The method according to claim 299, wherein said triangle is an equilateral triangle or an isosceles triangle.

301. The method according to any one of claims 287 to 298, wherein four or more said sensor/emitter arrays are integrated in said fuselage volume, arranged with their respective elongate axes in symmetrical disposition with respect to said longitudinal axis.

302. The method according to claim 301, wherein at least one said elongation axis is inclined at an angle of about 45 degrees with respect to said longitudinal axis.

303. The method according to any one of claims 287 to 302, wherein geometrical specifications comprise an array height dimension and an array width dimension for each sensor array, taken orthogonal to and along with, respectively, the elongate direction, and an aspect ratio of array width to array height for at least one said sensor/emitter array is between about 1.5 and about 10.

304. The method according to any one of claims 287 to 303, comprising positioning each said sensor/emitter array in said fuselage volume such to enable operation thereof in elevation below said azimuthal reference plane, at least for a respective portion of a 360 degree azimuth volume.

305. The method according to claim 304, wherein said sensors/emitters are arranged in said fuselage volume to enable operation thereof with respect to a hemispherical envelope centered on said fuselage and extending radially below said azimuthal reference plane.

306. The method according to any one of claims 287 to 305, each said sensor/emitter array being positioned in said fuselage volume such to enable operation thereof in elevation above said azimuthal reference plane, at least for a respective portion of said 360 degree azimuth volume.

307. The method according to claim 306, wherein said sensors/emitters are arranged in said fuselage volume to enable operation thereof with respect to elevation above said azimuthal reference plane, for said 360 degree azimuth volume excluding portions thereof associated with said wing arrangement.

308. The method according to any one of claims 287 to 307, wherein said sensor/emitter arrays are similarly dimensioned one to another.

309. The method according to any one of claims 287 to 308, further comprising dorsally mounting a propulsion system to said fuselage.

310. The method according to any one of claims 281 to 309, comprising configuring the air vehicle as a UAV.

311. The method according to any one of claims 281 to 309, comprising configuring the air vehicle as a manned air vehicle.

312. The method according to any one of claims 281 to 311, comprising configuring said air vehicle as a subsonic or a transonic air vehicle.

313. The method according to any one of claims 287 to 312, comprising forming said fuselage volume with a plurality of compartments, each said sensor/emitter array being comprised in a respective compartment in said fuselage and facing a respective said fairing.

314. The method according to claim 313, wherein at least one said fairing is made from a material that is substantially transparent to the radar beams transmitted from and/or received therethrough.

315. The method according to any one of claims 313 to 314, wherein said fairings are each formed comprising a smooth rounded shape.

316. The method according to any one of claims 281 to 314, wherein said fuselage skin is faceted, and wherein each said sensor/emitter array comprises a respective said fairing that is substantially flat and spaced from the respective sensor/emitter, and which forms part of said fuselage skin.

317. The method according to any one of claims 281 to 316, wherein said wing arrangement is formed as a port wing and a starboard wing, and mounting each wing to a corresponding side of said fuselage.

318. The method according to any one of claims 281 to 316, wherein said wing arrangement is formed as an integral wing having a port wing part and a starboard wing part, and comprising mounting the integral wing to said fuselage via a pylon structure, such that the dorsal surface of the fuselage is facing the underside of the integral wing.

319. The method according to any one of claims 287 to 318, wherein the sensor/emitter arrays and the wing arrangement are arranged with respect to the fuselage such that in plan view or in bottom view at least a majority of each said sensor/emitter array is free from superposition by said wings.

320. The method according to any one of claims 287 to 319, wherein said sensor/emitter arrays are radar arrays.

321. The method according to claim 320, wherein said radar arrays are phased arrays.

322. The method according to any one of claims 290 to 322, wherein said elongation axis is generally aligned with an azimuthal plane of said air vehicle.

291. The method according to claim 291, wherein said desired relative spatial relationships include arranging at least one said sensor/emitter array with the respective sensing/emitting face thereof at least partially facing one of a forward direction and an aft direction along said longitudinal axis, and at least partially facing at least one side direction along said pitch axis.