AERODYNAMIC BODY AND CARRIER WING COMPRISING AN AERODYNAMIC BODY, ACTUATING DRIVE CONTROL MODULE, COMPUTER, COMPUTER PROGRAM AND METHOD FOR INFLUENCING POST-TURBULENCES

• US 20100006706A1
• Filed: 09/15/2007
• Published: 01/14/2010
• Est. Priority Date: 09/15/2006
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE), Technische Universitat Munchen
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Allen, Alexander, Breitsamter, Christian
• Granted Patent: US 8,387,922 B2
• Time in Patent Office: Days
• US Class Current: 244/199.300
• CPC Class Codes: B64C 13/16 actuated automatically, e.g. responsive to gust detectors
• CPC Class Codes: B64C 23/076 the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

An aerodynamic element attachable to a primary wing to extend in a longitudinal direction at an angle to a spanwise direction of the primary wing. The aerodynamic element includes a downstream end having at least two flow flaps arranged next to each other and oriented in the longitudinal direction of the aerodynamic element.

Claims

1-41. -41. (canceled)

42. An aerodynamic element attachable to a primary wing to extend in a longitudinal direction at an angle to a spanwise direction of the primary wing, the aerodynamic element comprising:

a downstream end having at least two flow flaps arranged next to each other and oriented in the longitudinal direction of the aerodynamic element.

43. The aerodynamic element of claim 42, wherein the at least two flow flaps comprises an even number of flow flaps.

44. The aerodynamic element of claim 42, wherein the at least two flow flaps comprises an add number of flow flaps.

45. In combination with the aerodynamic element of claim 42, at least one other aerodynamic element, wherein said aerodynamic elements result in the following:

given a phase-shifted oscillation of the flow flaps, motion-induced aerodynamic forces generated by the flow flaps measures under 10% of a maximum aerodynamic force that can be induced by one of the flow flaps at any point in time.

46. In combination with the aerodynamic element of claim 42, at least one other aerodynamic element, wherein said aerodynamic elements results in the following:

given an oscillation in phase opposition of the flow flaps, motion-induced aerodynamic forces generated by said aerodynamic elements are precisely cancelled out at any point in a oscillation period.

47. In combination with the aerodynamic element of claim 42, a second aerodynamic element having at least two flow flaps arranged next to each other and oriented in a longitudinal direction of the second aerodynamic element.

48. The aerodynamic element of claim 42, wherein the flow flaps situated on the aerodynamic element are directly adjacent to each other.

49. The aerodynamic element of claim 42, further comprising at least one actuator configured to move one of:

the flow flaps from a zero setting; and

each flow flap from a zero setting.

50. The aerodynamic element of claim 42, wherein the flow flaps are mechanically coupled to each other, and further comprising an actuator coupled to the flow flaps, whereby an activation motion of the actuator simultaneously induces one of phase-shifted motions of the flow flaps and motions in phase opposition.

51. The aerodynamic element of claim 42, further comprising plural actuators each being configured to move one of the flow flaps from a reference setting, whereby each flow flap is movable in two opposite directions.

52. The aerodynamic element of claim 51, wherein the reference setting is a neutral setting.

53. The aerodynamic element of claim 51, wherein the reference setting is a setting that measures at most 10% of a minimum resistance value.

54. The aerodynamic element of claim 51, wherein the flow flaps are structured and arranged to perform flap excursions measuring in both directions proceeding from a reference setting one of:

between 10 and 40 degrees; and

between 15 and 25 degrees.

55. The aerodynamic element of claim 42, wherein the aerodynamic element is a winglet arranged at a tip of the primary wing.

56. The aerodynamic element of claim 42, wherein the aerodynamic element is arranged in an area between a root and a tip of the primary wing.

57. The aerodynamic element of claim 42, wherein the angle is 90 degrees.

58. The aerodynamic element of claim 42, wherein the angle is between 45 and 90 degrees.

59. A wing comprising an aerodynamic element of claim 42.

60. The wing of claim 59, wherein the aerodynamic element comprises at least one actuator for activating the at least two flow flaps.

61. The wing of claim 59, wherein the aerodynamic element comprises at least one actuator configured to move each of the at least two flow flaps.

62. The wing of claim 59, wherein the aerodynamic element comprises at least one actuator and a computer configured to activate at least one actuator.

73. A combination of a computer having an actuator-activation module, at least one actuator for activating flaps, and the aerodynamic element of claim 42.

74. The combination of claim 73, further comprising a wing.

63. A computer comprising an actuator-activation module structured and arranged to generate time-variable command signals for actuators and utilizing a function which, when activated, generates at least two oscillatory command signals, which are in phase opposition relative to each other.

64. The computer of claim 63, wherein the actuator-activation module is configured to change a frequency and/or an amplitude of the at least two oscillatory command signals.

65. The computer of claim 64, wherein the computer utilizes a ramp function, which continuously raises or lowers the frequency and/or amplitude in a prescribed time segment.

66. The computer of claim 64, further comprising a random-check generator, which determines one of:

the frequency and/or the amplitude for a prescribed time segment; and

plural frequencies and/or plural amplitudes for a prescribed time segment.

67. The computer of claim 66, wherein the random-check generator additionally determines a size of the prescribed time segment.

68. The computer of claim 63, wherein the function generates a white nose, and injects it into the at least two oscillatory command signals.

69. The computer of claim 63, wherein the computer is configured to generate frequencies within a prescribed bandwidth and in a prescribed time segment based on a normal distribution.

70. A computer program configured to be implemented on the computer of claim 63.

72. A combination of the computer of claim 63 and at least one actuator adapted to activate a pair of flaps.

71. A computer comprising an actuator-activation module structured and arranged to generate time-variable command signals for at least one actuator and exhibiting a function which, when activated, generates at least three oscillatory command signals, each of which is transmitted to the at least one actuator, wherein the at least three oscillatory command signals are phase-shifted relative to each other.

75. A method of influencing command signals for an actuator system, the method comprising:

generating activation signals that can be received by an actuator; and

changing an activation signal in such a way that at least two oscillatory command signals are generated for one respective actuator each, which are in phase opposition relative to each other.

76. The method of claim 75, wherein the at least two oscillatory command signals are phase-shifted relative to each other.

77. The method of claim 75, further comprising changing a frequency and/or an amplitude of each oscillatory command signal one of:

before the at least two oscillatory command signals are generated;

after the at least two oscillatory command signals are generated.

78. The method of claim 75, further comprising utilizing a ramp function, which continuously raises or lowers a frequency and/or an amplitude in a prescribed time segment.

79. The method of claim 75, further comprising utilizing a random-check generator that determines one of:

a frequency and/or an amplitude for a prescribed time segment; and

plural frequencies and/or plural amplitudes for a prescribed time segment.

80. The method of claim 79, wherein the random-check generator additionally determines a size of the prescribed time segment.

81. The method of claim 75, further comprising generating a white nose, and injecting it into an oscillating command signal.

82. The method of claim 75, further comprising generating frequencies and/or amplitudes within a prescribed bandwidth in a prescribed time segment based on a normal distribution.