Multipurpose modular spacecraft

• US 20060219846A1
• Filed: 04/01/2005
• Published: 10/05/2006
• Est. Priority Date: 04/01/2005
• Status: Active Grant

• Current Assignee: Spacehab, Inc.
• Original Assignee: Spacehab, Inc.
• Inventors: Johnson, Michael D., Baker, James D., Eichstadt, Frank T., Bain, Michael E.
• Granted Patent: US 7,219,859 B2
• Time in Patent Office: Days
• US Class Current: 244/158.900
• CPC Class Codes: B64G 1/12 manned
• CPC Class Codes: B64G 1/223 Modular spacecraft systems
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refueling in space B64G1/4024

Abstract

A reentry vehicle includes a nose section, a modular section comprised of two or more connected modules, a flared section. The nose section is connected to a first end of the modular section, and the flared section is positioned proximate a second end of the modular cylindrical section.

Claims

1. A reentry vehicle, comprising:

a nose section;

a modular section comprised of two or more connected modules; and

a flared section,

wherein the nose section is connected to a first end of the modular section, and the flared section is positioned proximate a second end of the modular cylindrical section.

2. The reentry vehicle of claim 1, wherein the modular section comprises a cylindrical cross section.

3. The reentry vehicle of claim 2, wherein a diameter of the modular section is selected to be less than a minimum inner diameter of one or more launch vehicles.

4. The reentry vehicle of claim 3, wherein two or more of the cylindrical modules have substantially the same length and substantially the same diameter.

5. The reentry vehicle of claim 4, wherein an aft module is configured to form an aft section of the reentry vehicle, and wherein the aft module, the plurality of modules, and the nose are connected to form an air-tight interior.

6. The reentry vehicle of claim 5, wherein the aft module comprises a hatch.

7. The reentry vehicle of claim 5, wherein the aft module comprises a propulsion and guidance system.

8. The reentry vehicle of claim 5, wherein the aft module is hingedly connected to a next cylindrical module and moveable between an open position and a closed position.

9. The reentry vehicle of claim 1, wherein the reentry vehicle is not air-tight.

10. The reentry vehicle of claim 1, wherein the flared section is moveable between a stowed position and a deployed position.

11. The reentry vehicle of claim 1, wherein the flared section is asymmetrical.

12. The reentry vehicle of claim 1, wherein the flared section comprises an adjustable geometry flared section that may be positioned in a selected configuration.

13. The reentry vehicle of claim 12, further comprising an inflatable bladder disposed under the flared section to selectively control the configuration of the flared section.

14. The reentry vehicle of claim 1, wherein the flared section comprises a first stage flared section having a first diameter and a second stage flared section having a second diameter, and wherein the first diameter is larger that the second diameter.

15. The reentry vehicle of claim 1, wherein the flared section is constructed of a refractory material having with an ablative coating.

16. The reentry vehicle of claim 15, wherein the refractory material is a fabric.

17. The reentry vehicle of claim 16, further comprising an inflatable bladder positioned under the flared section.

18. The reentry vehicle of claim 1, wherein the flared section is constructed of a high temperature tolerant material.

19. The reentry vehicle of claim 18, wherein the high temperature tolerant material is a metal.

20. The reentry vehicle of claim 19, wherein the metal is Inconel.

21. The reentry vehicle of claim 1, wherein a range for a center of gravity of the reentry vehicle is forward of a center of pressure of the reentry vehicle.

22. The reentry vehicle of claim 21, wherein the range for the center of gravity is separated from a centerline of the reentry vehicle.

23. The reentry vehicle of claim 1, wherein the nose is hingedly connected to a first module and moveable between an open position and a closed position.

24. The reentry vehicle of claim 1, wherein one or more of the modules includes a hinged section that forms at least one bay door.

25. The reentry vehicle of claim 1, wherein the nose is connected to the modular section by one or more rails, and wherein the nose is moveable on the rails between an open position and a closed position.

26. The reentry vehicle of claim 25, wherein the rails comprise powered rails.

27. The reentry vehicle of claim 1, wherein the nose and one or more modules are connected to an aft of the reentry vehicle by one or more rails, and wherein the nose and one or more modules are moveable on the rails between an open position and a closed position.

28. The reentry vehicle of claim 27, further comprising a perforated structure positioned inside the modular section when the nose and one or more modules are in the closed position.

29. The reentry vehicle of claim 28, wherein perforations in the perforated structure are sized to be larger than a payload.

30. The reentry vehicle of claim 1, wherein the reentry vehicle is configured to transport a crew.

31. The reentry vehicle of claim 1, wherein at least one of the modules includes an access port.

32. The reentry vehicle of claim 1, wherein the access port is configured to mate with a second access port in a launch vehicle fairing.

33. The reentry vehicle of claim 1, wherein the nose is a blunt nose.

34. The reentry vehicle of claim 1, wherein the nose is a hemispherical nose.

35. The reentry vehicle of claim 1, wherein the nose is constructed of a crushable material.

36. The reentry vehicle of claim 1, further comprising a deployable air bag disposed the nose.

37. The reentry vehicle of claim 1, further comprising one or more deceleration parachutes.

38. The reentry vehicle of claim 37, wherein the one or more deceleration parachutes comprise at least two deceleration parachutes having different sizes.

39. A method of transferring a payload in orbit, comprising:

docking a reentry vehicle with an object in orbit;

depressurizing the reentry vehicle;

opening an access port in the reentry vehicle;

transferring the payload;

closing the access port; and

pressurizing the reentry vehicle.

40. The method of claim 39, wherein the transferring the payload comprises capturing the payload.

41. The method of claim 39, wherein the transferring the payload comprises deploying the payload.

42. The method of claim 39, wherein the opening the access port comprises moving a nose section hinged to a modular section from a closed position to an open position.

43. The method of claim 39, wherein the opening the access port comprises moving at least one bay door from a closed position to an open position.

44. The method of claim 39, wherein the opening the access port comprises moving an aft section hinged to a modular section from a closed position to an open position.

45. The method of claim 39, wherein the opening the access port comprises moving a nose section connected to a modular section by rails from a closed position to an open position.

46. The method of claim 39, wherein the opening the access port comprises moving a nose section and a modular section connected to a aft section by rails from a closed position to an open position.

47. A method of entering a planetary atmosphere, comprising:

deploying a flared section of a reentry vehicle to a first position;

dissipating kinetic energy in a rarefied portion of the atmosphere; and

deploying the flared section in a second position,

wherein the first position has a larger cross sectional area than the second position, and

wherein the reentry vehicle approaches the planetary atmosphere above an overshoot boundary for the vehicle when the flared section is in the second position.

48. The method of claim 47, wherein the first position comprises a first stage flared section and the second position comprises a second stage section.

49. The method of claim 47, wherein the flared section is an adjustable geometry flared section moveable between the first position and the second position.

50. A reentry vehicle, comprising:

a modular section comprised of two or more modules sealingly coupled to each other;

a nose section connected to a first of the two or more modules at a first end of the modular cylindrical section; and

a flared section proximate a second end of the modular cylindrical section and positioned to protect at least one of the one or more cylindrical modules,

wherein an aft one of the one or more modules forms an aft cylindrical module and comprises a crew hatch and a propulsion and maneuvering system.

51. The reentry vehicle of claim 50, wherein the nose section is hingedly connected to the first cylindrical module and moveable between an open position and a closed position, and wherein the nose is sealingly coupled to the first cylindrical module when in the closed position.

52. The reentry vehicle of claim 50, wherein the nose is connected to the first module by one or more powered rails and moveable between an open position and a closed position, and wherein the nose is sealingly coupled to the first module when in the closed position.

53. The reentry vehicle of claim 50, wherein the nose and the modular section are connected to the aft module by one or more power rails and moveable between an open position and a closed position, and further comprising a perforated structure connected to the aft cylindrical module so that the perforated structure is disposed within in the modular section when the nose and the modular section are in the closed position.

54. The reentry vehicle of claim 50, wherein the aft cylindrical module is hingedly connected an adjacent cylindrical module and moveable between an open position and a closed position, and wherein the aft cylindrical module is sealingly coupled to the adjacent cylindrical module when in the closed position.

55. The reentry vehicle of claim 50, wherein one or more of the two or more cylindrical modules each comprise one or more connected hinged sections that form one or more bay doors moveable between an open position and a closed position.

56. The reentry vehicle of claim 50, further comprising crew accommodations in the reentry vehicle.

57. A reentry vehicle, comprising:

means for dissipating reentry heat;

means for stabilizing the reentry vehicle during hypersonic flight; and

means for selecting a payload volume of the reentry vehicle.

58. The reentry vehicle of claim 57, further comprising means for expanding entry parameters.

59. The reentry vehicle of claim 57, further comprising means for opening the reentry vehicle to capture or deploy a payload.

60. The reentry vehicle of claim 57, further comprising means for absorbing a landing impact.

61. The reentry vehicle of claim 57, further comprising means for deploying the means for stabilizing the vehicle.

62. A modular vehicle, comprising:

at least one module adapted to for a secondary structure for a primary vehicle; and

an adapter for connecting the modular vehicle to the primary vehicle.

63. The modular vehicle of claim 62, further comprising a common berthing mechanism.

64. The modular vehicle of claim 62, wherein the at least one module comprises a plurality of modules.

65. The modular vehicle of claim 62, wherein the at least one module comprises crew accommodations.