Combined space vehicle fuel cell and space station structural building component

• US 4,807,833 A
• Filed: 04/11/1986
• Issued: 02/28/1989
• Est. Priority Date: 04/11/1986
• Status: Expired due to Fees

• Current Assignee: James A. Pori
• Original Assignee: James A. Pori
• Inventors: Pori, James A.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US06/850,804
• Time in Patent Office: 1,054 Days
• Field of Search: 244/158 R, 244/159, 244/160, 244/161, 244/162, 244/163, 244/172, 244/2, 244/135 R, 220/426, 102/381
• US Class Current: 244/159.6
• CPC Class Codes: B64G 1/12 manned
• CPC Class Codes: B64G 1/14 Space shuttles reusable launch rockets B64G1/006
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 99/00 Subject matter not provided for in other groups of this subclass
• CPC Class Codes: Y10S 220/901 Liquified gas content, cryogenic

Abstract

A combined space vehicle fuel cell and modular space station structural building component which provides containment of propellants during launch and thereafter provides one of a plurality of modules which can be interconnected once orbit is achieved for constructing a space station or space platform. The combined space vehicle fuel cell and modular space station structural building component is configured so that a first pressure vessel for containment of one propellant is preferably concentrically positioned within a second pressure vessel for another propellant, which can result in a shorter fuel cell. Intervessel structure is included for interconnecting the pressure vessels but is lightweight due to the concentric configuration of the pressure vessels and is preferably concentrated in the aft end of the fuel cell for providing a rigid structure for receiving thrust through any and all thrust attaches to a spacecraft. The fuel cell configuration results in a lower center of gravity, which enables more vertically oriented thrust to be applied to the space vehicle. Docking structure is incorporated into the combined space vehicle fuel cell and modular space station structural building component for connection with other similar fuel cells after orbit is achieved for constructing a space station or space platform. Preferably, equipment which is not susceptible to damage through contact with the one propellant is pre-installed on the earth to alleviate the need to install such equipment after orbit is achieved, which results in a reduction in the payload requirements for space station construction. The fuel cell can also include a storage compartment for payload.

Claims

1. In a space shuttle having an orbiter spacecraft with main rocket engines, an external tank for propellants to which the orbiter spacecraft is mounted on one side, and a pair of solid rocket boosters mounted on opposed sides of the external tank, the improvement comprising:

the external tank having a first pressure vessel means for containing a first propellant and a second pressure vessel means for containing a second propellant;

the first pressure vessel means being contained within the second pressure vessel means;

a payload compartment disposed in tandem with the first pressure vessel means, the payload compartment being contained within the second pressure vessel means;

the solid rocket boosters being connected to the external tank and adapted to apply thrust generated by the rocket boosters to an aft end of the external tank; and

the orbiter spacecraft being connected to the external tank so as to apply thrust generated by the main rocket engines to the aft of the external tank.

2. The space shuttle of claim 1 wherein the first pressure vessel means is concentrically contained within the second pressure vessel means.

3. The space shuttle of claim 1 wherein the first pressure vessel means is concentrically contained within the second pressure vessel means and the payload compartment is coaxial with the first and second pressure vessel means.

4. The space shuttle of claim 1, further comprising intervessel structural means disposed in an interstitial region between the first pressure vessel means and the second pressure vessel means for stabilizing the first pressure vessel means within the second pressure vessel means.

5. The space shuttle of claim 4 wherein the intervessel structural means comprises at least one stiffening ring interposed between the first pressure vessel means and the second pressure vessel means in the interstitial region.

6. The space shuttle of claim 5 wherein there is a plurality of stiffening rings axially spaced along the length of the external tank in the interstitial region between the first pressure vessel means and the second pressure vessel means, the stiffening rings having cutouts for permitting flow of the second propellant from a forward end of the external tank to the aft end, the cutouts being oriented so as to prevent a coriolis effect at the aft end of the second pressure vessel means.

7. The space shuttle of claim 4 wherein the intervessel structural means comprises a crown interposed between the first pressure vessel means and the second pressure vessel means in the interstitial region.

8. The space shuttle of claim 4 wherein the intervessel structural means comprises a thrust frame disposed at the aft end of the external tank interposed between the first pressure vessel means and the second pressure vessel means in the interstitial region, and further comprising thrust attaches for the solid rocket boosters and the main rocket engines connected to the aft end of the external tank.

9. The space shuttle of claim 1, further comprising intervessel structural means including an intertank frame interposed between the first pressure vessel means and the payload compartment.

10. The space shuttle of claim 1, further comprising integrated intervessel structural and docking means interconnected between the first pressure vessel means and the second pressure vessel means for stabilizing the first pressure vessel means within the second pressure vessel means.

11. The space shuttle of claim 10 wherein the integrated intervessel structural and docking means comprises at least one bulkhead interconnected between the first pressure vessel means and the second pressure vessel means.

12. The space shuttle of claim 11 wherein there is a plurality of bulkheads axially spaced along the length of the external tank interconnected between the first pressure vessel means and the second pressure vessel means, the bulkheads having radial tunnels extending through an interstitial region between the first pressure vessel means and the second pressure vessel means, the second propellant flowing from a forward end of the external tank to the aft end through the interstitial region around the radial tunnels, the radial tunnels being oriented so as to prevent a coriolis effect at the aft end of the pressure vessel means.

13. The space shuttle of claim 11 wherein the at least one bulkhead comprises:

an axial tunnel aligned with a longitudinal axis of the external tank for permitting flow of the first propellant from a forward end of the external tank to the aft end; and

at least one radial tunnel extending through an interstitial region between the first pressure vessel means and the second pressure vessel means, the second propellant flowing from the forward end of the external tank to the aft end through the interstitial region around the at least one radial tunnel.

14. The space shuttle of claim 13 wherein the at least one radial tunnel comprises:

a first cylindrical section having a first end connected to the axial tunnel and having a second end having a flange; and

a second cylindrical section having a first end having a flange connectable to the flange at the second end of the first cylindrical section and having a second end adapted for mounting a docking module.

15. The space shuttle of claim 10 wherein the integrated intervessel structural and docking means comprises at least one access port interconnected between the first pressure vessel means and the second pressure vessel means, the at least one access port comprising:

a first cylindrical section having a first end and having a second end having a flange; and

a second cylindrical section having a first end having a flange connectable to the flange at the second end of the first cylindrical section and having a second end adapted for mounting a docking module.

16. The space shuttle of claim 11 wherein a bulkhead is located at the aft end of the external tank interconnected between the first pressure vessel means and the second pressure vessel means, and further comprising thrust attaches for the solid rocket boosters and the main rocket engines connected to the aft end of the external tank.

17. The space shuttle of claim 1, further comprising integrated intervessel structural and docking means including an intertank bulkhead interposed between the first pressure vessel means and the payload compartment.

18. The space shuttle of claim 17 wherein the intertank bulkhead comprises:

an axial tunnel aligned with a longitudinal axis of the external tank interconnected between the first pressure vessel means and the payload compartment;

at least one radial tunnel extending through the second pressure vessel means, the at least one radial tunnel comprising;

a first cylindrical section having a first end connected to the axial tunnel and having a second end having a flange; and

a second cylindrical section having a first end having a flange connectable to the flange at the second end of the first cylindrical section and having a second end adapted for mounting a docking module; and

a plurality of storage tanks disposed exterior to the axial tunnel and the at least one radial tunnel.

19. The space shuttle of claim 1 wherein the payload comprises decks installed in the first pressure vessel means.

20. The space shuttle of claim 1, further comprising a first pipeline in fluid circuit with the interior of the first pressure vessel means and a second pipeline in fluid circuit with the interior of the second pressure vessel means for feeding the first and second propellants from the first and second pressure vessel means, respectively, to the main rocket engines.

21. The space shuttle of claim 1 wherein the first pressure vessel means comprises an inner cylindrical wall capped at a forward end of the external tank by a first end dome and capped at the aft end by a second end dome and the second pressure vessel means comprises an outer cylindrical wall capped at the forward end by a third end dome and capped at the aft end by a fourth end dome, the outer cylindrical wall and third and fourth domes of the second pressure vessel means surrounding the first pressure vessel means so as to define an interstitial region between the first pressure vessel means and the second pressure vessel means.

22. The space shuttle of claim 21 wherein the payload comprises a payload compartment disposed in tandem with the first pressure vessel means, the payload compartment being contained within the second pressure vessel means, the payload compartment including a portion of the inner wall intermediate the first and third domes capped at the forward end by a fifth end dome and capped at the aft end by a sixth end dome.

23. The space shuttle of claim 1 wherein the first propellant is liquid hydrogen and the second propellant is liquid oxygen.

33. The modular space station structural building component of claim 21 wherein the one propellant is liquid hydrogen and the other propellant is liquid oxygen.

24. A modular space station structural building component, comprising:

a fuel cell having a first pressure vessel means for containing one propellant, a payload compartment connected in tandem with the first pressure vessel means, and a second pressure vessel means for containing another propellant;

the first pressure vessel means and payload compartment both being contained within the second pressure vessel means; and

docking means for interconnecting the fuel cell to a preselected structure in orbit.

25. The modular space station structural building component of claim 24 wherein the first pressure vessel means is concentrically contained within the second pressure vessel means and the payload compartment is coaxial with the first pressure vessel means.

26. The modular space station structural building component of claim 24 wherein the payload comprises decks installed in the first pressure vessel means.

27. The modular space station structural building component of claim 24 wherein the first pressure vessel means comprises an inner cylindrical wall capped at a forward end of the fuel cell by a first end dome and capped at an aft end of the fuel cell by a second end dome and the second pressure vessel means comprises an outer cylindrical wall capped at the forward end by a third end dome and capped at the aft end by a fourth end dome, the outer cylindrical wall and third and fourth domes of the second pressure vessel means surrounding the first pressure vessel means so as to define an interstitional region between the first pressure vessel means and the second pressure vessel means.

28. The modular space station structural building component of claim 27 wherein the payload comprises a payload compartment disposed in tandem with the first pressure vessel means, the payload compartment being contained within the second pressure vessel means, the payload compartment including a portion of the inner wall intermediate the first and third domes capped at the forward end by a fifth end dome and capped at the aft end by a sixth end dome.

29. The modular space station structural building component of claim 24 wherein the preselected structure is an end of a similarly configured fuel cell in orbit.

30. The modular space station structure building component of claim 27 wherein passages are provided in the first, second, third, and fourth domes and the docking means is associated with the respective ends of the fuel cell for interconnection with the ends of similarly configured fuel cells in end-to-end relation.

31. The modular space station structural building component of claim 29, further comprising at least one bulkhead interconnected between the first pressure vessel means and the second pressure vessel means and extending through the second pressure vessel means, the bulkhead being connectable to the docking means for interconnecting the fuel cell to the preselected structure in side-by-side relation.

32. The modular space station structural building component of claim 24, further comprising an intertank bulkhead interposed between the first pressure vessel means and the payload compartment and extending through the second pressure vessel means, the intertank bulkhead being connectable to the docking means for interconnecting the fuel cell to the preselected structure in side-by-side relation.

34. A combined space vehicle fuel cell and modular space station structural building component, comprising:

an external tank, comprising;

a first pressure vessel means for containing one propellant during launch of a space vehicle; and

a second pressure vessel means surrounding the first pressure vessel means so as to define an interstitial region between the interior of the second pressure vessel means and the exterior of the first pressure vessel means for containing a second propellant;

a payload compartment disposed in tandem with the first pressure vessel means, the payload compartment being contained within the second pressure vessel means;

the external tank being adapted for interconnection with similarly configured external tanks; and

docketing means for interconnecting at least two external tanks.

35. The combined space vehicle fuel cell and modular space station structural building component of claim 34 wherein the docking means comprises a docking module.

36. The combined space vehicle fuel cell and modular space station structural building component of claim 34 wherein the first pressure vessel means is concentrically contained within the second pressure vessel means.

37. The combined space vehicle fuel cell and modular space station structural building component of claim 34 wherein the first pressure vessel means is concentrically contained within the second pressure vessel means and the payload compartment is coaxial with the first pressure vessel means.

38. The combined space vehicle fuel cell and modular space station structural building component of claim 34, further comprising intervessel structural means for stabilizing the first pressure vessel means within the second pressure vessel means.

39. The combined space vehicle fuel cell and modular space station structural building component of claim 34, further comprising intervessel structural means including an intertank frame interposed between the first pressure vessel means and the payload compartment.

40. The combined space vehicle fuel cell and modular space station structural building component of claim 34, further comprising integrated intervessel structural and docking means for stabilizing the first pressure vessel means within the second pressure vessel means.

41. The combined space vehicle fuel cell and modular space station structural building component of claim 34, further comprising integrated intervessel structural and docking means including an intertank bulkhead interposed between the first pressure vessel means and the payload compartment.

42. The combined space vehicle fuel cell and modular space station structural building component of claim 34 wherein the payload comprises decks installed in the first pressure vessel means.

43. The combined space vehicle fuel cell and modular space station structural building component of claim 34 wherein the one propellant is liquid hydrogen and the second propellant is liquid oxygen.