Hybrid helium heater pressurization system and electrical ignition system for pressure-fed hybrid rockets

• US 5,722,232 A
• Filed: 10/13/1994
• Issued: 03/03/1998
• Est. Priority Date: 10/13/1994
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Martin Marietta Corporation
• Inventors: Jones, H. Stephen
• Primary Examiner(s): Thorpe, Timothy
• Assistant Examiner(s): KIM, TAE JUN
• Application Number:
  US08/322,781
• Time in Patent Office: 1,237 Days
• Field of Search: 60/251, 60/256, 60/257, 60/258, 60/259, 60/260, 60/39.48, 60/726
• US Class Current: 60/259
• CPC Class Codes: F02K 9/50 using pressurised fluid to pressurise the propellants
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants

Abstract

A system for pressurizing a liquid oxygen tank (20) in a pressure-fed hybrid rocket (100) provides pressure at a first end of the tank (20) so that liquid oxygen can exit the second end. A hybrid heater (50) creates the pressure by mixing gaseous oxygen with the solid fuel (51) in the hybrid heater (50) to create an extremely high temperature. Helium is then mixed with the combustion products via an inlet (60) and this hot, inert mixture enters the liquid oxygen tank (20) via a diffuser (70). A second hybrid heater (90) pressurizes the gaseous helium sphere (40) to reduce the pressure decay caused by the withdrawal of the helium. Two of the hybrid heaters (50 and 90) are fed gaseous oxygen from a sphere (30). A novel ignition system is used to ignite the hybrid heaters (50, 90, 250). One of the hybrid heaters (250) is used to ignite the hybrid motor (100) in the rocket (11).

Claims

1. Apparatus including a hybrid heater pressurization system, for a rocket comprising a first liquid fuel component and a second fuel component, comprising pressurization means, for forcing the first liquid fuel component into contact with the second fuel component, the pressurization means comprising:

(I) a gas initially stored at a cryogenic temperature;

(ii) a hybrid heater having a longitudinal axis and generating combustion products when ignited for heating the gas by mixing the combustion products of the hybrid heater with the gas in a mixing chamber;

the gas being injected through ports circumferentially disposed about the axis; and

(iii) diffuser means for introducing the heated gas into a container containing the first liquid fuel component.

2. The apparatus of claim 1, wherein the gas is inert.

3. The apparatus of claim 2, wherein the inert gas is helium.

4. The apparatus of claim 1, wherein the rocket is a hybrid rocket.

5. The apparatus of claim 1, further comprising the rocket.

6. The apparatus of claim 5, wherein the rocket is a hybrid rocket.

7. The apparatus of claim 5, further comprising an electric ignition system for electrically igniting the rocket.

8. The apparatus of claim 7, wherein:

the second fuel component is in a casing; and

the electric ignition system for electrically igniting the rocket includes;

a second hybrid heater having combustion products when ignited, the combustion products of the second hybrid heater entering the casing of the second fuel component when the second hybrid heater is ignited; and

spark-producing means for igniting the second hybrid heater.

9. The apparatus of claim 8, wherein:

the spark-producing means produces no sparks when in an inert-gas environment.

10. The apparatus of claim 9, wherein:

the spark-producing means is a carbon arc.

11. The apparatus of claim 5, further comprising a rocket case containing the rocket and the hybrid heater pressurization system, and wherein the gas is initially stored in the rocket case at a cryogenic temperature.

12. The apparatus of claim 11, further comprising a second container for initially storing the gas and a second heater for heating the gas while the gas is in the second container.

13. The apparatus of claim 12, wherein the second heater comprises a second hybrid heater.

14. The apparatus of claim 1, further comprising an ignition system for igniting a rocket, wherein the second fuel component is in a casing, and the ignition system comprises:

a second hybrid heater having combustion products when ignited, the second hybrid heater being connected to the casing and positioned such that the combustion products of the second hybrid heater enter the casing of the second fuel component when the second hybrid heater is ignited; and

means for igniting the second hybrid heater.

15. The apparatus of claim 14, wherein:

the means for igniting the second hybrid heater is a spark-producing means.

16. The apparatus of claim 15, wherein:

the spark-producing means produces no sparks when in an inert-gas environment.

17. The apparatus of claim 16, wherein:

the spark-producing means is a carbon arc.

18. The apparatus of claim 14, further comprising the rocket.

19. The apparatus of claim 18, wherein the rocket is a hybrid rocket.

20. The apparatus of claim 18, further comprising a rocket case in which are contained the first liquid fuel component, the second fuel component, and the pressurization means.

21. The apparatus of claim 1, further comprising a hybrid rocket comprising:

(a) a rocket case (115) having a first end (118) and a second end;

(b) a hybrid motor (100) in the rocket case (115), adjacent the second end (119) of the rocket case (115);

(c) fuel (101) in the hybrid motor (100);

(d) a tank (20) in the rocket case, intermediate the hybrid motor (100) and the first end (118) of the rocket case (115), the tank (20) being fluidly connected to the hybrid motor (100) and being at a first, ullage, pressure;

(e) liquid oxygen in the tank (20);

(f) a nozzle (111) connected to the second end (119) of the rocket case (115);

(g) a first sphere (40) in the rocket case (115), intermediate the first end (118) of the rocket case and the tank (20), the first sphere (40) initially containing helium at a second pressure which is higher than the first pressure and at a cryogenic temperature, the helium comprising the gas initially stored at a cryogenic temperature;

(h) a second sphere (30) in the rocket case (115), intermediate the first end (118) of the rocket case and the tank (20), the second sphere (30) initially containing gaseous oxygen at a third pressure which is higher than the second pressure;

(i) means for fluidly connecting the hybrid heater (50) to the tank (20), the hybrid heater (50) generating exhaust when ignited and being positioned such that its exhaust enters the tank (20);

(j) a first gas line (41) for allowing helium to flow from the first sphere (40) to the hybrid heater (50);

(k) a second gas line (36) for allowing oxygen gas to flow from the second sphere (30) to the hybrid heater (50);

(l) a second hybrid heater (90) connected to the first sphere (40), the second hybrid heater (90) generating exhaust when ignited and being positioned such that its exhaust enters the first sphere (40);

(m) a third gas line (37) for allowing oxygen gas to flow from the second sphere (30) to the first sphere (40);

(n) a plurality of pressure transducers (83) for detecting the ullage pressure in the tank (20);

(o) a pressure control mechanism (84) in communication with the pressure transducers (83); and

(p) a ganged control valve (80) in communication with the pressure control mechanism (84), the ganged control valve (80) controlling the flow of helium and oxygen gas from the first sphere (40) and the second sphere (30), respectively, into the first hybrid heater (50), in response to the ullage pressure in the tank (20) as detected by the pressure transducers (83).

22. The apparatus of claim 21, further comprising an electric ignition system for electrically igniting the rocket.

23. The apparatus of claim 22, wherein:

the electric ignition system for electrically igniting the rocket includes;

a third hybrid heater having combustion products when ignited, the combustion products of the third hybrid heater entering the casing of the second fuel component when the third hybrid heater is ignited; and

spark-producing means for igniting the third hybrid heater.

24. The apparatus of claim 23, wherein:

the spark-producing means produces no sparks when in an inert-gas environment.

25. The apparatus of claim 24, wherein:

the spark-producing means is a carbon arc.

26. The apparatus of claim 1, wherein the mixing chamber is between the hybrid heater and the container for containing the first liquid fuel component.

27. The apparatus of claim 26, further comprising a second container for initially storing the gas and a second heater for heating the gas while the gas is in the second container.

28. The apparatus of claim 27, wherein the second heater comprises a second hybrid heater.

29. The apparatus of claim 1, further comprising a second container for initially storing the gas and a second heater for heating the gas while the gas is in the second container.

30. The apparatus of claim 24, wherein the second heater comprises a second hybrid heater.