Attitude control system
An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.
1. An attitude control system comprising:
a hot gas generator;
propellant positioned in the hot gas generator;
a hot gas accumulator coupled to the hot gas generator, the hot gas accumulator being in fluid gas transfer communication with the hot gas generator; and
a valve positioned between the hot gas generator and the hot gas accumulator, the valve including a main body;
wherein the main body extends into the hot gas accumulator.
2. The attitude control system of claim 1 wherein the valve is a hot gas accumulator valve, the attitude control system comprising a vent valve and a passage extending between the hot gas generator and the hot gas accumulator valve, wherein the vent valve is movable between an open position where the passage is open to the outside and a closed position where the passage is not open to the outside.
3. The attitude control system of claim 1 comprising a valve shaft movable between a first position where the valve is closed and a second position where the valve is open, the valve shaft including a ceramic matrix composite.
4. The attitude control system of claim 1 wherein pressure in the hot gas accumulator causes hoop compression of the portion of the main body extending into the hot gas accumulator.
5. The attitude control system of claim 1 wherein the main body includes a ceramic matrix composite.
6. The attitude control system of claim 1 wherein the main body includes C—ZrOC or C—SiC.
7. The attitude control system of claim 1 comprising one or more thrusters coupled to the hot gas accumulator.
8. The attitude control system of claim 1 wherein the valve is a hot gas accumulator valve, the attitude control system comprising a divert valve movable between an open position where the hot gas accumulator and/or the hot gas generator are in fluid communication with a divert system and a closed position where the hot gas accumulator and/or the hot gas generator are not in fluid communication with the divert system.
9. The attitude control system of claim 1 wherein the propellant includes solid propellant.
10. An attitude control system comprising:
a hot gas generator;
propellant positioned in the hot gas generator;
a hot gas accumulator coupled to the hot gas generator, the hot gas accumulator being in fluid gas transfer communication with the hot gas generator; and
a valve positioned between the hot gas generator and the hot gas accumulator, the valve including a main body made of a ceramic matrix composite.
11. The attitude control system of claim 10 wherein the valve is a hot gas accumulator valve, the attitude control system comprising a vent valve and a passage extending between the hot gas generator and the hot gas accumulator valve, wherein the vent valve is movable between an open position where the passage is open to the environment outside the attitude control system and a closed position where the passage is not open to the environment outside the attitude control system.
12. The attitude control system of claim 10 wherein the main body includes C—ZrOC or C—SiC.
13. The attitude control system of claim 10 comprising a valve shaft that is movable between a first position where the valve is closed and a second position where the valve is open, the valve shaft including a ceramic matrix composite.
14. The attitude control system of claim 13 wherein the valve shaft includes C—ZrOC or C—SiC.
15. The attitude control system of claim 10 wherein pressure in the hot gas accumulator causes hoop compression of at least a portion of the main body of the valve.
16. The attitude control system of claim 10 comprising one or more thrusters coupled to the hot gas accumulator.
17. The attitude control system of claim 10 wherein the valve is a hot gas accumulator valve, the attitude control system comprising a divert valve movable between an open position where the hot gas accumulator and/or the hot gas generator are in fluid communication with a divert system and a closed position where the hot gas accumulator and/or the hot gas generator are not in fluid communication with the divert system.
18. The attitude control system of claim 10 wherein the propellant includes solid propellant.
19. An attitude control system comprising:
a hot gas generator;
propellant positioned in the hot gas generator;
a hot gas accumulator coupled to the hot gas generator, the hot gas accumulator being in fluid gas transfer communication with the hot gas generator; and
a valve positioned between the hot gas generator and the hot gas accumulator;
wherein the attitude control system is a low level attitude control system for a guided missile.
20. The attitude control system of claim 19 wherein the total impulse produced by the attitude control system is no more than 700 lbf-sec.
21. The attitude control system of claim 19 wherein the valve is a hot gas accumulator valve, the attitude control system comprising a vent valve and a passage extending between the hot gas generator and the hot gas accumulator valve, wherein the vent valve is movable between an open position where the passage is open to the outside and a closed position where the passage is not open to the outside.
22. The attitude control system of claim 19 comprising a valve shaft movable between a first position where the valve is closed and a second position where the valve is open, the valve shaft including a ceramic matrix composite.
23. The attitude control system of claim 19 wherein pressure in the hot gas accumulator causes hoop compression of at least a portion of the valve.
24. The attitude control system of claim 19 wherein the valve comprises a main body including a ceramic matrix composite.
25. The attitude control system of claim 19 comprising one or more thrusters coupled to the hot gas accumulator.
26. The attitude control system of claim 19 wherein the valve is a hot gas accumulator valve, the attitude control system comprising a divert valve movable between an open position where the hot gas accumulator and/or the hot gas generator are in fluid communication with a divert system and a closed position where the hot gas accumulator and/or the hot gas generator are not in fluid communication with the divert system.
27. The attitude control system of claim 19 wherein the propellant includes solid propellant.