Attitude control system

1. A method comprising:

positioning an initial charge of solid propellant in an accumulator;

igniting the initial charge of solid propellant, producing hot gas, and pressurizing the accumulator;

determining that the pressure in the accumulator has reached an initial threshold;

opening a first valve and allowing hot gas to flow from the accumulator to a gas generator based upon the pressure in the accumulator reaching the initial threshold, the hot gas igniting solid propellant in the gas generator;

closing the first valve; and

extinguishing the solid propellant in the gas generator by opening a second valve and depressurizing the gas generator.

2. The method of claim 1 , further comprising:

determining that the pressure in the accumulator has reached a lower threshold and/or a predetermined amount of time has elapsed since the first valve closed; and

opening the first valve and allowing hot gas to flow from the accumulator to the gas generator based upon the pressure in the accumulator reaching the lower threshold and/or the predetermined amount of time elapsing since a previous event, the hot gas igniting the solid propellant in the gas generator.

3. The method of claim 2 , further comprising:

maintaining the second valve in an open state until the pressure in the accumulator has reached the lower threshold.

4. The method of claim 1 , further comprising releasing hot gas from the accumulator through at least one thruster.

5. The method of claim 4 further comprising controlling attitude adjustments to a flight vehicle by controlling the release of the hot gas through the at least one thruster.

6. The method of claim 1 , further comprising:

determining that the pressure in the accumulator has reached an upper threshold; and

closing the first valve based upon the pressure in the accumulator reaching the upper threshold.

7. The method of claim 6 , further comprising extinguishing the solid propellant in the gas generator based upon the pressure in the accumulator reaching the upper threshold.

8. The method of claim 6 , further comprising:

determining that the pressure in the accumulator has reached a lower threshold and/or a predetermined amount of time has elapsed since the pressure in the accumulator reached the upper threshold; and

opening the first valve and allowing hot gas to flow from the accumulator to the gas generator based upon the pressure in the accumulator reaching the lower threshold and/or the predetermined amount of time elapsing since the pressure in the accumulator reached the upper threshold, the hot gas igniting the solid propellant in the gas generator.

9. The method of claim 1 , further comprising:

(a) determining that the pressure in the accumulator has reached an upper threshold;

(b) closing the first valve and extinguishing the solid propellant in the gas generator based upon the pressure in the accumulator reaching the upper threshold;

(c) determining that the pressure in the accumulator has reached a lower threshold and/or a predetermined amount of time has elapsed since the pressure in the accumulator reached the upper threshold; and

(d) opening the first valve and allowing hot gas to flow from the accumulator to the gas generator based upon the pressure in the accumulator reaching the lower threshold and/or the predetermined amount of time elapsing since the pressure in the accumulator reached the upper threshold, the hot gas igniting the solid propellant in the gas generator.

10. The method of claim 9 , further comprising repeating steps (a)-(d) at least twice.

11. A flight vehicle position control method comprising:

burning an initial charge of propellant in an accumulator and pressurizing the accumulator with hot gas;

burning propellant in a gas generator and producing hot gas;

storing the hot gas from the gas generator in an the accumulator, the gas generator and the accumulator being part of the flight vehicle; and

releasing the hot gas stored in the accumulator through one or more thrusters to control the position of the flight vehicle.

12. The method of claim 11 comprising

determining that the pressure in the accumulator has reached an upper threshold; and

extinguishing the propellant in the gas generator based upon the pressure in the accumulator reaching the upper threshold.

13. The method of claim 12 comprising

determining that a set point has been reached; and

igniting the propellant in the gas generator based upon the set point being reached.

14. The method of claim 13 wherein the set point is a lower threshold of the pressure in the accumulator or a set amount of time that has passed since a previous event.

15. The method of claim 11 comprising repeatedly igniting and extinguishing the propellant in the gas generator and repeatedly pressurizing the accumulator with the hot gas from the gas generator.

16. The method of claim 11 comprising igniting the propellant in the gas generator for the first time with the hot gas generated by the initial charge.

17. The method of claim 11 comprising igniting the propellant in the gas generator with the hot gas stored in the accumulator.

18. The method of claim 11 wherein the flight vehicle is a guided missile.

19. A flight vehicle position control method comprising:

burning propellant in a gas generator and producing hot gas;

storing the hot gas in an accumulator, the gas generator and the accumulator being part of the flight vehicle;

closing a valve positioned between the gas generator and the accumulator and preventing hot gas from flowing between the gas generator and the accumulator;

extinguishing the propellant in the gas generator; and

opening the valve and allowing the hot gas to flow from the accumulator to the gas generator and reignite the propellant.

20. The method of claim 19 comprising releasing the hot gas in the accumulator through one or more thrusters and controlling the attitude of the flight vehicle.

21. The method of claim 19 wherein extinguishing the propellant in the gas generator includes opening a vent valve.

22. The method of claim 19 comprising:

determining that the pressure in the accumulator has reached a lower threshold or a set amount of time has passed since a previous event; and

opening the valve based upon the pressure in the accumulator reaching the lower threshold or passage of the set amount of time since the previous event.

23. The method of claim 19 comprising:

determining that the pressure in the accumulator has reached an upper threshold; and

closing the valve based upon the pressure in the accumulator reaching the upper threshold.

24. The method of claim 19 wherein the flight vehicle is a guided missile.

25. A flight vehicle position control method comprising:

burning propellant in a gas generator and producing hot gas;

storing the hot gas in an accumulator, the gas generator and the accumulator being part of the flight vehicle;

releasing the hot gas in the accumulator through one or more thrusters to control the position of the flight vehicle;

extinguishing the propellant in the gas generator; and

reigniting the propellant in the gas generator with the hot gas stored in the accumulator.

26. The method of claim 25 comprising:

determining that the pressure in the accumulator has reached an upper threshold; and

extinguishing the propellant in the gas generator based upon the pressure in the accumulator reaching the upper threshold.

27. The method of claim 26 comprising: determining that a set point has been reached; and reigniting the propellant in the gas generator based upon the set point being reached.

28. The method of claim 27 wherein the set point is a lower threshold of the pressure in the accumulator or a set amount of time that has passed since a previous event.

29. The method of claim 25 comprising repeatedly igniting and extinguishing the propellant in the gas generator and repeatedly pressurizing the accumulator with the hot gas.

30. The method of claim 25 comprising:

burning an initial charge of propellant in the accumulator and pressurizing the accumulator with hot gas; and

igniting the propellant in the gas generator for the first time with the hot gas generated by the initial charge.

31. The method of claim 25 wherein the flight vehicle is a guided missile.