Method for controlling a flight vehicle

1. A flight attitude and/or flight path adjustment method comprising:

burning propellant in a gas generator and ejecting hot gas from the gas generator on the flight vehicle;

storing the hot gas in an accumulator on the flight vehicle; and

releasing the hot gas in the accumulator on the flight vehicle through one or more thrusters on the vehicle.

2. The method of claim 1 comprising extinguishing the propellant in the gas generator on the flight vehicle when the pressure in the accumulator reaches a set point.

3. The method of claim 2 wherein the set point is a first set point, the method comprising igniting the propellant in the gas generator on the flight vehicle when a second set point is reached.

4. The method of claim 3 wherein the second set point is a minimum pressure level in the accumulator or a set amount of time that has passed since a previous event.

5. The method of claim 1 comprising repeatedly igniting and extinguishing the propellant in the gas generator on the flight vehicle and repeatedly pressurizing the accumulator with the hot gas.

6. The method of claim 1 comprising burning an initial charge of propellant in the accumulator on the flight vehicle and pressurizing the accumulator with hot gas.

7. The method of claim 6 comprising igniting the propellant in the gas generator on the flight vehicle for the first time with the hot gas generated by the initial charge.

8. The method of claim 1 comprising igniting the propellant in the gas generator on the flight vehicle with the hot gas stored in the accumulator.

9. The method of claim 1 comprising igniting propellant in a divert system on the flight vehicle with the hot gas in the accumulator.

10. The method of claim 1 wherein the flight vehicle is a guided missile.

11. A flight attitude and/or flight path adjustment method comprising:

burning propellant in a gas generator and ejecting hot gas from the gas generator on the flight vehicle;

storing the hot gas in an accumulator on the flight vehicle;

closing a valve positioned between the gas generator and the accumulator on the flight vehicle to prevent hot gas from flowing between the gas generator and the accumulator; and

extinguishing the propellant in the gas generator on the flight vehicle.

12. The method of claim 11 comprising releasing the hot gas in the accumulator through one or more thrusters to control the attitude of the flight vehicle.

13. The method of claim 11 comprising releasing the hot gas in the accumulator through one or more thrusters to change the flight path of the flight vehicle.

14. The method of claim 11 wherein extinguishing the propellant in the gas generator on the flight vehicle includes opening a vent valve.

15. The method of claim 11 comprising opening the valve to allow the hot gas in the accumulator on the flight vehicle to flow to the gas generator and reignite the propellant.

16. The method of claim 15 wherein opening the valve includes opening the valve when the pressure in the accumulator on the flight vehicle reaches a minimum level or a set amount of time has passed since a previous event.

17. The method of claim 11 wherein closing the valve includes closing the valve when the pressure in the accumulator on the flight vehicle reaches a set point.

18. The method of claim 11 comprising igniting propellant in a divert system on the flight vehicle with the hot gas in the accumulator.

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

20. A flight vehicle divert system comprising:

a divert hot gas generator on the flight vehicle;

propellant positioned in the divert hot gas generator on the flight vehicle;

a hot gas accumulator on the flight vehicle, the hot gas accumulator being positioned in fluid gas transfer communication with the divert hot gas generator;

a divert thruster on the flight vehicle, the divert thruster being positioned in fluid gas transfer communication with the divert hot gas generator; and

a valve positioned between the divert hot gas generator and the hot gas accumulator on the flight vehicle.

21. A flight vehicle control system comprising:

the flight vehicle divert system of claim 20 , the divert hot gas generator being a first hot gas generator;

a second hot gas generator on the flight vehicle;

propellant positioned in the second hot gas generator on the flight vehicle;

another valve positioned between the second hot gas generator and the hot gas

accumulator on the flight vehicle;

wherein the hot gas accumulator is positioned in fluid gas transfer communication with the second hot gas generator.

22. The flight vehicle control system of claim 21 wherein the divert hot gas generator on the flight vehicle includes at least 1.5 times as much propellant as the second hot gas generator on the flight vehicle.

23. The flight vehicle control system of claim 21 wherein the divert hot gas generator on the flight vehicle is configured to provide at least 1.5 times as much total impulse as the second hot gas generator on the flight vehicle.

24. The flight vehicle control system of claim 21 comprising a vent valve positioned in fluid gas transfer communication with the second hot gas generator on the flight vehicle.

25. The flight vehicle divert system of claim 20 comprising an initial charge of propellant in the hot gas accumulator.

26. The flight vehicle divert system of claim 20 comprising a vent valve positioned in fluid gas transfer communication with the hot gas accumulator.

27. The flight vehicle divert system of claim 20 wherein the flight vehicle is a guided missile.