Flight vehicle 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. A flight vehicle position control system method comprising:
positioning an initial charge of solid propellant in an accumulator of a flight vehicle;
igniting the initial charge of solid propellant;
pressurizing the accumulator with hot gas produced by igniting the solid propellant;
determining a 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;
igniting solid propellant in the gas generator with the hot gas from the accumulator;
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 comprising:
determining the pressure in the accumulator has reached a lower threshold and/or a predetermined amount of time has elapsed since a previous event;
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 previous event; and
reigniting the solid propellant in the gas generator with the hot gas.
3. The method of claim 1 comprising maintaining the second valve in an open state until the pressure in the accumulator reaches a lower threshold.
4. The method of claim 1 comprising releasing hot gas from the accumulator through at least one thruster.
5. The method of claim 4 comprising adjusting an attitude of the flight vehicle using the hot gas released through the at least one thruster.
6. The method of claim 1 comprising:
determining 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 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 comprising:
determining 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;
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; and
reigniting the solid propellant in the gas generator with the hot gas.
9. The method of claim 1 comprising:
(a) determining 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 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;
(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; and
(e) reigniting the solid propellant in the gas generator with the hot gas.
10. The method of claim 9 comprising repeating steps (a)-(e) at least twice.
11. The method of claim 1 wherein the flight vehicle is a guided missile.
12. A flight vehicle position control method comprising:
burning solid propellant in a gas generator;
storing hot gas produced by burning the solid propellant in an accumulator, the gas generator and the accumulator being part of a flight vehicle;
releasing the hot gas in the accumulator through one or more thrusters to control the position of the flight vehicle; and
extinguishing the solid propellant in the gas generator and reigniting the solid propellant in the gas generator with the hot gas stored in the accumulator.
13. The method of claim 12 comprising:
determining that a pressure in the accumulator has reached an upper threshold;
wherein the solid propellant in the gas generator is extinguished based upon the pressure in the accumulator reaching the upper threshold.
14. The method of claim 13 comprising:
determining that a set point has been reached;
wherein the solid propellant in the gas generator is reignited based upon the set point being reached.
15. The method of claim 14 wherein the set point is a lower threshold of the pressure in the accumulator and/or a set amount of time that has passed since a previous event.
16. The method of claim 12 comprising repeatedly igniting and extinguishing the solid propellant in the gas generator and repeatedly pressurizing the accumulator with the hot gas produced by burning the solid propellant.
17. The method of claim 12 comprising:
burning an initial charge of solid propellant in the accumulator and pressurizing the accumulator with hot gas produced by burning the initial charge of the solid propellant; and
igniting the solid propellant in the gas generator for the first time with the hot gas generated by burning the initial charge of the solid propellant.
18. The method of claim 12 wherein the flight vehicle is a guided missile.
19. A flight vehicle position control method comprising:
burning solid propellant in a gas generator;
storing hot gas produced by burning the solid propellant in an accumulator, the gas generator and the accumulator being part of a flight vehicle;
closing a valve positioned between the gas generator and the accumulator and preventing the hot gas from flowing between the gas generator and the accumulator;
extinguishing the solid propellant in the gas generator; and
reigniting the solid propellant in the gas generator with the hot gas from the accumulator.
20. The method of claim 19 comprising:
determining that a pressure in the accumulator has reached an upper threshold;
wherein the solid propellant in the gas generator is extinguished based upon the pressure in the accumulator reaching the upper threshold.
21. The method of claim 20 comprising:
determining that a set point has been reached;
wherein the solid propellant in the gas generator is reignited based upon the set point being reached.
22. The method of claim 21 wherein the set point is a lower threshold of the pressure in the accumulator and/or a set amount of time that has passed since a previous event.
23. The method of claim 19 comprising repeatedly igniting and extinguishing the solid propellant in the gas generator and repeatedly pressurizing the accumulator with the hot gas produced by burning the solid propellant.
24. The method of claim 19 comprising:
burning an initial charge of solid propellant in the accumulator and pressurizing the accumulator with hot gas produced by burning the initial charge of the solid propellant; and
igniting the solid propellant in the gas generator for the first time with the hot gas generated by burning the initial charge of the solid propellant.
25. The method of claim 19 wherein the flight vehicle is a guided missile.