Extinguishable divert system
Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.
1. A method for controlling the trajectory of a flight vehicle comprising:
(a) igniting solid propellant in a first hot gas generator disposed in a first case and a second hot gas generator disposed in a second case on the flight vehicle and generating hot gas, the solid propellant in the first hot gas generator and the second hot gas generator burning at the same time, wherein the second case is spaced apart from the first case along a lengthwise axis;
(b) discharging the hot gas through at least one divert thruster on the flight vehicle;
(c) extinguishing the solid propellant by rapidly depressurizing the first hot gas generator and the second hot gas generator;
igniting solid propellant in a hot gas accumulator on the flight vehicle and igniting the solid propellant in the first hot gas generator and/or the second hot gas generator with hot gas from the hot gas accumulator, wherein the hot gas accumulator is configured to store hot gas; and
repeating (a) and (c) at least once;
wherein (b) and (c) can be performed in any order.
2. The method of claim 1 comprising repeating (a) and (c) at least twice.
3. The method of claim 1 comprising igniting the solid propellant in the first hot gas generator and/or the second hot gas generator with hot gas stored in a hot gas accumulator.
4. The method of claim 1 comprising igniting solid propellant in an attitude control gas generator with the hot gas from the hot gas accumulator.
5. The method of claim 1 comprising igniting the solid propellant in the first hot gas generator and/or the second hot gas generator with an igniter.
6. The method of claim 1 wherein rapidly depressurizing the first hot gas generator and the second hot gas generator comprises opening an extinguishment valve.
7. The method of claim 1 wherein the first hot gas generator and the second hot gas generator are part of a divert system and the first hot gas generator and the second hot gas generator are spaced apart and positioned opposite each other along a lengthwise axis of the divert system.
8. The method of claim 1 comprising providing on-demand, multi-pulse divert thrust for at least 1000 seconds operation time.
9. The method of claim 1 wherein the flight vehicle is a kill vehicle of a missile defense interceptor missile.
10. A divert system for a flight vehicle comprising:
a first hot gas generator including solid propellant positioned in the first hot gas generator;
a second hot gas generator including solid propellant positioned in the second hot gas generator;
divert thrusters on the flight vehicle pneumatically linked to at least one of the first hot gas generator or the second hot gas generator; and
an extinguishment valve pneumatically linked to the first hot gas generator and the second hot gas generator, the extinguishment valve being movable between a closed position where the hot gas generator is not vented and an open position where the hot gas generator is vented;
wherein the extinguishment valve is configured to rapidly depressurize the hot gas generator and extinguish the solid propellant when the extinguishment valve is moved from the closed position to the open position;
wherein the first hot gas generator and the second hot gas generator are spaced apart along a lengthwise axis of the divert system and positioned opposite each other along the lengthwise axis;
wherein the first hot gas generator and the second hot gas generator are pneumatically linked to each other;
a hot gas accumulator pneumatically linked to the first hot gas generator and/or the second hot gas generator; and
solid propellant positioned in the hot gas accumulator.
11. The divert system of claim 10 wherein the first hot gas generator and the second hot gas generator are pneumatically separate from any propulsion rocket motors on the flight vehicle.
12. The divert system of claim 10 wherein the divert thrusters are positioned between first hot gas generator and the second hot gas generator.
13. The divert system of claim 10 comprising an attitude control hot gas generator pneumatically linked to the hot gas accumulator.
14. A divert system for a flight vehicle comprising:
a first hot gas generator including solid propellant positioned in the first hot gas generator;
a second hot gas generator including solid propellant positioned in the second hot gas generator;
divert thrusters pneumatically linked to at least one of the first hot gas generator or the second hot gas generator;
wherein the first hot gas generator and the second hot gas generator are spaced apart along a lengthwise axis of the divert system and positioned opposite each other along the lengthwise axis;
wherein the first hot gas generator and the second hot gas generator are pneumatically linked to each other;
wherein the first hot gas generator and the second hot gas generator are pneumatically separate from any propulsion rocket motors on the flight vehicle;
wherein the divert thrusters are positioned between the first hot gas generator and the second hot gas generator along the lengthwise axis of the divert system;
a hot gas accumulator pneumatically linked to the first hot gas generator and/or the second hot gas generator; and
solid propellant positioned in the hot gas accumulator.
15. The divert system of claim 14 comprising:
an extinguishment valve pneumatically linked to the first hot gas generator and/or the second hot gas generator, the extinguishment valve being movable between a closed position where the first hot gas generator and/or the second hot gas generator is not vented and an open position where the first hot gas generator and/or the second hot gas generator is vented;
wherein the extinguishment valve is configured to rapidly depressurize the first hot gas generator and/or the second hot gas generator and extinguish the solid propellant when the extinguishment valve is moved from the closed position to the open position.
16. The divert system of claim 14 comprising an attitude control hot gas generator pneumatically linked to the hot gas accumulator.