Pulsed detonation engines for reaction control systems
View Patent ↗Pulsed detonation engines (PDEs) are adapted for use in reaction control systems (RCS), such as thrusters for orbital correction and control (e.g., for earth-orbiting satellites), divert thrust generation and control for space-based interceptor devices, and for missile trajectory correction and motion control. According to one aspect of the invention, PDEs are adapted for motion control of so-called “kill vehicles,” which are small devices, typically launched from satellites, for strategic missile defense.
1. A reaction control system for controlling motion of a vehicle, the reaction control system comprising:
at least one pulsed detonation engine comprising one or more propellant valves, an igniter, a detonation chamber, and a nozzle;
wherein the at least one pulsed detonation engine is adapted to controllably ignite detonation of a propellant to generate thrust in a predetermined vector for controlling motion of said vehicle.
2. The reaction control system of claim 1 which comprises a plurality of pulsed detonation engines capable of generating thrust in a plurality of vectors.
3. The reaction control system of claim 2 further comprising a controller for controlling operation of said plurality of pulsed detonation engines, wherein the controller is selected from the group consisting of a piezoelectric device, a thermo-fluidic device, a microelectronic mechanical system, an electromagnetic system, and combinations thereof.
4. The reaction control system of claim 1 wherein said at least one pulsed detonation engine comprises a detonation chamber having an igniter positioned downstream of a point at which propellant is injected.
5. The reaction control system of claim 1 wherein said at least one pulsed detonation engine comprises an igniter selected from the group consisting of a spark plug, a pyrotechnic device, and a laser.
6. The reaction control system of claim 1 further comprising an electrical energy regeneration and storage device capable of permitting remote operation of said at least one pulsed detonation engine for extended periods of time.
7. A vehicle comprising the reaction control system of claim 1 .
8. A reaction control system for controlling the motion of a missile or other vehicle, the reaction control system comprising:
at least four pulsed detonation engines arranged in a cruciform for selectively generating thrust in at least four vectors, wherein each of said pulsed detonation engines comprises electronically controlled propellant valves, an igniter, a detonation chamber, and a nozzle;
a controller for selectively actuating said at least four pulsed detonation engines, the controller comprising at least one of a piezoelectric device, a thermo-fluidic device, an electromagnetic device, and a microelectronic mechanical system.
9. A missile comprising the reaction control system of claim 8 .
10. The reaction control system of claim 1 which is a thruster for orbital correction and control of an earth-orbiting satellite.
11. The reaction control system of claim 1 which provides divert thrust generation and control for a space-based interceptor device.
12. The reaction control system of claim 1 which provides trajectory correction and motion control of a missile.