Integrated warhead ESAD/multi-pulse rocket motor EISD device

Patent metadata

Field	Value
Publication number	US-11047340-B2
Application number	US-201916541281-A
Country	US
Kind code	B2
Filing date	Aug 15, 2019
Priority date	Aug 15, 2019
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

A multi-pulse propulsion system for a launch vehicle includes a multi-pulse rocket motor module, a launchable payload module, and a safety module that is electromechanically coupled to the multi-pulse rocket motor module and the payload module. The safety module includes at two sensors for detecting at least one environmental characteristic and/or event that is common to both the multi-pulse rocket motor module and the payload module, such that the safety module is configured to activate the multi-pulse rocket motor module and the payload module in response to the detected environmental characteristic and/or event.

First claim

What is claimed is:

1. A multi-pulse propulsion system for a launch vehicle, the multi-pulse propulsion system comprising:
a multi-pulse rocket motor module;
a payload module; and
a safety module that is electromechanically coupled to the multi-pulse rocket motor module and the payload module, and includes at least one sensor for detecting at least one environmental characteristic and/or event that is common to both the multi-pulse rocket motor module and the payload module, wherein the safety module is configured to activate the multi-pulse rocket motor module and the payload module in response to the at least one detected environmental characteristic and/or event.

2. The multi-pulse propulsion system according to claim 1 , wherein the at least one sensor includes at least one of an accelerometer, a motion timer, a distance or proximity sensor, or a voltage detector.

3. The multi-pulse propulsion system according to claim 1 , wherein the safety module includes a processing module having a memory in which predetermined conditions for the at least one environmental characteristic and/or event are stored, and a processor that is configured to compare the detected environmental characteristic and/or event with a corresponding one of the predetermined conditions.

4. The multi-pulse propulsion system according to claim 1 further comprising a power circuit including at least one of an umbilical connector, a battery, or a logic power supply, wherein the at least one environmental characteristic and/or event includes at least one of i) a disconnect of the at least one umbilical connector, ii) a battery power of the battery, or iii) an application of logic power.

5. The multi-pulse propulsion system according to claim 4 , wherein the at least one sensor includes a voltage detector for detecting the disconnect of the at least one umbilical connector.

6. The multi-pulse propulsion system according to claim 4 , wherein the power circuit includes a firing capacitor.

7. The multi-pulse propulsion system according to claim 6 , wherein the at least one sensor includes a voltage detector, and wherein the at least one environmental characteristic and/or event includes a voltage of the firing capacitor.

8. The multi-pulse propulsion system according to preceding claim 1 further comprising at least one stage that is separable from the multi-pulse propulsion system.

9. The multi-pulse propulsion system according to claim 8 , wherein the at least one characteristic and/or event includes state transitions of the multi-pulse propulsion system, and wherein the state transitions include a pre-launch acceleration state, a separation state, and an arming state.

10. The multi-pulse propulsion system according to claim 9 , wherein the state transitions further include a first motion timer state and first motion validation state that are between the pre-launch acceleration state and the separation state, and a stabilized state that is between the separation state and the arming state.

11. The multi-pulse propulsion system according to any claim 8 , wherein the at least one sensor includes a distance or proximity sensor, and wherein the at least one environmental characteristic and/or event includes a predetermined distance at which the at least one stage is separable from the multi-pulse propulsion system.

12. The multi-pulse propulsion system according to claim 8 , wherein the at least one sensor includes a timer for separating the at least one stage from the multi-pulse propulsion system, and wherein the at least one environmental characteristic and/or event includes an expiration of the timer.

13. The multi-pulse propulsion system according to claim 1 , wherein the at least one sensor includes an accelerometer, and wherein the at least one environmental characteristic and/or event includes an acceleration of the multi-pulse propulsion system.

14. The multi-pulse propulsion system according to claim 1 , wherein the at least one sensor includes a distance or proximity sensor and the at least one environmental characteristic and/or event includes a predetermined arming distance of the multi-pulse propulsion system at which the multi-pulse rocket motor module and the payload module are activated.

15. The multi-pulse propulsion system according to claim 1 , wherein the payload module includes a warhead.

16. A multi-pulse propulsion launch method, the method comprising:
detecting at least one environmental characteristic and/or event that is common to both a multi-pulse rocket motor module and a payload module using a single safety module having a sensor; and
activating both the multi-pulse rocket motor module and the payload module in response to the detected environmental characteristic and/or event.

17. The multi-pulse propulsion launch method according to claim 16 further comprising:
activating the multi-pulse rocket motor module and the payload module if the detected environmental characteristic and/or event satisfies a predetermined condition of the environmental characteristic and/or event, or determining a failure in at least one of the multi-pulse rocket motor module and the payload module if the predetermined condition is not satisfied.

18. The multi-pulse propulsion launch method according to claim 16 wherein detecting at least one environmental characteristic and/or event includes detecting at least one of a disconnect of an umbilical connector, an expiration of a motion timer, an acceleration, a minimum arming distance, or a voltage of a firing capacitor.

19. The multi-pulse propulsion launch method according to claim 16 , wherein detecting the at least one environmental characteristic and/or event includes detecting state transitions of the multi-pulse propulsion system, wherein the state transitions include a pre-launch acceleration state, a separation state, and an arming state.

20. The multi-pulse propulsion launch method according to claim 16 further comprising separating at least one stage from the multi-pulse propulsion system in response to the detected environmental characteristic and/or event.

Assignees

• Raytheon Co

Inventors

• Lefcourt Adam I
• Meschberger John A

Classifications

• F02K9/94

  Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants · CPC title

• F42B15/00

  Self-propelled projectiles or missiles, e.g. rockets; Guided missiles (F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K) · CPC title

• F02K9/96 Primary

  characterised by specially adapted arrangements for testing or measuring · CPC title

• F42B15/01 Primary

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title

• F02K9/38

  Safety devices, e.g. to prevent accidental ignition · CPC title