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Found results for
 patents
1.
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Flight vehicle control system
| Application Number |
16827588 |
| Grant Number |
11448165 |
| Status |
In Force |
| Filing Date |
2020-03-23 |
| First Publication Date |
2022-09-20 |
| Grant Date |
2022-09-20 |
| Owner |
Valley Tech Systems, Inc. (USA)
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| Inventor |
- Carlson, Russell
- Barr, Dustin
- Yan, Allen
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Abstract
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.
IPC Classes ?
- F02K 9/94 - Re-ignitable or restartable rocket-engine plantsIntermittently operated rocket-engine plants
- F42B 15/01 - Arrangements thereon for guidance or control
- F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
- F02K 9/80 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control
- B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
- B64G 1/26 - Guiding or controlling apparatus, e.g. for attitude control using jets
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2.
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Extinguishable divert system
| Application Number |
17447623 |
| Grant Number |
11680543 |
| Status |
In Force |
| Filing Date |
2021-09-14 |
| First Publication Date |
2021-12-30 |
| Grant Date |
2023-06-20 |
| Owner |
Valley Tech Systems, Inc. (USA)
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| Inventor |
- Carlson, Russell
- Barr, Dustin
- Yan, Allen
- Carpenter, Justin
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Abstract
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.
IPC Classes ?
- F02K 9/26 - Burning control
- B64G 1/40 - Arrangements or adaptations of propulsion systems
- F02K 9/94 - Re-ignitable or restartable rocket-engine plantsIntermittently operated rocket-engine plants
- F02K 9/22 - Shape or structure of solid propellant charges of the front-burning type
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3.
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Extinguishable divert system
| Application Number |
16411108 |
| Grant Number |
11143143 |
| Status |
In Force |
| Filing Date |
2019-05-13 |
| First Publication Date |
2021-10-12 |
| Grant Date |
2021-10-12 |
| Owner |
Valley Tech Systems, Inc. (USA)
|
| Inventor |
- Carlson, Russell
- Barr, Dustin
- Yan, Allen
- Carpenter, Justin
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Abstract
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.
IPC Classes ?
- F02K 9/26 - Burning control
- B64G 1/40 - Arrangements or adaptations of propulsion systems
- B63H 11/14 - Marine propulsion by water jets the propulsive medium being steam or other gas the gas being produced by combustion
- F02K 9/94 - Re-ignitable or restartable rocket-engine plantsIntermittently operated rocket-engine plants
- F02K 9/22 - Shape or structure of solid propellant charges of the front-burning type
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4.
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Method for controlling a flight vehicle
| Application Number |
15935630 |
| Grant Number |
10712138 |
| Status |
In Force |
| Filing Date |
2018-03-26 |
| First Publication Date |
2020-07-14 |
| Grant Date |
2020-07-14 |
| Owner |
Valley Tech Systems, Inc. (USA)
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| Inventor |
- Carlson, Russell
- Barr, Dustin
- Yan, Allen
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Abstract
A method for controlling the attitude and/or flight path of a flight vehicle includes burning propellant in a gas generator to produce hot gas, storing the hot gas in an accumulator, and releasing the hot gas in the accumulator through one or more thrusters to control the attitude and/or flight path of the flight vehicle.
IPC Classes ?
- F42B 15/01 - Arrangements thereon for guidance or control
- F42B 10/66 - Steering by varying intensity or direction of thrust
- F42B 10/00 - Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missilesArrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
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5.
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Attitude control system
| Application Number |
14875424 |
| Grant Number |
10598128 |
| Status |
In Force |
| Filing Date |
2015-10-05 |
| First Publication Date |
2020-03-24 |
| Grant Date |
2020-03-24 |
| Owner |
Valley Tech Systems, Inc. (USA)
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| Inventor |
- Carlson, Russell
- Barr, Dustin
- Yan, Allen
|
Abstract
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.
IPC Classes ?
- F02K 9/94 - Re-ignitable or restartable rocket-engine plantsIntermittently operated rocket-engine plants
- F42B 15/01 - Arrangements thereon for guidance or control
- F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
- F02K 9/80 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control
- B64G 1/26 - Guiding or controlling apparatus, e.g. for attitude control using jets
- B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
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6.
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Attitude control system
| Application Number |
14847820 |
| Grant Number |
09927217 |
| Status |
In Force |
| Filing Date |
2015-09-08 |
| First Publication Date |
2018-03-27 |
| Grant Date |
2018-03-27 |
| Owner |
Valley Tech Systems, Inc. (USA)
|
| Inventor |
- Carlson, Russell
- Barr, Dustin
- Yan, Allen
|
Abstract
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.
IPC Classes ?
- F42B 10/66 - Steering by varying intensity or direction of thrust
- F42B 15/01 - Arrangements thereon for guidance or control
- F42B 10/00 - Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missilesArrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
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