CN108626029A - A kind of engine system can be used for recoverable carrier rocket - Google Patents
A kind of engine system can be used for recoverable carrier rocket Download PDFInfo
- Publication number
- CN108626029A CN108626029A CN201710143869.5A CN201710143869A CN108626029A CN 108626029 A CN108626029 A CN 108626029A CN 201710143869 A CN201710143869 A CN 201710143869A CN 108626029 A CN108626029 A CN 108626029A
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- China
- Prior art keywords
- rocket
- thrust
- engine system
- tons
- engine
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Separation, Recovery Or Treatment Of Waste Materials Containing Plastics (AREA)
Abstract
The engine system of traditional nonrecoverable rocket cannot be reused, rocket launching is with high costs, the application of recyclable recoverable rocket will greatly reduce rocket launching cost, for the recoverable rocket for realizing recyclable, a novel rocket engine need to be developed, the demand of recyclable recoverable rocket is met.The engine system for recyclable recoverable rocket, space shuttle or other be used for for space and celestial body surface aircraft, have the function of to control thrust size and thrust direction, meet rocket launching ascent stage thrust and gesture stability demand, meet landing phase thrust and gesture stability demand, realize rocket round-trip in this world, it can also be used to which rocket is in other celestial body surface take-off and landings.
Description
Technical field
The invention belongs to aerospace fields, are related to rocket engine overall design technique, aerospace Push Technology, automatic control
Technology processed and Aerospace Tracking ＆ Control.
Background technology
The engine system of traditional nonrecoverable rocket cannot be reused, and rocket launching is with high costs, recyclable
The application of recoverable rocket will greatly reduce rocket launching cost, for the recoverable rocket for realizing recyclable, need to develop a new
The rocket engine of type meets the demand of recyclable recoverable rocket.
Invention content
1, the engine system for recyclable recoverable rocket, space shuttle or other be used for be used for space and celestial body
The aircraft on surface has the function of to control thrust size and thrust direction, meets rocket launching ascent stage thrust and gesture stability
Demand meets landing phase thrust and gesture stability demand, realizes rocket round-trip in this world, it can also be used to which rocket is in other celestial bodies
Surface take-off and landing.2, the main hair for the single spraying pipe or multi nozzle that rocket engine system is 60 tons to 80 tons by a thrust
Assisted engine subsystem, structure rack and the control system group for the multi nozzle that motivation subsystem, a thrust are 1 ton to 5 tons
At partly or completely single engine jet pipe has the function of thrust adjusting or weave control.3, rocket ascent stage engine
System is operated under 60 tons to 80 tons of high thrust state, and rocket is pushed to rise, return stage, partial engine shutdown or control
Controlling push-force reduces, and is operated under 1 ton to 5 tons of low thrust state, lands for rocket.4, rocket engine system fuel working medium
For liquid propellant and the Solid-state Chemistry propellant such as dinitrogen tetroxide and uns-dimethylhydrazine, liquid oxygen and kerosene, liquid hydrogen and liquid oxygen, hydrazine
Deng.5, engine system has the function of engine start and stop, the control of thrust size, thrust direction control, Stateful Inspection etc..6, rocket
It returns after landing, for engine system by processing, some or all of component is reusable.7, engine system uses module
Change configuration and component polytypic common technology, engine system can continue to combine, and realize the engine system of bigger, meet and rise
80 tons to 4000 tons of section thrust range and 5 tons to 400 tons thrust requirements of descending branch thrust range.8, each single spray of engine system
Pipe can be distributed in recyclable recoverable rocket, space shuttle or other be used for the arbitrary of aircraft for space and celestial body surface
Ascent stage and return phase function are completed in position by the control cooperation of control system.
Description of the drawings
1, rocket is divided into multistage, is made of the first order and other grades.2, the rocket ascent stage, sustainer in engine system and
Assisted engine whole working condition.3, when the rocket first order is in exhausting section, the engine section shutdown in engine system,
Partial engine keeps working condition.4, when the rocket first order is in exhausting section, grid fin is opened, to keep rocket to drop
Fall posture.
Claims (8)
1. a kind of engine system, feature are：For recyclable recoverable rocket, space shuttle or other be used for for too
Empty and celestial body surface aircraft has the function of to control thrust size and thrust direction, meet rocket launching ascent stage thrust with
Gesture stability demand meets landing phase thrust and gesture stability demand, realizes rocket round-trip in this world, it can also be used to which rocket exists
Other celestial body surface take-off and landings.
2. engine system according to claim 1, feature are：The single spraying pipe for being 60 tons to 80 tons by a thrust
Or sustainer subsystem, assisted engine subsystem, the structure of the multi nozzle that thrust is 1 ton to 5 tons of multi nozzle
Rack and control system composition, partly or completely single engine jet pipe is with the big minor adjustment of thrust or thrust direction control
Function.
3. engine system according to claim 1, feature are：With engine start and stop, the control of thrust size, push away
The functions such as force direction control, Stateful Inspection.
4. engine system according to claim 1, feature are：System fuel working medium is dinitrogen tetroxide and inclined two
The liquid propellant such as methylhydrazine, liquid oxygen and kerosene, liquid hydrogen and liquid oxygen, hydrazine and Solid-state Chemistry propellant etc..
5. engine system according to claim 1, feature are：The rocket ascent stage, engine system operation was at 60 tons
To 80 tons of high thrust state, rocket is pushed to rise, return stage, partial engine shutdown or control thrust reduce, work
Make under 1 ton to 5 tons of low thrust state, lands for rocket.
6. engine system according to claim 1, feature are：After rocket returns to landing, engine system is passed through
Processing, some or all of component are reusable.
7. engine system according to claim 1, feature are：It is shared using modular arrangements and component polytypic
Technology, engine system can continue to combine, and realize the engine system of bigger, meet 80 tons to 4000 tons of ascent stage thrust range
With 5 tons to 400 tons thrust requirements of descending branch thrust range.
8. engine system according to claim 1, feature are：Each single jet pipe of engine system can be distributed in can
Recycle recoverable rocket, space shuttle or other be used for any part of the aircraft for space and celestial body surface, pass through control
Ascent stage and return phase function are completed in the control cooperation of system processed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710143869.5A CN108626029A (en) | 2017-03-16 | 2017-03-16 | A kind of engine system can be used for recoverable carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710143869.5A CN108626029A (en) | 2017-03-16 | 2017-03-16 | A kind of engine system can be used for recoverable carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108626029A true CN108626029A (en) | 2018-10-09 |
Family
ID=63686206
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710143869.5A Pending CN108626029A (en) | 2017-03-16 | 2017-03-16 | A kind of engine system can be used for recoverable carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108626029A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606738A (en) * | 2019-01-14 | 2019-04-12 | 北京星际荣耀空间科技有限公司 | A kind of reusable carrier rocket core first-stage rocket body recycling dynamical system |
| CN111071492A (en) * | 2019-12-02 | 2020-04-28 | 燕山大学 | Rocket for recovering turbine brake by utilizing gas energy and recovery deceleration method thereof |
| CN111891413A (en) * | 2020-06-05 | 2020-11-06 | 宋延军 | Auxiliary system for assisting launching and recovery of aircraft and launching and recovery method |
| CN112963269A (en) * | 2021-01-19 | 2021-06-15 | 中国人民解放军63921部队 | Carrier rocket base-level vertical recovery method using traveling engine |
| CN117781785A (en) * | 2024-02-22 | 2024-03-29 | 江苏深蓝航天有限公司 | Interstage section structure of recoverable rocket |
-
2017
- 2017-03-16 CN CN201710143869.5A patent/CN108626029A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606738A (en) * | 2019-01-14 | 2019-04-12 | 北京星际荣耀空间科技有限公司 | A kind of reusable carrier rocket core first-stage rocket body recycling dynamical system |
| CN109606738B (en) * | 2019-01-14 | 2024-03-29 | 北京星际荣耀空间科技有限公司 | Reusable carrier rocket core primary rocket body recovery power system |
| CN111071492A (en) * | 2019-12-02 | 2020-04-28 | 燕山大学 | Rocket for recovering turbine brake by utilizing gas energy and recovery deceleration method thereof |
| CN111071492B (en) * | 2019-12-02 | 2022-08-30 | 燕山大学 | Rocket for recovering turbine brake by utilizing gas energy and recovery deceleration method thereof |
| CN111891413A (en) * | 2020-06-05 | 2020-11-06 | 宋延军 | Auxiliary system for assisting launching and recovery of aircraft and launching and recovery method |
| CN112963269A (en) * | 2021-01-19 | 2021-06-15 | 中国人民解放军63921部队 | Carrier rocket base-level vertical recovery method using traveling engine |
| CN112963269B (en) * | 2021-01-19 | 2022-04-15 | 中国人民解放军63921部队 | Carrier rocket base-level vertical recovery method using traveling engine |
| CN117781785A (en) * | 2024-02-22 | 2024-03-29 | 江苏深蓝航天有限公司 | Interstage section structure of recoverable rocket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181009 |
|
| WD01 | Invention patent application deemed withdrawn after publication |