CN118004452B - Reusable escape system of manned carrier rocket - Google Patents
Reusable escape system of manned carrier rocket Download PDFInfo
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- CN118004452B CN118004452B CN202410134687.1A CN202410134687A CN118004452B CN 118004452 B CN118004452 B CN 118004452B CN 202410134687 A CN202410134687 A CN 202410134687A CN 118004452 B CN118004452 B CN 118004452B
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- 239000002775 capsule Substances 0.000 claims description 39
- 230000000087 stabilizing effect Effects 0.000 claims description 3
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- 238000004880 explosion Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The invention belongs to the technical field of manned space round-trip transportation, and discloses a reusable escape system of a manned carrier rocket, which comprises a modularized escape cabin, wherein the escape cabin is arranged between a modularized carrier rocket and a modularized manned module, and the escape cabin and the manned module are combined to form the escape system; an escape engine is arranged in the escape cabin, and a pneumatic component for assisting in flying is arranged outside the escape cabin; the escape system comprises a normal transmitting working mode and an escape working mode which are suitable for different conditions. The invention is arranged between the carrier rocket and the manned spacecraft, and the escape system is recycled by utilizing the return landing capability of the reusable rocket, so that the launching operation cost of the manned space-earth round-trip transportation is greatly reduced; meanwhile, the life safety of astronauts can be guaranteed when the danger occurs.
Description
Technical Field
The invention belongs to the technical field of manned space-earth round-trip transportation, and particularly relates to a reusable escape system of a manned carrier rocket.
Background
The traditional manned spacecraft is provided with a launching escape system, and under the condition of carrier rocket launching failure, the escape system can rapidly bring the manned spacecraft away from a rocket explosion dangerous area, so that the life safety of astronauts is ensured.
The typical escape tower system is positioned at the top end of the manned spacecraft, even if the rocket is launched normally and the escape tower is not used, the escape tower with high cost is discarded after the spacecraft reaches a certain height, so that the recovery and the repeated use of the escape system can not be realized, and the cost of the manned space-earth round-trip transportation is greatly increased; and the escape tower system has larger weight and limits the comprehensive performance index of the manned spacecraft.
The existing scheme of integrating the escape power system with the blunt body return cabin integrates the thrust engine required by escape into the return cabin, and realizes the reusability of the escape system by utilizing the characteristic of recoverable return cabin. However, this escape system integration scheme puts high technical demands on the miniaturization and light weight of the high-thrust engine. On the other hand, the escape system integration scheme is only suitable for blunt body airships, cannot be flexibly matched with schemes such as lifting body airships, and has a limited application range.
Therefore, the application designs a reusable escape system of the manned carrier rocket to solve the technical problems.
Disclosure of Invention
In order to solve the technical problems, the invention provides a reusable escape system of a manned carrier rocket.
In order to achieve the above purpose, the invention provides a reusable escape system of a manned carrier rocket, which comprises a escape capsule in a modularized design, wherein the escape capsule is arranged between a modularized carrier rocket and a modularized manned module, and the escape capsule and the manned module are combined to form the escape system;
an escape engine is arranged in the escape cabin, and a pneumatic component for assisting in flying is arranged outside the escape cabin;
The escape system comprises a normal emission working mode and an escape working mode which are suitable for different conditions.
Preferably, the aerodynamic component comprises a stabilizer, a strake or a resistance plate arranged outside the escape capsule.
Preferably, two ends of the escape capsule are respectively provided with a fire work lock, and the fire work locks are respectively fixedly connected with the manned module and the carrier rocket.
Preferably, when the escape system is in the normal launching working mode, an escape capsule of the escape system is separated from the manned module, and the escape capsule and the carrier rocket are repeatedly used after being combined and landed.
Preferably, when the escape system is in the escape working mode, the escape engine enables the escape system to be separated from the carrier rocket and then to be separated from the dangerous area, and then the manned module is separated from the escape capsule and then recovered to land.
Preferably, the manned module comprises a first manned spacecraft, and the escape capsule is fixed on the first manned spacecraft to form a first escape assembly.
Preferably, the manned module comprises a second manned spacecraft, and the escape capsule is fixed on the second manned spacecraft to form a second escape assembly.
Preferably, the manned module comprises a third manned spacecraft, and the escape capsule is fixed on the third manned spacecraft to form a third escape assembly.
Compared with the prior art, the invention has the following advantages and technical effects: the invention discloses a reusable escape system of a manned carrier rocket, wherein an escape cabin provided with an escape engine is arranged at the bottom end of a manned module to form the escape system, and then the escape system and the carrier rocket are combined together to form the reusable manned carrier rocket system, and the expensive escape system is recovered and reused by utilizing the reentry and return and fixed-point landing capabilities of the reusable carrier rocket, so that the operation cost of the manned round-trip transportation is greatly reduced; the pneumatic component outside the escape cabin is used for improving the aerodynamics of the escape system during the flight and ensuring the stability of the flight; the escape system comprises two different modes of a normal working mode escape working mode, can be suitable for two states of normal working and dangerous working of a rocket, is convenient for recycling and using when in normal working, and reduces cost; when faults or dangers occur, the escape system enters an escape working mode, so that the escape system is separated from a dangerous area, and the safety of astronauts is ensured; meanwhile, the technical scheme has relatively low requirements on the weight and the size of the high-thrust escape engine; the manned airship has good adaptability to manned airships of different configurations, and is beneficial to popularization and application of schemes; the scheme can effectively reduce the system cost and has higher economic benefit after popularization and application.
The invention is arranged between the carrier rocket and the manned spacecraft, and the escape system is recycled by utilizing the return landing capability of the reusable rocket, so that the launching operation cost of the manned space-earth round-trip transportation is greatly reduced; meanwhile, the life safety of astronauts can be guaranteed when the danger occurs.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic view of the escape capsule structure of the present invention;
FIG. 2 is a flow chart of the operation of the manned spacecraft escape system of the present invention under normal conditions;
FIG. 3 is a workflow diagram of the manned spacecraft escape system of the present invention in an abnormal situation;
FIG. 4 is a schematic view of a first escape assembly according to the present invention;
FIG. 5 is a schematic view of a second escape assembly according to the present invention;
FIG. 6 is a schematic view of a third escape assembly according to the present invention;
In the figure: 101. an escape capsule; 102. escaping the engine; 103. a pneumatic component; 104. a firer lock; 105. a first manned spacecraft; 106. a first escape assembly; 107. a second manned spacecraft; 108. a second escape assembly; 109. a third manned spacecraft; 110. and a third escape assembly.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Referring to fig. 1-6, the present embodiment provides a reusable escape system for a manned carrier rocket, including a escape capsule 101 of modular design, the escape capsule 101 being disposed between a modular carrier rocket and a modular manned module, the escape capsule 101 and the manned module being combined to form the escape system;
an escape engine 102 is arranged in the escape cabin 101, and a pneumatic component 103 for assisting flight is arranged outside the escape cabin 101;
the escape system comprises a normal transmitting working mode and an escape working mode which are suitable for different conditions.
The invention discloses a reusable escape system of a manned carrier rocket.A escape cabin 101 provided with an escape engine 102 is arranged at the bottom end of a manned module to form an escape system, and then the escape system and the carrier rocket are combined together to form a reusable manned carrier rocket system, and the expensive escape system is recycled and reused by utilizing the reentry and return and fixed-point landing capabilities of the reusable carrier rocket, so that the operation cost of the manned carrier rocket for round-trip transportation in the heaven and earth is greatly reduced; the pneumatic component 103 outside the escape cabin 101 is used for improving the aerodynamics of the escape system during the flight, so as to ensure the stability of the flight; the escape system comprises two different modes of a normal working mode escape working mode, can be suitable for two states of normal working and dangerous working of a rocket, is convenient for recycling and using when in normal working, and reduces cost; when faults or dangers occur, the escape system enters an escape working mode, so that the escape system is separated from a dangerous area, and the safety of astronauts is ensured; meanwhile, the technical scheme has relatively low requirements on the weight and the size of the high-thrust escape engine 102; the manned airship has good adaptability to manned airships of different configurations, and is beneficial to popularization and application of schemes. The scheme can effectively reduce the system cost and has higher economic benefit after popularization and application. The invention is arranged between the carrier rocket and the manned spacecraft, and the escape system is recycled by utilizing the return landing capability of the reusable rocket, so that the launching operation cost of the manned space-earth round-trip transportation is greatly reduced; meanwhile, the life safety of astronauts can be guaranteed when the danger occurs.
Further, escape engine 102 is installed in the flight deck 101 to provide the large thrust required for the escape flight of the escape assembly for rapid ignition in the event of a failure of the launch vehicle, and to rapidly carry the manned module away from the rocket explosion hazard.
Further, the escape system control function is required to realize the gesture control function during the escape working mode, and mainly includes configuring the escape engine 102 with a swing nozzle and a servo mechanism; installing a gas rudder system for escaping the engine 102; a large thrust reaction control system is independently installed on the escape capsule 101; by adopting a parallel installation scheme of a plurality of escape engines 102, each engine has deep thrust-changing capability, and the attitude control of the combined body is realized through the thrust-changing control of different engines, so that the attitude of the manned spacecraft is kept stable during the ignition of the escape engines 102.
Further, the escape capsule 101 does not need to be additionally provided with a parachute, a thrust reverser, and the like required for return control.
Further preferably, the aerodynamic components 103 comprise stabilizing wings, strake wings or resistance plates arranged outside the escape capsule 101. The pneumatic components 103 are installed on the periphery of the escape capsule 101 according to the pneumatic shape requirement, and the pneumatic components 103 such as pneumatic stabilizing wings, strake wings and resistance plates have the function of improving the pneumatic characteristics of the combined body during the escape flight, and can be used singly or in combination according to the design, and the embodiment is not limited.
Further optimizing scheme, the two ends of escape capsule 101 are provided with respectively and fire the worker lock 104, and fire the worker lock 104 respectively with manned module and carrier rocket fixed connection. The initiating explosive device locks 104 are arranged at two ends of the escape capsule 101, and are mainly used for quickly combining and separating with the manned rocket and the manned module; the loading and unloading of the modules are realized, and different separation areas can be activated in different working modes in the air.
Further optimizing scheme, when the escape system is in the normal launching working mode, the escape cabin 101 of the escape system is separated from the manned module, and the escape cabin 101 and the carrier rocket are combined and are reused after being landed. Referring to fig. 2, when the manned space launching is performed, if the carrier rocket normally works, after the carrier rocket reaches a certain height, the manned module is separated from the carrier rocket at a separation interface between the manned module and the escape capsule 101 according to a set time sequence, the escape capsule 101 and the carrier rocket form a combined body to drop back together, and the combined body precisely lands to a designated position under the actions of reverse thrust ignition and active position control of a rocket engine. The manned module continues manned aerospace flight; after the escape capsule 101 is brought back to the ground by a rocket, necessary function detection and maintenance are performed, so that the reuse of an escape system can be realized, and the manned ground round-trip transportation cost is greatly reduced.
Further optimizing scheme, when the escape system is in the escape working mode, the escape engine 102 enables the escape system to be separated from the carrier rocket and then to be separated from the dangerous area, and then the manned module is separated from the escape capsule 101 and then recovered to land. Referring to fig. 3, when the manned space launching activity is carried out, if the carrier rocket fails, the escape system is started to work, the escape engine 102 is ignited, the manned module and the escape cabin 101 form a combination, the combination is rapidly separated from the rocket at the separation interface of the escape cabin 101 and the carrier rocket, and the combination rapidly flies away from the explosion danger area of the rocket; after the ignition of the escape engine 102 is finished, the escape cabin 101 is separated from the return cabin, and the return cabin returns to the designated area, so that the safety of passengers is ensured.
Further preferably, the manned module includes a first manned spacecraft 105, and the escape capsule 101 is fixed to the first manned spacecraft 105 to form a first escape assembly 106. Referring to fig. 4, for a first manned spacecraft 105 of a single return tank configuration, the escape tanks 101 are essentially identical in construction to fig. 1, forming a first escape assembly 106 with the first manned spacecraft 105.
Further preferably, the manned module comprises a second manned spacecraft 107, and the escape capsule 101 is fixed to the second manned spacecraft 107 to form a second escape assembly 108. As shown in fig. 5, for a second manned spacecraft 107 of the return and propulsion configuration, the escape capsule 101 is essentially identical in construction to fig. 1, forming a second escape assembly 108 with the second manned spacecraft 107.
Further preferably, the manned module includes a third manned spacecraft 109, and the escape capsule 101 is fixed to the third manned spacecraft 109 to form a third escape assembly 110. As shown in fig. 6, the escape capsule 101 is mainly configured as in fig. 1 for a third manned spacecraft 109 of a lifting body configuration, and forms a third escape assembly 110 with the third manned spacecraft 109.
Therefore, the escape system of the embodiment adopts a modularized design, and has good adaptability to manned modules of different configurations.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solutions of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (4)
1. A human carrier rocket reusable escape system, characterized by: the escape capsule (101) is in a modularized design, the escape capsule (101) is arranged between a modularized carrier rocket and a modularized manned module, and the escape capsule (101) and the manned module are combined to form an escape system;
An escape engine (102) is arranged in the escape cabin (101), and a pneumatic component (103) for assisting in flying is arranged outside the escape cabin (101);
The escape system comprises a normal emission working mode and an escape working mode which are suitable for different conditions;
The pneumatic component (103) comprises a stabilizing wing, a strake wing or a resistance plate which are arranged outside the escape capsule (101);
Two ends of the escape cabin (101) are respectively provided with a fire work lock (104), and the fire work locks (104) are respectively fixedly connected with the manned module and the carrier rocket;
When the escape system is in a normal launching working mode, an escape cabin (101) of the escape system is separated from the manned module, and the escape cabin (101) and the carrier rocket are repeatedly used after being combined and landed;
When the escape system is in an escape working mode, the escape engine (102) enables the escape system to be separated from the carrier rocket and then to be separated from the dangerous area, and then the manned module is separated from the escape capsule (101) and then recovered to land.
2. A manned carrier rocket reusable escape system according to claim 1, wherein: the manned module comprises a first manned spacecraft (105), and the escape capsule (101) is fixed on the first manned spacecraft (105) to form a first escape assembly (106).
3. A manned carrier rocket reusable escape system according to claim 1, wherein: the manned module comprises a second manned spacecraft (107), and the escape capsule (101) is fixed on the second manned spacecraft (107) to form a second escape assembly (108).
4. A manned carrier rocket reusable escape system according to claim 1, wherein: the manned module comprises a third manned spacecraft (109), and the escape capsule (101) is fixed on the third manned spacecraft (109) to form a third escape assembly (110).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410134687.1A CN118004452B (en) | 2024-01-31 | 2024-01-31 | Reusable escape system of manned carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410134687.1A CN118004452B (en) | 2024-01-31 | 2024-01-31 | Reusable escape system of manned carrier rocket |
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| Publication Number | Publication Date |
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| CN118004452A CN118004452A (en) | 2024-05-10 |
| CN118004452B true CN118004452B (en) | 2024-07-12 |
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| CN202410134687.1A Active CN118004452B (en) | 2024-01-31 | 2024-01-31 | Reusable escape system of manned carrier rocket |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014021741A2 (en) * | 2012-07-31 | 2014-02-06 | Aleksandrov Oleg Aleksandrovich | Method for multiply lifting a wide load into and returning the latter from space, and apparatus for carrying out said method |
| CN111290426A (en) * | 2018-12-07 | 2020-06-16 | 上海航空电器有限公司 | Prediction control method for automatically avoiding escape path of aircraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6513472B2 (en) * | 2015-05-12 | 2019-05-15 | 株式会社Ｉｈｉエアロスペース | Rocket payload emergency escape system |
| CN106494649B (en) * | 2016-10-10 | 2019-01-29 | 南京航空航天大学 | A kind of manned rocket release apparatus and its working method based on aerodynamic force |
| CN110733669B (en) * | 2019-10-24 | 2021-06-18 | 北京空间技术研制试验中心 | Spacecraft re-entry capsule mass center dynamic adjusting device |
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- 2024-01-31 CN CN202410134687.1A patent/CN118004452B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014021741A2 (en) * | 2012-07-31 | 2014-02-06 | Aleksandrov Oleg Aleksandrovich | Method for multiply lifting a wide load into and returning the latter from space, and apparatus for carrying out said method |
| CN111290426A (en) * | 2018-12-07 | 2020-06-16 | 上海航空电器有限公司 | Prediction control method for automatically avoiding escape path of aircraft |
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| CN118004452A (en) | 2024-05-10 |
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