CN113324445A - Rocket rapid separation time sequence design method - Google Patents
Rocket rapid separation time sequence design method Download PDFInfo
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- CN113324445A CN113324445A CN202010128374.7A CN202010128374A CN113324445A CN 113324445 A CN113324445 A CN 113324445A CN 202010128374 A CN202010128374 A CN 202010128374A CN 113324445 A CN113324445 A CN 113324445A
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- 238000000926 separation method Methods 0.000 title claims abstract description 73
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000012772 sequence design Methods 0.000 title claims abstract description 13
- 238000013461 design Methods 0.000 claims description 12
- 230000001133 acceleration Effects 0.000 claims description 5
- 238000005259 measurement Methods 0.000 claims description 3
- 230000001934 delay Effects 0.000 claims 1
- 235000015842 Hesperis Nutrition 0.000 abstract description 7
- 235000012633 Iberis amara Nutrition 0.000 abstract description 7
- 239000007788 liquid Substances 0.000 abstract description 3
- 239000007787 solid Substances 0.000 abstract description 3
- 230000009471 action Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 239000002360 explosive Substances 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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- 238000004088 simulation Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a time sequence design method suitable for rapid interstage separation of various carrier rockets. The time sequence action of the invention comprises: the lower-level engine generates a shutdown signal, the controller sends an ignition signal to the upper-level engine after sensing the shutdown signal, the plug sheet opening sensor senses a plug sheet opening signal of the upper-level engine and sends a separation unlocking signal to the upper level, and the upper-level start control signal is sent after the inter-level separation is completed. The time sequence design method for the interstage separation of the carrier rocket can be used for solid rockets and liquid rockets, not only can ensure the effect of the interstage heat separation, but also can effectively control the interstage pressure peak value and the like, improves the separation speed, reduces the separation time, and improves the starting and controlling time margin of the engine at the upper stage.
Description
Technical Field
The invention relates to the field of inter-stage separation of carrier rocket, in particular to a time sequence design method for rapid separation of various rockets.
Background
The rocket separation design is very complex, and the restriction factors are many, such as cold separation or hot separation, separation height requirements, performance of upper and lower-level engines, time sequence selection, performance of initiating explosive devices and the like. In order to improve the separation speed, a thermal separation mode is usually adopted, and the time sequence design of the thermal separation mode is a key design point;
the rocket thermal separation time sequence is not properly selected, various abnormal conditions can occur, for example, the condition that the interstage pressure is too high due to overlong time sequence selection, and the shell of the stage section is broken; if the selected time sequence is too short, the pressure building time inside the interstage is too short, the internal pressure is too small, the separation time is too long, and even a recovery problem occurs;
therefore, it is a technical difficulty in the field to design a time sequence design method which is appropriate and can satisfy various condition constraints.
Disclosure of Invention
The invention aims to provide a time sequence design method capable of ensuring the safety of interstage separation and the quick interstage separation, which adopts proper sequence flow design such as engine ignition, plug opening, interstage cutting and the like under the premise of ensuring that the strong rigidity of a shell in a interstage section meets the requirement, so as to achieve the aim of quick and reliable interstage separation;
in order to achieve the purpose, the technical scheme of the invention is as follows:
(1) according to the characteristics of rocket thrust and stability, the separable residual thrust is given before flying, and the residual thrust value of the next stage rocket is determined according to the measurement result of the adding table in the flying process;
(2) according to the judgment result in the step (1), when the value reaches a required interval, sending an upper-level engine ignition instruction;
(3) after the upper-stage ignition instruction is sent out according to the step (2), the integrated controller starts to read the upper-stage engine plug opening information;
(4) according to the reading result in the step (3), after the integrated controller reads the opening information of the jam plate, delaying t1 to send an inter-stage separation ignition instruction;
(5) according to the time sequence point read in the step (3), delaying t3, and sending an upper-level start control instruction;
further, the rocket fast separation time sequence is as follows:
judging that the lower stage rocket is shut down, and sending an ignition signal by the upper stage engine by the controller on the basis;
the system waits for the upper-stage engine plug opening signal, and the moment when the plug opening signal is received is defined as T0 moment;
after a time delay of T1, a separation unlocking signal is sent to an interstage connection structure between the upper stage engine and the lower stage engine, and the time is defined as a time T1;
the interstage separation structure completes the cutting after T2 from the time when the separation unlocking signal is received to the time when the separation unlocking is completed, and the time is defined as T2;
after a delay time of T3 from the time T0, the control is defined as T3, and the upper-level control is started from the time T3;
further, in the rocket rapid separation time sequence design, the error at the time T0 is less than 1 ms;
further, after receiving the signal at the time T0, the controller of the rocket presets T1 time at intervals, and then sends an unlocking signal to the interstage connection structure, wherein the time of the delay T1 is 5-10 ms;
further, t2 is a fixed parameter, which is determined by the response and explosion propagation time of the interstage initiating explosive device;
further, the t3 is determined according to the characteristics of the lower-stage engine and the thrust of the upper-stage engine directly acting on the lower-stage rocket body, and the time of t3 is 40-50 ms;
compared with the prior art, the invention has the advantages that:
1. the interstage separation speed can be increased;
2. the technology realizes quick separation, can reduce electric separation devices for the separation connector, and simultaneously ensures the separation reliability of the separation plug;
3. the separation height has wide application range, can be implemented in the atmosphere and can also be implemented in a vacuum environment;
4. in the technology, because the pressure of the inner cavity of the stage section is greater than the external pressure, the separated redundant substances can fly out after being separated, and the risk of flying the redundant substances back to the cabin is reduced;
5. because the separation speed is high, the separation time is reduced, and the start control time of the upper stage can be advanced;
6. the method is suitable for both solid rockets and liquid rockets, has a wide application range, and can effectively reduce the design period and the test times.
Drawings
FIG. 1 is a flow chart of a rocket fast separation timing design method;
fig. 2 is a timing diagram of rocket fast separation.
Detailed Description
The following description of the embodiments of the present invention will be made with reference to the accompanying drawings 1 and 2:
reference will now be made in detail to various exemplary embodiments of the present invention, the detailed description should not be construed as limiting the invention but as a more particular description of the invention directed to certain specific factors;
it is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. Further, the numerical values selected for the purposes of this invention are to be understood as specifically disclosing the upper and lower limits of the range and any intermediate values therebetween;
unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs;
specific adaptations and modifications of the present disclosure may be made without departing from the scope or spirit of the disclosure, which is intended to be a matter of design consideration for the individual skilled in the art. The specification and examples are exemplary only;
the invention is further described by the following detailed description in conjunction with the accompanying drawings;
as shown in fig. 1 and 2, the timing design method of rocket interstage separation according to the present invention is applicable to both liquid and solid rockets. Firstly, the working condition of the engine of the next stage is judged, and the residual thrust is judged to be used as the basis for judging whether the rocket of the next stage finishes shutdown. The judging method comprises the following steps: before launching, according to the rocket mass m at the separation moment, the lowest residual thrust Ft of the rocket attitude can be controlled by a control system, and therefore the acceleration a = Ft/m of the rocket at the moment is obtained. The acceleration a is bound in an rocket computer of a rocket as a binding data value. During the flight of the rocket, the acceleration of the rocket body is sensed in real time through an adding table and is compared with the value. When the acceleration is judged to reach the required interval, the lower-level engine is considered to be shut down, and an upper-level engine ignition instruction is sent;
and then the control system waits for the plug opening signal of the upper-stage engine, a plug opening sensor or a target line and other structures are required in the upper-stage spray pipe to judge the opening condition of the plug of the upper-stage engine, and the moment when the plug opening signal is received is defined as the T0 moment. And after the time delay of T1, a separation unlocking signal is sent to an interstage connection structure between the upper-stage engine and the lower-stage engine, and the time is the T1 time. The opening time of the jam in the scheme is a key time point and is the basis of the following action and time sequence. The interstage separation device completes interstage cutting t2 from the time when the separation unlocking signal is received to the time when the separation unlocking is completed;
the time delay T3 is T3 after the time T0, the upper-level control is started from the time T3, and the whole process completes the upper-level and lower-level rapid thermal separation of the whole rocket;
the T0 moment in the time sequence design is a key control point, and the error of the moment point is ensured to be within 1 ms;
in the scheme, after receiving a time signal T0, a control system of the rocket presets a delay time T1 at intervals, and then sends an unlocking signal to an interstage connection structure, wherein the delay time needs to be designed according to the performance of an engine, the performance of electronic components in a controller, the internal pressure bearing capacity of a stage interval shell and the like, and is preferably 5-10 ms;
in the scheme, since t2 is mainly determined by the response and explosion propagation time of the inter-stage initiating explosive device, when the initiating explosive device scheme is determined, t2 is basically determined;
in the scheme, t3 is comprehensively determined according to the characteristics of residual thrust of the lower-stage engine, the ignition characteristic of the upper-stage engine and the posture condition of the separation moment of the upper-stage rocket body, the upper-stage engine is started and controlled under the condition that reliable separation is guaranteed, and the delay time t3 is recommended to be 40-50 ms;
in the scheme, the inter-stage separation structure of the rocket is a closed structure, and a shell structure and internal instrument equipment are subjected to short-time high-temperature and high-pressure effects;
in the scheme, the stage separation mode of the rocket is a thermal separation mode, namely, the upper stage engine is ignited firstly, and then the stage separation is carried out;
it will be apparent to those skilled in the art that various modifications and variations can be made in the embodiments of the present disclosure without departing from the scope or spirit of the disclosure, with the emphasis instead being placed upon performing detailed simulation analysis.
Claims (8)
1. A rocket rapid separation time sequence design method is characterized in that the separation time sequence comprises the following steps:
(1) giving separable residual thrust according to the thrust and stability characteristics of the rocket, and judging the residual thrust value of the next stage of rocket according to the acceleration value a obtained by adding table measurement;
(2) according to the judgment result of the step (1), when the measured value of the adding table reaches a required interval, sending an upper-level engine ignition instruction;
(3) after the upper-stage ignition instruction is sent out according to the step (2), the integrated controller reads the opening information of the upper-stage engine plug;
(4) after the integrated controller reads the jam opening information, delaying a first time length t1 and then sending an inter-stage separation ignition instruction;
(5) and (4) according to the opening time of the jam piece read in the step (3), delaying a second time length t3 and then issuing a start control instruction of the upper stage.
2. A rocket fast separation timing design method according to claim 1, characterized in that: the stage-to-stage separation mode of the rocket is a thermal separation mode.
3. A rocket fast separation timing design method according to claim 1, characterized in that: the determination step of adding the table measurement value a in the step (1) is as follows:
and the residual thrust Ft judgment is given by the whole rocket control system according to the control requirement, and if the total mass of the rocket at the separation moment is m, the addition table measured value a = Ft/m.
4. A rocket fast separation timing design method according to claim 1, characterized in that: and (4) reading the opening information of the plug sheet by the integrated controller in the step (3) to be an on-off instruction.
5. A method for designing a rocket fast separation sequence according to claim 1, wherein the rocket fast separation sequence is: judging that the lower stage rocket is shut down, and sending an ignition signal by the upper stage engine by the controller on the basis;
the system waits for the upper-stage engine plug opening signal, and the moment when the plug opening signal is received is defined as T0 moment;
after a time delay of T1, a separation unlocking signal is sent to an interstage connection structure between the upper stage engine and the lower stage engine, and the time is defined as a time T1;
the interstage separation structure finishes cutting at T2 from the time when the separation unlocking signal is received to the time when the separation unlocking is finished, and the time is defined as T2;
after a delay of T3 from the time T0, defined as T3, the upper control is started from the time T3.
6. A rocket fast separation timing design method according to claim 5, wherein the error of T0 in said rocket fast separation timing is less than 1 ms.
7. A rocket fast separation sequence design method according to claim 5, wherein said rocket controller delays T1 after receiving said signal of time T0, and then sends out unlocking signal to said inter-stage connection structure.
8. A rocket fast separation sequence design method according to claim 5, wherein said time delay t3 is determined according to the characteristics of the lower stage engine and the magnitude of the thrust of the upper stage engine directly acting on the rocket body of the lower stage.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114739240A (en) * | 2022-03-30 | 2022-07-12 | 蓝箭航天空间科技股份有限公司 | Carrier rocket stage cold separation time sequence optimization method and device |
| CN114962076A (en) * | 2022-04-28 | 2022-08-30 | 蓝箭航天空间科技股份有限公司 | Method and device for optimizing stage cold separation time sequence of liquid carrier rocket |
| CN116499321A (en) * | 2023-02-03 | 2023-07-28 | 彭昆雅 | Separation control method, device and equipment for solid binding carrier rocket booster |
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| US5203844A (en) * | 1989-10-05 | 1993-04-20 | Leonard Byron P | Multiple payload/failure mode launch vehicles |
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| CN110456810A (en) * | 2019-07-31 | 2019-11-15 | 湖北航天技术研究院总体设计所 | Hypersonic aircraft head body separation system and its design method, control method |
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2020
- 2020-02-28 CN CN202010128374.7A patent/CN113324445A/en active Pending
Patent Citations (4)
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| US5203844A (en) * | 1989-10-05 | 1993-04-20 | Leonard Byron P | Multiple payload/failure mode launch vehicles |
| CN109855483A (en) * | 2019-01-22 | 2019-06-07 | 北京蓝箭空间科技有限公司 | The time sequence design method of Solid Launch Vehicle stage separation |
| CN110297481A (en) * | 2019-07-01 | 2019-10-01 | 中国航天空气动力技术研究院 | It unites when a kind of stage separation flight control system high-precision method |
| CN110456810A (en) * | 2019-07-31 | 2019-11-15 | 湖北航天技术研究院总体设计所 | Hypersonic aircraft head body separation system and its design method, control method |
Non-Patent Citations (1)
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114739240A (en) * | 2022-03-30 | 2022-07-12 | 蓝箭航天空间科技股份有限公司 | Carrier rocket stage cold separation time sequence optimization method and device |
| CN114962076A (en) * | 2022-04-28 | 2022-08-30 | 蓝箭航天空间科技股份有限公司 | Method and device for optimizing stage cold separation time sequence of liquid carrier rocket |
| CN114962076B (en) * | 2022-04-28 | 2023-03-31 | 蓝箭航天空间科技股份有限公司 | Method and device for optimizing stage cold separation time sequence of liquid carrier rocket |
| CN116499321A (en) * | 2023-02-03 | 2023-07-28 | 彭昆雅 | Separation control method, device and equipment for solid binding carrier rocket booster |
| CN116499321B (en) * | 2023-02-03 | 2024-01-23 | 彭昆雅 | Separation control method, device and equipment for solid binding carrier rocket booster |
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Address after: Room 403, 4th Floor, Building 2, No. 15 Ronghua South Road, Daxing District Economic and Technological Development Zone, Beijing, 100176 Applicant after: Beijing Xinghe Power Aerospace Technology Co.,Ltd. Applicant after: Beijing Xinghe Power Equipment Technology Co.,Ltd. Address before: 100176 room 1301, 13 / F, building 7, yard 15, Ronghua South Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing Applicant before: Xinghe power (Beijing) Space Technology Co.,Ltd. Applicant before: Beijing Xinghe Power Equipment Technology Co.,Ltd. |
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