CN101419037B - Air spring slow-releasing mechanism - Google Patents
Air spring slow-releasing mechanism Download PDFInfo
- Publication number
- CN101419037B CN101419037B CN 200810239455 CN200810239455A CN101419037B CN 101419037 B CN101419037 B CN 101419037B CN 200810239455 CN200810239455 CN 200810239455 CN 200810239455 A CN200810239455 A CN 200810239455A CN 101419037 B CN101419037 B CN 101419037B
- Authority
- CN
- China
- Prior art keywords
- cylinder
- releasing
- arm
- slowly
- air spring
- Prior art date
- 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.)
- Expired - Fee Related
Links
Abstract
The invention discloses an air reed type slow release mechanism which can improve the reliability of launching a rocket. The air reed type slow release mechanism comprises a gas supply system (1), a slow release cylinder (2), a traction cylinder (3), a soleplate (4), a traction arm (5), a swinging lever (6) and a lever arm (7); the soleplate (4) is connected with a rocket launching pad; the lever arm (7) is fixed on the soleplate (4); the lower ends of the slow release cylinder (2) and the traction cylinder (3) are movably fixed on the soleplate (4) respectively; the upper end of the slow release cylinder (2) is movably connected with the lever arm (7); the upper end of the traction cylinder (3) is connected with the lower end of the traction arm (5); the upper end of the traction arm (5) is fixedly connected with the swinging lever (6); the other end of the swinging lever (6) is movably connected with the lever arm (7); and the gas supply system (1) provides high-pressure gas for the slow release cylinder (2) and the traction cylinder (3). The mechanism can meet the requirement of traction load of 180 KN and can achieve the function of slow release after the rocket is launched.
Description
Technical field
The invention belongs to the rocket launching technical field, particularly a kind of reliability and economy that is used to improve rocket launching, the air spring slow-releasing mechanism of guarantee launching site safety.
Background technology
China has begun the carrier rocket of new generation of the emission large-tonnage satellite of the nontoxic pollution-free developed, and wherein the slowly-releasing discharge technique is one of difficult point of development.
Pining down slowly-releasing and put device and be installed in the position that is connected and fixed between rocket and the transmitting station, is that rocket realizes pining down the indispensable facility that slowly-releasing is put radiation pattern.During former rocket launching, rocket discharges rocket after the thrust that the engine of rocket produces reaches predetermined value before discharging from transmitting station, and high thrust discharges the impact meeting that produces rocket is caused bigger vibration suddenly, and rocket and various precision instrument are damaged.So wish to leave the utmost point that transmitting station begins in the short time, rocket discharged slowly at rocket.
Have only a few countries such as the U.S., France to grasp this technology at present abroad.The slowly-releasing power that the U.S. uses the plastic deformation of drawing pin to produce slowly discharges rocket, but the slowly-releasing pin exists characteristics such as slowly-releasing power instability; France has adopted the slow-releasing mechanism of hydraulic system, but this device exists characteristics such as system complex.
At home, this Study on Technology is started late, and does not still have the report and the application of correlative study.
Summary of the invention
The objective of the invention is: overcome the deficiencies in the prior art, a kind of air spring slow-releasing mechanism that can reduce the axial vibration of rocket, the reliability that improves rocket launching and economy, guarantee launching site safety is provided.
Technical scheme of the present invention is: air spring slow-releasing mechanism, and comprise air supply system, slowly-releasing venting cylinder, pin down cylinder, base plate, pin down arm, arrange bar and lever arm, base plate is connected with rocket launching pad, and lever arm is fixed on the base plate; Slowly-releasing venting cylinder and the lower end that pins down cylinder activity respectively are fixed on the base plate, the upper end and the lever arm of slowly-releasing venting cylinder flexibly connect, the upper end connection that pins down cylinder pins down the arm lower end, pins down the fixedly connected bar of arranging in arm upper end, arranges the bar other end and lever arm and flexibly connects; Air supply system is for slowly-releasing venting cylinder and pin down cylinder gases at high pressure are provided.
Described slowly-releasing venting cylinder and pin down cylinder and be installed on the base plate by the form of bearing with dovetail groove guarantees that the moving position of cylinder can be adjusted.
Described arranging is equipped with spring assembly in the bar, make can to hightail rocket after pining down arm rises to requirement at rocket distance.
Described slowly-releasing venting cylinder, pin down cylinder, arrange bar and pin down arm and be connected with lever arm by bearing pin.
Described slowly-releasing venting cylinder, pin down cylinder, arrange bar with pin down arm can be with the link position of lever arm according to the different requirement adjustment that design holdback force.
On the described bearing pin self-lubricating plain bearing is housed, guarantees slowly-releasing venting cylinder, pin down cylinder, arrange bar, pin down between arm and the lever arm and can rotate flexibly.
The pressure of described gases at high pressure is 0～23Mpa.
Described air spring slow-releasing mechanism be symmetrically distributed in rocket around.
The quantity of described air spring slow-releasing mechanism is 4 or 8.
The present invention's beneficial effect compared with prior art is:
1) because before rocket takes off, air supply system is full of gases at high pressure to the cavity of resorption of slowly-releasing venting cylinder with the epicoele that pins down cylinder, the power that cylinder produces has auxiliary restraining function to passing to by lever arm to pin down on the arm to rocket, makes this device can realize the requirement of holdback force 180KN;
2) after rocket begins emission, the thrust drive of rocket pins down arm and moves upward, compress the acting force arm that the gases at high pressure that pin down in the lower chamber of air cylinder reduce slowly-releasing venting cylinder simultaneously by the regulations and parameters arm, thereby reach the effect that reduces holdback force, in 0～120mm stroke that rocket discharges, holdback force is decremented to 0KN by 150～180KN, plays the slowly-releasing playing function.
3) in addition, the bearing that is connected with cylinder is installed on the base plate with the form of dovetail groove, makes the activity direction of cylinder to adjust; Slowly-releasing venting cylinder, pin down cylinder, arrange bar and pin down arm and be connected with lever arm, self-lubricating plain bearing is housed on the bearing pin, guaranteed the flexible rotation of each parts by bearing pin.
4) air spring slow-releasing mechanism of the present invention can make that slowly-releasing clearance journey is adjustable by changing the position of each pin joint; By changing the pressure of cylinder, make holdback force adjustable.
Description of drawings
Fig. 1 is an air spring slow-releasing mechanism schematic diagram of the present invention.
The specific embodiment
The present invention is further illustrated below in conjunction with accompanying drawing.
As shown in Figure 1, air spring slow-releasing mechanism of the present invention comprises air supply system 1, slowly-releasing venting cylinder 2, pins down cylinder 3, base plate 4, pins down arm 5, arranges bar 6 and lever arm 7, and base plate 4 is connected with rocket launching pad, and lever arm 7 is fixed on the base plate 4; Slowly-releasing venting cylinder 2 and the lower end that pins down cylinder 3 activity respectively are fixed on the base plate 4, the upper end and the lever arm 7 of slowly-releasing venting cylinder 2 flexibly connect, the upper end connection that pins down cylinder 3 pins down arm 5 lower ends, pins down the fixedly connected bar 6 of arranging in arm 5 upper ends, arranges bar 6 other ends and lever arm 7 flexible connections; Air supply system 1 is for slowly-releasing venting cylinder 2 and pin down cylinder 3 gases at high pressure are provided.
Slowly-releasing venting cylinder 2 and pin down cylinder 3 and be installed on the base plate 4 by the form of bearing with dovetail groove guarantees that the moving position of cylinder can be adjusted.
Arrange in the bar 6 spring assembly is housed, can make to pin down arm rises to regulation at rocket the rapid rocket of throwing off in distance back.
Slowly-releasing venting cylinder 2, pin down cylinder 3, arrange bar 6 and pin down arm 5 and is connected with lever arm 7 by bearing pin, each link position can be according to the difference requirement adjustment of design holdback force.
On the bearing pin that connects, self-lubricating plain bearing is housed, guarantees slowly-releasing venting cylinder 2, pin down cylinder 3, arrange bar 6, pin down between arm 5 and the lever arm 7 and can rotate flexibly.
The pressure of the gases at high pressure that air supply system provides is 0～23MPa, and choosing air pressure in the present embodiment is 16MPa.
4 air spring slow-releasing mechanisms are symmetrically distributed around rocket in the present embodiment.
Dynamic duty process of the present invention is:
A, air spring slow-releasing mechanism is installed on rocket launching pad props up leg outer side, be connected with transmitting station, pin down arm 5 and be buckled on the rocket supporting leg, apply slowly-releasing power by base plate 4;
Before b, the emission, fill gases at high pressure by air supply system 1 in slowly-releasing venting cylinder 2 cavity of resorptions, air pressure is 16MPa, produce atmospheric pressure 50.4t, the moment that acts on lever arm 7 intermediate supports is counter clockwise direction, is delivered to by lever arm 7 and pins down arm 5, and the slowly-releasing power that puts on rocket is 18t;
After c, rocket were removed and pind down, rich thrust was greater than initial slow release force, and rocket begins drive and pins down arm 5 risings, this moment, slowly-releasing was exitted cylinder 2 cavity of resorption gases by compression, and aerodynamic force increases, but the arm of force reduces rapidly, the moment that acts on the lever arm intermediate support reduces, and slowly-releasing power reduces; The spring pressurized of meanwhile arranging dress in the bar 6 shortens; The pressure that pins down in cylinder 3 epicoeles raises gradually;
D, drive when pining down arm and rising to 120mm when rocket, lever arm 7 intermediate supports and 2 two hinged points of slowly-releasing venting cylinder are point-blank, the moment that the intermediate support of slowly-releasing venting cylinder 2 relative lever arms 7 produces is zero, and just slowly-releasing power is zero, and it is bigger to arrange bar 6 inner spring power;
E, rocket continue to rise, the clockwise moment that slowly-releasing venting cylinder 2 relative lever arm 7 intermediate supports produce, promotion pins down arm 5 and moves to the back upper place, simultaneously under the effect of arranging bar 6 inner spring power, pin down arm 5 and arrange the disengaging rocket rapidly, the pressure that pins down cushion dashpot 2 epicoeles this moment raises rapidly and produces the power that downward pulling force balance slowly-releasing venting cylinder produces, play the effect of buffering, finish the process that slowly-releasing is put.
The present invention has adopted the frame for movement of lever and Pneumatic spring type first, and mechanical system, pneumatic system and electric-control system are carried out comprehensive integration, has optimized system schema, can satisfy the requirement of emission carrier rocket of new generation.
The foregoing description is a kind of the enumerating that the present invention uses, and those skilled in the art can carry out various improvement and replacing according to different designing requirements and design parameter under the situation that does not depart from technical solution of the present invention, fall into protection scope of the present invention equally.
Claims (9)
1. air spring slow-releasing mechanism, comprise air supply system (1), slowly-releasing venting cylinder (2), pin down cylinder (3), base plate (4), pin down arm (5), arrange bar (6) and lever arm (7), base plate (4) is connected with rocket launching pad, lever arm (7) is fixed on the base plate (4), it is characterized in that: slowly-releasing venting cylinder (2) and the lower end that pins down cylinder (3) activity respectively are fixed on the base plate (4), the upper end of slowly-releasing venting cylinder (2) and lever arm (7) flexibly connect, the upper end connection that pins down cylinder (3) pins down arm (5) lower end, pin down the fixedly connected bar (6) of arranging in arm (5) upper end, arrange bar (6) other end and lever arm (7) and flexibly connect; Air supply system (1) is for slowly-releasing venting cylinder (2) and pin down cylinder (3) gases at high pressure are provided.
2. according to the air spring slow-releasing mechanism of claim 1, it is characterized in that: described slowly-releasing venting cylinder (2) and pin down cylinder (3) and be installed on the base plate (4) by the form of bearing with dovetail groove guarantees that the moving position that described slowly-releasing is exitted cylinder (2) and pind down cylinder (3) can adjust.
3. according to the air spring slow-releasing mechanism of claim 1, it is characterized in that: described arranging in the bar (6) is equipped with spring assembly, makes can to hightail rocket after pining down arm (5) rises to requirement at rocket distance.
4. according to the air spring slow-releasing mechanism of claim 1, it is characterized in that: described slowly-releasing venting cylinder (2), pin down cylinder (3), arrange bar (6) and pin down arm (5) and be connected with lever arm (7) by bearing pin.
5. according to the air spring slow-releasing mechanism of claim 4, it is characterized in that: on the described bearing pin self-lubricating plain bearing is housed, guarantees slowly-releasing venting cylinder (2), pin down cylinder (3), arrange bar (6), pin down between arm (5) and the lever arm (7) and can rotate flexibly.
6. according to the air spring slow-releasing mechanism of claim 1, it is characterized in that: described slowly-releasing venting cylinder (2), the link position that pins down cylinder (3), arrange bar (6) and pin down arm (5) and lever arm (7) are according to the different requirements adjustment that design holdback force.
7. according to the air spring slow-releasing mechanism of claim 1, it is characterized in that: the pressure of described gases at high pressure is 0～23Mpa.
8. according to the air spring slow-releasing mechanism of claim 1, it is characterized in that: described air spring slow-releasing mechanism be symmetrically distributed in rocket around.
9. air spring slow-releasing mechanism according to Claim 8, it is characterized in that: the quantity of described air spring slow-releasing mechanism is 4 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200810239455 CN101419037B (en) | 2008-12-11 | 2008-12-11 | Air spring slow-releasing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200810239455 CN101419037B (en) | 2008-12-11 | 2008-12-11 | Air spring slow-releasing mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101419037A CN101419037A (en) | 2009-04-29 |
| CN101419037B true CN101419037B (en) | 2010-09-22 |
Family
ID=40629947
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200810239455 Expired - Fee Related CN101419037B (en) | 2008-12-11 | 2008-12-11 | Air spring slow-releasing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101419037B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128477A (en) * | 2017-12-22 | 2018-06-08 | 航天神舟飞行器有限公司 | A kind of adjustable rocket bracket of rato formula unmanned plane launcher |
| CN110002015B (en) * | 2019-04-11 | 2022-07-01 | 上海宇航系统工程研究所 | Normal-temperature propellant charging and discharging connector and method for carrier rocket falling off at 0 second |
| CN110132072B (en) * | 2019-04-26 | 2020-11-24 | 蓝箭航天空间科技股份有限公司 | Rocket body supporting and windproof pressing device |
| CN111207625B (en) * | 2020-01-10 | 2022-06-17 | 北京航天发射技术研究所 | Traction release device integrating supporting, traction and slow release |
| CN112062071B (en) * | 2020-08-13 | 2022-06-17 | 北京航天发射技术研究所 | Compact hinge point-changing erecting mechanism |
| CN114459289B (en) * | 2021-08-06 | 2023-08-22 | 北京天兵科技有限公司 | Rocket corner connecting device |
| CN113739634B (en) * | 2021-08-11 | 2023-06-09 | 浙江蓝箭航天空间科技有限公司 | Drag slow-release device and launching pad of carrier rocket |
| CN115507699A (en) * | 2022-08-15 | 2022-12-23 | 蓝箭航天空间科技股份有限公司 | Automatic reverse type drag release device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3415156A (en) * | 1966-04-29 | 1968-12-10 | Nasa Usa | Controlled release device |
| GB2096287A (en) * | 1981-04-04 | 1982-10-13 | British Aerospace | Launch vehicle constraining |
| US4453449A (en) * | 1981-09-10 | 1984-06-12 | Westinghouse Electric Corp. | Holding apparatus |
-
2008
- 2008-12-11 CN CN 200810239455 patent/CN101419037B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3415156A (en) * | 1966-04-29 | 1968-12-10 | Nasa Usa | Controlled release device |
| GB2096287A (en) * | 1981-04-04 | 1982-10-13 | British Aerospace | Launch vehicle constraining |
| US4453449A (en) * | 1981-09-10 | 1984-06-12 | Westinghouse Electric Corp. | Holding apparatus |
Non-Patent Citations (1)
| Title |
|---|
| 王瑞铨.浅析牵制释放发射技术.导弹与航天运载技术.2001,(254),1-5. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101419037A (en) | 2009-04-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101419037B (en) | Air spring slow-releasing mechanism | |
| CN106424652B (en) | A kind of mesohigh Casting Equipment control pressurer system and control method | |
| CN103476517B (en) | For running the method for the forcing press with lower driving means and the forcing press running according to the method | |
| CN201885864U (en) | Pneumatic impact response spectrum testing machine | |
| CN102121869A (en) | Pneumatic shock response spectrum tester | |
| CN103389197A (en) | Drive device of horizontal impacting test bed and bi-directional multifunctional horizontal impacting test bed | |
| CN106671966A (en) | Air control valve and air control valve assembly | |
| CN103241091A (en) | Air spring closed-loop air circuit system with multistage self-pressurization mechanism | |
| CN207673762U (en) | Automobile brake chamber with energy storage air bag | |
| CN202790244U (en) | Brake cylinder for braking clamp unit of railway vehicle | |
| CN210089966U (en) | High-energy impact test bed | |
| CN208912889U (en) | Stamping device is used in a kind of production of LED light lamp housing | |
| CN201255016Y (en) | Engine braking device | |
| CN203465074U (en) | Horizontal impacting test stand driving device and bi-directional multifunctional horizontal impacting test stand | |
| CN104942968B (en) | A kind of brick machine servo liftout attachment | |
| CN109855471B (en) | Anti-recoil device of multistage air cannon | |
| CN208068760U (en) | A kind of new type of compression casing processing mold | |
| CN114235326A (en) | Free piston shock tunnel quality buffer mechanism | |
| CN202010754U (en) | Hydro-pneumatic counterblow hammer | |
| CN203835848U (en) | Electric brake closing valve body | |
| CN107121030A (en) | The solid bullet of tail pushing-type ejector single-stage flexibility and tripper and method | |
| CN215409944U (en) | High-speed rail energy storage type shock absorber | |
| CN110224539A (en) | A kind of electric motor damping structure for electronic actuators | |
| CN101372893A (en) | Forced vibration direct-action power generation system same beat mechanical mechanism | |
| CN208203692U (en) | A kind of mounting structure of hydraulic cylinder |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100922 Termination date: 20201211 |