CN108583940A - A kind of four-point satellite and the rocket separating mechanism - Google Patents
A kind of four-point satellite and the rocket separating mechanism Download PDFInfo
- Publication number
- CN108583940A CN108583940A CN201810562615.1A CN201810562615A CN108583940A CN 108583940 A CN108583940 A CN 108583940A CN 201810562615 A CN201810562615 A CN 201810562615A CN 108583940 A CN108583940 A CN 108583940A
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- China
- Prior art keywords
- separating mechanism
- rocket
- satellite
- switching cylinder
- spring
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
This application involves a kind of four-point satellite and the rocket separating mechanisms comprising 4 sets of connection trippers, 4 sleeve spring thrust devices and 4 sets of stroke switchgears.
Description
Technical field
This application involves a kind of satellite and the rocket separators, more particularly to a kind of four point attachment formula satellite and the rocket separator.
Background technology
The invention solves satellites and safe release problem of the rocket in being reliably connected before entering the orbit and after entering the orbit.In rocket
Before reaching planned orbit, satellite bears harsh vibration and acceleration load.After rocket is entered the orbit, it is desirable that speed of the satellite to design
Degree and Separation, and ensure that satellite is small as possible in the angular speed in three directions.
For this purpose, there is an urgent need in the art to develop a kind of novel satellite and the rocket separator.
Invention content
The application's is designed to provide a kind of satellite and the rocket separating mechanism.
To achieve the goals above, the application provides following technical proposals.
In the first aspect, the application provides a kind of four-point satellite and the rocket separating mechanism comprising 4 sets of connection trippers, 4
Sleeve spring thrust device and 4 sets of stroke switchgears.
The wherein described connection tripper includes a blasting bolt, a load nut, switching cylinder on one, once switching cylinder,
One spherical washer, a collecting board, a combined vibration-damping pad and a honeycomb.
The wherein described spring thrust device includes a self-locking nut, a spring, a push rod and a sleeve.
The wherein described stroke switchgear includes one stroke switch bracket and one stroke switch.
Compared with prior art, the advantageous effect of the application be to solve satellite with rocket being reliably connected before entering the orbit
With enter the orbit after safe release problem.
Description of the drawings
Fig. 1 is the schematic diagram of the four-point satellite and the rocket separating mechanism of the application.
Fig. 2 is the four-point satellite and the rocket separating mechanism of the application and the connection diagram of satellite.
Fig. 3 is the schematic diagram of the connection tripper of the application.
Fig. 4 is the schematic diagram of the spring thrust device of the application.
Fig. 5 is the schematic diagram of the stroke switchgear of the application.
Specific implementation mode
Below in conjunction with attached drawing and embodiments herein, carries out clear to the technical solution of the application and completely retouch
It states.
The four-point satellite and the rocket separating mechanism of the application is by pedestal, 4 sets of connection trippers (including upper switching cylinder, lower switching
Cylinder, blasting bolt, and load nut etc.), 4 sleeve spring thrust devices (including sleeve, self-locking nut, spring and push rod), 4 sets of rows
Journey switching device (including travel switch and holder) forms.
In one embodiment of the application, the connection tripper as shown in figure 3, including blasting bolt, load nut,
Upper switching cylinder, lower switching cylinder, spherical washer, collecting board, combined vibration-damping pad and honeycomb etc..
As shown in figure 3, upper switching cylinder lower end is designed as taper slot structure, the taper platform of this structure and lower switching cylinder upper end is matched
It closes, bears the lateral shear load between connected piece；Certain torque is applied to load nut, upper and lower switching cylinder is by explosion spiral shell
Bolt, which tenses, realizes connection, bears the longitudinal loading and moment of flexure between connected piece.When requiring connected piece to detach, blasting bolt
Work, blasting bolt are weakening fracture at slot, are realizing satellite and the rocket unlock.Shock resistance padded coaming -- honeycomb is set in upper switching cylinder,
To reduce bolt head and load impact of the nut when exploding unlock to connected piece.It transports downwards unlock rear bolt lower half portion
It is dynamic, it is collected plate collection.
Combined vibration-damping pad is installed in upper switching cylinder upper surface, and combined vibration-damping pad is docked with connected piece, lower end and lower switching cylinder
Docking.The upper surface of upper switching cylinder is 3 to 6 reserved, preferably 4 equally distributed screw holes；The through-hole diameter model of screw hole
For 3.2~φ of φ 6, preferably φ 5.5；The lower face of upper switching cylinder is provided with cone tank and through-hole, is used for and lower switching cylinder frustum
Docking, through-hole are used for the connection of blasting bolt.Upper switching cylinder is using whole machining forging, and in inner cavity, there are load nuts
Mounting platform and the cellular placement space of buffering；It is provided with through-hole among lower end, is used for the installation of blasting bolt.Upper switching cylinder height
Can within the scope of 25mm~40mm, preferably 25mm~35mm, more preferably 25mm~30mm, most preferably 25mm~
27.5mm。
In the embodiment of the application, the spring thrust device as shown in figure 4, include self-locking nut, spring,
Push rod and sleeve.The outer surface of the sleeve constitutes the guiding mandrel of spring.Sleeve can be applied in the mating surface of push rod (φ 10)
It is covered with molybdenum disulfide coating, guide surface long 40mm, distance of relative movement 100mm.The installation of spring thrust device by sleeve with
Threaded hole cooperation on pedestal is positioned.When satellite discharges, spring pushes pushrod movement, until self-locking nut contact sleeve.
With reference to GB/T2089 cylindroid helical-coil compression spring dimensional parameters, the design spring parameter of selection is as follows：
(1) spring material：SUS304 stainless steels；
(2) stiffness K=0.9N/mm, steel wire d=3.5mm, spring wrap diameter D=42mm, number of effective coils n=20；
(3) free height H0=340mm, the height H2=140mm, thrust 180N of compressive state when work；It is high after release
Spend H1=242mm, thrust 88N；Single spring releases energy as 13.7J, design satellite separating rate 1.4m/s.
In one embodiment of the application, the stroke switchgear comprising a travel switch bracket as shown in figure 5, use
In the installation of delivery travel switch.The interface of delivery travel switch is stayed in upper surface, lower face is connected with pedestal.Travel switch branch
Frame material is aluminium alloy, and available model includes 2KX-1A.
The working method of 4 separating mechanisms of the application is：Connect the cone of the upper switching cylinder and lower switching cylinder of tripper
Shape slot structure bears the shear-type load between the satellite and the rocket；Certain torque is applied to load nut.Upper cylinder and pedestal are by blasting bolt
It tenses and realizes satellite and the rocket connection, bear the longitudinal loading and moment of flexure between the satellite and the rocket.When the satellite and the rocket detach, blasting bolt work, explosion
Bolt weakens in inside to be broken at slot, and bolt head and load nut move upwards under the action of detaching momentum, to reduce to defending
The impact of star places damping material in upper cylinder.Buffer board is by stainless steel plate, magnesium alloy plate, three pieces of glass epoxy and inside
Rubber slab forms.
Satellite tail portion is pressed on before installing two travel switch separation on the travel switch bracket of separating mechanism, row after separation
Cheng Kaiguan is flicked provides separation signal to satellite.
Two stroke switchgears are installed on separating mechanism simultaneously, after separation, the signal being successfully separated is provided to rocket.
Submount material is aluminium alloy, and igniter head of priming system power supply is mounted on the peace of pedestal design by whole milling forming
It fills on hole.
Reliability design and analysis
1, reliability is connected
Separating mechanism reliability depends primarily on the company of the bearing members such as the bonding strength of blasting bolt and upper and lower switching cylinder
Connect intensity.
It is true by the size for applying torque on locking nut to ensure that separation nut applies the accurate, reliable of pretightning force
Pretightning force size is determined, in such a way that torque spanner gradually loads, it is ensured that platform and adapter are reliably connected.It is given according to overall
The load gone out, is checked through Strength co-mputation, and each spare part of separating mechanism has higher intensity residual coefficient.
2, reliability is unlocked
In order to realize that unlock, four blasting bolt explosions realize that the unlock of the platform satellite and the rocket, unlock reliability are：
R=R1 4
Wherein R1：Blasting bolt reliability, 0.9996 (confidence level 0.95), is converted into confidence level 0.7, and reliability is
0.9999。
It is computed, the four-point satellite and the rocket connect tripper unlock reliability 0.9996 (confidence level 0.7), meet index and want
It asks.
3, reliability analysis is detached
It is R that mechanism, which unlocks reliability,2 4, R2For spring separator reliability.Spring separator is with reference to ripe little Wei
Star spring separator designs, and is examined by actual flying test, reliability 1.Therefore, entire separating mechanism detaches reliability
For：RSeparation=1.
4, mechanism reliability
Entirely connection separation mechanism reliability is：R=RConnection×RUnlock×RSeparation=0.9996 (confidence level 0.7).
Safety Design and analysis
It is evaluated by risk analysis, there are one danger source blasting bolts for satellite and the rocket separating mechanism.Danger source priority control, takes
Following safety prevention measure：The design of blasting bolt belongs to insensitiveness design, meets GJB1307A-2004《Space Pyrotechnics Devices
General specification》The environmental requirements such as pollution-free, antistatic, anti-radio frequency, anti-vibration, shock resistance, blasting bolt are carried out with banjo
Short-circuit protection, reliability, safety meet requirement, ensure that the requirement safe to use of product.
Maintainability and interchangeability design and analysis
Maintainability refers to product under the defined conditions in the stipulated time, is repaired by regulated procedure and method
When, keep or be restored to the ability of specified states.The probability metrics of maintainability are also referred to as maintainability.
Accessibility, interchangeability and standardization, error protection and distinguishing mark, repair safety, detection are fully considered in design
Diagnosis, repair human engineering and parts recoverability reduce the requirement to maintenance skills to reduce repair content, realize
Make faulty product, required maintenance is simple when restoring or keeping its defined functional status, accurate, safety and warp
Ji.
Environmental suitability design and analysis
In design using environment proper capacity as a technical indicator of product design, development and material selection, and press
According to environmental suitability design criteria and relevant environmental requirement, development quality is improved, raw material selection is examined by repeatedly flight
Conventional material, make product have preferable environmental suitability.
Usability analysis
Separating mechanism infinitely uses technique, new process, and technique inheritance is good, and maturity is high.
Inheritance is analyzed
Separating mechanism is made of four parts：Pedestal, connection tripper, spring thrust device and travel switch bracket.Bottom
Seat and travel switch bracket are that conventional aluminium alloy adds structure, inheritance preferable.Connect tripper and spring thrust device
Previous model is used for reference, adaptation has been carried out.
The above-mentioned description to embodiment is that this Shen can be understood and applied for the ease of those skilled in the art
Please.Person skilled in the art obviously easily can make various modifications to these embodiments, and described herein
General Principle is applied in other embodiments without paying performing creative labour.Therefore, the application is not limited to implementation here
Example, those skilled in the art make according to herein disclosed content in the case where not departing from the application scope and spirit
It improves and changes within all scope of the present application.
Claims (4)
1. a kind of four-point satellite and the rocket separating mechanism, which is characterized in that the separating mechanism includes 4 sets of connection trippers, 4 sets of bullets
Spring thrust device and 4 sets of stroke switchgears.
2. four-point satellite and the rocket separating mechanism as described in claim 1, which is characterized in that the connection tripper includes one quick-fried
Fried bolt, a load nut, switching cylinder, once switching cylinder, a spherical washer, a collecting board, a combined vibration-damping pad and one on one
Honeycomb.
3. four-point satellite and the rocket separating mechanism as described in claim 1, which is characterized in that the spring thrust device include one from
Split nut, a spring, a push rod and a sleeve.
4. four-point satellite and the rocket separating mechanism as described in claim 1, which is characterized in that the stroke switchgear includes a line
Journey switch bracket and one stroke switch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810562615.1A CN108583940A (en) | 2018-06-04 | 2018-06-04 | A kind of four-point satellite and the rocket separating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810562615.1A CN108583940A (en) | 2018-06-04 | 2018-06-04 | A kind of four-point satellite and the rocket separating mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108583940A true CN108583940A (en) | 2018-09-28 |
Family
ID=63630394
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810562615.1A Pending CN108583940A (en) | 2018-06-04 | 2018-06-04 | A kind of four-point satellite and the rocket separating mechanism |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131953A (en) * | 2018-10-12 | 2019-01-04 | 北京微分航宇科技有限公司 | A kind of Payload Attach Fitting that single-point compresses |
| CN109229433A (en) * | 2018-10-29 | 2019-01-18 | 浙江大学 | A kind of skin satellite satellite and the rocket are fixed and separator |
| CN110697091A (en) * | 2019-11-08 | 2020-01-17 | 北京电子工程总体研究所 | Spacecraft adaptive separation frame and adaptive separation device comprising same |
| CN111123086A (en) * | 2019-11-26 | 2020-05-08 | 航天东方红卫星有限公司 | Synchronous release tool for satellite disconnecting switch |
| CN111891390A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
| CN112055686A (en) * | 2020-04-15 | 2020-12-08 | 中国科学院微小卫星创新研究院 | Point type separation satellite and rocket butt joint structure |
| CN112591141A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Compressing and releasing device suitable for flexible spacecraft |
| CN112697184A (en) * | 2020-11-30 | 2021-04-23 | 上海航天控制技术研究所 | Base of separation satellite of mars detector |
| CN112815788A (en) * | 2021-01-05 | 2021-05-18 | 航天行云科技有限公司 | One-arrow-multi-satellite separation system |
| CN112894338A (en) * | 2021-02-05 | 2021-06-04 | 广州明森合兴科技有限公司 | Automatic explosive bolt mounting equipment |
| WO2021143428A1 (en) * | 2020-01-16 | 2021-07-22 | 清华大学 | Electromagnetic locking and releasing mechanism for satellite-rocket separation and electromagnetic locking and releasing method |
| CN114313320A (en) * | 2021-12-10 | 2022-04-12 | 北京理工大学 | Multistage buffer of firer part separation for space flight |
| CN114476144A (en) * | 2022-03-28 | 2022-05-13 | 北京中科宇航技术有限公司 | Satellite-rocket separation device for unlocking low-impact explosive bolt |
| CN115402542A (en) * | 2022-08-01 | 2022-11-29 | 长光卫星技术股份有限公司 | Single-point compression satellite and rocket adapter and satellite and rocket separation device |
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| CN105151330A (en) * | 2015-09-18 | 2015-12-16 | 浙江大学 | Pico/Nano satellite and rocket fixing and separating device |
| CN106052490A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航***工程研究所 | Satellite-rocket point type connection and separation module and device |
| CN208325673U (en) * | 2018-06-04 | 2019-01-04 | 上海微小卫星工程中心 | A kind of four-point satellite and the rocket separating mechanism |
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| US4187759A (en) * | 1977-09-16 | 1980-02-12 | The United States Of America As Represented By The Secretary Of The Navy | Separation nut system |
| CN103010489A (en) * | 2012-12-26 | 2013-04-03 | 浙江大学 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
| CN104859870A (en) * | 2014-10-09 | 2015-08-26 | 航天东方红卫星有限公司 | Integrally-designed satellite-rocket separation mechanism |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131953A (en) * | 2018-10-12 | 2019-01-04 | 北京微分航宇科技有限公司 | A kind of Payload Attach Fitting that single-point compresses |
| CN109229433A (en) * | 2018-10-29 | 2019-01-18 | 浙江大学 | A kind of skin satellite satellite and the rocket are fixed and separator |
| CN110697091B (en) * | 2019-11-08 | 2021-07-13 | 北京电子工程总体研究所 | Spacecraft adaptive separation frame and adaptive separation device comprising same |
| CN110697091A (en) * | 2019-11-08 | 2020-01-17 | 北京电子工程总体研究所 | Spacecraft adaptive separation frame and adaptive separation device comprising same |
| CN111123086A (en) * | 2019-11-26 | 2020-05-08 | 航天东方红卫星有限公司 | Synchronous release tool for satellite disconnecting switch |
| US11597540B2 (en) | 2020-01-16 | 2023-03-07 | Tsinghua University | Electromagnetic lock release mechanism and method for separating satellite from rocket |
| WO2021143428A1 (en) * | 2020-01-16 | 2021-07-22 | 清华大学 | Electromagnetic locking and releasing mechanism for satellite-rocket separation and electromagnetic locking and releasing method |
| CN112055686A (en) * | 2020-04-15 | 2020-12-08 | 中国科学院微小卫星创新研究院 | Point type separation satellite and rocket butt joint structure |
| WO2021207955A1 (en) * | 2020-04-15 | 2021-10-21 | 中国科学院微小卫星创新研究院 | Point-type separation satellite-rocket butt joint structure |
| CN112055686B (en) * | 2020-04-15 | 2023-11-24 | 中国科学院微小卫星创新研究院 | Point type separation satellite rocket docking structure |
| CN111891390B (en) * | 2020-08-11 | 2021-08-10 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
| CN111891390A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
| CN112697184A (en) * | 2020-11-30 | 2021-04-23 | 上海航天控制技术研究所 | Base of separation satellite of mars detector |
| CN112591141A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Compressing and releasing device suitable for flexible spacecraft |
| CN112815788A (en) * | 2021-01-05 | 2021-05-18 | 航天行云科技有限公司 | One-arrow-multi-satellite separation system |
| CN112894338A (en) * | 2021-02-05 | 2021-06-04 | 广州明森合兴科技有限公司 | Automatic explosive bolt mounting equipment |
| CN114313320A (en) * | 2021-12-10 | 2022-04-12 | 北京理工大学 | Multistage buffer of firer part separation for space flight |
| CN114476144A (en) * | 2022-03-28 | 2022-05-13 | 北京中科宇航技术有限公司 | Satellite-rocket separation device for unlocking low-impact explosive bolt |
| CN114476144B (en) * | 2022-03-28 | 2023-09-29 | 北京中科宇航技术有限公司 | Satellite and rocket separating device for unlocking low-impact explosion bolt |
| CN115402542A (en) * | 2022-08-01 | 2022-11-29 | 长光卫星技术股份有限公司 | Single-point compression satellite and rocket adapter and satellite and rocket separation device |
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Application publication date: 20180928 |
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