CN208325673U - 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 PDF

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Publication number
CN208325673U
CN208325673U CN201820852687.5U CN201820852687U CN208325673U CN 208325673 U CN208325673 U CN 208325673U CN 201820852687 U CN201820852687 U CN 201820852687U CN 208325673 U CN208325673 U CN 208325673U
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China
Prior art keywords
separating mechanism
rocket
satellite
switching cylinder
spring
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CN201820852687.5U
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诸成
郭彤
李晓莉
赵学聪
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Shanghai Engineering Center for Microsatellites
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Shanghai Engineering Center for Microsatellites
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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

A kind of four-point satellite and the rocket separating mechanism
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 technique
The invention solves the safe release problem of satellite and 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 guarantee that satellite is small as far 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.
Summary of the invention
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.
Wherein the connection tripper include 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.
Wherein the spring thrust device includes a self-locking nut, a spring, a push rod and a sleeve.
Wherein the stroke switchgear includes one stroke switch bracket and one stroke switch.
Compared with prior art, the beneficial effects of the present application are as follows solving satellite and rocket being reliably connected before entering the orbit With enter the orbit after safe release problem.
Detailed description of the invention
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 schematic 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 embodiment
Below in conjunction with attached drawing and embodiments herein, clear and complete retouch is carried out to the technical solution of the application 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 bracket) composition.
In one embodiment of the application, the connection tripper as shown in figure 3, include 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 longitudinal loading and moment of flexure between connected piece.When requiring connected piece to separate, 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 end surface 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;Through-hole is provided among lower end, the installation for 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.It can be applied in sleeve and 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 steel;
(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 end surface 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: connecting the upper switching cylinder of tripper and the cone of lower switching cylinder 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 satellite and the rocket separation, 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 separate momentum, is reduction 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 composition.
Satellite tail portion is pressed on the travel switch bracket of separating mechanism before installing two travel switch separation, row after separation Cheng Kaiguan, which 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 that priming system is powered 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 bonding strength of blasting bolt and the company of the bearing members such as 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 Load 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 the unlock of the platform satellite and the rocket, unlock reliability are as follows:
R=R1 4
Wherein R1: blasting bolt reliability, 0.9996 (confidence level 0.95) are 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 separated
It is R that mechanism, which unlocks reliability,2 4, R2For spring separator reliability.Spring separator is referring to mature little Wei The design of star spring separator, is examined, reliability 1 by actual flying test.Therefore, entire separating mechanism separates reliability Are as follows: RSeparation=1.
4, mechanism reliability
Entire connection separation mechanism reliability are as follows: R=RConnection×RUnlock×RSeparation=0.9996 (confidence level 0.7).
Safety Design and analysis
It is evaluated by risk analysis, satellite and the rocket separating mechanism has a danger source blasting bolt.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 " environmental requirements, the blasting bolt such as pollution-free, antistatic, anti-radio frequency, anti-vibration, shock resistance carry out with banjo Short-circuit protection, reliability, safety meet requirement, and ensure that product uses safety requirements.
Maintainability and interchangeability design and analysis
Maintainability refers to that product under the defined conditions and 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, maintenance safety, detection are fully considered in design Diagnosis, maintenance human engineering and components recoverability reduce the requirement to maintenance skills to reduce maintenance content, realize Make faulty product, required maintenance is simple when restoring or keeping functional status as defined in it, 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 by repeatedly flight examination 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 analysis
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, and inheritance is 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 creative labor.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 modifies 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.
CN201820852687.5U 2018-06-04 2018-06-04 A kind of four-point satellite and the rocket separating mechanism Active CN208325673U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Application Number Priority Date Filing Date Title
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108583940A (en) * 2018-06-04 2018-09-28 上海微小卫星工程中心 A kind of four-point satellite and the rocket separating mechanism
CN110228608A (en) * 2019-05-24 2019-09-13 上海宇航***工程研究所 A kind of point type connection separator being adapted to side hanging satellite
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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108583940A (en) * 2018-06-04 2018-09-28 上海微小卫星工程中心 A kind of four-point satellite and the rocket separating mechanism
CN110228608A (en) * 2019-05-24 2019-09-13 上海宇航***工程研究所 A kind of point type connection separator being adapted to side hanging satellite
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

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