CN209008895U - A kind of horizontal satellite and the rocket separating mechanism - Google Patents
A kind of horizontal satellite and the rocket separating mechanism Download PDFInfo
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- CN209008895U CN209008895U CN201820852689.4U CN201820852689U CN209008895U CN 209008895 U CN209008895 U CN 209008895U CN 201820852689 U CN201820852689 U CN 201820852689U CN 209008895 U CN209008895 U CN 209008895U
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- satellite
- rocket
- separating mechanism
- horizontal
- guide rail
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Abstract
This application involves a kind of horizontal satellite and the rocket separating mechanisms comprising main frame, 2 sets of connection trippers, 2 hold and cut positioning pin, 3 sleeve spring thrust devices and travel switch bracket.
Description
Technical field
This application involves a kind of satellite and the rocket separation systems, more particularly to a kind of horizontal satellite and the rocket suitable for 50kg grades of satellites
Separation system.
Background technique
For the carrying micro-nano satellite of 5Kg or more, the current overwhelming majority is installed vertically on rocket, both satellite disengaging movement side
To axially parallel with rocket.Rocket cone section carries satellite and uniform arrangement is needed to be mounted on outside cone section for installing primary
Mounting base.This satellite and the rocket separation system rocket gesture stability is fairly simple, and separation is not susceptible to collide, and safety is good.
Existing level satellite and the rocket separating mechanism using more, is unable to satisfy 50kg grades of satellites on cube star less than 5kg
It is required that.
And the satellite and the rocket separating mechanism occupied space of conventional vertical installation is larger, for existing rocket space, utilization rate compares
It is low.
For this purpose, there is an urgent need in the art to develop a kind of Novel horizontal satellite and the rocket separating mechanism, in order to 50kg grades of satellites of arranging in pairs or groups
It uses.
Summary of the invention
The application's is designed to provide a kind of Novel horizontal satellite and the rocket separating mechanism, and in order to arrange in pairs or groups, 50kg grades of satellites make
With.
To achieve the goals above, the application provides a kind of horizontal satellite and the rocket separating mechanism characterized by comprising
Main frame；
2 sets of connection trippers are mounted on the inside of main back end of frame face and have blasting bolt；
2 are held and cut positioning pin, and longitudinal loading is born in the taper hole cooperation with satellite；
3 sleeve spring thrust devices are mounted on the inside of main back end of frame face and are configured as inciting somebody to action after blasting bolt unlocks
Satellite releases main frame with the separating rate designed；And
Travel switch bracket, wherein travel switch the satellite and the rocket separation before be pressed on the travel switch bracket and
After satellite and the rocket separation, the travel switch, which is flicked, provides separation signal to satellite.
In the another embodiment of the application, the main frame includes internal guide rail, the internal guide rail and satellite
Outer guide cooperation.
In the another embodiment of the application, between the internal guide rail and satellite outer rail of the separating mechanism
Spacing is 0.5 to 0.9mm.
In the another embodiment of the application, the surface of the guide rail and separating mechanism connection tripper
It sputters molybdenum disulfide or smears space flight lubricating grease.
In the another embodiment of the application, satellite rear end is strained and fixed by the connection tripper in main frame
On the inside of rear end face.
In the another embodiment of the application, 10 M6 screws of underrun of the horizontal satellite and the rocket separating mechanism
It is connected with rocket arm.
In the another embodiment of the application, the inclined-plane of the horizontal satellite and the rocket separating mechanism passes through 12 M6 screws
It is connected with the reinforcing rib of rocket and upper flange.
Compared with prior art, the beneficial effects of the present application are as follows can be realized the machine of 50kg rank satellite and carrier rocket
Tool connection meets 50kg rank satellite connection request under various load working conditions, and realizes that satellite is in the horizontal direction by instruction
Reliable unlock, safe separating.Meanwhile by Vibration Absorption Designing, impact that priming system explosion generates satellite is reduced, it can be achieved that frequency domain
Within the scope of 5000Hz, impact is less than 1000g.Again, it can be achieved that the lesser separation angular speed of satellite, remains less than 3o/s.
Detailed description of the invention
Fig. 1 is the schematic diagram of the horizontal satellite and the rocket separating mechanism of the application.
Fig. 2 is the front view schematic diagram of the main frame of the horizontal satellite and the rocket separating mechanism of the application.
Fig. 3 is the left view schematic diagram of the main frame of the horizontal satellite and the rocket separating mechanism of the application.
Fig. 4 is the schematic bottom view of the main frame of the horizontal satellite and the rocket separating mechanism of the application.
Fig. 5 be the application horizontal satellite and the rocket separating mechanism on connect connection tripper one embodiment signal
Figure.
Fig. 6 is the signal of one embodiment of spring thrust device that connects on the horizontal satellite and the rocket separating mechanism of the application
Figure.
Fig. 7 is the front view schematic diagram that can be packed into the rocket cone section of the horizontal satellite and the rocket separating mechanism of the application.
Fig. 8 is the side view schematic diagram that can be packed into the rocket cone section of the horizontal satellite and the rocket separating mechanism of the application.
Fig. 9 is the top view illustration that can be packed into the rocket cone section of the horizontal satellite and the rocket separating mechanism 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.
Fig. 1 is the schematic diagram of the horizontal satellite and the rocket separating mechanism 100 of the application.As shown in Figure 1, the horizontal satellite and the rocket seperator of the application
Structure mainly includes with lower component: connection tripper 104,2 of 101,2 sets of main frame, which is held, cuts 109,3 sets of positioning pin (or taper pin)
Spring thrust device 102 and travel switch bracket 103.
Whole 3D printing forming can be used, by machining to reach precision after forming due to complex-shaped in main frame 101
It is required that.Longitudinal loading is born in the cooperation of the taper hole of 2 taper pins 201 and satellite.Internal guide rail and 108 outer guide 107 of satellite cooperate.It examines
Considering manufacturing tolerance and influence of thermal deformation, the spacing between the internal guide rail and satellite outer rail of the separating mechanism can be
0.5~0.9mm, preferably 0.7mm.Design the spacing between spacing 0.7mm separating mechanism internal guide rail and satellite outer rail
It can be taken as 0.5~0.9mm, preferably 0.7mm.Guide rail is not carried in rocket powered phase, primarily serves auxiliary slip apart effect.Essence
After processing, satellite 108 connect the upper switching cylinder of tripper 104, lower switching cylinder with the guide rail of separating mechanism and separating mechanism
Surface can sputter molybdenum disulfide or smear space flight lubricating grease to reduce coefficient of friction, anti-cold welding.
Mountable one to two of satellite tail portion, preferably two travel switches, the travel switch are pressed before satellite and the rocket separation
Tightly on the travel switch bracket 103 of horizontal satellite and the rocket separating mechanism；After satellite and the rocket separation, the travel switch is flicked to be mentioned to satellite
For separating signal.
2 sets of connection trippers 104 (containing blasting bolt) and 3 sleeve spring thrusts dress are installed on the inside of main 101 rear end face of frame
Set 102.Satellite rear end is strained and fixed on the inside of main back end of frame face by set connection tripper 104.The Main Load of satellite by
It holds and cuts positioning pin 109, set connection tripper 104 and the blasting bolt included undertake.
It is surveyed in main 101 rear end face of frame and is also equipped with 3 groups of spring thrust devices 102, Resulting thrust force is designed in centroidal axis,
Active force when separation is inhibited to bias.After blasting bolt unlock, separating rate that the spring thrust device 102 designs satellite
Release main frame.
The bottom surface 401 of the horizontal satellite and the rocket separating mechanism is connected with rocket arm by 10 M6 screws (such as Fig. 4 institute
Show), inclined-plane is connected by 12 M6 screws (as shown in Figure 2) with the reinforcing rib of rocket and upper flange.
In the embodiment of the application, the set connection tripper 104 is as shown in figure 5, include blasting bolt
504, nut 502, upper switching cylinder, 508 lower switching cylinder, spherical washer 503, collecting board 505, combined vibration-damping pad 501 and bees are loaded
Nest 509 etc..
As shown in figure 5, upper switching cylinder lower end is designed as taper slot structure, the taper of this structure and lower 506 upper end of switching cylinder
Platform cooperation, bears the lateral shear load between connected piece；Certain torque, upper and lower switching cylinder are applied to load nut 502
It is tensed by blasting bolt 504 and realizes connection, bear the longitudinal loading and moment of flexure between connected piece.When requiring connected piece to separate
When, blasting bolt work, blasting bolt is weakening fracture at slot 507, realizes satellite and the rocket unlock.Setting shock resistance is slow in upper switching cylinder
Rush material -- honeycomb, to reduce bolt head and load impact of the nut 502 when exploding unlock to connected piece.Unlock rear bolt
Lower half portion moves downward, and is collected plate collection.
Combined vibration-damping pad 501 is installed in upper switching cylinder upper surface, and combined vibration-damping pad 501 is docked with connected piece, and lower end is under
Switching cylinder 506 is docked.The upper surface of upper switching cylinder 508 is 3 to 6 reserved, preferably 4 equally distributed screw holes；Screw hole
3.2~φ of through-hole diameter model φ 6, preferably φ 5.5；The lower end surface of upper switching cylinder is provided with cone tank and through-hole, for and
Lower switching cylinder frustum docking, through-hole are used for the connection of blasting bolt.Upper switching cylinder is to be stayed using whole machining forging in inner cavity
There is the mounting platform of load nut and buffers cellular placement space；Through-hole is provided among lower end, the installation for blasting bolt.
Upper switching cylinder height can be within the scope of 25mm~40mm, preferably 25mm~35mm, more preferably 25mm~30mm, most preferably
For 25mm~27.5mm.
In the embodiment of the application, the spring thrust device 102 is as shown in fig. 6, include self-locking nut
602, spring 603, push rod 604 and sleeve 601.The outer surface of the sleeve 601 constitutes the guiding mandrel of spring 603.Sleeve 601
With in the mating surface of push rod 604 (φ 10) can be coated with molybdenum disulfide coating, guide surface long 40mm, distance of relative movement 100mm.
The installation of spring thrust device 102 is positioned by sleeve and the threaded hole cooperation on pedestal.When satellite discharges, spring
603 push push rod 604 to move, 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.
After scene covers the connection realization unlock of tripper 104 as shown in Figure 1: when satellite is separated with separating mechanism, the upper half
Divide and is released with satellite by spring thrust device 102.After spring stretching in place not further along, satellite flies forward due to inertia continuation
Row.The guide rail of satellite end evagination and the guide rail of separating mechanism indent limit the rotation of satellite, to ensure that satellite is lesser
Separate angular speed.
As Figure 7-9, the scheme of installation in section 703 is bored in rocket for the horizontal satellite and the rocket separated structure 100 of the application.
Rocket bores static state and dynamic load of the section 703 as load-carrying construction carrying rocket launching powered phase, and provides three
The mounting base 701 of primary.Cone section is Stringer skin formula sheet metal structural.In the covering upper opening of cone section, 702 elder generation of satellite and seperator
Structure is assembled into assembly, then whole to fill in cone section.
Horizontal 100 outer surface of satellite and the rocket separating mechanism uses bright anodic oxidation, to guarantee not generate before unlock separation
Heat.
Technical indicator for the horizontal satellite and the rocket separating mechanism of the application is as described below.
1. satisfactory quality: gross mass≤10kg, wherein power-supply system quality about 2kg, stays on star and is partially no more than
0.5kg。
2. being of the required size: inlet part structure external envelope is no more than 285 × 263 × 680mm when semi-buried installation,
The structure height being retained on star after separation is no more than 35mm.
3. separating rate meets the requirements: 1.4m/s.
4. separation attitude l-G simulation test meets the requirements: maximum posture angular displacement: 3.2 ° of pitching；Roll 1 °；1 ° of yaw.
5. attitude angular velocity deviation l-G simulation test meets the requirements: pitching≤3 °/s；Yaw≤3 °/s；Roll≤2 °/s.
6. spring force deviation meets the requirements: the power deviation between spring is not more than 2%.
7. parting surface impact meets the requirements: no more than 1000g within the scope of 5000Hz；Cushion blocking is installed.
8. reliability meets the requirements: 0.999 (r=0.7).
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 (7)
1. a kind of horizontal satellite and the rocket separating mechanism characterized by comprising
Main frame；
2 sets of connection trippers are mounted on the inside of main back end of frame face and have blasting bolt；
2 are held and cut positioning pin, and longitudinal loading is born in the taper hole cooperation with satellite；
3 sleeve spring thrust devices are mounted on the inside of main back end of frame face and are configured as satellite after blasting bolt unlocks
Main frame is released with the separating rate of design；And
Travel switch bracket, wherein travel switch is pressed on the travel switch bracket and in the satellite and the rocket before satellite and the rocket separation
After separation, the travel switch, which is flicked, provides separation signal to satellite.
2. horizontal satellite and the rocket separating mechanism as described in claim 1, which is characterized in that the main frame includes internal guide rail, described
The cooperation of the outer guide of internal guide rail and satellite.
3. horizontal satellite and the rocket separating mechanism as claimed in claim 2, which is characterized in that the internal guide rail of the separating mechanism and defend
Spacing between star outer rail is 0.5 to 0.9mm.
4. horizontal satellite and the rocket separating mechanism as claimed in claim 2, which is characterized in that the guide rail and the separating mechanism connect
It connects the surface sputtering molybdenum disulfide of tripper or smears space flight lubricating grease.
5. horizontal satellite and the rocket separating mechanism as described in claim 1, which is characterized in that satellite rear end passes through connection unlock dress
It sets and is strained and fixed on the inside of main back end of frame face.
6. horizontal satellite and the rocket separating mechanism as described in claim 1, which is characterized in that the bottom surface of the horizontal satellite and the rocket separating mechanism
It is connected by 10 M6 screws with rocket arm.
7. horizontal satellite and the rocket separating mechanism as described in claim 1, which is characterized in that the inclined-plane of the horizontal satellite and the rocket separating mechanism
It is connected by 12 M6 screws with the reinforcing rib of rocket and upper flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820852689.4U CN209008895U (en) | 2018-06-04 | 2018-06-04 | A kind of horizontal satellite and the rocket separating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820852689.4U CN209008895U (en) | 2018-06-04 | 2018-06-04 | A kind of horizontal satellite and the rocket separating mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209008895U true CN209008895U (en) | 2019-06-21 |
Family
ID=66828196
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820852689.4U Active CN209008895U (en) | 2018-06-04 | 2018-06-04 | A kind of horizontal satellite and the rocket separating mechanism |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319867A (en) * | 2020-10-29 | 2021-02-05 | 上海宇航系统工程研究所 | Ejection type connecting and separating integrated device |
| CN113148243A (en) * | 2021-05-08 | 2021-07-23 | 上海卫星工程研究所 | Primary-secondary configuration satellite group with inter-satellite unlocking and separating device and installation method |
| 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 |
-
2018
- 2018-06-04 CN CN201820852689.4U patent/CN209008895U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112319867A (en) * | 2020-10-29 | 2021-02-05 | 上海宇航系统工程研究所 | Ejection type connecting and separating integrated device |
| CN113148243A (en) * | 2021-05-08 | 2021-07-23 | 上海卫星工程研究所 | Primary-secondary configuration satellite group with inter-satellite unlocking and separating device and installation method |
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