CN207809824U - Microsatellite separator - Google Patents
Microsatellite separator Download PDFInfo
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- CN207809824U CN207809824U CN201721813289.4U CN201721813289U CN207809824U CN 207809824 U CN207809824 U CN 207809824U CN 201721813289 U CN201721813289 U CN 201721813289U CN 207809824 U CN207809824 U CN 207809824U
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- flange
- satellite
- adapter
- delivery adapter
- installation
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Abstract
The utility model is related to a kind of microsatellite separators, for safely detaching microsatellite with delivery adapter.The microsatellite separator of the utility model, pass through setting retaining mechanism and positioning push mechanism between satellite mounting flange and delivery adapter, and it is powered and powers off in an orderly manner respectively to retaining mechanism and positioning push mechanism, it realizes in flight course of the retaining mechanism before satellite injection and locks satellite mounting flange reverse side and delivery adapter front flange, positioning push mechanism plays the role of positioning when retaining mechanism is locked and is opened, and when satellite mounting flange reverse side after retaining mechanism is opened is detached with delivery adapter front flange, thrust is provided for the satellite mounting flange reverse side.Realize the purpose that microsatellite is detached with the safety adapter of rocket.
Description
Technical field
The utility model is related to a kind of satellites and Separation device, more particularly to a kind of microsatellite separator.
Background technology
The separation of conventional satellite and carrier rocket often uses the separate mode that band and blasting bolt combine.This separation
Technology is more mature, also widely used on large satellite.But with the development of technology, the separating mechanism based on blasting bolt exists
The moment of blasting bolt explosion will produce larger uncertain impact force and some uncontrolled clasts, can give to be separated
Satellite and the adapter of rocket bring certain injury.It, may be to it especially in the emission process of several satellite in a rocket
His satellite causes to damage.
Utility model content
Based on this, it is necessary to be directed to existing microsatellite separator, in separation process can to satellite to be separated with
And the adapter of rocket brings certain injury problem, provides a kind of microsatellite separator for capableing of safe separating.
A kind of microsatellite separator provided by the utility model, including：
Satellite installs first flange, and the satellite offered in the satellite installation first flange for connecting satellite is installed
Hole；
Satellite installs second flange；
Deliver adapter first flange；
Adapter second flange is delivered, the delivery adapter second flange offers the installation for connecting carrier rocket
Hole；
The satellite can be installed second flange and the first method of the delivery adapter by retaining mechanism, the retaining mechanism
Orchid locking；
Positioning push mechanism, the positioning push mechanism are used to install the to the satellite when the retaining mechanism lock
Two flanges are positioned with the delivery adapter first flange, and after retaining mechanism opening, are pacified to the satellite
Dress second flange, which provides thrust, makes satellite installation second flange be detached with delivery adapter first flange.
In one of the embodiments, fluted, the positioning push mechanism is opened up in the satellite installation second flange
For permanent magnetism-electromagnetic mechanism, the permanent magnetism-electromagnetic mechanism includes permanent magnet and electromagnet, and the permanent magnet is set to the satellite
Bottom portion of groove in second flange is installed, the electromagnet is corresponding with the permanent magnet, passes through mounting flange and the delivery
Adapter first flange is connected.
The electromagnet is tapered close to one end of the permanent magnet in one of the embodiments, the satellite installation
The slot opening shape opened up in second flange is adapted with the tapering point of the permanent magnet.
The groove and permanent magnet are multiple and install second flange along the satellite in one of the embodiments,
Circumferential direction it is uniformly distributed, the electromagnet is also multiple, and with the permanent magnet correspondingly along the first method of the delivery adapter
Blue circumferential direction is uniformly distributed.
It is offered in the satellite installation second flange for connecting delivery adapter first in one of the embodiments,
The locking hole of flange, the retaining mechanism are mechanical interlock mechanism, and the mechanical interlock mechanism passes through retaining mechanism mounting flange
In delivery adapter first flange, the mechanical interlock mechanism includes shell, and lock is provided on the inner wall of the shell
Tight motor slideway is provided with locking motor in the shell, and the bottom of the locking motor is connected with tie down screw, the locking
Motor is placed in the locking motor slideway, and can drive the locking screw by back and forth movement in the locking motor slideway
Bar screws in or screws out the locking hole in the satellite installation second flange.
Tension spring, the pulling force are additionally provided in the shell of the mechanical interlock mechanism in one of the embodiments,
The both ends of spring are connect with the top of the inside top of the shell and the locking motor respectively.
The mechanical interlock mechanism is multiple in one of the embodiments, and along the first method of the delivery adapter
Blue circumferential direction is uniformly distributed.
The microsatellite separator further includes satellite mounting flange reinforcing rib in one of the embodiments, described
First flange is installed at the both ends of satellite mounting flange reinforcing rib with the satellite respectively and satellite installation second flange is connect.
The microsatellite separator further includes delivery adapter reinforcing rib, the fortune in one of the embodiments,
The both ends for carrying adapter reinforcing rib are connect with the delivery adapter first flange and delivery adapter second flange respectively.
A kind of method for releasing of microsatellite is included the following steps using above-mentioned microsatellite separator：
Satellite installation process：
Satellite is mounted in satellite installation first flange, on the launch vehicle by the installation of delivery adapter second flange；
Using the positioning push mechanism to satellite installation second flange and the delivery adapter first flange into
Row positioning；
Retaining mechanism is controlled by satellite installation second flange and the delivery adapter first flange butt-joint locking；
After satellier injection：
Control the retaining mechanism unlock；
Control the positioning push mechanism makes satellite install second flange to satellite installation second flange offer thrust
It is detached with delivery adapter first flange.
The positioning push mechanism is permanent magnetism-electromagnetic mechanism, the permanent magnetism-electromagnetic mechanism in one of the embodiments,
Including the electromagnet that the permanent magnet in satellite installation second flange is arranged and is arranged in delivery adapter first flange, including
Following steps：
In satellite installation process, it is powered to the electromagnet forward direction, makes to generate electromagnetism between the permanent magnet and electromagnet
Attraction positions satellite installation second flange with the delivery adapter first flange；
During satellite launch, the electromagnet power-off；
After satellier injection, in the retaining mechanism releasing process, the electromagnet is positive again to be powered, and makes the permanent magnet
Electromagnetic attraction is generated between electromagnet；
After the retaining mechanism unlock, reversely it is powered to the electromagnet, makes to generate between the permanent magnet and electromagnet
Electromagnetic repulsive force makes satellite installation second flange be detached with delivery adapter first flange.
Above-mentioned microsatellite separator, by satellite mounting flange and delivery adapter between setting retaining mechanism and
Positioning push mechanism, and be powered and power off in an orderly manner respectively to retaining mechanism and positioning push mechanism, it realizes retaining mechanism and exists
Satellite mounting flange reverse side and delivery adapter front flange are locked in flight course before satellite injection, positioning push
Mechanism plays the role of positioning when retaining mechanism is locked and is opened, and satellite mounting flange reverse side and fortune after retaining mechanism opening
When carrying the flange separation of adapter front, thrust is provided for the satellite mounting flange reverse side.Overcome existing microsatellite point
From device use blasting bolt separating mechanism, blasting bolt explosion moment will produce larger uncertain impact force and
Some uncontrolled clasts, the problem of bringing injury to the adapter of satellite and rocket to be separated.Realize small defend
The purpose that star is detached with the safety adapter of rocket.
Description of the drawings
It is required in being described below to embodiment in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
Attached drawing to be used is briefly described, it should be apparent that, the accompanying drawings in the following description is only some realities of the utility model
Example is applied, it for those of ordinary skill in the art, without creative efforts, can also be according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the schematic diagram of the microsatellite separator of the utility model embodiment；
Fig. 2 is the satellite mounting flange and delivery adapter flange of the microsatellite separator of the utility model embodiment
Schematic diagram after installation is fixed；
Fig. 3 is the schematic diagram of the mechanical interlock mechanism of the microsatellite separator of the utility model embodiment.
Specific implementation mode
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, the present invention will be further described in detail.It should be appreciated that specific implementation described herein is only used to explain this
Utility model is not used to limit the utility model.
It should be noted that when element is referred to as " being fixed on " another element, it can be directly on another element
Or there may also be elements placed in the middle.When an element is considered as " connection " another element, it can be directly connected to
To another element or it may be simultaneously present centering elements.On the contrary, when element is referred to as " directly existing " another element "upper",
There is no intermediary elements.On the contrary, when element is connect referred to as " direct " with another element, intermediary element is not present.This paper institutes
Term " vertically ", " horizontal ", "left", "right" and the similar statement used is for illustrative purposes only.
In the description of the present invention, it should be understood that term " length ", " width ", " thickness ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "top", "bottom", "inner", "outside" is based on ... shown in the drawings
Orientation or positional relationship is merely for convenience of describing the present invention and simplifying the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as to the utility model
Limitation.
Refer to Fig. 1 and Fig. 2, a kind of microsatellite separator that one embodiment of the utility model provides, including：Satellite
First flange 100 is installed, the satellite mounting hole 110 for connecting satellite, institute are offered in the satellite installation first flange 100
It states satellite mounting hole 110 and is distributed on the satellite installation first flange 100 circumferentially, the number of the satellite mounting hole 110 is not done
It is specific to limit, it is selected according to specific practical situation.Microsatellite is fixed on described defend by the satellite mounting hole 110
Star is installed in first flange 100.Satellite installs second flange 200, and the satellite installation second flange 200 is used to be adapted to delivery
Device flange is attached.Adapter first flange 300 is delivered, the delivery adapter first flange 300 is installed with the satellite
200 corresponding connection of second flange.Adapter second flange 400 is delivered, the delivery adapter second flange 400 opens up useful
In the mounting hole 410 of connection carrier rocket, the mounting hole 410 is distributed on the circumferential direction of the delivery adapter second flange 400,
The number of the mounting hole 410 is not specifically limited, and is selected according to specific practical situation.
The satellite can be installed second flange 200 and the delivery adapter the by retaining mechanism, the retaining mechanism
One flange 300 is locked, and after locking, satellite mounting flange is fixedly connected with delivery adapter flange.
Positioning push mechanism, the positioning push mechanism are used to install the to the satellite when the retaining mechanism lock
Two flanges 200 are positioned with the delivery adapter first flange 300, and after retaining mechanism opening, to described
Satellite installation second flange 200, which provides thrust, makes satellite installation second flange 200 be detached with delivery adapter first flange 300.
Accordingly, it realizes satellite and delivers the safe separating of adapter.
Continuing with referring to Fig. 1 and Fig. 2, in one embodiment of the utility model, the satellite installs second flange 200
On open up it is fluted, the positioning push mechanism be permanent magnetism-electromagnetic mechanism, the permanent magnetism-electromagnetic mechanism includes 210 He of permanent magnet
Electromagnet 310, the permanent magnet 210 are set to the bottom portion of groove in the satellite installation second flange 200, the electromagnet
310 is corresponding with the permanent magnet 210, is connected with the delivery adapter first flange 300 by mounting flange 320.Institute
The energization of electromagnet 310 is stated, electromagnetic attraction is generated between the permanent magnet 210, electromagnetic attraction can be in satellite Method for Installation
When orchid docks fixed with delivery adapter mounting flange, positioning and fixed function are played.The electromagnet 310 is reversely powered, with
Electromagnetic repulsive force is generated between the permanent magnet 210, electromagnetic repulsive force can be in satellite mounting flange and delivery adapter installation
When flange detaches, thrust is provided to satellite mounting flange, it is ensured that satellite mounting flange is being detached with delivery adapter mounting flange
Shi Buhui is mutually collided, and realizes safe separating.
Preferably, the electromagnet 310 is tapered close to one end of the permanent magnet 210, and the satellite installs the second method
The slot opening shape opened up on orchid 200 is adapted with the tapering point of the permanent magnet 210.One end of the permanent magnet 210 is in
The slot opening shape opened up in taper and second flange 200 is adapted with the tapering point of the permanent magnet 210, be conducive to
After the electromagnet 310 is powered, guide the electromagnet 310 slide into the groove that is opened up in the second flange 200 with
The permanent magnet 210 attracts each other, with the accurate positionin and locking realized satellite mounting flange with deliver adapter flange.
Optionally, the groove and permanent magnet 210 are multiple and install the circumferential direction of second flange 200 along the satellite
Uniformly distributed, the electromagnet 310 is also multiple, and with the permanent magnet 210 correspondingly along the first method of the delivery adapter
The circumferential direction of orchid 300 is uniformly distributed.Permanent magnet 210 in the permanent magnetism-electromagnetic mechanism uses in pairs with electromagnet 310, but specific logarithm
It does not limit, is selected according to practical situation.In one embodiment of the utility model, the permanent magnet 210 with it is described
Electromagnet 310 is four pairs, and is correspondingly distributed on the circumferential and described delivery of the satellite installation second flange 200 respectively
The circumferential direction of adapter first flange 300.
Referring to Fig. 3, in one embodiment of the utility model, opened up in the satellite installation second flange 200 useful
In the locking hole of connection delivery adapter first flange 300, the retaining mechanism is mechanical interlock mechanism, the mechanical interlocking machine
Structure is mounted on by retaining mechanism mounting flange 330 in delivery adapter first flange 300, and the mechanical interlock mechanism includes outer
Shell 340 is provided with locking motor slideway 350 on the inner wall of the shell 340, locking motor is provided in the shell 340
360, the bottom of the locking motor 360 is connected with tie down screw 370, and the locking motor 360 is placed on the locking motor
In slideway 350, and the tie down screw 370 can be driven to screw in or revolve by back and forth movement in the locking motor slideway 350
Go out the locking hole in the satellite installation second flange 200.The mechanical interlock mechanism is pacified by retaining mechanism mounting flange 330
It is fixedly connected with the delivery adapter first flange 300 after in delivery adapter first flange 300.The locking motor
When 360 directions for installing second flange 200 towards the satellite in the locking motor slideway 350 move, the lock is driven
Tight screw rod 370 screws in the locking hole in the satellite installation second flange 200, the satellite installation second flange 200 with it is described
It delivers adapter first flange 300 and realizes screw-threaded coupling.The locking motor 360 in the locking motor slideway 350 towards
When direction movement far from satellite installation second flange 200, the tie down screw 370 is driven to screw out satellite installation the
Locking hole on two flanges 200, the satellite installation second flange 200 realize spiral shell with the delivery adapter first flange 300
Line unlocks.
Further, tension spring 380, the tension spring 380 are additionally provided in the shell 330 of the mechanical interlock mechanism
Both ends connect respectively with the top of the inside top of the shell 330 and the locking motor 360.Specifically, when the lock
It is described when the direction that tight motor 360 installs second flange 200 in the locking motor slideway 350 towards the satellite moves
Tension spring 380 undergoes one from free state to the deformation process for stretching state.When the locking motor 360 is in the locking motor
When installing the direction movement of second flange 200 in slideway 350 away from the satellite, the tension spring 380 undergoes one
From deformation process of the state to free state is stretched, in the process, the tension spring 380 provides one to the locking motor 360
A longitudinal pulling force, this pulling force too big need not just ensure fully being installed from the satellite for the tie down screw 370
It is screwed out in locking hole in second flange 200, and then enhances the satellite installation second flange 200 and the delivery adapter
The reliability that first flange 300 detaches.
Further, the mechanical interlock mechanism is multiple, and along the circumferential direction of the delivery adapter first flange 300
It is uniformly distributed.The specific number of mechanical interlock mechanism does not limit, and is selected according to actual conditions.In a reality of the utility model
It applies in example, the mechanical interlock mechanism is four, and it is suitable to be arranged at intervals on the delivery successively with aforementioned four permanent magnetism-electromagnetic mechanism
The circumferential direction of orchestration first flange 300.
In one embodiment of the utility model, the microsatellite separator further includes that satellite mounting flange is reinforced
First flange 100 and the satellite are installed with the satellite respectively in the both ends of muscle 220, the satellite mounting flange reinforcing rib 220
Second flange 200 is installed to connect.Satellite mounting flange reinforcing rib 220 is used to enhance the intensity of satellite mounting flange.
In one embodiment of the utility model, the microsatellite separator further includes delivery adapter reinforcing rib
390, the both ends of the delivery adapter reinforcing rib 390 respectively with the delivery adapter first flange 300 and deliver adapter
Second flange 400 connects.Intensity of the delivery adapter reinforcing rib 390 for enhancing delivery adapter flange.
A kind of method for releasing of microsatellite is included the following steps using above-mentioned microsatellite separator：
In satellite installation process, satellite is mounted in satellite installation first flange, by delivery adapter second flange peace
Dress is on the launch vehicle.Using the positioning push mechanism to satellite installation second flange and the delivery adapter first
Flange is positioned.Satellite installation second flange is docked lock by control retaining mechanism with the delivery adapter first flange
Tightly.After satellier injection, the retaining mechanism unlock is controlled.It controls the positioning push mechanism and second flange is installed to the satellite
There is provided thrust makes satellite installation second flange be detached with delivery adapter first flange.
The positioning push mechanism is permanent magnetism-electromagnetic mechanism, the permanent magnetism-electromagnetic mechanism in one of the embodiments,
Including the electromagnet that the permanent magnet in satellite installation second flange is arranged and is arranged in delivery adapter first flange, including
Following steps：In satellite installation process, it is powered to the electromagnet forward direction, makes to generate electromagnetism between the permanent magnet and electromagnet
Attraction positions satellite installation second flange with the delivery adapter first flange.During satellite launch,
The electromagnet power-off.After satellier injection, in the retaining mechanism releasing process, the electromagnet is positive again to be powered, and makes institute
It states and generates electromagnetic attraction between permanent magnet and electromagnet.After the retaining mechanism unlock, reversely it is powered, makes to the electromagnet
Electromagnetic repulsive force is generated between the permanent magnet and electromagnet, makes satellite installation second flange and delivery adapter first flange point
From.
Specifically, the satellite mounting hole opened up in satellite installation process, passing of satelline satellite installation first flange 100
110 are mounted on satellite mounting flange, and carrier rocket is installed by delivering the mounting hole 410 that adapter second flange 400 opens up
On delivery adapter flange.
It is powered to positioning push mechanism, the positioning push mechanism is to the satellite mounting flange and the delivery adapter
Flange provides electromagnetic attraction, realizes being accurately positioned for the two.Specifically, the taper electromagnet 310 is given to be powered, the taper
Electromagnetic attraction is generated between electromagnet 310 and the permanent magnet 210, realizes satellite mounting flange and delivers adapter flange
It is accurately positioned and sucks.
Retaining mechanism is by the satellite mounting flange and the delivery adapter flange butt-joint locking.Specifically, locking is given
Motor 360 is powered, and locking motor 360 installs the side of second flange 200 in the locking motor slideway 350 towards the satellite
It drives tie down screw 370 to screw in the locking hole in the satellite installation second flange 200 to movement, realizes satellite mounting flange
With the screw-threaded coupling of delivery adapter flange.
Satellite launch process：
The positioning push mechanism power-off.Specifically, taper electromagnet 310 and locking motor 360 power off, and ensure entire
It is carried to adapter in flight course and is in off-position, reduces safety problem.
After satellier injection：
The positioning push mechanism is once again powered up, the positioning push mechanism again give the satellite mounting flange with it is described
It delivers adapter flange and electromagnetic attraction is provided, to ensure that satellite is in stable state.Specifically, taper electromagnet 310 is given again
Secondary energization, generates electromagnetic attraction between the taper electromagnet 310 and the permanent magnet 210, realize satellite mounting flange with
Delivery adapter flange sucks.
The retaining mechanism unlock, the satellite mounting flange are separately located with satellite one with the delivery adapter flange
In free movement state；During retaining mechanism unlocks, positioning push mechanism persistently gives the satellite mounting flange and institute
It states delivery adapter flange and electromagnetic attraction is provided, it is ensured that satellite is to be in stable state, even if retaining mechanism not right and wrong
Normal synchronization, it is also ensured that the normal development of separation.Specifically, taper electromagnet 310 remains powered on, and locking motor 360 is again
Secondary energization, locking motor 360 install the side of second flange 200 in the locking motor slideway 350 away from the satellite
It drives tie down screw 370 to screw out in the locking hole in the satellite installation second flange 200 to movement, realizes satellite mounting flange
It is unlocked with the screw thread of delivery adapter flange.
The positioning push mechanism is reversely powered, and the positioning push mechanism is to the satellite mounting flange and the delivery
Adapter flange provides electromagnetic repulsive force and satellite and satellite mounting flange is released together, realizes the safe separating of satellite.Specifically
Ground is reversely powered to taper electromagnet 310, electrodynamic repulsion is generated between the taper electromagnet 310 and the permanent magnet 210
Power, the electromagnetic repulsive force are together released satellite and satellite mounting flange, realize satellite and deliver the safe separating of adapter.
Above-mentioned microsatellite separator, by satellite mounting flange and delivery adapter between setting retaining mechanism and
Positioning push mechanism, and be powered and power off in an orderly manner respectively to retaining mechanism and positioning push mechanism, it realizes retaining mechanism and exists
Satellite mounting flange reverse side and delivery adapter front flange are locked in flight course before satellite injection, positioning push
Mechanism plays the role of positioning when retaining mechanism is locked and is opened, and satellite mounting flange reverse side and fortune after retaining mechanism opening
When carrying the flange separation of adapter front, thrust is provided for the satellite mounting flange reverse side.Overcome existing microsatellite point
From device use blasting bolt separating mechanism, blasting bolt explosion moment will produce larger uncertain impact force and
Some uncontrolled clasts, the problem of to the adapter of satellite to be separated and rocket is brought injury.It realizes small
The purpose that satellite is detached with the safety adapter of rocket.
The beneficial effects of the utility model are：
The first, it is mounted in delivery adapter first flange 300 by retaining mechanism mounting flange 330, by locking electricity
The moving handle tie down screw 370 of machine 360 screws out and installs threaded hole realization and the satellite Method for Installation of second flange 200 by satellite
Blue locking.
The second, used locking motor slideway 350 is fixed on locking motor 360 inside fastening system shell 340；It is special
The helical spring 380 of design provides a pulling force when tie down screw 370 screws out and ensures that the safety of tie down screw 370 screws out.
Third, positioning push mechanism are taper permanent magnetism-electromagnetic mechanism, are adapted to delivery in satellite installation second flange 200
When device first flange 300 is assembled, the accurate positionin of two flanges is realized by permanent magnet 210 and taper electromagnet 310；It is detaching
When, an electromagnetic attraction is provided when tie down screw 370 screws out, and an electromagnetic push is provided separation satellite after back-out
It pushes open, realizes the safe separating of satellite.
Each technical characteristic of embodiment described above can be combined arbitrarily, to keep description succinct, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, it is all considered to be the range of this specification record.
Above-described embodiments merely represent several embodiments of the utility model, the description thereof is more specific and detailed,
But it should not be understood as limiting the scope of the patent of the utility model.It should be pointed out that for the common of this field
For technical staff, without departing from the concept of the premise utility, various modifications and improvements can be made, these all belong to
In the scope of protection of the utility model.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (9)
1. a kind of microsatellite separator, which is characterized in that including：
Satellite installs first flange, and the satellite mounting hole for connecting satellite is offered in the satellite installation first flange；
Satellite installs second flange；
Deliver adapter first flange；
Adapter second flange is delivered, the delivery adapter second flange offers the mounting hole for connecting carrier rocket；
The satellite can be installed second flange and be locked with the delivery adapter first flange by retaining mechanism, the retaining mechanism
Tightly；
Positioning push mechanism, the positioning push mechanism are used to install the second method to the satellite when the retaining mechanism is locked
It is blue to be positioned with the delivery adapter first flange, and after retaining mechanism opening, to satellite installation the
Two flanges, which provide thrust, makes satellite installation second flange be detached with delivery adapter first flange.
2. microsatellite separator according to claim 1, which is characterized in that opened in the satellite installation second flange
Equipped with groove, the positioning push mechanism is permanent magnetism-electromagnetic mechanism, and the permanent magnetism-electromagnetic mechanism includes permanent magnet and electromagnet,
The permanent magnet is set to the bottom portion of groove in the satellite installation second flange, and the electromagnet is opposite with the permanent magnet
It answers, is connected with the delivery adapter first flange by mounting flange.
3. microsatellite separator according to claim 2, which is characterized in that the electromagnet is close to the permanent magnet
One end it is tapered, the slot opening shape and the tapering point of the permanent magnet opened up in satellite installation second flange is mutually fitted
Match.
4. microsatellite separator according to claim 3, which is characterized in that the groove and permanent magnet are multiple
And the circumferential direction that second flange is installed along the satellite is uniformly distributed, the electromagnet is also multiple and corresponding with the permanent magnet
Ground is uniformly distributed along the circumferential direction of the delivery adapter first flange.
5. microsatellite separator according to claim 3, which is characterized in that opened in the satellite installation second flange
Equipped with the locking hole for connecting delivery adapter first flange, the retaining mechanism is mechanical interlock mechanism, the mechanical lock
Tight mechanism is mounted on by retaining mechanism mounting flange in delivery adapter first flange, and the mechanical interlock mechanism includes outer
Shell is provided with locking motor slideway on the inner wall of the shell, locking motor is provided in the shell, the locking motor
Bottom is connected with tie down screw, and the locking motor is placed in the locking motor slideway, and can be in the locking motor
Back and forth movement drives the tie down screw to screw in or screw out the locking hole in the satellite installation second flange in slideway.
6. microsatellite separator according to claim 5, which is characterized in that in the shell of the mechanical interlock mechanism
It is additionally provided with tension spring, the both ends of the tension spring top with the inside top of the shell and the locking motor respectively
Portion connects.
7. microsatellite separator according to claim 6, which is characterized in that the mechanical interlock mechanism be it is multiple,
And it is uniformly distributed along the circumferential direction of the delivery adapter first flange.
8. microsatellite separator according to claim 1, which is characterized in that the microsatellite separator also wraps
Include satellite mounting flange reinforcing rib, the both ends of the satellite mounting flange reinforcing rib installed respectively with the satellite first flange and
The satellite installation second flange connection.
9. microsatellite separator according to claim 1, which is characterized in that the microsatellite separator also wraps
Include delivery adapter reinforcing rib, it is described delivery adapter reinforcing rib both ends respectively with the delivery adapter first flange and fortune
Carry the connection of adapter second flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721813289.4U CN207809824U (en) | 2017-12-21 | 2017-12-21 | Microsatellite separator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721813289.4U CN207809824U (en) | 2017-12-21 | 2017-12-21 | Microsatellite separator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207809824U true CN207809824U (en) | 2018-09-04 |
Family
ID=63330443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721813289.4U Expired - Fee Related CN207809824U (en) | 2017-12-21 | 2017-12-21 | Microsatellite separator |
Country Status (1)
| Country | Link |
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| CN (1) | CN207809824U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100311A (en) * | 2017-12-21 | 2018-06-01 | 星际漫步（北京）航天科技有限公司 | Microsatellite separator and its method for releasing |
| CN109533341A (en) * | 2018-09-20 | 2019-03-29 | 广东工业大学 | A kind of logistics aircraft and cargo hold and logistics aircraft and cargo hold automatic butt, the control system and control method that separate |
| CN110816893A (en) * | 2019-10-16 | 2020-02-21 | 上海空间电源研究所 | Limiting device for dismounting large-space bearing product |
| 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 |
| CN112046788A (en) * | 2020-08-07 | 2020-12-08 | 航天科工空间工程发展有限公司 | Satellite screw recovery unit |
| CN113548198A (en) * | 2021-08-17 | 2021-10-26 | 北京微纳星空科技有限公司 | Satellite configuration suitable for installation of different satellite carriers |
-
2017
- 2017-12-21 CN CN201721813289.4U patent/CN207809824U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100311A (en) * | 2017-12-21 | 2018-06-01 | 星际漫步（北京）航天科技有限公司 | Microsatellite separator and its method for releasing |
| CN108100311B (en) * | 2017-12-21 | 2024-04-12 | 星际漫步（北京）航天科技有限公司 | Microsatellite separation device and release method thereof |
| CN109533341A (en) * | 2018-09-20 | 2019-03-29 | 广东工业大学 | A kind of logistics aircraft and cargo hold and logistics aircraft and cargo hold automatic butt, the control system and control method that separate |
| CN109533341B (en) * | 2018-09-20 | 2023-05-16 | 广东工业大学 | Logistics aircraft and cargo hold, control system and control method for automatic docking and detaching of logistics aircraft and cargo hold |
| CN110816893A (en) * | 2019-10-16 | 2020-02-21 | 上海空间电源研究所 | Limiting device for dismounting large-space bearing product |
| CN110816893B (en) * | 2019-10-16 | 2021-02-09 | 上海空间电源研究所 | Limiting device for dismounting large-space bearing product |
| CN112046788A (en) * | 2020-08-07 | 2020-12-08 | 航天科工空间工程发展有限公司 | Satellite screw recovery unit |
| 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 |
| 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 |
| CN113548198A (en) * | 2021-08-17 | 2021-10-26 | 北京微纳星空科技有限公司 | Satellite configuration suitable for installation of different satellite carriers |
| CN113548198B (en) * | 2021-08-17 | 2022-04-05 | 北京微纳星空科技有限公司 | Satellite configuration suitable for installation of different satellite carriers |
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