CN207732095U - A kind of space deployable reflector antenna bi-directional locking arrangement - Google Patents
A kind of space deployable reflector antenna bi-directional locking arrangement Download PDFInfo
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- CN207732095U CN207732095U CN201820082407.7U CN201820082407U CN207732095U CN 207732095 U CN207732095 U CN 207732095U CN 201820082407 U CN201820082407 U CN 201820082407U CN 207732095 U CN207732095 U CN 207732095U
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- bolt
- reflector antenna
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Abstract
The utility model is related to a kind of space deployable reflector antenna bi-directional locking arrangement, the utility model includes end member, middle member, intermediate connector, compressed spring, pin.There are two the end members, is symmetrically distributed in the outside of locking mechanism, and bolt or screw can be used to be connected with fixing end, and equipped with the sleeve being connected with middle member；There are two middle members, is connected with end member by sleeve.The two-way pin of spring is provided in middle member, after being rotated in place, pin can be popped up and be locked, and the middle member other end is connected with intermediate connector by bolt or screw with ring flange.The utility model design is simple, easy to operate, and the locking of energy efficient stable effectively improves the fundamental frequency and surface accuracy of unfolding mechanism, ensures the smooth realization of satellite deployable structure function.
Description
Technical field
The utility model belongs to space technology field, and in particular to a kind of space deployable reflector antenna Bidirectional locking machine
Structure.
Background technology
With the development of economy, higher and higher to the requirement of satellite capacity, satellite antenna diameter is also increasing, but due to
The limitation of the dome space size of rocket, it is therefore desirable to satellite deployable antenna.As illustrated in fig. 1 and 2, the deployable reflection of satellite
Device antenna is by antenna 1, support arm 2, locking mechanism 3 and pedestal 4.Deployable antenna is in rounding state in transmitting, predetermined to space
Behind position, support arm can be rotated around fixing axle, be deployed into working condition, need locking mechanism that boom position is fixed and provided at this time
Structural support rigidity.
Current this kind of spring release mechanism all be traditional unidirectional locking mechanism of pulling pin, the mistake being unfolded in antenna of pulling pin
It is the inside that locking mechanism is pressed in by antenna arm in journey.When antenna expands in place, support arm is blocked by block, is pulled pin in spring
It is popped up from mechanism mouth under thrust, is inserted into the outside of antenna support arm, prevents from the reverse movement of antenna in this way.《Satellite
The determination of impact velocity and torque is unfolded in antenna reflector》It the article pointed out：Under spring force, antenna branch can be increased by pulling pin
The velocity of rotation of arm, to increase the collision impact of support arm and link stopper.Moreover, in the extreme high/low temperature of space orbit,
Reflector antenna can generate certain deformation due to the variation of temperature, and deformation is applied on pin by support arm, can be produced to pin
The raw power along pin axial direction, this power can cause pin side to move back.This will reduce the rigidity of antenna, while cause day
The larger error that line is directed toward.
In view of it is unidirectional pull pin locking mechanism the shortcomings that, the utility model proposes a kind of two-way plug-type locking machines of pin
Structure, the mechanism are located inside the rotation axis of antenna support arm, and after support arm rotate in place, two use, two spring driven pins are same
When along 180 ° of reversed directions, shaft is locked.The mechanism has higher locking rigidity as a result of two pins,
In this way, pointing accuracy of the reflector under track high/low temperature can be improved.Simultaneously as spring and pin is small-sized, because
This, to the impact force very little of reflector and support arm when locking.
Invention content
The purpose of this utility model is to provide a kind of space deployable reflector antenna bi-directional locking arrangements.
The utility model includes two end members, two middle members, a connector, four locking pins and two
Spring；Two middle member structures are identical, include central flange disk, main shaft and pin hole.One end of main shaft is arranged
There are central flange disk, the other end to be provided with step, pin hole is provided on step；Two end members middle parts and reflector bottom branch
Arm connects；
Two end member structures are identical, include end flange disk, sleeve, pin jack and guide groove.Set
Circular ring shape pin guide groove is arranged in the orbital position of the inside of cylinder, two locking pin rotations.With the guide groove center of circle on guide groove
Centered on be symmetrical arranged there are two pin jack, screens is carried out to end member pin nail hole inside pin.
It is hollow cylindrical shape axis in the middle part of the connector, axis both ends are both provided with mounting flange；In two
Central flange disk on portion's component is connect with the mounting flange at connector both ends respectively；Step difference on two middle members
It is inserted into the sleeve of two end members, is rotatablely connected by guide groove and end member；End method on two end members
Blue disk is fixedly connected with pedestal respectively；Middle member is rotated with connector by rotation center of the sleeve central axes of end member；
The locking pin is boss shape, and four locking pins are arranged two-by-two in the pin hole of two middle members,
Two springs are separately positioned in the middle part of the pin hole of two middle members, the top surface of the counter sink portion of two locking pins respectively with
Place pin hole inner spring both ends are fixedly connected.The lock portion of two locking pins can be pierced by pin hole.
Two end members and two middle members are symmetrically distributed in connector both sides.
There are two semi-girders, two semi-girders to be arranged in parallel in the middle part of main shaft, stretch for setting in the middle part of two end members
It is provided with bolt connecting hole on arm, is connect by bolt or screw with reflector bottom support arm.
It is provided with bolt connecting hole on the central flange disk, is connect with mounting flange by bolt or screw.
It is provided with bolt connecting hole on the end flange disk, passes through the fixation of bolt or screw and pedestal.
The spring uses high intensity compressed spring.
The utility model solve the problems, such as satellite antenna expand in place locking rigidity it is small, with existing satellite antenna be unfolded
Locking mechanism is compared, and realizes the Bidirectional locking of satellite antenna, while realizing the elimination of lock up gap, can greatly improve locking rigidity
With the pointing accuracy for improving antenna, when locking is smaller to the impact force of antenna.
Description of the drawings
Fig. 1 is the structure diagram that lock-out state is unfolded in Satellite Unfurlable Antenna；
Fig. 2 is the structure diagram of Satellite Unfurlable Antenna undeployed configuration；
Fig. 3 is the utility model overall structure diagram；
Fig. 4 is the Structure explosion diagram of Fig. 3 tip members；
Fig. 5 is the structural schematic diagram of middle member in Fig. 3；
Fig. 6 is the utility model overall structure installation diagram；
Fig. 7 is the structural schematic diagram for locking pin.
Specific implementation mode
Hereinafter reference will be made to the drawings, and the preferred embodiment of the utility model is described in detail.
As illustrated in figures 3-6, a kind of space deployable reflector antenna bi-directional locking arrangement is arranged at reflector antenna bottom
On, reflector bottom support arm is connect with locking mechanism；Locking mechanism includes two end members, 41, two middle members 42, one
43, four locking pins of a connector and two springs.Two middle members 42 are identical；Two 41 complete phases of end member
Together；It is symmetrical along connector 43.The setting of connector 43 is hollow cylindrical shape axis at middle part, middle part, and axis both ends are equal
It is provided with mounting flange；Central flange disk 6-1 on the two middle members mounting flange with 43 both ends of connector respectively
Connection；5 place step of pin hole is inserted into respectively in the sleeve 14 of two end members on two middle members, on end member
End flange disk 6-2 is fixedly connected with pedestal；So that with the sleeve axis of end member while locking mechanism is fixed on pedestal
Line rotates for rotation center；Locking pin is arranged in the pin hole of middle member.
Two middle members 41 include central flange disk 6-1, two semi-girders 7, main shaft 13 and pin hole 5.Main shaft 13
One end is provided with central flange disk 6-1, and the other end is provided with step, pin hole 5 is provided on step；Two semi-girders 7 are arranged in parallel
At the middle part of main shaft 13, bolt connecting hole 8 is provided on semi-girder 7, for being connect by bolt or screw with reflector bottom support arm；
It is provided with bolt connecting hole on central flange disk 6-1, for being connected by bolt or screw with intermediate connector.Where pin hole 5
The diameter of step is identical as the sleeve diameter of middle member, is installed for realizing the cooperation of middle member and end member, in machine
Structure is after installation is complete, and due to the limitation of axial displacement, middle member is only capable of being rotated about axis relative to end member.In pin hole
Between be placed with fixed compressed spring, both ends of the spring places two pins, the top surface of the counter sink portion 11 of two pins respectively with
Both ends of the spring is fixedly connected.The lock portion 12 of two locking pins can be pierced by pin hole.It is (not deployed to arrive in antenna expansion process
Position) in, locking pin is buried in pin hole always, and compressed spring is in complete compressive state.
Two end members include end flange disk 6-2, sleeve 14, pin jack 9 and guide groove 10.End flange disk 6-
Bolt connecting hole is provided on 2, for being fixed by bolt or screw with pedestal 4.14 internal diameter of sleeve and pin hole in end member
Place stepped diameters are identical, installed for realizing the cooperation of end member and middle member.The inside of sleeve locks pin rotation
Orbital position setting circular ring shape pin guide groove 10, the used time limits the movement of pin, makes pin can only be in specified track
Rotation.Two pin jacks 9 are arranged in corresponding position on sleeve, and two pin jacks are arranged on guide groove 10, with guide groove
It is symmetrical arranged centered on 10 centers of circle；After antenna expansion completely, the screens of end member pin hole inside pin is realized.
As shown in fig. 7, locking pin is boss shape, 11 diameter of counter sink portion and pin bore dia phase in two middle members
Together, lock part 12 is identical as pin jack in end member, realizes the cooperation peace of pin, two middle members and middle member
Dress.
The course of work is as follows：Launching phase, satellite antenna are bundled in rocket corresponding position, and locking mechanism is in unlocked shape
State, compressed spring is in complete compressive state in pin hole, and pin is buried in pin hole completely.
Satellite reaches track designation, and antenna binding releases, and under the driving of motor, two middle members of locking mechanism start
Rotation drives reflector antenna expansion by support arm.During expansion, two compressed springs are in two middle member pin holes
Complete compressive state, two locking pin lock parts be in cage guiding slot with two middle members turn in each pin hole
It is dynamic.
Antenna be deployed on two middle members pin hole with when pin jack is directed at position completely on end member sleeve,
In two pin holes under the promotion of compressed spring, two locking pin pin langrages go out in each pin hole, two locking pin sticking departments
Divide and be inserted into pin jack, limit the rotational freedom of reflector antenna, completes locking.At this time in sleeve space high-strength press
Contracting spring thrust plays the role of eliminating pin lock part and pin socket gap.
Finally, it should also be noted that it is listed above be only the utility model a specific embodiment.This field
All deformations that those of ordinary skill directly can export or associate from content disclosed by the utility model, are considered as this reality
With novel protection domain.
Claims (6)
1. a kind of space deployable reflector antenna bi-directional locking arrangement, including two end members, two middle members, one
Connector, four locking pins and two springs；It is characterized in that：Two middle member structures are identical, in including
Portion's ring flange, main shaft and pin hole；One end of main shaft is provided with central flange disk, and the other end is provided with step, is provided on step
Pin hole；It is connect with reflector bottom support arm in the middle part of two end members；
Two end member structures are identical, include end flange disk, sleeve, pin jack and guide groove；Sleeve
Circular ring shape pin guide groove is arranged in the orbital position of inside, two locking pin rotations；In being with the guide groove center of circle on guide groove
The heart is symmetrical arranged there are two pin jack, and screens is carried out to end member pin nail hole inside pin；
It is hollow cylindrical shape axis in the middle part of the connector, axis both ends are both provided with mounting flange；Two middle part structures
Central flange disk on part is connect with the mounting flange at connector both ends respectively；Step on two middle members is inserted into respectively
In the sleeve of two end members, it is rotatablely connected by guide groove and end member；End flange disk on two end members
It is fixedly connected respectively with pedestal；Middle member is rotated with connector by rotation center of the sleeve central axes of end member；
The locking pin is boss shape, and four locking pins are arranged two-by-two in the pin hole of two middle members, two
Spring is separately positioned in the middle part of the pin hole of two middle members, the top surface of the counter sink portion of two locking pins respectively with place
Pin hole inner spring both ends are fixedly connected；The lock portion of two locking pins can be pierced by pin hole.
2. a kind of space deployable reflector antenna bi-directional locking arrangement as described in claim 1, it is characterised in that：Described
Two end members and two middle members are symmetrically distributed in connector both sides.
3. a kind of space deployable reflector antenna bi-directional locking arrangement as described in claim 1, it is characterised in that：Described
There are two semi-girders, two semi-girders to be arranged in parallel in the middle part of main shaft for setting in the middle part of two end members, and bolt company is provided on semi-girder
Hole is connect, is connect by bolt or screw with reflector bottom support arm.
4. a kind of space deployable reflector antenna bi-directional locking arrangement as described in claim 1, it is characterised in that：Described
It is provided with bolt connecting hole on central flange disk, is connect with mounting flange by bolt or screw.
5. a kind of space deployable reflector antenna bi-directional locking arrangement as described in claim 1, it is characterised in that：Described
It is provided with bolt connecting hole on end flange disk, passes through the fixation of bolt or screw and pedestal.
6. a kind of space deployable reflector antenna bi-directional locking arrangement as described in claim 1, it is characterised in that：Described
Spring uses high intensity compressed spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820082407.7U CN207732095U (en) | 2018-01-18 | 2018-01-18 | A kind of space deployable reflector antenna bi-directional locking arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820082407.7U CN207732095U (en) | 2018-01-18 | 2018-01-18 | A kind of space deployable reflector antenna bi-directional locking arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207732095U true CN207732095U (en) | 2018-08-14 |
Family
ID=63082887
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820082407.7U Active CN207732095U (en) | 2018-01-18 | 2018-01-18 | A kind of space deployable reflector antenna bi-directional locking arrangement |
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| CN (1) | CN207732095U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110021808A (en) * | 2019-04-21 | 2019-07-16 | 彭小玲 | One kind having support bracket fastened household antenna |
-
2018
- 2018-01-18 CN CN201820082407.7U patent/CN207732095U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110021808A (en) * | 2019-04-21 | 2019-07-16 | 彭小玲 | One kind having support bracket fastened household antenna |
| CN110021808B (en) * | 2019-04-21 | 2021-04-13 | 吉林吉大通信设计院股份有限公司 | Domestic antenna with fixed bolster |
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