CN105659919B - A kind of spaceborne servomechanism system - Google Patents
A kind of spaceborne servomechanism systemInfo
- Publication number
- CN105659919B CN105659919B CN201110015262.1A CN201110015262A CN105659919B CN 105659919 B CN105659919 B CN 105659919B CN 201110015262 A CN201110015262 A CN 201110015262A CN 105659919 B CN105659919 B CN 105659919B
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- 238000009434 installation Methods 0.000 claims abstract description 21
- 238000007906 compression Methods 0.000 claims abstract description 10
- 210000003165 Abomasum Anatomy 0.000 claims abstract description 8
- 235000014676 Phragmites communis Nutrition 0.000 claims abstract description 8
- 239000003638 reducing agent Substances 0.000 claims description 12
- 210000000078 Claw Anatomy 0.000 claims description 6
- 210000001847 Jaw Anatomy 0.000 claims description 6
- 210000004279 Orbit Anatomy 0.000 claims description 4
- 230000000875 corresponding Effects 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000001429 stepping Effects 0.000 description 1
- 230000001702 transmitter Effects 0.000 description 1
Abstract
The invention discloses a kind of spaceborne servomechanism system, belong to spacecraft driving mechanism field. Described system comprises system installing plate, three compression relieving mechanisms, Two-shaft drive mechanism, bottom bracket, antenna installation stent, limit switch, control system; Wherein Two-shaft drive mechanism comprises transverse axis driving mechanism, longitudinal axis driving mechanism and between centers support; Transverse axis driving mechanism and longitudinal axis driving mechanism arrange respectively limit switch, when Two-shaft drive mechanism exceeds the range of movement of-25 ~+25 °, by contacting of between centers support and reed, make Two-shaft drive mechanism stop motion. Spaceborne servomechanism system of the present invention, adopt XY type plane cross crossed geometry and compact layout configurations, ensure that three axis vertical take-off of antenna photo electric axis and driving mechanism two axles, make sensing and angular surveying to target relative rotational angular degree more accurate.<pb pnum="1" />
Description
Technical field
The present invention relates to a kind of spaceborne servomechanism system, belong to spacecraft driving mechanism field.
Background technology
The middle of last century, the states such as the U.S., Europe, the former Soviet Union, under the support energetically of industrial department, openThe begun development of space-vehicle antenna driving mechanism, at present, space-vehicle antenna driving mechanism has been widely used in respectivelyClass spacecraft, as repeater satellite, telecommunication satellite, all kinds of detector, remote sensing satellite, space station, scouting are defendedMagnitude etc. Through the development of decades, space driving mechanism of a great variety, different properties, is widely used,Become seriation, reliability is higher. Be directed to the servomechanism system that radar is load also along with driving mechanismDevelopment get rapid development, and come into operation in last century eight, the nineties.
China, in last century end, just starts the development of pedestal, and the unit of development driving mechanism has veryMany, product comprises the removable spot beam anternma of Ka, antenna swing mechanism, relay antenna driving mechanism, SARAntenna deployment mechanism, MCSR scan driving mechanism etc., be successfully applied to multiple models.
Said mechanism product all can not meet at aspects such as movement velocity, range of movement, control modes spaceborne andThe needs of antenna also cannot realize two under the prerequisite of the installation matrix for radar special-purpose member and radar antennaDimension high-speed motion the needs that meet target search and tracking.
Summary of the invention
The object of this invention is to provide a kind of spaceborne servomechanism system, described system can be arranged on spaceborneAntenna carries out two-dimensional high speed movement, meet target search simultaneously and follow the tracks of needs.
For achieving the above object, technical scheme of the present invention is as follows:
A kind of spaceborne servomechanism system, described system comprise system installing plate, three compression relieving mechanisms,Two-shaft drive mechanism, bottom bracket, antenna installation stent, limit switch, control system;
Wherein, Two-shaft drive mechanism comprises transverse axis driving mechanism, longitudinal axis driving mechanism and between centers support; Transverse axisDriving mechanism is identical with longitudinal axis driving mechanism structure, includes three of code-discs, harmonic speed reducer, stepper motorPoint; Harmonic speed reducer is between code-disc and stepper motor, in transverse axis driving mechanism and longitudinal axis driving mechanismPortion is respectively equipped with output shaft, and output shaft one end is connected with harmonic speed reducer, and the other end exposes code-disc;
Wherein, antenna installation stent is positioned at system installing plate middle part;
Transverse axis driving mechanism is fixed on system installing plate by bottom bracket, and between centers support is L bracket,The output shaft of transverse axis driving mechanism is fixedly connected with one end of between centers support; The other end of between centers support has logicalHole, the code-disc of longitudinal axis driving mechanism is through through hole and be fixedly connected with between centers support, longitudinal axis driving mechanism defeatedShaft is fixedly connected with antenna installation stent; Difference on the code-disc of transverse axis driving mechanism and longitudinal axis driving mechanismLimit switch is set;
Preferably limit switch is positioned in the plane that code-disc output shaft exposes one end, and limit switch is provided with reed,When Two-shaft drive mechanism exceeds the range of movement of-25 ~+25 °, by contacting of between centers support and reed, makeTwo-shaft drive mechanism stop motion.
Output shaft on the code-disc of longitudinal axis driving mechanism is positioned at L bracket inner side, the code-disc of transverse axis driving mechanism,Harmonic speed reducer and stepper motor are all positioned at L bracket outside;
The pivot center of transverse axis driving mechanism and longitudinal axis driving mechanism is in the orthogonal configuration of cross;
Three compression relieving mechanisms are fixed on system installing plate, and one of them compresses relieving mechanism and passes through lock clawBe fixedly connected with the compressor arm between centers support, two other compresses relieving mechanism respectively by lock claw and antennaCompressor arm on mounting bracket is fixedly connected with, and realizes the compression of described spaceborne servomechanism system and discharges meritCan;
Wherein, acting as of antenna installation stent, as the installation matrix of radar antenna;
Acting as of Two-shaft drive mechanism, realizes the two-dimensional rotary of radar antenna, meets target search and followsThe needs of track;
Compress acting as of relieving mechanism, in the Spacecraft Launch stage, described servo control mechanism is pressed in systemOn installing plate, this antenna system is made can to bear compared with large load do not damage at the transmitter section of spacecraft; BoatAfter it device is entered the orbit, the compressor arm in this mechanism is cut into two sections by the firer's cutter compressing on relieving mechanism,The lock claw that compresses relieving mechanism is opened, and compresses relieving mechanism and removes the constraint to servomechanism system, realizes twoThe motion of axle driving mechanism and radar antenna;
Acting as of limit switch, when Two-shaft drive mechanism exceeds the range of movement of-25 ~+25 °, passes through axleBetween the contacting of support and reed, make Two-shaft drive mechanism stop motion, play protection Two-shaft drive mechanism and thunderReach the effect of antenna.
Wherein, system installing plate, compression relieving mechanism, Two-shaft drive mechanism first axle, Two-shaft drive mechanismThe second axle all can adopt device of the prior art, wherein compresses relieving mechanism and has applied for national defence patent "Plant the locking releasing device that can independently dodge ", application number 200810078177.8.
Control system is arranged on inside satellite, is connected with Two-shaft drive mechanism by cable;
Control system comprises external command module, processing module, receiver module, Executive Module;
Each model calling relation is as follows: external command module is connected with processing module, processing module respectively with connectReceive module to be connected with Executive Module, receiver module is connected with the code-disc of Two-shaft drive mechanism, and Executive Module is with twoThe stepper motor of axle driving mechanism is connected;
Wherein, external command module, for inputing to the various instructions that set or the provisional injunction of inputProcessing module, instruction includes but not limited to the rotational angle of Two-shaft drive mechanism; Instruction is set before testGet well or change according to actual conditions temporarily, strengthening the enforceability of instruction;
Receiver module, the rotational angle Monitoring Data transmitting from code-disc for real-time reception, and be transmitted toProcessing module;
Processing module, the rotational angle Monitoring Data receiving from receiver module for basis, in processing moduleIn inner judging unit, judge in conjunction with the instruction of external command or storage in advance, and judged result is sent outGive Executive Module; Wherein judged result has 2 kinds of situations:
The first moves in the angular range of-25 ~+25 ° for Two-shaft drive mechanism;
The second is the angular range that the range of movement of Two-shaft drive mechanism exceedes at-25 ~+25 °;
Executive Module is for carrying out action executing according to above-mentioned 2 kinds of judged results to performing object:
If this Executive Module receives the first judged result, then send instructions to Executive Module, twin shaft drivesMotivation structure continues motion;
If this Executive Module receives the second judged result, then send instructions to Executive Module, twin shaft drivesThe stop motion of motivation structure.
A kind of spaceborne servomechanism system method of work, described method workflow is as follows:
Step 1, on antenna installation stent install radar antenna, in the Spacecraft Launch stage, by compressDescribed spaceborne servomechanism system is pressed on system installing plate by relieving mechanism; After spacecraft is entered the orbit, compressCompressor arm in this mechanism is cut into two sections by the firer's cutter on relieving mechanism, compresses the lock of relieving mechanismPawl is opened, and removes the constraint to spaceborne servomechanism system; By the default angle of rotation of external command module inputDegree, code-disc measures the rotational angle of Two-shaft drive mechanism, and rotational angle data are this moment transferred to reception mouldPiece;
The rotational angle data receiver that code-disc imports into by step 2, receiver module is also transmitted to processing module;
Step 3, in the judging unit internal ratio of processing module to receiving the real-time rotational angle data of module forwardsDefault rotational angle instruction with the input of external command module, according to comparison result, carries out situation judgement; ItsIn, instruction can be set before test or change according to actual conditions temporarily;
Step 4, give Executive Module perform judged result, judged result and corresponding implementation status divide 2Kind:
1. move in the angular range of-25 ~+25 ° when Two-shaft drive mechanism, now between centers support is not with spacing
Switch jaw contact on switch, then sends instructions to Executive Module, connects step 5;
2. when the range of movement of Two-shaft drive mechanism exceedes the angular range at-25 ~+25 °, now between centers support
With the switch jaw contact on limit switch, then send instructions to Executive Module, connect step 6;
Step 5, Executive Module send instructions to Two-shaft drive mechanism, and Two-shaft drive mechanism continues motion, connectsStep 7;
Step 6, connect step 4, Executive Module sends instructions to Two-shaft drive mechanism, and Two-shaft drive mechanism is stoppedOnly motion;
Step 7, according to the moving situation of Two-shaft drive mechanism, code-disc measures the angle of rotation of Two-shaft drive mechanismDegree, is transferred to the receiver module in step 2 by rotational angle data this moment, thus forms closed loop monitoring systemSystem.
Beneficial effect
1. spaceborne servomechanism system of the present invention, the Two-shaft drive mechanism of employing is XY type plane crossCrossed geometry, ensure that three axis vertical take-off of antenna photo electric axis and driving mechanism two axles, makes target phaseMore accurate to the sensing of angle and angular surveying;
2. have employed the consistent compression releasing device of three covers (possess and independently dodge function) and compact layout structureType mode, ensure that this cover servomechanism system and large-scale fortune can be realized after satellier injection mechanism dischargesDynamic, two free degree directions all can reach-25 ~+25 °;
3. devise novel between centers support and antenna installation stent, achieve antenna, antenna wave guide, radarThe installation of the products such as special-purpose member on servo control mechanism and servo-actuated.
Accompanying drawing explanation
Fig. 1 is the front view of a kind of spaceborne servomechanism system provided by the present invention;
Fig. 2 is the top view of a kind of spaceborne servomechanism system provided by the present invention;
Fig. 3 is the perspective view of a kind of spaceborne servomechanism system provided by the present invention;
Fig. 4 is the structural representation of Two-shaft drive mechanism provided by the present invention;
Fig. 5 is the model calling figure of a kind of spaceborne servomechanism system provided by the present invention;
Wherein: 1-system installing plate, 2-compress relieving mechanism, 3-transverse axis driving mechanism, 4-bottom bracket, 5-Between centers support, 6-longitudinal axis driving mechanism, 7-antenna installation stent, 8-radar antenna, 9-limit switch, 10-Stepper motor, 11-harmonic speed reducer, 12-code-disc.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described.
Embodiment
As shown in Figure 1, Figure 2 and Figure 3, a kind of spaceborne servomechanism system, described system comprises system and installsPlate 1, three compression relieving mechanisms 2, Two-shaft drive mechanism, bottom bracket 4, antenna installation stent 7, limitBit switch 9, control system;
Wherein, Two-shaft drive mechanism comprises transverse axis driving mechanism 3, longitudinal axis driving mechanism 6 and between centers support 5;Transverse axis driving mechanism 3 is identical with longitudinal axis driving mechanism 6 structure, include code-disc 12, harmonic speed reducer 11,Stepper motor 10 3 part; Harmonic speed reducer 11 is between code-disc 12 and stepper motor 10, at transverse axisDriving mechanism 3 and longitudinal axis driving mechanism 6 inside are respectively equipped with output shaft, output shaft one end and harmonic speed reducer11 connections, the other end exposes code-disc 12;
Wherein, antenna installation stent 7 is positioned at system installing plate 1 middle part;
Transverse axis driving mechanism 3 is fixed on system installing plate 1 by bottom bracket 4, and between centers support 5 is LShape support, the output shaft of transverse axis driving mechanism 3 is fixedly connected with one end of between centers support 5; Between centers support 5The other end have through hole, the code-disc of longitudinal axis driving mechanism 6 is through through hole and be fixedly connected with between centers support 5,The output shaft of longitudinal axis driving mechanism 6 is fixedly connected with by screw with antenna installation stent 7; At transverse axis driving machineThe code-disc 12 of structure 3 and longitudinal axis driving mechanism arranges respectively limit switch 9; Limit switch 9 is positioned at code-disc 12Output shaft exposes in the plane of one end, and limit switch 9 is provided with reed, when Two-shaft drive mechanism exceed-25 ~During the range of movement of+25 °, by contacting of between centers support 5 and reed, make Two-shaft drive mechanism stop motion.
Output shaft on the code-disc 12 of longitudinal axis driving mechanism 6 is positioned at L bracket inner side, transverse axis driving mechanism 3Code-disc 12, harmonic speed reducer 11 and stepper motor 10 be all positioned at L bracket outside;
The pivot center of transverse axis driving mechanism 3 and longitudinal axis driving mechanism 6 is in the orthogonal configuration of cross;
Three compression relieving mechanisms 2 are fixed on system installing plate, and one of them compresses relieving mechanism by lockPawl is fixedly connected with the compressor arm between centers support 5, two other compress relieving mechanism respectively by lock claw withCompressor arm on antenna installation stent 7 is fixedly connected with, realize the compression of described spaceborne servomechanism system andRelease function;
Control system is arranged on inside satellite, by the code-disc in cable and Two-shaft drive mechanism 12 and stepping electricityMachine 10 connects;
Control system comprises external command module, processing module, receiver module, Executive Module;
Each model calling relation is as follows: external command module is connected with processing module, processing module respectively with connectReceive module to be connected with Executive Module, receiver module is connected with the code-disc in Two-shaft drive mechanism 12, Executive ModuleBe connected with the stepper motor in Two-shaft drive mechanism 10;
Wherein, external command module, for inputing to the various instructions that set or the provisional injunction of inputProcessing module, instruction includes but not limited to the rotational angle of Two-shaft drive mechanism; Instruction is set before testGet well or change according to actual conditions temporarily, strengthening the enforceability of instruction;
Receiver module, the rotational angle Monitoring Data transmitting from code-disc 12 for real-time reception, and by its forwardingGive processing module;
Processing module, the rotational angle Monitoring Data receiving from receiver module for basis, in processing moduleIn inner judging unit, judge in conjunction with the instruction of external command or storage in advance, and judged result is sent outGive Executive Module; Wherein judged result has 2 kinds of situations:
The first moves in the angular range of-25 ~+25 ° for Two-shaft drive mechanism;
The second is the angular range that the range of movement of Two-shaft drive mechanism exceedes at-25 ~+25 °;
Executive Module is for carrying out action executing according to above-mentioned 2 kinds of judged results to performing object:
If this Executive Module receives the first judged result, then send instructions to Executive Module, twin shaft drivesMotivation structure continues motion;
If this Executive Module receives the second judged result, then send instructions to Executive Module, twin shaft drivesThe stop motion of motivation structure.
A kind of spaceborne servomechanism system method of work, described method workflow is as follows:
Step 1, on antenna installation stent 7 install radar antenna 8, in the Spacecraft Launch stage, by pressDescribed spaceborne servomechanism system is pressed on system installing plate 1 by tight relieving mechanism 2; After spacecraft is entered the orbit,Compressor arm in this mechanism is cut into two sections by the firer's cutter compressing on relieving mechanism 2, compresses machine for releasingThe lock claw of structure 2 is opened, and removes the constraint to spaceborne servomechanism system; Pre-by the input of external command moduleIf rotational angle, code-disc 12 measures the rotational angle of Two-shaft drive mechanism, and rotational angle data are this moment passedBe defeated by receiver module;
The rotational angle data receiver that code-disc 12 imports into by step 2, receiver module is also transmitted to processing module;
Step 3, in the judging unit internal ratio of processing module to receiving the real-time rotational angle data of module forwardsDefault rotational angle instruction with the input of external command module, according to comparison result, carries out situation judgement; ItsIn, instruction can be set before test or change according to actual conditions temporarily;
Step 4, give Executive Module perform judged result, judged result and corresponding implementation status divide 2Kind:
2. in the angular range of-25 ~+25 °, move when Two-shaft drive mechanism, now between centers support 5 not with limitSwitch jaw contact on bit switch 9, then sends instructions to Executive Module, connects step 5;
3. when the range of movement of Two-shaft drive mechanism exceedes the angular range at-25 ~+25 °, now between centers support5 with limit switch 9 on switch jaw contact, then send instructions to Executive Module, connect step 6;
Step 5, Executive Module send instructions to Two-shaft drive mechanism, and Two-shaft drive mechanism continues motion, connectsStep 7;
Step 6, connect step 4, Executive Module sends instructions to Two-shaft drive mechanism, and Two-shaft drive mechanism is stoppedOnly motion;
Step 7, according to the moving situation of Two-shaft drive mechanism, code-disc 12 measures the rotation of Two-shaft drive mechanismAngle, is transferred to the receiver module in step 2 by rotational angle data this moment, thus forms closed loop monitoringSystem, realizes the search of target and following function.
In sum, these are only preferred embodiment of the present invention, be not intended to limit guarantor of the present inventionProtect scope. Within the spirit and principles in the present invention all, any amendment of doing, be equal to replacement, improvement etc.,Within protection scope of the present invention all should be included in.
Claims (3)
1. a spaceborne servomechanism system, is characterized in that: comprise system installing plate (1), three compressionsRelieving mechanism (2), Two-shaft drive mechanism, bottom bracket (4), antenna installation stent (7), limit switch(9), control system;
Wherein, Two-shaft drive mechanism comprises transverse axis driving mechanism (3), longitudinal axis driving mechanism (6) and between centers and props upFrame (5); Transverse axis driving mechanism (3) is identical with longitudinal axis driving mechanism (6) structure, include code-disc (12),Harmonic speed reducer (11), stepper motor (10) three part; Harmonic speed reducer (11) is positioned at code-disc (12)And between stepper motor (10), respectively inner at transverse axis driving mechanism (3) and longitudinal axis driving mechanism (6)Be provided with output shaft, output shaft one end is connected with harmonic speed reducer (11), and the other end exposes code-disc (12);
Wherein, antenna installation stent (7) is positioned at system installing plate (1) middle part;
It is upper that transverse axis driving mechanism (3) is fixed on system installing plate (1) by bottom bracket (4), and between centers props upFrame (5) is L bracket, and the output shaft of transverse axis driving mechanism (3) and one end of between centers support (5) are fixedConnection; The other end of between centers support (5) has through hole, and the code-disc of longitudinal axis driving mechanism (6) is through through holeOutput shaft and the antenna installation stent (7) of longitudinal axis driving mechanism (6) and is fixedly connected with between centers support (5)Be fixedly connected with; The code-disc (12) of transverse axis driving mechanism (3) and longitudinal axis driving mechanism arrange respectively spacingSwitch (9);
Output shaft on the code-disc (12) of longitudinal axis driving mechanism (6) is positioned at L bracket inner side, and transverse axis drivesCode-disc (12), harmonic speed reducer (11) and the stepper motor (10) of mechanism (3) are all positioned at L bracketOutside;
The pivot center of transverse axis driving mechanism (3) and longitudinal axis driving mechanism (6) is in the orthogonal configuration of cross;
Three compression relieving mechanisms (2) are fixed on system installing plate, and one of them compresses relieving mechanism and passes throughLock claw is fixedly connected with the compressor arm between centers support (5), and two other compresses relieving mechanism respectively by lockPawl is fixedly connected with the compressor arm on antenna installation stent (7), realizes described spaceborne servomechanism systemCompress and release function;
Control system is arranged on inside satellite, is connected with Two-shaft drive mechanism by cable;
Control system comprises external command module, processing module, receiver module, Executive Module;
Each model calling relation is as follows: external command module is connected with processing module, processing module respectively with connectReceive module to be connected with Executive Module, receiver module is connected with the code-disc (12) of Two-shaft drive mechanism, performs mouldPiece is connected with the stepper motor (10) of Two-shaft drive mechanism;
Wherein, external command module, for inputing to the various instructions that set or the provisional injunction of inputProcessing module, instruction includes but not limited to the rotational angle of Two-shaft drive mechanism; Instruction is set before testGet well or change according to actual conditions temporarily, strengthening the enforceability of instruction;
Receiver module, the rotational angle Monitoring Data transmitting from code-disc (12) for real-time reception, and by itBe transmitted to processing module;
Processing module, the rotational angle Monitoring Data receiving from receiver module for basis, in processing moduleIn inner judging unit, judge in conjunction with the instruction of external command or storage in advance, and judged result is sent outGive Executive Module; Wherein judged result has 2 kinds of situations:
The first moves in the angular range of-25 ~+25 ° for Two-shaft drive mechanism;
The second is the angular range that the range of movement of Two-shaft drive mechanism exceedes at-25 ~+25 °;
Executive Module is for carrying out action executing according to above-mentioned 2 kinds of judged results to performing object:
If this Executive Module receives the first judged result, then send instructions to Executive Module, twin shaft drivesMotivation structure continues motion;
If this Executive Module receives the second judged result, then send instructions to Executive Module, twin shaft drivesThe stop motion of motivation structure.
2. the spaceborne servomechanism system of one according to claim 1, is characterized in that: limit switch(9) be positioned at code-disc (12) output shaft to expose in the plane of one end, limit switch (9) be provided with reed,When Two-shaft drive mechanism exceeds the range of movement of-25 ~+25 °, by contacting of between centers support (5) and reed,Make Two-shaft drive mechanism stop motion.
3. a spaceborne servomechanism system method of work, described method uses as claimed in claim 1 onePlant spaceborne servomechanism system, it is characterized in that: described method workflow is as follows:
Step 1, at the upper radar antenna (8) of installing of antenna installation stent (7), in the Spacecraft Launch stage,By compressing relieving mechanism (2), described spaceborne servomechanism system is pressed on system installing plate (1);After spacecraft is entered the orbit, the compressor arm in this mechanism is cut into by the firer's cutter compressing on relieving mechanism (2)Two sections, the lock claw that compresses relieving mechanism (2) is opened, and removes the constraint to spaceborne servomechanism system; Pass throughThe default rotational angle of external command module input, code-disc (12) measures the rotational angle of Two-shaft drive mechanism,Rotational angle data are this moment transferred to receiver module;
The rotational angle data receiver that code-disc (12) imports into by step 2, receiver module is also transmitted to processing mouldPiece;
Step 3, in the judging unit internal ratio of processing module to receiving the real-time rotational angle data of module forwardsDefault rotational angle instruction with the input of external command module, according to comparison result, carries out situation judgement; ItsIn, instruction can be set before test or change according to actual conditions temporarily;
Step 4, give Executive Module perform judged result, judged result and corresponding implementation status divide 2Kind:
1. move in the angular range of-25 ~+25 ° when Two-shaft drive mechanism, now between centers support (5) noSwitch jaw contact with on limit switch (9), then sends instructions to Executive Module, connects step 5;
2. when the range of movement of Two-shaft drive mechanism exceedes the angular range at-25 ~+25 °, now between centers support(5) with the switch jaw contact on limit switch (9), then send instructions to Executive Module, connect step 6;
Step 5, Executive Module send instructions to Two-shaft drive mechanism, and Two-shaft drive mechanism continues motion, connectsStep 7;
Step 6, connect step 4, Executive Module sends instructions to Two-shaft drive mechanism, and Two-shaft drive mechanism is stoppedOnly motion;
Step 7, according to the moving situation of Two-shaft drive mechanism, code-disc (12) measures Two-shaft drive mechanismRotational angle, is transferred to the receiver module in step 2 by rotational angle data this moment, thus forms closed loopMonitoring system.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105659919B true CN105659919B (en) | 2014-06-04 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106932775A (en) * | 2017-03-09 | 2017-07-07 | 北京空间飞行器总体设计部 | A kind of ISAR imaging tests high accuracy indicator device |
| CN107240764A (en) * | 2017-05-22 | 2017-10-10 | 上海宇航系统工程研究所 | The directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed |
| CN107994312A (en) * | 2017-10-19 | 2018-05-04 | 成都锦江电子系统工程有限公司 | A kind of folded antenna erection method |
| CN108054515A (en) * | 2017-10-27 | 2018-05-18 | 上海卫星工程研究所 | The specific spaceborne two-dimentional driving number being initially directed toward can be achieved and pass antenna system |
| CN108054512A (en) * | 2017-12-08 | 2018-05-18 | 上海宇航系统工程研究所 | A kind of high-torque anti-interference antenna directing mechanism for survey of deep space |
| CN109552672A (en) * | 2018-11-12 | 2019-04-02 | 上海宇航系统工程研究所 | A kind of hard limit adjustable position-limit mechanism of angle |
| CN107819196B (en) * | 2017-09-25 | 2020-05-29 | 上海卫星工程研究所 | Three-dimensional pointing to ground data transmission antenna layout system with performance constraint |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106932775A (en) * | 2017-03-09 | 2017-07-07 | 北京空间飞行器总体设计部 | A kind of ISAR imaging tests high accuracy indicator device |
| CN106932775B (en) * | 2017-03-09 | 2019-05-24 | 北京空间飞行器总体设计部 | A kind of ISAR imaging test high-precision indicator device |
| CN107240764A (en) * | 2017-05-22 | 2017-10-10 | 上海宇航系统工程研究所 | The directing mechanism that a kind of spaceborne Complex Radar antenna high rigidity offset is fixed |
| CN107240764B (en) * | 2017-05-22 | 2020-08-28 | 上海宇航系统工程研究所 | High-rigidity offset type fixed pointing mechanism of satellite-borne complex radar antenna |
| CN107819196B (en) * | 2017-09-25 | 2020-05-29 | 上海卫星工程研究所 | Three-dimensional pointing to ground data transmission antenna layout system with performance constraint |
| CN107994312A (en) * | 2017-10-19 | 2018-05-04 | 成都锦江电子系统工程有限公司 | A kind of folded antenna erection method |
| CN108054515A (en) * | 2017-10-27 | 2018-05-18 | 上海卫星工程研究所 | The specific spaceborne two-dimentional driving number being initially directed toward can be achieved and pass antenna system |
| CN108054515B (en) * | 2017-10-27 | 2020-10-27 | 上海卫星工程研究所 | Satellite-borne two-dimensional driving data transmission antenna system capable of realizing specific initial pointing |
| CN108054512A (en) * | 2017-12-08 | 2018-05-18 | 上海宇航系统工程研究所 | A kind of high-torque anti-interference antenna directing mechanism for survey of deep space |
| CN108054512B (en) * | 2017-12-08 | 2020-09-08 | 上海宇航系统工程研究所 | High-torque anti-interference antenna pointing mechanism for deep space exploration |
| CN109552672A (en) * | 2018-11-12 | 2019-04-02 | 上海宇航系统工程研究所 | A kind of hard limit adjustable position-limit mechanism of angle |
| CN109552672B (en) * | 2018-11-12 | 2021-12-17 | 上海宇航系统工程研究所 | Hard limiting angle-adjustable limiting mechanism |
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