CN103674026A - Miniaturized liquid-floated inertial attitude sensor suitable for microsatellite - Google Patents
Miniaturized liquid-floated inertial attitude sensor suitable for microsatellite Download PDFInfo
- Publication number
- CN103674026A CN103674026A CN201310648777.4A CN201310648777A CN103674026A CN 103674026 A CN103674026 A CN 103674026A CN 201310648777 A CN201310648777 A CN 201310648777A CN 103674026 A CN103674026 A CN 103674026A
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- Prior art keywords
- microsatellite
- support
- board
- attitude sensor
- gyro
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/24—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 specially adapted for cosmonautical navigation
Abstract
The invention provides a miniaturized liquid-floated inertial attitude sensor suitable for a microsatellite, and the sensor comprises a seat arranged on an arbitrary plane, a gyro meter fixed on the seat by a pressing block and a screw, a power amplifier board bracket fixed on the seat and with the front side facing to the gyro meter, a power amplifier board vertically fixed on the front side of the power amplifier board bracket with the power amplifier board surface facing to the gyro meter, a miniaturized three-channel power operational amplifier arranged on the power amplifier board, a supporting column vertically arranged on the seat, a servo board erected on the supporting column and arranged above the gyro meter and the power amplifier board, and a modular rebalance circuit arranged on the servo board. The miniaturized liquid-floated inertial attitude sensor has the advantages of simple structure, less parts needing machining, simple assembly process, easiness in processing, assembly, adjustment and repair, low cost, suitability for mass production, substantial reduction of weight and volume, low power consumption, and suitability for the microsatellite with strict requirements on weight, size and power dissipation.
Description
Technical field
The present invention relates to a kind of inertial attitude sensor, be specifically related in a kind of the floating inertial attitude sensor of miniaturization single-degree-of-freedom liquid for low rail microsatellite.
Background technology
Along with the development of spationautics, to all kinds of satellites particularly weight, volume and the power consumption of microsatellite more and more higher requirement has been proposed, its supporting unit and load have also been proposed to corresponding requirement.
The composition form of the floating inertial attitude sensor of present stage liquid is various, according to the mounting means of contained gyro gauge outfit in sensor, divides these the three kinds of patterns of 3 quadratures, 6 quadratures and 3+1S that mainly contain.These three kinds of inertial attitude sensors contain respectively 3,6 and 4 gauge outfits, and amount of parts is many, complex structure, debugs difficulty, and weight, volume and power consumption are all larger simultaneously.
Summary of the invention
The invention provides a kind of floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite, be applicable to the microsatellite that certain has special applications to require, amount of parts reduces, simple in structure, it is convenient to install, lightweight, volume is little, can realize the inertial attitude sensor that microsatellite attitude is measured.
For achieving the above object, the invention provides a kind of floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite, be characterized in, this sensor comprises:
Be arranged on the support on arbitrary plane;
Gyro gauge outfit, it is fixed on support by briquetting and screw;
Power board support, it is fixed on support, positive in the face of gyro gauge outfit;
Power board, it is positive that it is vertically fixed on power board support, and power board surface is over against gyro top-of-form set;
Miniaturization triple channel power operational amplifier, it is arranged on power board;
Support column, it is vertically arranged on support;
Servoboard, it is erected on support column, and is arranged at the top of gyro gauge outfit and power board;
Modularization rebalancing circuit, it is arranged on servoboard.
Inner integrated three the identical power operational amplifiers of passage of triple channel power operational amplifier of above-mentioned miniaturization.
This sensor includes case that can integral demounting, and this case comprises front side board, back side panel, left plate, the right plate being located at respectively on support edge and is arranged on the top cover at this front side board, back side panel, left plate, right plate top.
Above-mentioned front side board, back side panel, left plate, right plate and top cover are by being arranged on the reinforcement on support, and the fixing case that forms of screw.
Above-mentioned support is provided with gyro installation hole, and described gyro gauge outfit is fixed in gyro installation hole by briquetting and screw.
Above-mentioned front side board is provided with socket, and socket is provided with connector; This connector circuit is connected to servoboard.
The floating inertial attitude sensor of liquid that a kind of miniaturization liquid that is applicable to microsatellite of the present invention floats inertial attitude sensor and prior art is compared, its advantage is, inertial attitude sensor design of part of the present invention is simple, need processing parts quantity few, assembly technology is simple, be easy to processing, debug and reprocess, with low cost, can be mass-produced, sensor weight is 1/4 of 3 quadratures simultaneously, 1/6 of 6 quadratures, 1/7 of 3+1S, volume is 1/3 of 3 quadratures, 1/8 of 6 quadratures, 1/13 of 3+1S, weight and volume all significantly reduces, low in energy consumption, applicable to weight and size power consumption being had to the microsatellite of strict demand,
Miniaturization triple channel power operational amplifier and the required component number of modularization rebalancing circuit that the present invention adopts are few, and shared pcb board area is little, and reliability is higher simultaneously;
The longitudinal mounting means of power board of the present invention has increased thermocontact area, reduces thermal contact resistance, has improved radiating efficiency;
The present invention arranges the ability that reinforcement has improved the mechanical environments such as product adaptation vibration, impact.
Accompanying drawing explanation
Fig. 1 is the inner structure schematic diagram that the present invention is applicable to the floating inertial attitude sensor of miniaturization liquid of microsatellite;
Fig. 2 is the support part schematic diagram that the present invention is applicable to the floating inertial attitude sensor of miniaturization liquid of microsatellite;
Fig. 3 is the leading flank schematic diagram that the present invention is applicable to the floating inertial attitude sensor of miniaturization liquid of microsatellite.
Embodiment
Below in conjunction with accompanying drawing, further illustrate specific embodiments of the invention.
As Fig. 1 and in conjunction with as shown in Fig. 2, the present invention discloses a kind of floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite, this sensor includes the support 7 being arranged on arbitrary plane, support 7 is slab construction, support 7 upper surfaces are provided with for the mount pad of gyro gauge outfit 10 is installed, and mount pad is provided with horizontal gyro installation hole.The power supply input of gyro gauge outfit 10 is provided by power board 3, and the signal of gyro gauge outfit 10 exports servoboard 11 to.Gyro gauge outfit 10 strings are located in gyro installation hole, and by being arranged on briquetting 8 and the screw on Si Ge summit, gyro installation hole, gyro gauge outfit 10 are fixed in gyro installation hole.
On support 7, to the position of gyro gauge outfit 10 is installed, by screw, be longitudinally fixed with power board support 5, the front of this power board support 5 is in the face of gyro gauge outfit 10.
The front of power board support 5 is vertically fixed with power board 3 by screw, and these power board 3 surfaces arrange over against gyro gauge outfit 10.
The back side of power board support 5 is welded with miniaturization triple channel power operational amplifier 15, and miniaturization triple channel power operational amplifier 15 circuit are connected in power board 3.Preferred miniaturization triple channel power operational amplifier 15, as one of device of power board 3, can be directly installed on the pcb board of power board 3.Inner integrated three the identical power operational amplifiers of passage of triple channel power operational amplifier 15 of miniaturization.Compare with the power amplifier driving for gyro machine in the past, number of devices and shared PCB area significantly reduce, and precision is constant.
At four drift angles of support 7, be vertically provided with 4, four of four groups of support columns and support the 4 added servoboards 11 that are provided with, and be fixed on support column 4 by clamp-screw 2.This servoboard 11 is arranged at the top of described gyro gauge outfit 10 and power board 3.
Servoboard is welded with modularization rebalancing circuit 14 on 11 surfaces, and modularization rebalancing circuit 14 circuit are connected in servoboard 11.Preferably, modularization rebalancing circuit 14, as one of device of servoboard 11, is directly installed on the pcb board of servoboard 11.Modularization rebalancing circuit 14 is as the gyro gauge outfit control circuit of brand-new design, compares with servo circuit in the past, and shared PCB area is less, and precision and reliability index higher.In prior art, modularization rebalancing circuit is to realize the functions such as demodulation, correction, amplification by 38 discrete devices, in the present invention, only by a device, realizes repertoire, and device volume dwindles greatly.By theory, calculate, reliability index greatly improves.
The floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite also includes case that can integral demounting, this case comprises front side board 17, back side panel 13, left plate 6 and the right plate 9 being located at respectively on support 7 four edges, limit, and is erected at the top cover 1 at this front side board 17, back side panel 13, left plate 6, right plate 9 tops.This front side board 17, back side panel 13, left plate 6, right plate 9 and top cover 1 are by being arranged on four reinforcements 12 and the fixing case that forms of screw on support 7.This case is arranged on the skin of sensor, as the contour structures of sensor.
As shown in Figure 3, front side board 17 is provided with socket 16, and socket 16 is provided with two connectors 18.The input and output of two connectors 18 are all connected with servoboard 11 circuit.
Although content of the present invention has been done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.Those skilled in the art, read after foregoing, for multiple modification of the present invention with to substitute will be all apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (6)
1. the floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite, is characterized in that, this sensor comprises:
Be arranged on the support (7) on arbitrary plane;
Gyro gauge outfit (10), it is fixed on support (7) by briquetting (8) and screw;
Power board support (5), it is upper that it is fixed on described support (7), positive in the face of gyro gauge outfit (10);
Power board (3), it is vertically fixed on power board support (5) front, and power board (3) surface arranges over against gyro gauge outfit (10);
Miniaturization triple channel power operational amplifier (15), it is arranged on described power board (3);
Support column (4), it is vertically arranged on described support (7);
Servoboard (11), it is upper that it is erected at described support column (4), and be arranged at the top of described gyro gauge outfit (10) and power board (3);
Modularization rebalancing circuit (14), it is arranged on described servoboard (11);
The power supply input of described gyro gauge outfit (10) connects power board (3), and the signal output of gyro gauge outfit (10) is connected to servoboard (11).
2. the floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite as claimed in claim 1, is characterized in that, inner integrated three the identical power operational amplifiers of passage of triple channel power operational amplifier (15) of described miniaturization.
3. the miniaturization liquid that is applicable to microsatellite as claimed in claim 1 floats inertial attitude sensor, it is characterized in that, this sensor includes case that can integral demounting, and this case comprises front side board (17), back side panel (13), left plate (6), the right plate (9) being located at respectively on support (7) edge and is arranged on the top cover (1) at this front side board (17), back side panel (13), left plate (6), right plate (9) top.
4. the miniaturization liquid that is applicable to microsatellite as claimed in claim 3 floats inertial attitude sensor, it is characterized in that, described front side board (17), back side panel (13), left plate (6), right plate (9) and top cover (1) are by being arranged on the reinforcement (12) on support (7), and the fixing case that forms of screw.
5. the floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite as claimed in claim 1, is characterized in that, described support (7) is provided with gyro installation hole, and described gyro gauge outfit (10) is fixed in gyro installation hole by briquetting (8) and screw.
6. the floating inertial attitude sensor of miniaturization liquid that is applicable to microsatellite as claimed in claim 3, is characterized in that, described front side board (17) is provided with socket (16), and socket (16) is provided with connector (18); This connector (18) circuit is connected to servoboard (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310648777.4A CN103674026B (en) | 2013-12-06 | 2013-12-06 | The miniaturization liquid being applicable to microsatellite floats inertial attitude sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310648777.4A CN103674026B (en) | 2013-12-06 | 2013-12-06 | The miniaturization liquid being applicable to microsatellite floats inertial attitude sensor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103674026A true CN103674026A (en) | 2014-03-26 |
| CN103674026B CN103674026B (en) | 2015-12-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310648777.4A Active CN103674026B (en) | 2013-12-06 | 2013-12-06 | The miniaturization liquid being applicable to microsatellite floats inertial attitude sensor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289253A (en) * | 2016-09-12 | 2017-01-04 | 上海航天控制技术研究所 | A kind of small-sized inertial attitude sensor peculiar to vessel |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040088127A1 (en) * | 2002-06-25 | 2004-05-06 | The Regents Of The University Of California | Integrated low power digital gyro control electronics |
| CN101021418A (en) * | 2006-12-30 | 2007-08-22 | 西安中星测控有限公司 | Angular speed rate and angle gyroscope |
| CN101900554A (en) * | 2010-06-24 | 2010-12-01 | 西北工业大学 | Method for digitally driving and detecting multi-gauge head gyroscope |
| CN102768554A (en) * | 2012-07-23 | 2012-11-07 | 中国兵器工业集团第二一四研究所苏州研发中心 | Constant-current source for gyroscope gauge outfit torquer |
-
2013
- 2013-12-06 CN CN201310648777.4A patent/CN103674026B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040088127A1 (en) * | 2002-06-25 | 2004-05-06 | The Regents Of The University Of California | Integrated low power digital gyro control electronics |
| CN101021418A (en) * | 2006-12-30 | 2007-08-22 | 西安中星测控有限公司 | Angular speed rate and angle gyroscope |
| CN101900554A (en) * | 2010-06-24 | 2010-12-01 | 西北工业大学 | Method for digitally driving and detecting multi-gauge head gyroscope |
| CN102768554A (en) * | 2012-07-23 | 2012-11-07 | 中国兵器工业集团第二一四研究所苏州研发中心 | Constant-current source for gyroscope gauge outfit torquer |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289253A (en) * | 2016-09-12 | 2017-01-04 | 上海航天控制技术研究所 | A kind of small-sized inertial attitude sensor peculiar to vessel |
| CN106289253B (en) * | 2016-09-12 | 2019-07-02 | 上海航天控制技术研究所 | A kind of small-sized inertial attitude sensor peculiar to vessel |
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| Publication number | Publication date |
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| CN103674026B (en) | 2015-12-02 |
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Effective date of registration: 20170621 Address after: 200233 Xuhui District, Yishan Road, No. 710, Patentee after: SHANGHAI AEROSPACE CONTROL TECHNOLOGY RESEARCH INSTITUTE Address before: 200233 Xuhui District, Yishan Road, No. 710, Patentee before: Shanghai Xinyue Instrument Factory |
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