CN103278267B - Spacecraft force exertion measurement mechanism - Google Patents
Spacecraft force exertion measurement mechanism Download PDFInfo
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- CN103278267B CN103278267B CN201310153512.7A CN201310153512A CN103278267B CN 103278267 B CN103278267 B CN 103278267B CN 201310153512 A CN201310153512 A CN 201310153512A CN 103278267 B CN103278267 B CN 103278267B
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Abstract
The invention provides a kind of spacecraft force exertion measurement mechanism, comprise: upper protective cover, the first output shaft, angular position pick up, the second output shaft, scroll spring, deep groove ball bearing, end cap and low protection cover, upper protective cover is connected with low protection cover, and end cap is connected with low protection cover; First output shaft is connected with upper protective cover, angular position pick up is connected with the first output shaft and low protection cover respectively, second output shaft one end is connected the other end through end cap with the first output shaft, deep groove ball bearing cover to be connected to outside the second output shaft and to be connected with end cap, and scroll spring cover is connected to outside the second output shaft and is connected with low protection cover.The invention solves problem segment space aircraft needing accurate power and torgue measurement, this device also has that quality is light, initial torque is adjustable, volume is little and the compatible feature such as good simultaneously, effectively ensure that the accuracy that power is measured and reliability, have broad application prospects.
Description
Technical field
The present invention relates to a kind of force measuring device, particularly, relate to a kind of spacecraft force exertion measurement mechanism.
Background technology
Along with the development of spacecraft technology, the movable part that spacecraft adopts is increasingly extensive, and the mechanism with power or the accurate control overflow of moment also produces thereupon.But general domestic and international common commercial force snesor mainly contains following problem:
1) force snesor mostly needs comparatively complicated modulate circuit, and weight and volume is all large;
2) general all as ground use, the reliability used in space and environment all need special verification experimental verification to its impact.
Above technical matters limits power measuring technique in spaceborne uses such as spacecrafts, even also limit correlated activation parts in the spaceborne use of spacecraft.Along with the light-weighted development trend of spacecraft, require that the weight of each load on spacecraft is more and more less, and the mode that general force measuring technique uses is all comparatively large because of its weight and resource, cannot meet the user demand of spacecraft.
For this reason, angularly consider from product applicability, thermal adaptability, product weight and connection use-pattern, the present invention devises a kind of force measuring device be applied on spacecraft.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of spacecraft force exertion measurement mechanism.
According to an aspect of the present invention, a kind of spacecraft force exertion measurement mechanism is provided, comprise: upper protective cover, the first output shaft, angular position pick up, the second output shaft, scroll spring, deep groove ball bearing, end cap and low protection cover, upper protective cover is connected with low protection cover, and end cap is connected with low protection cover; First output shaft is connected with upper protective cover, angular position pick up is connected with the first output shaft and low protection cover respectively, second output shaft one end is connected the other end through end cap with the first output shaft, deep groove ball bearing cover to be connected to outside the second output shaft and to be connected with end cap, and scroll spring cover is connected to outside the second output shaft and is connected with low protection cover.
Preferably, this spacecraft force exertion measurement mechanism also comprises pogo barrel and screw, and pogo barrel is arranged between scroll spring outer ring and low protection cover, and low protection cover is provided with threaded hole, and screw is connected with screw hole through spring spool.
Preferably, low protection cover is provided with in order to carry out unidirectional spacing positive stop lug boss to the second output shaft.
Preferably, this spacecraft force exertion measurement mechanism also comprises circlip, and circlip is arranged between deep groove ball bearing and end cap and carries out spacing to deep groove ball bearing.
Preferably, position corresponding with angular position pick up on upper protective cover is provided with square hole, draws with for the supply lines of angular position pick up and signal wire.
Preferably, upper protective cover and the first output shaft are made into integration.
Preferably, screw is hex screw.
Preferably, scroll spring adopts spiral of Archimedes coiling to form.
Preferably, scroll spring adopts 55CrMnA spring steel band to make, and the cross sectional dimensions of scroll spring is 9mm × 0.8mm, and number of active coils is 6 circles, and maximum output torque is 4Nm, and minimum Driving Torque is 0.1Nm.
Preferably, angular position pick up adopts resistance-type angular position measurement sensor, and weight is no more than 100g, and total mechanical travel is 360 °.
The course of work of the present invention and principle as follows: when the second output shaft is relative to a first output shaft rotation angle, scroll spring and angular position pick up projecting shaft all rotate identical angle, and the angle θ measured according to angular position pick up and wind spring stiffness K can calculate the torque T=K θ between the second output shaft and the first output shaft.
The present invention is realizing, on the basis that space product power or moment accurately measures, alleviating product weight, improve the scope of application of product, thus improve the reliability of product, reach the effect improving spacecraft performance.Compared with prior art, the present invention has following beneficial effect: the plane scroll spring that spacecraft force exertion measurement mechanism of the present invention uses spiral of Archimedes to turn to is as flexible member, measured the rotational angle of wind spring inner ring under the effect of extraneous input torque by angular position pick up, and calculate extraneous moment thus.Compared with prior art, the invention solves problem segment space aircraft needing accurate power and torgue measurement, this device also has that quality is light, initial torque is adjustable, volume is little and the compatible feature such as good simultaneously, effectively ensure that the accuracy that power is measured and reliability, have broad application prospects.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the structural representation of spacecraft force exertion measurement mechanism of the present invention;
Fig. 2 is the annexation schematic diagram of low protection cover and angular position pick up and scroll spring;
In figure: 1 is upper protective cover, 2 is angular position pick up, and 3 is the second output shaft, and 4 is scroll spring, and 5 is deep groove ball bearing, and 6 is end cap, and 7 is low protection cover, and 8 is pogo barrel, and 9 is hex screw, and 10 is positive stop lug boss, and 11 is the first output shaft.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
Please refer to Fig. 1 and Fig. 2, a kind of spacecraft force exertion measurement mechanism, comprise: upper protective cover 1, first output shaft 11, angular position pick up 2, second output shaft 3, scroll spring 4, deep groove ball bearing 5, end cap 6 and low protection cover 7, upper protective cover 1 is connected with low protection cover 7, and end cap 6 is connected with low protection cover 7; First output shaft 11 is connected with upper protective cover 1, angular position pick up 2 is connected with the first output shaft 11 and low protection cover 7 respectively, one end of second output shaft 3 is connected the other end through end cap 6 with the first output shaft 11, deep groove ball bearing 5 cover to be connected to outside the second output shaft 3 and to be connected with end cap 6, and scroll spring 4 cover is connected to outside the second output shaft 3 and is connected with low protection cover 7.
The flexible member of this device and scroll spring 4 adopt the wind spring of spiral of Archimedes coiling.Plane scroll spring carries out its dimensional parameters according to machinery industry relevant criterion and selects and performance calculating, its Material selec-tion is 55CrMnA spring steel band, obtain the design data of wind spring: cross sectional dimensions is 9mm × 0.8mm, number of active coils is 6 circles, maximum output torque is 4Nm, and minimum Driving Torque is 0.1Nm.The inner ring of wind spring is connected with the second output shaft 3, can by the second output shaft 3 with rotation, and outer ring is fixed on low protection cover 7.
Angular position pick up 2 is selected and be can be applicable to space environment resistance-type angular position measurement sensor, and its weight is no more than 100g, and total mechanical trip is 360 °, the requirement that insulation resistance and the equal meeting spatial aircraft of proof voltage value use.
Low protection cover 7 is installed for angular position pick up 2 and end cap 6 and is provided interface, fixedly provides interface for scroll spring 4 outer ring, and scroll spring 4 outer ring is positioned by pogo barrel 8, and hex screw 9 is through pogo barrel 8, and end screws in the screw of low protection cover 7.Low protection cover 7 is processed with a positive stop lug boss 10 simultaneously, can carry out unidirectional spacing to the second output shaft 3, make the second output shaft 3 can not drive scroll spring 4 counter-rotation at initial position.
End cap 6 provides encapsulation to the second output shaft 3 side, and it is installed deep groove ball bearing 5 and support the second output shaft 3, the two ends circlip of bearing carries out spacing.Upper protective cover 1 also has encapsulation effect, and is made of one with the first output shaft 11.Upper protective cover 1 is processed with square opening to stretch out for the signal wire of angular position pick up 2 and supply lines.
Design philosophy of the present invention and the course of work and principle are: when the second output shaft 3 rotates an angle relative to the first output shaft 11, scroll spring 4 and angular position pick up 2 projecting shaft all rotate identical angle, and the angle θ measured according to angular position pick up 2 and wind spring stiffness K can calculate the torque T=K θ between output shaft 2 and output shaft 1.
At present, this force measuring device has been applied to the Zeng Pin mechanism on certain spacecraft, and its function meets request for utilization, reaches design objective.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (6)
1. a spacecraft force exertion measurement mechanism, comprise: upper protective cover, the first output shaft, angular position pick up, the second output shaft, scroll spring, deep groove ball bearing, end cap, low protection cover, pogo barrel and screw, described upper protective cover is connected with low protection cover, and described end cap is connected with described low protection cover, described first output shaft is connected with described upper protective cover, described angular position pick up is connected with described first output shaft and low protection cover respectively, described second output shaft one end is connected the other end through described end cap with described first output shaft, described deep groove ball bearing cover to be connected to outside described second output shaft and to be connected with described end cap, described scroll spring cover is connected to outside described second output shaft and is connected with described low protection cover, it is characterized in that, pogo barrel is arranged between described scroll spring outer ring and low protection cover, described low protection cover is provided with threaded hole, described screw is connected with described screw hole through described spring spool, wherein, described scroll spring adopts spiral of Archimedes coiling to form, and described scroll spring adopts 55CrMnA spring steel band to make, the cross sectional dimensions of described scroll spring is 9mm × 0.8mm, number of active coils is 6 circles, and maximum output torque is 4Nm, and minimum Driving Torque is 0.1Nm, described angular position pick up adopts resistance-type angular position measurement sensor, and weight is no more than 100g, and total mechanical travel is 360 °.
2. spacecraft force exertion measurement mechanism according to claim 1, is characterized in that, described low protection cover is provided with in order to carry out unidirectional spacing positive stop lug boss to described second output shaft.
3. spacecraft force exertion measurement mechanism according to claim 1, is characterized in that, also comprise circlip, and described circlip is arranged between described deep groove ball bearing and end cap and carries out spacing to described deep groove ball bearing.
4. spacecraft force exertion measurement mechanism according to claim 1, is characterized in that, on described upper protective cover, the position corresponding with described angular position pick up is provided with square hole, draws with for the supply lines of described angular position pick up and signal wire.
5. spacecraft force exertion measurement mechanism according to claim 1, is characterized in that, described upper protective cover and described first output shaft are made into integration.
6. spacecraft force exertion measurement mechanism according to claim 1, is characterized in that, described screw is hex screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310153512.7A CN103278267B (en) | 2013-04-27 | 2013-04-27 | Spacecraft force exertion measurement mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310153512.7A CN103278267B (en) | 2013-04-27 | 2013-04-27 | Spacecraft force exertion measurement mechanism |
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| Publication Number | Publication Date |
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| CN103278267A CN103278267A (en) | 2013-09-04 |
| CN103278267B true CN103278267B (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310153512.7A Active CN103278267B (en) | 2013-04-27 | 2013-04-27 | Spacecraft force exertion measurement mechanism |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108204782B (en) * | 2017-12-08 | 2019-12-24 | 西安飞机工业（集团）有限责任公司 | Angle measurement and indicating device based on Archimedes spiral disk |
| CN111855438A (en) * | 2020-08-17 | 2020-10-30 | 资阳中车电气科技有限公司 | Testing device and testing method for volute spring |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2457594Y (en) * | 2000-12-21 | 2001-10-31 | 周伟 | Spring torque tester |
| CN201251449Y (en) * | 2008-07-25 | 2009-06-03 | 宁波市北仑机械电器有限公司 | Automatic reset angular transducer |
| CN201628597U (en) * | 2010-02-01 | 2010-11-10 | 神奇电碳集团有限公司 | Scroll spring force measuring device |
| CN202362594U (en) * | 2011-12-14 | 2012-08-01 | 轻工业钟表研究所 | Device for testing torque of clockwork spring |
-
2013
- 2013-04-27 CN CN201310153512.7A patent/CN103278267B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2457594Y (en) * | 2000-12-21 | 2001-10-31 | 周伟 | Spring torque tester |
| CN201251449Y (en) * | 2008-07-25 | 2009-06-03 | 宁波市北仑机械电器有限公司 | Automatic reset angular transducer |
| CN201628597U (en) * | 2010-02-01 | 2010-11-10 | 神奇电碳集团有限公司 | Scroll spring force measuring device |
| CN202362594U (en) * | 2011-12-14 | 2012-08-01 | 轻工业钟表研究所 | Device for testing torque of clockwork spring |
Non-Patent Citations (1)
| Title |
|---|
| 一种近似恒力弹簧装置的设计;郭洁等;《天津理工学院学报》;20000630;第16卷(第2期);第46-48页 * |
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| CN103278267A (en) | 2013-09-04 |
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