CN103245451B - For the rope tension monitoring device in-orbit of spacecraft - Google Patents
For the rope tension monitoring device in-orbit of spacecraft Download PDFInfo
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- CN103245451B CN103245451B CN201310147997.9A CN201310147997A CN103245451B CN 103245451 B CN103245451 B CN 103245451B CN 201310147997 A CN201310147997 A CN 201310147997A CN 103245451 B CN103245451 B CN 103245451B
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Abstract
The invention discloses a kind of rope tension for spacecraft monitoring device in-orbit, comprise angular position pick up, rack pinion assembly, microswitch, installing sleeve, Compress Spring, push rod and roll wheel assembly, rope rotates around roll wheel assembly, roll wheel assembly is compressed by push rod by Compress Spring, Compress Spring is arranged in installing sleeve, the first end of push rod slides in installing sleeve, the end of the second end of push rod is connected with roll wheel assembly, on rope, the change of tension force causes the translation motion of roll wheel assembly, described translation motion is converted into rotation by rack pinion assembly, the corner of angular position pick up prototype gear rack-driving assembly, microswitch carries out the triggering of limit signal.The tension force that the invention solves on spacecraft on rope part needs the problem of precise monitoring.This device also has that quality is light, debugging is simple, volume is little, security is high and the advantage such as low in energy consumption simultaneously, effectively ensure that the reliability that rope tension is monitored in-orbit and applicability.
Description
Technical field
The present invention relates to for spacecraft motion rope class mechanism technology field, specifically for the rope tension monitoring device in-orbit of spacecraft.
Background technology
Along with the development of spacecraft technology, the motion rope base part application that spacecraft adopts is increasingly extensive, and the device with the requirement of precise monitoring rope tension also produces thereupon.General common commercial force snesor mainly contains following problem both at home and abroad: 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;
These problems limit rope and open monitoring technology in spaceborne uses such as spacecrafts, even also limit correlated activation parts and use on spacecraft.Along with the light-weighted development trend of spacecraft, require that the weight of each load on spacecraft is more and more less, therefore, its weight of mode and the resource of the use of general force measuring technique are all larger.
Summary of the invention
The present invention is directed to above shortcomings in prior art, provide a kind of rope tension for spacecraft monitoring device in-orbit.
The present invention is achieved by the following technical solutions.
A kind of rope tension for spacecraft monitoring device in-orbit, comprise angular position pick up, rack pinion assembly, microswitch, installing sleeve, Compress Spring, push rod and roll wheel assembly, wherein, rope rotates around roll wheel assembly, roll wheel assembly is compressed by push rod by Compress Spring, Compress Spring is arranged in installing sleeve, the first end of push rod slides in installing sleeve, the end of the second end of push rod is connected with roll wheel assembly, on rope, the change of tension force causes the translation motion of roll wheel assembly, described translation motion is converted into rotation by rack pinion assembly, the corner of angular position pick up prototype gear rack-driving assembly, microswitch carries out the triggering of limit signal.
Described roll wheel assembly comprises rolling wheel support, roller, bearing, sleeve and quill, and wherein, bearing is arranged in quill, and sleeve is arranged on the two ends of bearing respectively, and roller is arranged on bearing, and rolling wheel support is arranged on the top of roller; The end of the second end of described push rod is connected with roller through after rolling wheel support, and rope is around on roller.
The winding portion of described roller is provided with coiling grain.
Described installing sleeve is that Compress Spring proposes storage and for activity space, the bottom of installing sleeve has hole push rod to guide effect.
Described roll wheel assembly comprises rolling wheel support, and the first end of described push rod is socket cap, and the second end of described push rod is square bar, and wherein socket cap can slide in installing sleeve, and the hole that square bar partially passes through bottom installing sleeve is connected with rolling wheel support.The profile of square bar can the rotation of pair roller support be carried out spacing, guarantees that rolling wheel support can not around installing sleeve axial-movement.
Described roll wheel assembly comprises rolling wheel support, described rack pinion assembly comprises pitch wheel and tooth bar, the right side that described gear is arranged on rolling wheel support is stretched out on platform, the output shaft of described angular position pick up is through the axle center of gear, and mounting hole platform is processed with for adjusting tooth bar installation site is stretched out on described right side.
Rolling wheel support provides mounting interface for roll wheel assembly, is had an effect by push rod and Compress Spring in its top.Rolling wheel support is initially located at lower limit position (its lower surface contacts with low protection cover), the upper extreme position of rolling wheel support is the position that its upper surface contacts with the lower surface of installing sleeve, along with the change of rope upper pulling force, namely rolling wheel support moves up and down at these two extreme positions.
Described angular position pick up is resistance-type angular position measurement sensor, and the total mechanical travel of resistance-type angular position measurement sensor is 360 °.
The above-mentioned rope tension for spacecraft monitoring device in-orbit, also comprise and be encapsulated in angular position pick up, rack pinion assembly, microswitch, installing sleeve, Compress Spring, the low protection cover of push rod and roll wheel assembly outside and upper protective cover, described low protection cover is provided with mounting interface.
Described microswitch passes through microswitch support installing on the sidewall of low protection cover.
The present invention angularly considers from product applicability, thermal adaptability, product weight and connection use-pattern, and provide a kind of rope tension for spacecraft monitoring device in-orbit, this device has following beneficial effect:
First, the present invention takes into full account the installation in-orbit of spacecraft and rope and environment for use requirement in the design process, by design, make tension force in-orbit monitoring device have rope Accurate tension measure and monitor, restraining position monitoring function, make this invention meet spacecraft rope tension monitoring request for utilization.
Secondly, the present invention has taken into full account the factors such as processing installation in the design process, makes whole mechanism have interface simple, lighter weight, the features such as extensibility is strong, only need modify to associated components, what just can meet different spacecraft installs and uses requirement, has higher versatility.
In sum, rope tension for spacecraft provided by the invention monitoring device in-orbit, it increases frequently in-orbit, and mechanism principle is correct, have the function that rope Accurate tension is measured and supervision, restraining position are monitored, it is simple that whole mechanism has interface, lighter weight, the features such as extensibility is strong, what can meet different spacecraft installs and uses requirement, has higher versatility, has a extensive future.
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 rope tension for spacecraft provided by the invention monitoring device structural representation in-orbit;
Fig. 2 is tension assembly structural representation of the present invention;
Fig. 3 is upper protective roof structure schematic diagram of the present invention;
In figure: 1 is low protection cover, 2 is angular position pick up, and 3 is rack pinion assembly, and 4 is rope, and 5 is microswitch, 6 is installing sleeve, and 7 is Compress Spring, and 8 is push rod, and 9 is rolling wheel support, and 10 is roller, 11 is bearing, and 12 is microswitch support, and 13 is upper protective cover, and 14 is tension assembly.
Embodiment
Below embodiments of the invention are elaborated: the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and change and spout, these all belong to protection scope of the present invention.
As shown in Figure 1, present embodiments provide a kind of rope tension for spacecraft monitoring device in-orbit, comprise angular position pick up, rack pinion assembly, microswitch, installing sleeve, Compress Spring, push rod and roll wheel assembly, wherein, rope rotates around roll wheel assembly, roll wheel assembly is compressed by push rod by Compress Spring, Compress Spring is arranged in installing sleeve, the first end of push rod slides in installing sleeve, the end of the second end of push rod is connected with roll wheel assembly, on rope, the change of tension force causes the translation motion of roll wheel assembly, described translation motion is converted into rotation by rack pinion assembly, the corner of angular position pick up prototype gear rack-driving assembly, microswitch carries out the triggering of limit signal.Describedly be arranged on the tension assembly that Compress Spring in installing sleeve, push rod and roll wheel assembly constitute the present embodiment.
Further, described roll wheel assembly comprises rolling wheel support, roller, bearing, sleeve and quill, and wherein, bearing is arranged in quill, and sleeve is arranged on the two ends of bearing respectively, and roller is arranged on bearing, and rolling wheel support is arranged on the top of roller; The end of the second end of described push rod is connected with roller through after rolling wheel support, and rope is around on roller.Sleeve ensures that the location of installation and roller reliably rotate, and the diameter of roller and width dimensions can according to the concrete rope situation adjustment that will monitor.
Further, the winding portion of described roller is provided with winding slot.
Further, described installing sleeve is that Compress Spring proposes storage and for activity space, the bottom of installing sleeve has hole push rod to guide effect.Have certain decrement when Compress Spring is initially installed, the system of guarantee has certain pretension, there will not be the phenomenon of swing.
Further, the first end of described push rod is socket cap, and the second end of described push rod is square bar, and wherein socket cap can slide in installing sleeve, and the hole that square bar partially passes through bottom installing sleeve is connected with rolling wheel support.The profile of square bar can the rotation of pair roller support be carried out spacing, guarantees that rolling wheel support can not around installing sleeve axial-movement.
Further, described roll wheel assembly comprises rolling wheel support, described rack pinion assembly comprises pitch wheel and cutter bar, the right side that described cutter wheel is arranged on rolling wheel support is stretched out on platform, the output shaft of described angular position pick up is through the axle center of gear, and mounting hole platform is processed with for adjusting tooth bar installation site is stretched out on described right side.
Rolling wheel support provides mounting interface for roll wheel assembly, is had an effect by push rod and Compress Spring in its top.Rolling wheel support is initially located at lower limit position (its lower surface contacts with low protection cover), the upper extreme position of rolling wheel support is the position that its upper surface contacts with the lower surface of installing sleeve, along with the change of rope upper pulling force, namely rolling wheel support moves up and down at these two extreme positions.
Further, described angular position pick up is resistance-type angular position measurement sensor, and its total mechanical travel is 360 °.Resistance-type angular position measurement sensor, its lighter in weight, insulation resistance and proof voltage value all meet the requirement that spacecraft uses.
Further, the above-mentioned rope tension for spacecraft monitoring device in-orbit, also comprise and be encapsulated in angular position pick up, rack pinion assembly, microswitch, installing sleeve, Compress Spring, the low protection cover of push rod and roll wheel assembly outside and upper protective cover, described low protection cover is provided with mounting interface.
Further, described microswitch passes through microswitch support installing on the sidewall of low protection cover.The upper extreme position of microswitch pair roller support is monitored, and after arriving top by rolling wheel support, the left side of rolling wheel support is stretched out platform and triggered microswitch.The installation site of microswitch support and low protection cover is processed with mounting hole and adjusts for installation site.
In the present embodiment, installing sleeve, rolling wheel support, upper protective cover, low protection cover all adopt 2Al4T6 to process, and its size is determined primarily of the size envelope of rope and drive disk assembly;
The rope tension for spacecraft that the present embodiment provides monitoring device in-orbit; installed by bracing frame and spacecraft body; it has the unthreaded hole of 4 Φ 6.5, be connected with screw pre-buried on spacecraft body by the screw of 4 M6, concrete installation site can according to circumstances adjust;
First push rod is installed into installing sleeve during assembling, Compress Spring reinstalls, and first roller and bearing also will assemble, then it are connected with push rod;
The winding portion of roller is processed with the coiling grain of 2mm width, and middle ring is connected with the outer ring of bearing.
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 (9)
1. the rope tension for spacecraft monitoring device in-orbit, comprise installing sleeve, Compress Spring, push rod and roll wheel assembly, rope rotates around roll wheel assembly, roll wheel assembly is compressed by push rod by Compress Spring, Compress Spring is arranged in installing sleeve, the first end of push rod slides in installing sleeve, and the end of the second end of push rod is connected with roll wheel assembly, and on rope, the change of tension force causes the translation motion of roll wheel assembly; It is characterized in that, also comprise angular position pick up, rack pinion assembly and microswitch, described translation motion is converted into rotation by rack pinion assembly, the corner of angular position pick up prototype gear rack-driving assembly, and microswitch carries out the triggering of limit signal;
Also comprise and be encapsulated in angular position pick up, rack pinion assembly, microswitch, installing sleeve, Compress Spring, the low protection cover of push rod and roll wheel assembly outside and upper protective cover, described low protection cover is provided with mounting interface;
Described roll wheel assembly comprises rolling wheel support, and described rolling wheel support provides mounting interface for roll wheel assembly, is had an effect by push rod and Compress Spring in the top of rolling wheel support; Rolling wheel support is initially located at lower limit position, described lower limit position is the position that rolling wheel support lower surface contacts with low protection cover, the upper extreme position of rolling wheel support is the position that rolling wheel support upper surface contacts with installing sleeve lower surface, along with the change of rope upper pulling force, namely rolling wheel support moves up and down between lower limit position and upper extreme position.
2. the rope tension for spacecraft according to claim 1 monitoring device in-orbit, it is characterized in that, described roll wheel assembly also comprises roller, bearing, sleeve and quill, wherein, bearing is arranged in quill, sleeve is arranged on the two ends of bearing respectively, and roller is arranged on bearing, and rolling wheel support is arranged on the top of roller; The end of the second end of described push rod is connected with roller through after rolling wheel support, and rope is around on roller.
3. the rope tension for spacecraft according to claim 2 monitoring device in-orbit, it is characterized in that, the winding portion of described roller is provided with winding slot; Ring in the middle of roller is connected with the outer ring of bearing.
4. the rope tension for spacecraft according to claim 1 monitoring device in-orbit, is characterized in that, described installing sleeve is that Compress Spring proposes storage and for activity space, the bottom of installing sleeve has hole push rod to guide effect.
5. the rope tension for spacecraft according to claim 1 monitoring device in-orbit, it is characterized in that, the first end of described push rod is socket cap, second end of described push rod is square bar, wherein socket cap slides in installing sleeve, and the hole that square bar partially passes through bottom installing sleeve is connected with rolling wheel support.
6. the rope tension for spacecraft according to claim 1 monitoring device in-orbit, it is characterized in that, described rack pinion assembly comprises pitch wheel and tooth bar, the right side that described gear is arranged on rolling wheel support is stretched out on platform, the output shaft of described angular position pick up is through the axle center of gear, and mounting hole platform is processed with for adjusting tooth bar installation site is stretched out on described right side.
7. the rope tension for spacecraft according to claim 1 monitoring device in-orbit, is characterized in that, described angular position pick up is resistance-type angular position measurement sensor, and the total mechanical travel of resistance-type angular position measurement sensor is 360 °.
8. the rope tension for spacecraft according to claim 1 monitoring device in-orbit, is characterized in that, described microswitch passes through microswitch support installing on the sidewall of low protection cover.
9. the rope tension for spacecraft according to claim 8 monitoring device in-orbit, is characterized in that, the installation site of microswitch support and low protection cover is provided with the mounting hole adjusted for installation site.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310147997.9A CN103245451B (en) | 2013-04-25 | 2013-04-25 | For the rope tension monitoring device in-orbit of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310147997.9A CN103245451B (en) | 2013-04-25 | 2013-04-25 | For the rope tension monitoring device in-orbit of spacecraft |
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| Publication Number | Publication Date |
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| CN103245451A CN103245451A (en) | 2013-08-14 |
| CN103245451B true CN103245451B (en) | 2015-11-18 |
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| CN201310147997.9A Active CN103245451B (en) | 2013-04-25 | 2013-04-25 | For the rope tension monitoring device in-orbit of spacecraft |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644996B (en) * | 2013-12-10 | 2015-12-02 | 上海大众汽车有限公司 | The measurement mechanism of roller switch and method |
| CN105588677B (en) * | 2014-11-14 | 2018-06-05 | 北京弗圣威尔科技有限公司 | The relaxation of detection line and the mechanism of tension |
| CN105865698B (en) * | 2016-06-17 | 2023-08-25 | 浙江工业职业技术学院 | Silk thread tension measuring device |
| CN109159926A (en) * | 2018-06-14 | 2019-01-08 | 上海卫星工程研究所 | A kind of rope tension precision adjustment unit applied to spacecraft |
| CN108444631A (en) * | 2018-07-05 | 2018-08-24 | 陈俊胤 | A kind of real-time stretching force detecting apparatus of unmanned plane and its pull force calculation method |
| CN113167667B (en) * | 2018-12-13 | 2023-04-18 | 三菱电机株式会社 | Traction detection device and mobile body system provided with same |
| CN109724739B (en) * | 2019-01-24 | 2020-12-04 | 中国人民解放军国防科技大学 | Rope buffer force testing device and measuring method |
| CN110987270A (en) * | 2019-11-01 | 2020-04-10 | 成都云铁智能交通科技有限公司 | Contact net tension sensor device |
| CN111747224A (en) * | 2020-07-21 | 2020-10-09 | 哈尔滨工业大学 | Self-adaptive rope tension adjusting system and method |
| CN113176027B (en) * | 2021-03-26 | 2022-06-24 | 上海卫星工程研究所 | Spring tube torque measuring device and test method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87211269U (en) * | 1987-10-06 | 1988-09-14 | 中国矿业学院 | Steel-wire rope tension tester |
| EP0573831A1 (en) * | 1992-06-11 | 1993-12-15 | Paul Vahle GmbH & Co. KG | Measuring device for indicating the loading limit of ropes and the like |
| CN2369236Y (en) * | 1999-03-01 | 2000-03-15 | 王兆威 | Directly connecting tension sensor |
| CN201955181U (en) * | 2010-12-06 | 2011-08-31 | 西安金和光学科技有限公司 | Optical fiber type high-accuracy tension detecting device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08278215A (en) * | 1995-03-31 | 1996-10-22 | Yaskawa Electric Corp | Automatic tension monitor of overhead wire |
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2013
- 2013-04-25 CN CN201310147997.9A patent/CN103245451B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87211269U (en) * | 1987-10-06 | 1988-09-14 | 中国矿业学院 | Steel-wire rope tension tester |
| EP0573831A1 (en) * | 1992-06-11 | 1993-12-15 | Paul Vahle GmbH & Co. KG | Measuring device for indicating the loading limit of ropes and the like |
| CN2369236Y (en) * | 1999-03-01 | 2000-03-15 | 王兆威 | Directly connecting tension sensor |
| CN201955181U (en) * | 2010-12-06 | 2011-08-31 | 西安金和光学科技有限公司 | Optical fiber type high-accuracy tension detecting device |
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| CN103245451A (en) | 2013-08-14 |
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