CN109827689A - Measuring device is loaded for spaceborne radar antenna pressing force - Google Patents
Measuring device is loaded for spaceborne radar antenna pressing force Download PDFInfo
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- CN109827689A CN109827689A CN201910115075.7A CN201910115075A CN109827689A CN 109827689 A CN109827689 A CN 109827689A CN 201910115075 A CN201910115075 A CN 201910115075A CN 109827689 A CN109827689 A CN 109827689A
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- pressing force
- measuring device
- tapered sleeve
- load
- radar antenna
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Abstract
The present invention relates to measuring device is loaded for spaceborne radar antenna pressing force in a kind of satellite antenna accessories field, the pressing force load measuring device includes to compress tapered sleeve combination, expanded truss and axial force sensor；Axial force sensor is connected respectively to the compression tapered sleeve and combines, on the expanded truss；The compression tapered sleeve combination axially extends wherein one end in the both ends in direction and forms attachment part, is provided with jack hole on the expanded truss, the attachment part is encased in jack hole；Loading device is provided on the expanded truss, the loading device, the axial force sensor, attachment part are sequentially connected.The present apparatus pressing force load in place and lock after it is removable unload down, especially suitable for the limit-type pressing system of Large Deployable rigid antenna plate pressing force load measuring device.
Description
Technical field
The present invention relates to satellite antenna accessories fields, and in particular, to one kind is loaded for spaceborne radar antenna pressing force
Measuring device.
Background technique
Traditional plate aerial clamping plan vertically penetrates antenna array using a metal compaction bar, when antenna is in
When rounding state, by the pretightning force formulated is applied to compressor arm, by edge between antenna plate perpendicular to plate face normal orientation freedom degree
Constraint；By each antenna plate and compress support base on compression inner room male and female cooperation cross spacing effect or plane it
Between WC great friction coefficient coating generate frictional force, two freedom degrees in each antennas orthogonal compressor arm direction are used restraint,
To which the antenna of rounding state is pressed in spacecraft main structure side, meet envelope requirement and rigidity requirement.Spacecraft is entered the orbit
Afterwards, it compresses relieving mechanism and receives unlock instruction, cutter work cuts off all compressor arms, releases the constraint to antenna plate, make it
Can smoothly it be unfolded.
On the one hand the radar antenna plate big for rounding state span navigates if continuing to use conventional metals continuous lever+tapered sleeve scheme
The unbearable excessive mechanical loading of its device structure, metal continuous lever can not detach when another aspect antenna is unfolded, and cause to be unfolded
Failure.Therefore, limit-type discontinuous compression release embodiments to be studied.The load measurement of pressing force is entire compresses in release embodiments
Key, the prior art shortage can be to the device that pressing force is accurately measured.
Through the retrieval to the prior art, Chinese invention patent CN201710877190.9, a kind of entitled spaceborne exhibition
Kaitian's line pressing device comprising antenna installation stent component, pressed seat, compressor arm；The side of antenna installation stent component is logical
It crosses compressor arm to fix with pressed seat, firer's cutter is located at the side of pressed seat；The other side of antenna installation stent component
It is fixed with an antenna expanding unit.The present invention provides a high rigidity pressing device for columnar antenna；What the present invention needed
Powering, number is minimum and light-weight, high reliablity.But the limit-type pressing system of Large Deployable rigid antenna plate is not suitable for it
Pressing force loads measuring device.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of pressing forces to load measuring device.The present invention
Measurement result repeatability preferably, directly can characterize the pressing force on whole string tapered sleeve with the axial force sensor on head, and structure is simple,
Measurement is convenient, and axial force sensor is located at the outside of expanded truss, locks axle power by head locking nut, realizes axle power sensing
The unloading of device avoids damaging due to mechanical loading of the axial force sensor when bearing Spacecraft Launch, while axial force sensor passes through
Rotation stop part limits circumferential rotation, works relatively reliable.
The present invention relates to a kind of pressing forces to load measuring device, comprising compressing tapered sleeve combination 6, expanded truss 2 and axle power
Sensor 47；Axial force sensor 47 is connected respectively to the compression tapered sleeve and combines on the 6, expanded truss 2；
Wherein one end that the compression tapered sleeve combination 6 axially extends in the both ends in direction forms attachment part, the expansion
Jack hole is provided on truss 2, the attachment part is encased in jack hole；It is provided with loading device 4 on the expanded truss 2,
The loading device 4, the axial force sensor 47, attachment part are sequentially connected.
Preferably, the loading device 4 includes loaded seat 44 and load screw 41；The fastening of loaded seat 44 installation
On the expanded truss 2, the load screw 41 is axially adjustable to be mounted in the loaded seat 44.
Preferably, the load screw 41 is connected directly or is indirectly connected with the axial force sensor 47.
Preferably, the loading device 4 also includes rotation stop body 46 and bearing 45, is provided in the loaded seat 44 tolerant
Slot, the rotation stop body 46 are mounted in tolerant slot；
Preferably, the axial force sensor 47, the rotation stop body 46, the bearing 45, the load screw 41 successively phase
Even.
Preferably, pilot hole is provided in the load screw 41, the guide part that the rotation stop body 46 includes, which is extend into, leads
Xiang Kongzhong；The rotation stop body 46 is provided on two end faces opposite with attachment part for installing the axial force sensor 47
Axle power mounting hole.
Preferably, the load screw 41 is located in tolerant slot, outside tolerant slot along axial both ends, the load spiral shell
The part that nail 41 is located at outside tolerant slot is equipped with one or more stop nuts.
Preferably, the compression tapered sleeve combination 6 includes multiple sequentially connected tapered sleeves, includes head in multiple tapered sleeves
Portion's tapered sleeve 65, head tapered sleeve 65 form the attachment part.
Preferably, the head tapered sleeve 65 is equipped with the head locking nut 66；
The head locking nut 66, the loaded seat 44 are located at along the 2 thickness extending direction of expanded truss
Both ends.
Preferably, the head tapered sleeve 65 is stairstepping.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, measurement result repeatability of the present invention preferably, can be characterized directly on whole string tapered sleeve with the axial force sensor on head
Pressing force, structure is simple, and measurement is convenient；
2, the outside that axial force sensor is located at expanded truss in the present invention is realized by head locking nut locking axle power
The unloading of axial force sensor avoids damaging due to mechanical loading of the axial force sensor when bearing Spacecraft Launch；
3, axial force sensor limits circumferential rotation by rotation stop part, works relatively reliable.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is that pressing force loads measuring device structural schematic diagram.
In figure, corresponding appended drawing reference are as follows: 2- expanded truss, 4- loading device, 41- load screw, the locking spiral shell of 42- first
Mother, the second stop nut of 43-, 44- loaded seat, 45- bearing, 46- rotation stop body, 47- axial force sensor, 6- compress tapered sleeve group
It closes, the head 65- tapered sleeve, the head 66- locking nut.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
Embodiment
When designing pressing force load measuring device, foil gauge, torque wrench and axial force sensor three are considered at the beginning
Kind pressing force characterizing method.The method for using strain measurement first, takes a significant amount of time on the head, centre, tail of a string of tapered sleeves
Upper foil gauge is all pasted on portion's tapered sleeve, as a result, it has been found that differently strained measurement data difference is very big, repeatability is bad, strain and axis
The relationship of power can not be demarcated effectively, therefore give up the program.Then used torque spanner, it is intended to by the torque of load screw come
Pressing force is characterized, as a result, it has been found that the relationship between torque and pressing force is unstable, does not have repeatability, is characterized and compressed using torque
The confidence level of power is equally also poor, therefore gives up the program.Final decision is compressing tapered sleeve internal series-connection axial force sensor, is read with it
Number directly reflects the size of pressing force.
As shown in Figure 1, pressing force provided by the invention loads measuring device, 6, expanded truss 2 are combined comprising compressing tapered sleeve
And axial force sensor 47；Axial force sensor 47 is connected respectively to compression tapered sleeve and combines on 6, expanded truss 2；Compress tapered sleeve combination
6 wherein one end for axially extending in the both ends in direction form attachment part, are provided with jack hole on the expanded truss 2, described
Attachment part is encased in jack hole；Loading device 4, loading device 4, axial force sensor 47, dress are provided on the expanded truss 2
Socket part is sequentially connected.
The loading device 4 includes loaded seat 44 and load screw 41；Loaded seat 44 is securedly mounted to expanded truss 2
On, load screw 41 is axially adjustable to be mounted in loaded seat 44, load screw 41 and axial force sensor 47 be connected directly or
Connect connected, the axially adjustable corresponding structure can be screw thread, be also possible to axial gear adjusting structure etc..Embodiment
In, the loading device 4 also includes rotation stop body 46 and bearing 45, is provided with tolerant slot, rotation stop body 46 in the loaded seat 44
It is mounted in tolerant slot；Axial force sensor 47, rotation stop body 46, bearing 45, load screw 41 are sequentially connected.The load screw 41
On be provided with pilot hole, the guide part that the rotation stop body 46 includes is extend into pilot hole.Rotation stop body 46 is opposite with attachment part
The axle power mounting hole for installing axial force sensor 47 is provided on two end faces.Preferably, the load screw 41 is along axis
To both ends be located in tolerant slot, outside tolerant slot, the part that load screw 41 is located at outside tolerant slot is equipped with one or more
A stop nut.
The compression tapered sleeve combination 6 includes multiple sequentially connected tapered sleeves, forms discrete machine by the series connection of tapered sleeve
Tool structure, antenna plate are just mounted on the tapered sleeve.It include head tapered sleeve 65, the formation of head tapered sleeve 65 in multiple tapered sleeves
The attachment part.The head tapered sleeve 65 is equipped with head locking nut 66；Head locking nut 66, loaded seat 44 are respectively
With along the both ends of 2 thickness extending direction of expanded truss.In a preferred embodiment, adjustable loading device 4 senses axle power
After pressing force to setting value on device 47, head locking nut 66 is tightened, i.e., detachable loading device 4 and axial force sensor 47；
It is of course also possible to not dismantle loading device 4 and axial force sensor 47 according to actual needs.Preferably, the head tapered sleeve 65 is
Stairstepping.
The working principle of the invention: cannot bear mechanical loading when Spacecraft Launch because of axial force sensor 47, therefore cannot
It is connected in series between antenna plate between tapered sleeve, tapered sleeve array head end (outside of expanded truss 2) can only be connected in series to, when pressing force applies
After the completion, axle power is locked by head locking nut 66, realizes the unloading of axial force sensor 47.Based on the above method, through excessive
After secondary repeated load test, discovery 47 measurement result of axial force sensor repeatability preferably, directly uses the axial force sensor 47 on head
The pressing force on whole string tapered sleeve is characterized, is a kind of more satisfactory compression force measuring method.
In conclusion measurement result repeatability of the present invention is preferably, whole string directly can be characterized with the axial force sensor on head
Pressing force on tapered sleeve, structure is simple, and measurement is convenient, and axial force sensor is located at the outside of expanded truss, is locked by head
Nut locking axle power realizes the unloading of axial force sensor, avoids axial force sensor because bearing mechanical loading when Spacecraft Launch
And damage, while axial force sensor limits circumferential rotation by rotation stop part, it works relatively reliable.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. one kind for spaceborne radar antenna pressing force load measuring device, which is characterized in that including compress tapered sleeve combination (6),
Expanded truss (2) and axial force sensor (47)；Axial force sensor (47) is connected respectively to the compression tapered sleeve combination (6), institute
It states on expanded truss (2)；
The compression tapered sleeve combination (6) axially extends wherein one end in the both ends in direction and forms attachment part, the expansion purlin
Jack hole is provided on frame (2), the attachment part is encased in jack hole；
It is provided with loading device (4) on the expanded truss (2), the loading device (4), the axial force sensor (47), dress
Socket part is sequentially connected.
2. according to claim 1 load measuring device for spaceborne radar antenna pressing force, characterized in that the load
Device (4) includes loaded seat (44) and load screw (41)；
The loaded seat (44) is securedly mounted on the expanded truss (2), the axially adjustable installation of the load screw (41)
On the loaded seat (44).
3. according to claim 2 load measuring device for spaceborne radar antenna pressing force, characterized in that the load
Screw (41) is connected directly or is indirectly connected with the axial force sensor (47).
4. according to claim 3 load measuring device for spaceborne radar antenna pressing force, characterized in that the load
Device (4) also includes rotation stop body (46) and bearing (45), is provided with tolerant slot, the rotation stop body on the loaded seat (44)
(46) it is mounted in tolerant slot.
5. according to claim 4 load measuring device for spaceborne radar antenna pressing force, characterized in that the axle power
Sensor (47), the rotation stop body (46), the bearing (45), the load screw (41) are sequentially connected.
6. according to claim 4 load measuring device for spaceborne radar antenna pressing force, characterized in that the load
Pilot hole is provided on screw (41), the guide part that the rotation stop body (46) includes is extend into pilot hole；
The rotation stop body (46) is provided on two end faces opposite with attachment part for installing the axial force sensor (47)
Axle power mounting hole.
7. according to claim 4 load measuring device for spaceborne radar antenna pressing force, characterized in that the load
Screw (41) is located in tolerant slot, outside tolerant slot along axial both ends, and the load screw (41) is located at outside tolerant slot
Part is equipped with one or more stop nuts.
8. according to claim 2 load measuring device for spaceborne radar antenna pressing force, characterized in that the compression
It includes multiple sequentially connected tapered sleeves that tapered sleeve, which combines (6), includes head tapered sleeve (65), head tapered sleeve in multiple tapered sleeves
(65) attachment part is formed.
9. according to claim 8 load measuring device for spaceborne radar antenna pressing force, characterized in that the head
Tapered sleeve (65) is equipped with the head locking nut (66)；The head locking nut (66), the loaded seat (44) are respectively
Positioned at the both ends along the expanded truss (2) thickness extending direction.
10. according to claim 8 load measuring device for spaceborne radar antenna pressing force, characterized in that the head
Portion's tapered sleeve (65) is stairstepping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910115075.7A CN109827689B (en) | 2019-02-14 | 2019-02-14 | Be used for satellite-borne radar antenna packing force loading measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910115075.7A CN109827689B (en) | 2019-02-14 | 2019-02-14 | Be used for satellite-borne radar antenna packing force loading measuring device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109827689A true CN109827689A (en) | 2019-05-31 |
| CN109827689B CN109827689B (en) | 2020-12-11 |
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ID=66863725
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910115075.7A Active CN109827689B (en) | 2019-02-14 | 2019-02-14 | Be used for satellite-borne radar antenna packing force loading measuring device |
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| CN207701126U (en) * | 2017-12-29 | 2018-08-07 | 黑龙江兰德超声科技股份有限公司 | A kind of head harness with detection tension |
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| CN109827689B (en) | 2020-12-11 |
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