CN203100723U - Clamping pendulum-type micro-angle adjustment reflecting device - Google Patents
Clamping pendulum-type micro-angle adjustment reflecting device Download PDFInfo
- Publication number
- CN203100723U CN203100723U CN 201220729750 CN201220729750U CN203100723U CN 203100723 U CN203100723 U CN 203100723U CN 201220729750 CN201220729750 CN 201220729750 CN 201220729750 U CN201220729750 U CN 201220729750U CN 203100723 U CN203100723 U CN 203100723U
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- CN
- China
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- pendulum
- type micro
- angle adjustment
- missile
- angle
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Abstract
The utility model discloses a clamping pendulum-type micro-angle adjustment reflecting device, and relates to light reflecting angle measurement devices. According to the principle, a C-shaped clamp is fixed together with a missile wing profile through a screwing hand wheel; a soft material is additionally cushioned between the contact surfaces of the C-shaped clamp and missile wings, so that a missile wing profile paint layer achieves a protecting effect when the C-shaped clamp and the missile wing profile are tightly connected; a pendulum-type micro-angle adjustment reflector and the C-shaped clamp are connected and fastened through a rotary shaft screw; an optical reflector of the pendulum-type micro-angle adjustment reflecting device obtains an adjustable pitch angle within a two-dimensional plane through a rocker arm structure; and the clamping pendulum-type micro-angle adjustment reflecting device is mainly used for accurately guiding bomb folding missile wings by an extended range satellite, accurately calibrating a torsion angle error before assembly, and measuring a comprehensive angle error of left and right missile wings after assembly.
Description
Technical field
The utility model is suitable for and cooperates with transit, little angular error is accurately demarcated and the comprehensive angle error measure of assembling back to carrying out before the structural member assembling, be specially adapted to the folding missile wing of extended range model satellite precision-guided bomb of glide missile wing, the measurement of accurate demarcation of windup-degree error and the left and right sides, assembling back missile wing deployed condition comprehensive angle error before the assembling.
Background technology
In the development of extended range model satellite precision-guided bomb, to the proposition of assembling the back left and right sides missile wing deployed condition comprehensive angle error higher requirement, requirement comprises missile wing manufacturing torsion angle, every composition error sum≤0.25o, for satisfying test request, the integral type catoptron self has the fitting surface consistent with the missile wing curved surface, by mobile mirror on the airfoil camber fore-and-aft direction, reduction missile wing self is made the torsion angle error amount, carries out viscose glue by 502 Instant cements after moving into place and fixes.This catoptron have running fix difficulty, testing efficiency low, operator's technical ability is required high shortcoming, fixedly needs 502 Instant cements of catoptron and missile wing profile bonding is fixing simultaneously, the adhesion of glue to the enamelled coating of missile wing curved surface have destruction, surplus glue is difficult to reason, influences product quality.
The flexible pendulous little angular setting reflection unit of clamping, this device is bonding with C clamp or be threaded fastening, its integral type optical mirror is connected by flexible structure with mount pad, catoptron is regulated by the adjustment screw of mount pad both sides, produces the bidirectional swinging drift angle on relative structural symmetry plane.Its angular setting scope is less, and it is carefully careful that operation requires.
The utility model content
The utility model purpose provides the little angular setting reflection unit of a kind of clamping pendulum-type, to improve its operating accuracy.
The little angular setting reflection unit of a kind of clamping pendulum-type, it is characterized in that having a C clamp, the optical mirror of the little angular setting reflection unit of pendulum-type is connected by rocker structure with C clamp, and it is fixing that mirror deflection contacts with bearing, and C clamp is by screwing handwheel and the missile wing profile is fixed.
The utility model relates to a kind of smooth reflection angle measurement mechanism, its principle is: C clamp is by screwing handwheel and the missile wing profile is fixed, by at cushioning soft material between itself and the missile wing surface of contact, make to reach between C clamp and the missile wing profile to be fastenedly connected the effect that is protected with missile wing profile enamelled coating; It is fastening that the little angular setting catoptron of pendulum-type and C clamp are connected by shaft screw, and catoptron obtains the adjustable angle of pitch in the two dimensional surface by rocker structure; The little angular setting reflection unit of pendulum-type has the characteristics of delicate structure, efficient height, precision height, small investment, easy-maintaining, is mainly used in the measurement of accurate demarcation of the preceding windup-degree error of folding missile wing assembling of extended range model satellite precision-guided bomb and the left and right sides, assembling back missile wing comprehensive angle error.
Description of drawings
Fig. 1 is the front view of the little angular setting reflection unit of clamping pendulum-type;
Fig. 2 is the rear view of the little angular setting catoptron of pendulum-type;
Fig. 3 is the vertical view of the little angular setting catoptron of pendulum-type.
Embodiment
As Figure 1-3, the little angular setting reflection unit of a kind of clamping pendulum-type, it is characterized in that having a C clamp 2, the optical mirror 7 of the little angular setting reflection unit of pendulum-type is connected by rocker structure 6 with C clamp 2, catoptron 7 deflections contact fixing with bearing 3, C clamp 2 is fixed with the missile wing profile by screwing handwheel 1.Optical mirror 7 adds optical reflecting layer 8 on basal body of reflector, optical reflecting layer 8 is by installing, paste or being coated on the optical mirror matrix.Cushioning soft material between C clamp 2 and the missile wing surface of contact.
Principle of work: at first adjust the shaft screw 5 on the rocker structure 6, regulate the adjustment screw 4 of side again, catoptron 7 is produced around the bidirectional swinging drift angle that connects shaft screw 5; When device was in off working state, adjusting screw 4 can screw out, and catoptron 7 deflections is contacted with bearing 3 fix, and prevented catoptron 7 damages.Service mode can separate optical mirror 7 by removing shaft screw 5 with C clamp 2.
Optical mirror adds optical reflecting layer 8 on basal body of reflector, optical reflecting layer 8 is by installing, paste or being coated on the optical mirror matrix, be convenient to quick maintenance and replacing after catoptron damages, can be used for temperature difference and change little or less demanding test environment.
Enforcement of the present utility model, at first analytical test environment and designing requirement, in the design tolerance band, select the little angular setting reflection unit of the described clamping pendulum-type of claim, wherein the physical dimension of the little angular setting catoptron 7 of pendulum-type is determined with actual needs, this device adopts the alloy structure steel, and makes moulding through bakingout process, machining, accurate polishing processing and line cutting processing etc.; Because compact conformation helps the equipment miniaturization manufacturing.
To seek out bigger measurement of angle scope in the practical application, should suitably strengthen the width of line cutting groove shown in Figure 2 and adjust screw length, so that catoptron 7 obtains bigger space, rotation angle; Since adjust the torsion of screw limited, simultaneously for preventing that rocking arm from crossing pine and introducing measuring error, the pretightning force that should adjust shaft screw 5 before test makes the little distortion of C type support, increases or reduces catoptron 7 and C type and press from both sides friction force between 2; Screw is adjustable to adjust for the size of pretightning force, the not loosening degree of being of catoptron; Adjust the use of screw and should eliminate the gap,, should return again and regulate in case adjust outrange.
Claims (3)
1. little angular setting reflection unit of clamping pendulum-type, it is characterized in that having a C clamp (2), the optical mirror (7) of the little angular setting reflection unit of pendulum-type is connected by rocker structure (6) with C clamp (2), catoptron (7) deflection contacts fixing with bearing (3), C clamp (2) is fixed with the missile wing profile by screwing handwheel (1).
2. the little angular setting reflection unit of a kind of clamping pendulum-type according to claim 1, it is characterized in that optical mirror (7) adds optical reflecting layer (8) on basal body of reflector, optical reflecting layer (8) is by installing, paste or being coated on the optical mirror matrix.
3. the little angular setting reflection unit of a kind of clamping pendulum-type according to claim 1 is characterized in that cushioning soft material between C clamp (2) and the missile wing surface of contact.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220729750 CN203100723U (en) | 2012-12-26 | 2012-12-26 | Clamping pendulum-type micro-angle adjustment reflecting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220729750 CN203100723U (en) | 2012-12-26 | 2012-12-26 | Clamping pendulum-type micro-angle adjustment reflecting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203100723U true CN203100723U (en) | 2013-07-31 |
Family
ID=48852117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220729750 Expired - Lifetime CN203100723U (en) | 2012-12-26 | 2012-12-26 | Clamping pendulum-type micro-angle adjustment reflecting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203100723U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108466197A (en) * | 2018-03-28 | 2018-08-31 | 湖南大学 | A kind of fixture can adjust spatial position for fixing various sizes of mandible model |
| CN108555795A (en) * | 2018-03-28 | 2018-09-21 | 湖南大学 | One kind can stepless changing spatial position and posture fixture for fixing mandible model |
-
2012
- 2012-12-26 CN CN 201220729750 patent/CN203100723U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108466197A (en) * | 2018-03-28 | 2018-08-31 | 湖南大学 | A kind of fixture can adjust spatial position for fixing various sizes of mandible model |
| CN108555795A (en) * | 2018-03-28 | 2018-09-21 | 湖南大学 | One kind can stepless changing spatial position and posture fixture for fixing mandible model |
| CN108555795B (en) * | 2018-03-28 | 2019-07-05 | 湖南大学 | One kind can stepless changing spatial position and posture fixture for fixing mandible model |
| CN108466197B (en) * | 2018-03-28 | 2019-09-24 | 湖南大学 | It can adjust the fixture of spatial position for fixing various sizes of mandible model |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20161018 Address after: 430056 hi tech park, Wuhan economic and Technological Development Zone, Hubei Patentee after: Aerospace Times Electronic Technology Co.,Ltd. Address before: Baoji City, Shaanxi Province, 721006 West Road Weibin District No. 43 Patentee before: SHAANXI SPACEFLIGHT NAVIGATION EQUIPMENT CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20171225 Address after: 721006 Baoji hi tech Development Zone, new town, science and technology, Shaanxi Patentee after: SHAANXI AEROSPACE TIMES NAVIGATION EQUIPMENT Co.,Ltd. Address before: 430056 hi tech park, Wuhan economic and Technological Development Zone, Hubei Patentee before: Aerospace Times Electronic Technology Co.,Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130731 |