CN102539096A - Pressing device for aircraft belt-free adapter state vibration test - Google Patents
Pressing device for aircraft belt-free adapter state vibration test Download PDFInfo
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- CN102539096A CN102539096A CN2011103624817A CN201110362481A CN102539096A CN 102539096 A CN102539096 A CN 102539096A CN 2011103624817 A CN2011103624817 A CN 2011103624817A CN 201110362481 A CN201110362481 A CN 201110362481A CN 102539096 A CN102539096 A CN 102539096A
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- hold down
- down gag
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- vibration test
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Abstract
A pressing device for an aircraft belt-free adapter state vibration test is characterized in that a pressing device (4) is in a sectioned circular shape. A cross section (5) is in a shape as the following: a boss (6) for a pressing vibration clamp (1) is arranged at the lower bottom of the lower bottom surface right-angle position of a right trapezoid, a certain depth is cut at the position a certain distance away from an another angle of the lower bottom of the right trapezoid along the direction of the lower bottom of the right trapezoid in the direction perpendicular to the lower bottom, a matched inclined plane (7) is processed at the position of cutting destination towards the sloping side of the right trapezoid, the gradient of the matched inclined plane is smaller than that of an aircraft lower end frame installing inclined plane matched with the pressing device, an inclined angle formed by the matched inclined plane and the right trapezoid is circular angle (8), and a plurality of screw installing holes (9) are evenly distributed on the pressing device along the periphery of the pressing device.
Description
Technical field
The present invention relates to a kind of vibration test hold down gag, particularly a kind of aircraft does not have band adapter state vibration test hold down gag.
Background technology
In the past, aircraft was in doing vibration test, and the vibratory response enveloping curve that adopts band adapter bottom surface mostly is as initial conditions, and promptly the band adapter is together participated in vibration test.In the manufacturing process of aircraft and rocket; The band adapter is a part that belongs to rocket; Therefore, in being directed against the vibration test of aircraft, in order better to reflect the vibratory response characteristic that aircraft is individual; Should remove the influence of band adapter for whole star vibration characteristics, be the most rational with moving on to the band parting plane on the initial conditions.At present, increasing aircraft all adopts the vibration test pattern of not being with the band adapter.This pattern requires being connected of vibration tong and aircraft to adopt and simulates the mode that band compresses, and hold down gag has just played this effect.
At present do not have band adapter state lower end frame and the face on inclined-plane is installed is compressed in order to pursue aircraft; Hold down gag generally reaches pressuring action through the oblique angle precision of mating surface; In use because cooperate the foozle on inclined-plane to be easy to cause not press tightly, the virtual pressure phenomenon; This problem can cause test to carry out, and perhaps the test findings error is excessive.
Summary of the invention
Do not have at aircraft and cooperate the inclined-plane foozle to compressing the influence of effect in the band adapter state vibration test in order to solve existing hold down gag, the invention provides a kind of aircraft does not have band adapter state vibration test hold down gag.Utilize the present invention, can eliminate cooperation inclined-plane foozle basically compressing the influence of effect.
The technical scheme that the present invention is adopted for its technical matters of solution is:
A kind of aircraft does not have band adapter state vibration test hold down gag; It is characterized in that: said hold down gag is the segmentation annular; Its xsect adopts following shape: on the going to the bottom of the place, bottom surface right angle of right-angled trapezium, a boss 6 is set; Direction is cut certain depth apart from another edge, a distance, angle that said right-angled trapezium is gone to the bottom and the direction of going to the bottom vertical going to the bottom along said right-angled trapezium; Hypotenuse processing at from said cutting end point place to right-angled trapezium cooperates the inclined-plane; The gradient that the gradient on said cooperation inclined-plane is installed the inclined-plane less than the aircraft lower end frame that cooperates with said hold down gag, the angle that said cooperation inclined-plane and right-angled trapezium form is a fillet, said hold down gag circumferentially is uniformly distributed with a plurality of screw mounting holes in said hold down gag upper edge.
The gradient that described hold down gag cooperates the inclined-plane than the gradient on the frame installation inclined-plane, aircraft lower end that cooperates with said hold down gag little 0.2 °～0.5 °.
Said boss 6 is circular-arc.
Described radius of corner is 2mm-5mm.
8 the above hold down gag first places join and form complete annulus.
Adopt hold down gag of the present invention, mating surface changes the line contact into by original face contact, so more meets the actual conditions of band pretension.In order to realize the line contact, cooperate bevel angle to be arranged to install the angle on inclined-plane hold down gag less than the lower end frame, concrete difference is 0.2 °～0.5 °.Thus, hold down gag because its bevel angle is little, must forms line with frame inclined-plane, lower end and contact when mounted, and in addition because angle difference is a scope, so the tolerance ability is stronger, can eliminate the influence of mismachining tolerance basically.In order to strengthen compressing effect; At the circular-arc boss of hold down gag arranged outside, make hold down gag form cavity after the installation and between the vibration tong, at this moment; Cooperate osculatory, the boss on inclined-plane to can be considered bridge pier; Hold down gag can be considered bridge, and the three forms the stressed relation (bridge effect) as bridge, can fully guarantee to cooperate the compress effect of inclined-plane to the lower end frame; And the convex structure of boss can make boss have the effect of inside extruding as bridge pier when stressed, has further strengthened compressing ability.Hold down gag is 360 ° of toroidals, can bring into play the effect of inside extruding in order to make above-mentioned circular-arc boss, and hold down gag is truncated into the segmentation more than eight sections, so not only has been convenient to install but also help snap-in force is passed to the lower end frame.At last, cooperate the top, inclined-plane that fillet is set, can effectively prevent the impaction state injury of contact of rolling off the production line frame inclined-plane, lower end at hold down gag.
The invention has the beneficial effects as follows: solved existing hold down gag and cooperated the inclined-plane mismachining tolerance, under the situation that does not change the hold down gag agent structure, had the stronger ability that compresses compressing the harmful effect of effect.Simple in structure, processing technology is identical with existing hold down gag, and because the tolerance ability is strong, the rejection rate in the manufacturing process reduces greatly, can effectively practice thrift cost.
Description of drawings
Fig. 1 is the scheme of installation of hold down gag of the present invention and aircraft lower end frame, vibration tong;
Fig. 2 is single hold down gag and schematic cross-section thereof;
Fig. 3 hold down gag and aircraft lower end frame impaction state schematic cross-section.
Wherein: 1. vibration tong, 2. aircraft lower end frame is 3. formed the hold down gag of annulus, 4. hold down gag, 5. hold down gag xsect, 6. circular-arc boss, 7. cooperation inclined-plane, 8. fillet, 9. screw mounting hole, 10. lower end frame cross section, 11. installation inclined-planes.
Embodiment
Referring to Fig. 1; Aircraft does not have band adapter state vibration test, and vibration tong 1 is installed on the vibration table, and aircraft lower end frame 2 is placed on the vibration tong 1; 8 hold down gags 3 are close to aircraft lower end frame 2 and vibration tong 1 successively, through screw the three are connected as a single entity.
Referring to Fig. 2 and Fig. 3; Said hold down gag is the segmentation annular; Its xsect adopts following shape: on the going to the bottom of the place, bottom surface right angle of right-angled trapezium, a boss 6 is set; Direction is cut certain depth apart from another edge, a distance, angle that said right-angled trapezium is gone to the bottom and the direction of going to the bottom vertical going to the bottom along said right-angled trapezium; Hypotenuse processing at from said cutting end point place to right-angled trapezium cooperates the inclined-plane; The gradient that the gradient on said cooperation inclined-plane is installed the inclined-plane less than the aircraft lower end frame that cooperates with said hold down gag, the angle that said cooperation inclined-plane and right-angled trapezium form is a fillet, said hold down gag circumferentially is uniformly distributed with a plurality of screw mounting holes in said hold down gag upper edge.The gradient that described hold down gag cooperates the inclined-plane than the gradient on the frame installation inclined-plane, aircraft lower end that cooperates with said hold down gag little 0.2 °～0.5 °.Said boss 6 is circular-arc.Described radius of corner is 2mm-5mm.8 the above hold down gag first places join and form complete annulus.The gradient on cooperation inclined-plane 7 that plays main pressuring action in the hold down gag 3 is less than the gradient on frame 2 installation inclined-planes 11, aircraft lower end, and both form the line contact, can effectively prevent the influence of mismachining tolerance; The tip designs on hold down gag 3 cooperation inclined-planes 7 is a fillet 8, can make the contact site smooth-out, plays the effect on the installation inclined-plane 11 of protection lower end frame 2; When cooperating inclined-plane 7 and installation inclined-plane 11 formation lines to contact, circular-arc boss 6 contacts with vibration tong 1, makes hold down gag 3 after the installation that is spirally connected through screw mounting hole 9 and vibration tong 3; Form cavity between hold down gag 3 and the vibration tong 1; At this moment, cooperate inclined-plane 7, circular-arc boss 6 to can be considered bridge pier, hold down gag 3 can be considered bridge; The three forms the stressed relation (bridge effect) as bridge, can fully guarantee to cooperate the effect that compresses of the 7 pairs of lower end frames 2 in inclined-plane; In addition, circular-arc boss 6 through in the process of screw in compression, can form inside extruding force at single hold down gag 4, and lower end frame 2 is formed the stronger effect that compresses.
In sum; Aircraft of the present invention does not have band adapter state vibration test hold down gag; Can eliminate mismachining tolerance basically to compressing the influence of effect; And in the transmission of power, strengthened compressing ability greatly, and can effectively prevent of the damage of the high snap-in force of hold down gag in vibration test lower end frame installation inclined-plane.
Claims (5)
1. an aircraft does not have band adapter state vibration test hold down gag; It is characterized in that: said hold down gag (4) is the segmentation annular; Its xsect (5) adopts following shape: on the going to the bottom of the place, bottom surface right angle of right-angled trapezium, be provided with one be used to compress vibration tong (1) boss (6); Direction is cut certain depth apart from another edge, a distance, angle that said right-angled trapezium is gone to the bottom and the direction of going to the bottom vertical going to the bottom along said right-angled trapezium; Hypotenuse processing at from said cutting end point place to right-angled trapezium cooperates inclined-plane (7); The gradient that the gradient on said cooperation inclined-plane is installed the inclined-plane less than the aircraft lower end frame that cooperates with said hold down gag, the angle that said cooperation inclined-plane and right-angled trapezium form is fillet (8), said hold down gag circumferentially is uniformly distributed with a plurality of screw mounting holes (9) in said hold down gag upper edge.
2. aircraft as claimed in claim 1 does not have band adapter state vibration test hold down gag, it is characterized in that: the gradient that described hold down gag cooperates the inclined-plane than the gradient on the frame installation inclined-plane, aircraft lower end that cooperates with said hold down gag little 0.2 °～0.5 °.
3. aircraft as claimed in claim 1 does not have band adapter state vibration test hold down gag, it is characterized in that: said boss (6) is circular-arc.
4. aircraft as claimed in claim 1 does not have band adapter state vibration test hold down gag, it is characterized in that: described radius of corner is 2mm-5mm.
5. aircraft as claimed in claim 1 does not have band adapter state vibration test hold down gag, it is characterized in that: 8 the above hold down gag first places join and form complete annulus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103624817A CN102539096A (en) | 2011-11-15 | 2011-11-15 | Pressing device for aircraft belt-free adapter state vibration test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103624817A CN102539096A (en) | 2011-11-15 | 2011-11-15 | Pressing device for aircraft belt-free adapter state vibration test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102539096A true CN102539096A (en) | 2012-07-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011103624817A Pending CN102539096A (en) | 2011-11-15 | 2011-11-15 | Pressing device for aircraft belt-free adapter state vibration test |
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| Country | Link |
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| CN (1) | CN102539096A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107991046A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | Test fixture for large space station ground vibration |
| CN112676809A (en) * | 2020-12-17 | 2021-04-20 | 北京航星机器制造有限公司 | Disassembling device and method for warhead product |
| CN114425642A (en) * | 2021-12-21 | 2022-05-03 | 贝隆精密科技股份有限公司 | Electric spark machining device utilizing center-separating ball jig |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003114165A (en) * | 2001-10-05 | 2003-04-18 | Canon Inc | Vibration tester |
| US20090223261A1 (en) * | 2006-08-23 | 2009-09-10 | Herbert Steinbeck | Device and method for the detachable connection of structural parts, in particular in an aircraft |
| CN102012303A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Clamping device in vibration distressing of satellite mechanical experiment pressure ring |
-
2011
- 2011-11-15 CN CN2011103624817A patent/CN102539096A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003114165A (en) * | 2001-10-05 | 2003-04-18 | Canon Inc | Vibration tester |
| US20090223261A1 (en) * | 2006-08-23 | 2009-09-10 | Herbert Steinbeck | Device and method for the detachable connection of structural parts, in particular in an aircraft |
| CN102012303A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Clamping device in vibration distressing of satellite mechanical experiment pressure ring |
Non-Patent Citations (2)
| Title |
|---|
| 张逸波: "卫星振动压环优化设计", 《航天器环境工程》 * |
| 齐晓军等: "卫星虚拟振动试验仿真效果研究", 《航天器环境工程》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107991046A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | Test fixture for large space station ground vibration |
| CN112676809A (en) * | 2020-12-17 | 2021-04-20 | 北京航星机器制造有限公司 | Disassembling device and method for warhead product |
| CN112676809B (en) * | 2020-12-17 | 2022-06-10 | 北京航星机器制造有限公司 | Disassembling device and method for warhead product |
| CN114425642A (en) * | 2021-12-21 | 2022-05-03 | 贝隆精密科技股份有限公司 | Electric spark machining device utilizing center-separating ball jig |
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Owner name: SHANGHAI SATELLITE EQUIPMENT INSTITUTE Free format text: FORMER OWNER: SHANGHAI SATELLITE ENGINEERING RESEARCH INSTITUTE Effective date: 20130909 |
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Effective date of registration: 20130909 Address after: 200240 Shanghai city Minhang District Huaning Road No. 251 Applicant after: Shanghai Institute of Satellite Equipment Address before: 200240 Shanghai city Minhang District Huaning Road No. 251 Applicant before: Shanghai Satellite Engineering Research Institute |
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Application publication date: 20120704 |