CN106289690B - A kind of vibration test fixture - Google Patents

A kind of vibration test fixture Download PDF

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Publication number
CN106289690B
CN106289690B CN201610607351.8A CN201610607351A CN106289690B CN 106289690 B CN106289690 B CN 106289690B CN 201610607351 A CN201610607351 A CN 201610607351A CN 106289690 B CN106289690 B CN 106289690B
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CN
China
Prior art keywords
sliding block
pitman
loose slot
block loose
valve
Prior art date
Application number
CN201610607351.8A
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Chinese (zh)
Other versions
CN106289690A (en
Inventor
倪博慧
徐敏
殷小房
张伟
缪发根
李旺林
高欣
郑宏海
吴涛
邱少波
连群
张翔
杨光
Original Assignee
江西洪都航空工业集团有限责任公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Application filed by 江西洪都航空工业集团有限责任公司 filed Critical 江西洪都航空工业集团有限责任公司
Priority to CN201610607351.8A priority Critical patent/CN106289690B/en
Publication of CN106289690A publication Critical patent/CN106289690A/en
Application granted granted Critical
Publication of CN106289690B publication Critical patent/CN106289690B/en

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Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00Vibration-testing of structures; Shock-testing of structures
    • G01M7/02Vibration-testing by means of a shake table
    • G01M7/027Specimen mounting arrangements, e.g. table head adapters
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00Vibration-testing of structures; Shock-testing of structures
    • G01M7/02Vibration-testing by means of a shake table
    • G01M7/06Multidirectional test stands

Abstract

The invention belongs to a kind of vibration test fixture, sliding block loose slot (1) is screwed on cage fixture, and pitman (5) are passed through to the lifting lug of missile launcher, lifting lug is made to be in the intermediate position of pitman (5);Pitman (5) and two movable sliders (2) are subjected to clearance fit installation;Movable slider (2) is inserted into from below in sliding block loose slot (1);Connecting screw (4) is fixed by the through-hole on sliding block loose slot (1) with the through-hole in the U-type groove and pitman (5) of movable slider (2) two sides;Outer adjutage (3) is installed on the outside of sliding block loose slot (1);Threaded hole is equipped on the outside of outer adjutage (3);Valve (7) and ball screw (6) are sub-assembly, and valve (7) can turn an angle around ball screw (6) one end;Ball screw (6) other end is screwed onto the threaded hole of outer adjutage (3);The position of governor valve (7) and angle, missile launcher is fixed.

Description

A kind of vibration test fixture

Technical field

The invention belongs to a kind of vibration test fixture, using the fixture can will missile launcher it is fixed after, complete it is vertical, The vibration test in three directions of transverse direction and longitudinal direction.

Background technique

Vibration test is a big event in environmental test, can be used to find in product design and production process Defect improves the purpose of the vibration resistance environment capacity of product to reach improvement product design.

Test indoor simulation guided missile passes through the vibration test for leading the guided missile for the truth that hair frame is suspended on aircraft at present, is It effectively examines guided missile and leads the most effective mode of hair frame vibration resistance ability.So a fixed missile launcher need to specially be made Vibration test fixture.

Summary of the invention

The purpose of the present invention:It proposes a kind of vibration test fixture, rigid connection fixation is carried out to suspension type missile launcher.

Technical solution of the present invention:

A kind of vibration test fixture, including:

Sliding block loose slot (1), movable slider (2), outer adjutage (3), connecting screw (4), pitman (5), ball screw (6), valve (7);

Sliding block loose slot (1) is screwed on cage fixture, and pitman (5) are passed through to the lifting lug of missile launcher, make lifting lug Intermediate position in pitman (5);Pitman (5) and two movable sliders (2) are subjected to clearance fit installation;Movable slider (2) from below in insertion sliding block loose slot (1);Connecting screw (4) passes through the through-hole and movable slider on sliding block loose slot (1) (2) through-hole on the U-type groove of two sides and pitman (5) is fixed;Outer adjutage is installed on the outside of sliding block loose slot (1) (3);Threaded hole is equipped on the outside of outer adjutage (3);Valve (7) and ball screw (6) are sub-assembly, and valve (7) can be around bulb Screw rod (6) one end turns an angle;Ball screw (6) other end is screwed onto the threaded hole of outer adjutage (3);Governor valve (7) position and angle, missile launcher is fixed.

The vibration test fixture is using 30CrMnSiA as making material.

Advantages of the present invention:Cooperated by the intercombination of several group parts and reasonable size design, reaches fixation and lead The purpose of launcher is played, and can be with the valve distance and different length of flexible choice different location when installing missile launcher Spiro rod length installed, can satisfy stationary phase with the technical requirements of lifting lug spacing but various sizes of missile launcher, Suitable for the missile launcher of multiple and different models, the experimentation cost of vibration test has been saved.

Detailed description of the invention:

Fig. 1 is the part combination part front view of the fixed lifting lug of the present invention.

Wherein:1 --- --- movable slider 3 --- outer adjutage 4 --- connecting screw of sliding block loose slot 2

5 --- pitman

Fig. 2 is the part combination part left view of the fixed lifting lug of the present invention.

Fig. 3 is the part combination part top view of the fixed lifting lug of the present invention.

Fig. 4 is ball screw and valve sub-assembly schematic diagram of the present invention.

Wherein:6 --- ball screw 7 --- valve

Specific embodiment:

The invention will be described in further detail with reference to the accompanying drawing.

The present invention provides a kind of vibration test fixture, as shown in Figure 1,2,3, 4, including:

Sliding block loose slot 1, movable slider 2, outer adjutage 3, connecting screw 4, pitman 5, ball screw 6, valve 7;

Sliding block loose slot 1 is screwed on cage fixture, and pitman 5 is passed through to the lifting lug of missile launcher, is in lifting lug The intermediate position of pitman 5;Pitman 5 and two movable sliders 2 are subjected to clearance fit installation;Movable slider 2 is inserted into from below In sliding block loose slot 1;The U-type groove and connection that connecting screw 4 passes through through-hole and 2 two sides of movable slider on sliding block loose slot 1 Through-hole on stick 5 is fixed;Outer adjutage 3 is installed on the outside of sliding block loose slot 1;Threaded hole is equipped on the outside of outer adjutage 3;It is living Door 7 is sub-assembly with ball screw 6, and valve 7 can turn an angle around 6 one end of ball screw;6 other end spiral shell of ball screw It connects in the threaded hole of outer adjutage 3;The position of governor valve 7 and angle, missile launcher is fixed.

The vibration test fixture should be using the big material that meets with stresses, for example uses 30CrMnSiA as making material.

Use process:

The present invention is divided into two groups with piece pitman of two sliding blocks for one group and fixes two lifting lugs respectively.Pitman and sliding block Sliding slot is installed by clearance fit, this component is seated to sliding block loose slot, is reused screw rod and is passed through leading on sliding block loose slot Hole is fixed with the through-hole in the U-type groove and pitman of sliding block two sides;Outer adjutage is installed in the outside of sliding block loose slot And the sub-assembly of ball screw and valve, the specific position of valve is determined by the selection of the position of opening on outer adjutage It sets, thus fixed various sizes of missile launcher.

Claims (2)

1. a kind of vibration test fixture, which is characterized in that including:
Sliding block loose slot (1), movable slider (2), outer adjutage (3), connecting screw (4), pitman (5), ball screw (6), Valve (7);
Sliding block loose slot (1) is screwed on cage fixture, and pitman (5) are passed through to the lifting lug of missile launcher, are in lifting lug The intermediate position of pitman (5);Pitman (5) and two movable sliders (2) are subjected to clearance fit installation;Movable slider (2) from Lower section is inserted into sliding block loose slot (1);Connecting screw (4) passes through through-hole and movable slider (2) two sides on sliding block loose slot (1) U-type groove and pitman (5) on through-hole be fixed;Outer adjutage (3) is installed on the outside of sliding block loose slot (1);Extension Threaded hole is equipped on the outside of semi-girder (3);Valve (7) and ball screw (6) are sub-assembly, and valve (7) can be around ball screw (6) one End turns an angle;Ball screw (6) other end is screwed onto the threaded hole of outer adjutage (3);The position of governor valve (7) And angle, missile launcher is fixed.
2. a kind of vibration test fixture as described in claim 1, which is characterized in that the vibration test fixture uses 30CrMnSiA is as making material.
CN201610607351.8A 2016-07-29 2016-07-29 A kind of vibration test fixture CN106289690B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610607351.8A CN106289690B (en) 2016-07-29 2016-07-29 A kind of vibration test fixture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610607351.8A CN106289690B (en) 2016-07-29 2016-07-29 A kind of vibration test fixture

Publications (2)

Publication Number Publication Date
CN106289690A CN106289690A (en) 2017-01-04
CN106289690B true CN106289690B (en) 2018-11-27

Family

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CN201610607351.8A CN106289690B (en) 2016-07-29 2016-07-29 A kind of vibration test fixture

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109489925A (en) * 2017-09-12 2019-03-19 江西洪都航空工业集团有限责任公司 A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4155286A (en) * 1977-12-01 1979-05-22 Mihm John J Wedge clamp for missile launcher
CN1614376A (en) * 2004-12-11 2005-05-11 燕山大学 Environmental experimental platform for mechanical vibration with three freedom degrees
EP1857766A1 (en) * 2006-05-18 2007-11-21 Saab Ab Missile launcher
CN101793613A (en) * 2010-03-11 2010-08-04 浙江工业大学 Vehicle shock absorber test-bed by adopting sine transmission device
CN102023116A (en) * 2010-10-14 2011-04-20 中国人民解放军空军工程大学 Test analysis method for bolt connecting piece fatigue crack expanding
CN102937456A (en) * 2012-10-31 2013-02-20 杭州亿恒科技有限公司 Grid-shaped sensor clamp for elevator vibration tests
CN104034498A (en) * 2014-05-20 2014-09-10 于涛 Quick clamping vibration test bench for missile vibration tests

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4155286A (en) * 1977-12-01 1979-05-22 Mihm John J Wedge clamp for missile launcher
CN1614376A (en) * 2004-12-11 2005-05-11 燕山大学 Environmental experimental platform for mechanical vibration with three freedom degrees
EP1857766A1 (en) * 2006-05-18 2007-11-21 Saab Ab Missile launcher
CN101793613A (en) * 2010-03-11 2010-08-04 浙江工业大学 Vehicle shock absorber test-bed by adopting sine transmission device
CN102023116A (en) * 2010-10-14 2011-04-20 中国人民解放军空军工程大学 Test analysis method for bolt connecting piece fatigue crack expanding
CN102937456A (en) * 2012-10-31 2013-02-20 杭州亿恒科技有限公司 Grid-shaped sensor clamp for elevator vibration tests
CN104034498A (en) * 2014-05-20 2014-09-10 于涛 Quick clamping vibration test bench for missile vibration tests

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
机载飞行器翻倒式吊耳设计与试验;宋磊,金玲,聂青,许俊伟,廖选平,周剑波;《机械设计与研究》;20131231;第32卷(第6期);全文 *

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