CN204758274U - Space flight electric connector separation test special fixture - Google Patents
Space flight electric connector separation test special fixture Download PDFInfo
- Publication number
- CN204758274U CN204758274U CN201520428622.4U CN201520428622U CN204758274U CN 204758274 U CN204758274 U CN 204758274U CN 201520428622 U CN201520428622 U CN 201520428622U CN 204758274 U CN204758274 U CN 204758274U
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Abstract
The utility model discloses a space flight electric connector separation test special fixture, including socket anchor clamps and plug clip utensil, the socket anchor clamps possess with plug clip and are used for fixing the space flight electric connector that awaits measuring, socket anchor clamps rear is equipped with the cylinder, and the cylinder pushes away the socket anchor clamps, and socket anchor clamps and plug clip utensil one side are equipped with fastener for adjust the centre gripping size of socket anchor clamps and plug clip utensil. These anchor clamps are gone up and are born based on the basis of separation performance comprehensive testing system, and for the electric connector who adapts to different models, these anchor clamps need be realized removing adjustablely. Width location, elevation positioning, the longitudinal separation location of anchor clamps are realized according to the corresponding frock cushion needs of its size design.
Description
Technical field
The utility model belongs to Aerospace Electric Connector field, specifically a kind of Aerospace Electric Connector discrete testing unit clamp.
Background technology
The major function of Aerospace Electric Connector is the transmission, the control that realize electric signal between space flight carrier electrical equipment.It as the military products such as guided missile, satellite have a wide range of applications, is a kind of most basic components and parts in many systems.
Being separated the general name that umbilical connector is separation connector and umbilical connector, is belong to special electric connector.Similar in separation, umbilical connector structure, there is the requirement of separation.Generally according to use occasion, it is classified, to be applied in the flight course such as guided missile, rocket play interstage circuit connect, disconnection effect be called separation connector; For when being used in guided missile, rocket launching, play the connection of circuit and uphole equipment, disconnection effect be called umbilical connector.Be emitted as example with satellite, at launching phase, application umbilical connector, to realize electrical connection between rocket and ground, disconnection, has requirement that is rainproof, dust-proof and fire resistant to its performance; In satellite and Separation stage, application separation connector is to realize electrical connection, the disconnection of rocket inter-stage, and the separation of separation connector must being separated early than rocket and satellite, has requirement that is dust-proof and fire resistant to it.For this two type electric connector, if be separated or come off unsuccessful, then can window rocket attitude, affect safety satellite or cause abortive launch.
Data display according to statistics, in the fault of all Space Vehicle Systems, the fault caused by component failures such as electric connectors accounts for 30% of sum, the loss caused cannot be estimated, for this reason, NASA drops into the funds of 100,000,000 dollars specially for carrying out the research of the component failure such as electric connector, life-span aspect.But domestic at present Aerospace Electric Connector released state measuring technology also not to be carried out in a deep going way, do not work out more easily for assessment of the test macro of Aerospace Electric Connector separating property.Given this, developing separating property comprehensive detection system is exactly in order to Efficient Evaluation and the separating property analyzing electric connector.
Be separated umbilical connector and have multiple different model, when being separated, electric connector inherently has individual elastic force, and the outside pulling force that applies is needed when mechanical release, meet the electric connector of different model batch thus and aobvious just necessary of fastener is installed.To the electric connector of different model batch at every turn when testting, all to change frock cushion block, the each very important persons of fixture of socket, plug are fastening, and must ensure to fasten, otherwise when carrying out testting, electrical connector plug easily ejects fixture when driven by servomotor pulling force, causes the outer damage that electric connector is unnecessary.
Be separated the occasion that umbilical connector is widely used in the separation of the needs such as guided missile, rocket, its the normal operation of separating property to whole system is most important, but, studying it of current domestic and international also non-system, unlocks its electromagnetism and clear effective data record and Treatment Analysis were not carried out in the detachment process of mechanical release two kinds of separate modes.
Utility model content
In order to solve the above-mentioned technical matters existed in prior art, the utility model provides a kind of Aerospace Electric Connector discrete testing unit clamp, comprise socket fixture and plug fixture, socket fixture and plug fixture are used for fixing Aerospace Electric Connector to be measured, described socket fixture rear is provided with cylinder, cylinder pushes away socket fixture, and socket fixture and plug fixture side are provided with fastener, for the clamping dimension of adjustable socket fixture and plug fixture.
Further, frock cushion block is provided with between described socket fixture and plug fixture.
Further, be provided with dynamic plate below described plug fixture, many guide rods are through dynamic plate.
Further, the described guide rod being positioned at centre is provided with spring and withstands dynamic plate, is provided with bearing between guide rod and dynamic plate.
Further, described dynamic plate arranged beneath has the stop cylinder be located on base.
The detachment process systematic research also Aerospace Electric Connector is not separated both at home and abroad at present, come off, development separating property comprehensive detection system is in order to its detachment process of systematic research and its valid data produced of Treatment Analysis, and this fixture is born based on the basis of separating property comprehensive detection system.When system is normally run, no matter be that electromagnetism unlocks or mechanical release, it not only wants to fix separation umbilical connector, and socket also will be made successfully to be separated with plug, and coordinates high-speed camera to obtain separate picture.In order to adapt to the electric connector of different model, this fixture needs realization mobile adjustable.Need to realize the width location of fixture, altitude location, longitudinal separation location according to the corresponding frock cushion block of its size design.
This fixture developed based on separating property comprehensive detection system basis, is utility model people autonomous Design completely, has originality., there is not the most similar technical scheme in the technical matters that before solving, nobody solves.
Accompanying drawing explanation
Fig. 1 is the structural representation of Aerospace Electric Connector discrete testing unit clamp of the present utility model;
Fig. 2 is the front elevation of this Aerospace Electric Connector discrete testing unit clamp;
Fig. 3 is the side view of this Aerospace Electric Connector discrete testing unit clamp;
Fig. 4 is the backplan of this Aerospace Electric Connector discrete testing unit clamp.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As Figure 1-4, Aerospace Electric Connector discrete testing unit clamp of the present utility model, comprise socket fixture 2 and plug fixture 7, socket fixture 2 and plug fixture 7 are used for fixing Aerospace Electric Connector to be measured, socket fixture 2 rear is provided with cylinder 1, cylinder 1 pushes away socket fixture 2, and socket fixture 2 and plug fixture 7 side are provided with fastener 3, for the clamping dimension of adjustable socket fixture 2 and plug fixture 7.Frock cushion block 8 is provided with between socket fixture 2 and plug fixture 7.
Be provided with dynamic plate 4 below plug fixture 7, many guide rods 5 are through dynamic plate 4, and guide rod 5 is provided with spring 9 and withstands dynamic plate 4, is provided with bearing 10 between guide rod 5 and dynamic plate 4, and dynamic plate 4 arranged beneath has the stop cylinder 6 be located on base 11.
Electric connector has electromagnetism to unlock separate mode, have a lot of wire in use to draw, electric connector is made to have a downward electric wire Action of Gravity Field, in order to the service condition of energy real simulation electric connector, when electric connector is fixed by socket fixture 2 and plug fixture 7, need cylinder 1 to provide air pressure thrust to make electric connector uniform force, can be up to the standard when separation separation.In order to adapt to the electric connector of different model, fastener 3 can be regulated to be used for clamping electric connector.When servomotor generation driving force pulls electric connector to be separated, dynamic plate 4 moves together with electrical connector plug, dynamic plate 4 is stopped in time stopping cylinder 6, at this moment air pressure hand valve is pressed, stop that cylinder 6 loses barrier effect, dynamic plate 4 spring be added on guide rod 5 applies elastic force and bounces back into original position, prepares electric connector discrete testing next time.Bearing 10 and guide rod 5 will keep less sliding resistance as far as possible, are conducive to the motion of dynamic plate 4 and electrical connector plug like this.Base 11 is installed on cabinet, fixing whole fixture module.
The true service condition of the complete analog electrical connector of this fixture energy, its applicability is extensive, and the electric connector that can meet different model batch is test, and only needs to regulate once to the electric connector fastener of same model batch, just can clamp electric connector both sides, convenient and swift.Frock cushion block, according to different electric connector sizes, possesses the parameters such as specific width, thickness, alternative abundant.
Guide rod adds spring, dynamic plate can not only be bounce back into the pulling force acted on electric connector that servomotor generation can also be cushioned in original position in time, be unlikely to damage electric connector, safe and reliable.High-speed camera record electric connector separation attitude track can be coordinated, embody technical advance.
Claims (5)
1. an Aerospace Electric Connector discrete testing unit clamp, comprise socket fixture (2) and plug fixture (7), socket fixture (2) and plug fixture (7) are used for fixing Aerospace Electric Connector to be measured, it is characterized in that: described socket fixture (2) rear is provided with cylinder (1), cylinder (1) pushes away socket fixture (2), socket fixture (2) and plug fixture (7) side are provided with fastener (3), for the clamping dimension of adjustable socket fixture (2) and plug fixture (7).
2. Aerospace Electric Connector discrete testing unit clamp as claimed in claim 1, is characterized in that: be provided with frock cushion block (8) between described socket fixture (2) and plug fixture (7).
3. Aerospace Electric Connector discrete testing unit clamp as claimed in claim 1, is characterized in that: described plug fixture (7) below is provided with dynamic plate (4), and many guide rods (5) are through dynamic plate (4).
4. Aerospace Electric Connector discrete testing unit clamp as claimed in claim 3, is characterized in that: the described guide rod (5) being positioned at centre is provided with spring (9) and withstands dynamic plate (4), is provided with bearing (10) between guide rod (5) and dynamic plate (4).
5. Aerospace Electric Connector discrete testing unit clamp as claimed in claim 4, is characterized in that: described dynamic plate (4) arranged beneath has the stop cylinder (6) be located on base (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520428622.4U CN204758274U (en) | 2015-06-19 | 2015-06-19 | Space flight electric connector separation test special fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520428622.4U CN204758274U (en) | 2015-06-19 | 2015-06-19 | Space flight electric connector separation test special fixture |
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| Publication Number | Publication Date |
|---|---|
| CN204758274U true CN204758274U (en) | 2015-11-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520428622.4U Active CN204758274U (en) | 2015-06-19 | 2015-06-19 | Space flight electric connector separation test special fixture |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104977160A (en) * | 2015-06-19 | 2015-10-14 | 中国计量学院 | Special fixture for aerospace electrical connector separation test |
| CN106443262A (en) * | 2016-10-08 | 2017-02-22 | 浙江大学 | Online salt fog test device for spaceflight electric connector |
| CN110865317A (en) * | 2019-11-08 | 2020-03-06 | 上海航天设备制造总厂有限公司 | Rocket connector drop signal feedback sensor |
| CN114001935A (en) * | 2021-10-08 | 2022-02-01 | 浙江蓝箭航天空间科技有限公司 | Gas-liquid connector assembly test device |
-
2015
- 2015-06-19 CN CN201520428622.4U patent/CN204758274U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104977160A (en) * | 2015-06-19 | 2015-10-14 | 中国计量学院 | Special fixture for aerospace electrical connector separation test |
| CN106443262A (en) * | 2016-10-08 | 2017-02-22 | 浙江大学 | Online salt fog test device for spaceflight electric connector |
| CN106443262B (en) * | 2016-10-08 | 2019-06-07 | 浙江大学 | A kind of online salt spray test device of Aerospace Electric Connector |
| CN110865317A (en) * | 2019-11-08 | 2020-03-06 | 上海航天设备制造总厂有限公司 | Rocket connector drop signal feedback sensor |
| CN114001935A (en) * | 2021-10-08 | 2022-02-01 | 浙江蓝箭航天空间科技有限公司 | Gas-liquid connector assembly test device |
| CN114001935B (en) * | 2021-10-08 | 2023-08-04 | 浙江蓝箭航天空间科技有限公司 | Gas-liquid connector assembly test device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |