CN209834047U

CN209834047U - Novel machine body pressure sensor clamp

Info

Publication number: CN209834047U
Application number: CN201920334998.7U
Authority: CN
Inventors: 莫焘; 芶炜豪; 王智; 余漪川
Original assignee: Chengdu Aircraft Industrial Group Co Ltd
Current assignee: Chengdu Aircraft Industrial Group Co Ltd
Priority date: 2019-03-18
Filing date: 2019-03-18
Publication date: 2019-12-24
Anticipated expiration: 2029-03-18

Abstract

The utility model belongs to aeronautical manufacturing related field especially relates to a novel fuselage pressure sensor anchor clamps that is used for air data system airtight test, ventilation test, pressure sensor performance to be experimental, carries out the ground test equipment through test pipeline and the last left and right fuselage pressure sensor of machine to be connected, including two at least test sucking discs and two at least supplementary sucking discs, the test sucking disc passes through the connecting rod with supplementary sucking disc and links to each other, the static pressure hole of fuselage pressure sensor is aimed at to the test sucking disc, and every test sucking disc all is connected with static pressure pipe connector mouth, supplementary sucking disc links to each other with the pressurize switch. This application has reduced installation time, avoids the condition that fuselage pressure sensor special fixture dropped the damage during the experiment to appear, has promoted experimental success rate, has improved work efficiency. The clamp is more convenient and faster to clamp, the special clamp for the machine body pressure sensor is more reliably fixed, and the probability of falling and damage of the clamp is reduced.

Description

Novel machine body pressure sensor clamp

Technical Field

The utility model belongs to aeronautical manufacturing related field especially relates to a novel fuselage pressure sensor anchor clamps that is used for air data system airtight test, ventilation test, pressure sensor performance test time, carries out ground test equipment through test pipeline and the last left and right fuselage pressure sensor of machine to be connected.

Background

When an air data system airtight test, a ventilation test and a pressure sensor performance test are carried out, ground test equipment needs to be communicated with a static pressure hole of a pressure sensor of an upper machine body of a machine through a pipeline by a special clamp.

The fuselage pressure sensor is embedded installation, and its surface flushes with the fuselage surface, and the surface quality requires highly can not destroy, can not fix with conventional anchor clamps when test pipeline is connected with the sensor, and the sucking disc mode of mainly adopting at present adsorbs the fixed anchor clamps body, and anchor clamps are connected with fuselage pressure sensor. The static pressure hole of the 1 st section and the static pressure hole of the 3 rd section of the pressure sensor of the machine body are respectively adsorbed on the surface by using a sucker, and one person needs to hold two clamp bodies with two hands at the beginning of a test to enable the sucker to be tightly attached to the outer surface of the static pressure hole. The ground test equipment works, a static pressure source is provided for the sucker through the test pipeline and the test pipe joint, the hand can not be loosened to continue the test until the static pressure generated in the sealed space formed by the sucker and the machine body pressure sensor is enough to overcome the gravity of the clamp and the test pipeline, and the sealed space comprises the space formed by the sucker and the outer surface of the static pressure hole of the machine body pressure sensor and the space of the pipeline inside the machine body pressure sensor. When the test is started, a user needs to hold the clamp for a certain time, if the time for releasing the hand is too early, the clamp can fall off, the situation often occurs in the actual work, the test efficiency is low, and the clamp can fall off the ground and be damaged. In addition, under the condition of ground test equipment normal work, if there is the leakage in fuselage pressure sensor internal line itself, probably lead to the anchor clamps sucking disc can not stably adsorb in the sensor surface, can't the quick judgement be the problem of fuselage pressure sensor itself still test the problem of pipeline and anchor clamps, influence experimental progress and efficiency.

Disclosure of Invention

In order to solve the problem that the special clamp for the fuselage pressure sensor drops and is damaged during the test in the prior art, the novel clamp for the fuselage pressure sensor, which can reduce the installation time and improve the test success rate and the working efficiency, is provided.

In order to achieve the technical problem, the technical scheme adopted by the application is as follows:

the utility model provides a novel fuselage pressure sensor anchor clamps which characterized in that: including two at least test sucking discs and two at least supplementary sucking discs, the test sucking disc passes through the connecting rod with supplementary sucking disc and links to each other, the static pressure hole of fuselage pressure sensor is aimed at to the test sucking disc, and every test sucking disc all is connected with static pressure pipe connector mouth, supplementary sucking disc links to each other with the pressurize switch.

A channel is arranged in the connecting rod, and the test sucker is communicated with the static pressure pipe through the channel.

A channel is arranged in the connecting rod, and the auxiliary sucker is communicated with the pressure maintaining switch through the channel.

And the static pressure pipe joint is connected with a static pressure end of the ground test equipment.

The connecting rod is of a long strip structure or a rectangular frame structure.

The working principle of this application does:

at the beginning of the test, the special fixture test sucker is aligned to the mounting position on the pressure sensor of the machine body, the ground test equipment provides a vacuum source, and the auxiliary sucker can be more quickly adsorbed on the surface of the sensor because the surface of the sensor adsorbed by the auxiliary sucker is not provided with a static pressure hole, so that the time required by installation is reduced. Supplementary sucking disc is stably adsorbed in sensor surface back, closes the pressurize switch, and the negative pressure that produces in the supplementary sucking disc makes special fixture reliably be fixed in the sensor surface, even there is the inside pipeline of sensor to leak in the test process, the condition that anchor clamps dropped the damage can not appear yet.

The application has the advantages that:

this application has reduced installation time, avoids the condition that fuselage pressure sensor special fixture dropped the damage during the experiment to appear, has promoted experimental success rate, has improved work efficiency. The clamp is more convenient and faster to clamp, the special clamp for the machine body pressure sensor is more reliably fixed, and the probability of falling and damage of the clamp is reduced.

Drawings

Fig. 1 is a top view of the present application.

Fig. 2 is a side view of the present application.

In the drawings: 1-test sucker, 2-auxiliary sucker, 3-static pressure pipe connector, 4-pressure maintaining switch, and 5-connecting rod.

Detailed Description

Example 1

The utility model provides a novel fuselage pressure sensor anchor clamps includes two at least test sucking discs 1 and two at least supplementary sucking discs 2, test sucking disc 1 links to each other through connecting rod 5 with supplementary sucking disc 2, the static pressure hole of fuselage pressure sensor is aimed at to test sucking disc 1, and every test sucking disc 1 all is connected with static pressure pipe connector 3, supplementary sucking disc 2 links to each other with pressurize switch 4. This application has reduced installation time, avoids the condition that fuselage pressure sensor special fixture dropped the damage during the experiment to appear, has promoted experimental success rate, has improved work efficiency. The clamp is more convenient and faster to clamp, the special clamp for the machine body pressure sensor is more reliably fixed, and the probability of falling and damage of the clamp is reduced.

In the picture, when novel fuselage pressure sensor anchor clamps were installed, two test sucking disc 1 on the anchor clamps aimed at the static pressure port, opened pressurize switch 4, and ground test equipment work provides the vacuum source, and supplementary sucking disc 2 adsorbs the position and does not have the static pressure port, and its inside confined space is compared test sucking disc 1 inside confined space littleer, therefore can be more quick adsorb and mounting fixture, reduces anchor clamps installation time. Supplementary sucking disc 2 adsorbs stable back, closes pressurize switch 4, even there is the inside leakage problem of fuselage pressure sensor, though negative pressure is not enough to make anchor clamps adsorb in the test sucking disc 1, nevertheless because the absorption fixed action of supplementary sucking disc 2, anchor clamps still can not drop the damage. This novel anchor clamps have reduced test time, have reduced the anchor clamps probability of damage that drops, have promoted test efficiency.

Example 2

The utility model provides a novel fuselage pressure sensor anchor clamps includes two at least test sucking discs 1 and two at least supplementary sucking discs 2, test sucking disc 1 links to each other through connecting rod 5 with supplementary sucking disc 2, the static pressure hole of fuselage pressure sensor is aimed at to test sucking disc 1, and every test sucking disc 1 all is connected with static pressure pipe connector 3, supplementary sucking disc 2 links to each other with pressurize switch 4.

A channel is arranged in the connecting rod 5, and the test sucker 1 is communicated with the static pressure pipe through the channel. A channel is arranged in the connecting rod 5, and the auxiliary sucker 2 is communicated with the pressure maintaining switch 4 through the channel.

The static pressure pipe joint 3 is connected with the static pressure end of ground test equipment. The connecting rod 5 is in a long strip structure or a rectangular frame structure.

At the beginning of the test, aim at the last mounted position of fuselage pressure sensor with special fixture test sucking disc 1, ground test equipment provides the vacuum source, because the adsorbed sensor surface of supplementary sucking disc 2 does not have the static pressure hole, therefore supplementary sucking disc 2 can be adsorbed on the sensor surface more fast, has reduced the installation required time. Supplementary sucking disc 2 stably adsorbs behind the sensor surface, closes pressurize switch 4, and the negative pressure that produces in supplementary sucking disc 2 makes special fixture reliably be fixed in the sensor surface, even there is the inside pipeline of sensor to leak in the test process, the condition that the anchor clamps damage that drops can not appear yet.

Claims

1. The utility model provides a novel fuselage pressure sensor anchor clamps which characterized in that: including two at least test sucking disc (1) and two at least auxiliary suction disc (2), test sucking disc (1) links to each other through connecting rod (5) with auxiliary suction disc (2), fuselage pressure sensor's static pressure port is aimed at in test sucking disc (1), and every test sucking disc (1) all is connected with static pressure pipe connector mouth (3), auxiliary suction disc (2) link to each other with pressurize switch (4).

2. The novel fuselage pressure sensor clamp of claim 1, wherein: a channel is arranged in the connecting rod (5), and the test sucker (1) is communicated with the static pressure pipe through the channel.

3. The novel fuselage pressure sensor clamp of claim 1, wherein: a channel is arranged in the connecting rod (5), and the auxiliary sucker (2) is communicated with the pressure maintaining switch (4) through the channel.

4. The novel fuselage pressure sensor clamp of claim 1 or 2, characterized in that: the static pressure pipe connector (3) is connected with a static pressure end of ground test equipment.

5. The novel fuselage pressure sensor clamp of claim 4, wherein: the connecting rod (5) is of a long strip structure or a rectangular frame structure.