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A method for measuring the time sequence of the auxiliary support in front of the launching box

An auxiliary support and timing technology, applied in the direction of jet engine testing, gas turbine engine testing, etc., can solve the problems of lack of models and data, and achieve the effects of safe and convenient use, significant economic benefits, and complete test data

Active Publication Date: 2021-06-11
BEIJING INST OF STRUCTURE & ENVIRONMENT ENG +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention provides a method for measuring the disengagement timing of the auxiliary support in front of the launch box, which can effectively solve the extremely challenging problem of measuring related parameters in the box proposed in the background technology above. The disengagement timing of the front auxiliary support is limited to the launch safety Considering that the existing models and data do not have any experience for reference

Method used

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  • A method for measuring the time sequence of the auxiliary support in front of the launching box
  • A method for measuring the time sequence of the auxiliary support in front of the launching box
  • A method for measuring the time sequence of the auxiliary support in front of the launching box

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Embodiment 1

[0040] Embodiment 1: as figure 1 As shown, the present invention provides a technical solution, a device for measuring the time sequence of the front auxiliary support disengagement, including a box wall 1, a support rod 2 is installed at one end above the box wall 1, and a front support rod 2 is installed on the top of the support rod 2 through a rotating shaft 4. Auxiliary support 3, a stop pin 5 is installed in the middle of one side of the front auxiliary support 3, and a spring leaf 6 is installed at the upper end of the stop pin 5. The high temperature causes separation between the spring piece 6 and the stop pin 5, and the spring piece 6 and the stop pin 5 are fixedly connected by high-temperature tape. One side of the spring piece 6 is installed with an aluminum piece 7, and the bottom side of the aluminum piece 7 is installed. The bakelite block 8 is installed, in order to make the connection between the bakelite block 8 and the box wall 1 more tightly, and there will...

Embodiment 2

[0041] Embodiment 2: as figure 2 As shown, a method for measuring the timing of auxiliary support disengagement in front of the launching box includes the following steps:

[0042] S1. Circuit design of timing measurement device;

[0043] S2. Structural design of timing measurement device;

[0044] S3. Functional design of timing measurement device;

[0045] S4. Strength analysis of timing structure device;

[0046] S5. Test implementation effect measurement.

[0047] According to the above technical solution, in step S1, the output end of the power supply is electrically connected to the input end of the resistor, the input end of the power supply and the output end of the resistor are port A and port B respectively, and the input end and output end of the resistor are respectively port C and D port, when the A port and the B port in the circuit are connected and disconnected, the voltage across the resistor in the circuit, that is, the voltage of the C port and the D po...

Embodiment 3

[0059] Embodiment 3: as figure 2 As shown, a method for measuring the timing of auxiliary support disengagement in front of the launching box includes the following steps:

[0060] S1. Circuit design of timing measurement device;

[0061] S2. Structural design of timing measurement device;

[0062] S3. Functional design of timing measurement device;

[0063] S4. Strength analysis of timing structure device;

[0064] S5. Test implementation effect measurement.

[0065] According to the above technical solution, in step S1, the output end of the power supply is electrically connected to the input end of the resistor, the input end of the power supply and the output end of the resistor are port A and port B respectively, and the input end and output end of the resistor are respectively port C and D port, when the A port and the B port in the circuit are connected and disconnected, the voltage across the resistor in the circuit, that is, the voltage of the C port and the D po...

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Abstract

The invention discloses a timing measurement method for disengagement of an auxiliary support in front of a launch box, which includes the circuit design of a timing measurement device, the structural design of the timing measurement device, the function design of the timing measurement device, the strength analysis of the timing structure device, and the measurement of the experimental implementation effect. It is reasonable, safe and convenient to use. Use this measuring device to obtain the disengagement timing of the auxiliary support in front of the launch box. The test data is complete and the data quality is good. Using this method can successfully obtain the disengagement timing of the auxiliary support before the missile launch process. An effective attempt has been made to measure technical capabilities in the environment. This method has good measurement stability and high safety. It has been used in flight tests many times. The data measurement effect is good, effectively saving test costs, and the economic benefits are significant.

Description

technical field [0001] The invention relates to the technical field of engine ground measurement, in particular to a timing measurement method for disengagement of an auxiliary support in front of a launch box. Background technique [0002] In the project design of the missile launch box, two front auxiliary support mechanisms are set on the left and right side walls of the box to limit the lateral movement of the missile in the box. After the missile is packed, the two front auxiliary support mechanisms need to be pressed tightly The surface of the missile ensures the safety of the missile. After the missile is ignited, the jet pressure of the engine tail flame directly acts on the back cover of the box. When the back cover breaks, the pressure wave propagates from the tail of the missile to the head of the missile along the axial direction of the box. When it reaches the front cover of the box body, it reaches the cover breaking pressure of the front cover, causing the box...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/14
Inventor 张菩仁张永杰肖健陈璐王求生
Owner BEIJING INST OF STRUCTURE & ENVIRONMENT ENG