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Test method for verifying ejection separation of cruise aircraft assembly

A cruise flight and test method technology, applied in the field of aviation, to achieve the effect of simple form, easy implementation, and large adjustable range

Inactive Publication Date: 2020-10-09
BEIJING SPACE TECH RES & TEST CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The unlocking and separation of the catapult is difficult to simulate by simulation analysis, so it must be verified by special tests

Method used

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  • Test method for verifying ejection separation of cruise aircraft assembly
  • Test method for verifying ejection separation of cruise aircraft assembly
  • Test method for verifying ejection separation of cruise aircraft assembly

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Embodiment Construction

[0023] In order to more clearly describe the embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings that are used in the embodiments. Apparently, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to these drawings without creative efforts.

[0024] When describing the embodiments of the present invention, the terms "vertical", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", " The orientation or positional relationship expressed by "horizontal", "top", "bottom", "inner" and "outer" is based on the orientation or positional relationship shown in the relevant drawings, which are only for the convenience of describing the present invention and simplifying the description, and It is not to indicate or imply that the device or element referred to must have a particu...

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Abstract

The invention relates to a test method for verifying ejection separation of a cruise aircraft assembly. The test method comprises the steps of S1, simulating an actual aircraft by adopting an aircraftmass characteristic simulation tool; S2, adjusting the position of the mass center of the aircraft mass characteristic simulation tool relative to an ejection point to be consistent with that of an actual aircraft; S3, installing a catapult to the position of a connecting interface of the aircraft mass characteristic simulation tool, and applying pre-tightening force the same as that of installation of the actual aircraft; and S4, installing a thrust sensor at the other end of the catapult, then placing the aircraft mass characteristic simulation tool on four pulleys, and installing the thrust sensor on an ignition test bed. According to the method, the specially designed aircraft mass characteristic simulation tool is concise in form and large in adjustable range, and can meet the requirements of multiple working conditions; adopted instruments and equipment are measuring tools commonly used in a laboratory; the test method is very easy to implement, so that the test method has relatively high popularization and application values.

Description

technical field [0001] The invention belongs to the field of aviation technology, and in particular relates to a test method for verifying ejection separation of cruise aircraft assemblies. Background technique [0002] The catapult is a device used to realize the fast connection between the aircraft and the rocket, and to provide the separation speed for the cruise flight combination when separating. At the moment of catapult detonation, the separation speed and attitude changes of the aircraft are directly related to the success or failure of the space launch mission. The catapult relies on the impact force generated by the explosion of gunpowder to achieve unlocking and separation, and the data is highly discrete. It is necessary to evaluate the impact of the explosion before finally determining the design of the aircraft. The unlocking and separation of the catapult is difficult to simulate by simulation analysis, so it must be verified by special experiments. Content...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 付新卫刘群石泳张志贤
Owner BEIJING SPACE TECH RES & TEST CENT
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