A model launching device and its application

A technology for launching devices and models, which is used in measuring devices, testing of machines/structural components, instruments, etc. It can solve the problems of safe launching launch devices for unseen models, and achieve long flight time, high use efficiency and fast launch speed. Effect

Active Publication Date: 2020-08-04
中国空气动力研究与发展中心超高速空气动力研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there is currently no report on a launching device that can safely launch the model into the uniform flow field of the wind tunnel in the hypersonic wind tunnel test environment without interfering with the free flight of the test model.

Method used

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  • A model launching device and its application
  • A model launching device and its application
  • A model launching device and its application

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Embodiment Construction

[0034] In order to make the purpose, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are the embodiment of the present invention. Some examples, but not all examples. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0035] The present invention provides a model launching device in a first aspect, figure 1 It is a structural schematic diagram of a model launching device in a specific embodiment of the present invention; figure 2 yes figure 1 Enlarged view of part A in the middle; image 3 yes figure 1 Enlarged view of part B in; Figure 4 yes figure 1 Schematic diagram ...

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Abstract

The invention relates to a model launchingdevice and application thereof. The device comprises a sleeve, a three-level air cylinder, a two-level air cylinder and a one-level air cylinder which are coaxially arranged and sequentially connected; a model holder and a clamp limited by the sleeve are arranged in the sleeve; a three-level piston rod provided with a three-level piston rod plug and an airguiding groove are arranged in the three-level air cylinder; a two-level air cylinder cover provided with a communication groove is arranged at one end of the two-level air cylinder, and a two-levelpiston rod which is operationally clamped to the interior of the communication groove or breaks away from the communication groove is arranged in the two-level air cylinder; a one-level plug, a one-level piston, a spring base and a compression spring provided with pre-tightened load are arranged in the one-level air cylinder, and the two-level piston rod is sequentially sleeved with a one-level plug and a one-level piston; and a cavity is formed between the one-level plug and the one-level piston, and the one-level air cylinder is provided with a two-level air cylinder air inlet communicated with the two-level air cylinder and a one-level air cylinder air inlet communicated with the cavity. The device provided by the invention achieves free flight of a hypersonic speed wind tunnel test model in the uniform flow field.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel model free flight test, and in particular relates to a model launching device and its application. Background technique [0002] With the expansion of the flight envelope of modern fighter jets and missiles, including maneuvering at high angles of attack and with sideslips, nonlinear flow phenomena appearing under these conditions will have a strong impact on the dynamic stability of the aircraft. To predict the dynamic characteristics of the aircraft, it is necessary to establish its dynamic model and obtain its dynamic stability derivative, which is an important prerequisite and basis for effective aircraft control system design, flight quality evaluation and ground simulation. [0003] The dynamic stability research of aircraft mainly relies on flight test and wind tunnel simulation test at present. The wind tunnel test methods for dynamic stability can be divided into two categ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08G01M9/04G01M9/06
CPCG01M9/04G01M9/065G01M9/08
Inventor 何超马晓宇谢飞许晓斌朱涛
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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