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Trajectory capture system for aircraft-missile simultaneous separation simulation

A simultaneous separation and trajectory capture technology, applied in the field of inter-stage separation of aviation vehicles, can solve the problems that simultaneous simulation tests cannot meet

Active Publication Date: 2021-04-13
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: in view of the current prior art, the traditional aircraft-bomb separation ground simulation test can only realize the fixed position and attitude of the aircraft while the real-time simulation of the position and attitude of the aircraft is carried out. The simulated test cannot satisfy the problem, and a trajectory acquisition system for simultaneous separation and simulation of aircraft and bombs is proposed

Method used

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  • Trajectory capture system for aircraft-missile simultaneous separation simulation
  • Trajectory capture system for aircraft-missile simultaneous separation simulation
  • Trajectory capture system for aircraft-missile simultaneous separation simulation

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Embodiment Construction

[0019] A trajectory capture system for the simultaneous separation and simulation of aircraft and bombs, using a double-shaft support mechanism as the support system for the carrier, using a parallel multi-degree-of-freedom mechanism as the support system for the carrier, and performing three-degree-of-freedom attitudes on the model of the carrier and the model of the carrier Simulation, to realize the simultaneous simulation of the position and attitude of the bomb and the carrier aircraft during the separation process of the aircraft and bomb, mainly including the wind tunnel test section, the half-arm angle of attack mechanism, the double-rotary shaft mechanism, the parallel multi-degree-of-freedom bomb-loading support mechanism, and the measurement of the carrier aircraft Balances, aircraft models, bomb-loaded measuring balances, bomb-loaded models, of which:

[0020] The parallel multi-degree-of-freedom bomb-carrying support mechanism is installed on the wall of the wind t...

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Abstract

A trajectory capture system for aircraft-missile simultaneous separation simulation adopts a double-rotating-shaft supporting mechanism as a supporting system of a carrier aircraft and adopts a parallel multi-degree-of-freedom mechanism as a supporting system of a carrier missile to perform three-degree-of-freedom attitude simulation on an aircraft carrier model and a missile carrier model so as to realize simultaneous simulation of positions and attitudes of the missile and the carrier aircraft in an aircraft-missile separation process. The system mainly comprises a wind tunnel test section, a half-arm attack angle mechanism, a double-rotating-shaft mechanism, a parallel multi-degree-of-freedom missile-carrying supporting mechanism, a carrier aircraft measurement balance, a carrier aircraft model, a missile-carrying measurement balance and a missile-carrying model.

Description

technical field [0001] The invention relates to a trajectory capture system for simultaneous separation and simulation of aircraft and bombs, and belongs to the technical field of inter-stage separation of aviation vehicles. Background technique [0002] Launching a large aircraft in the air can increase the initial speed of the aircraft, effectively save fuel or increase the range, and at the same time have higher autonomy and maneuverability. Since the early 1980s, the United States and the former Soviet Union have successively started the development of a number of air-launch projects. The objects of air-launch include air-launched strategic ballistic missiles and air-launched launch vehicles. [0003] The essence of the separation process of air launch is a complex unsteady multi-body separation process. There is serious aerodynamic interference between the external storage and the carrier aircraft. If the launch fails, it will seriously endanger the safety of the carri...

Claims

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Application Information

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IPC IPC(8): G01M9/04B64G7/00
CPCG01M9/04B64G7/00
Inventor 魏忠武谢峰李广良董金刚张晨凯王帅张江秦永明
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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