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Mechanism to control the roll of the separated body model

A separate body model and resolver technology, applied in the direction of attitude control, etc., can solve the problems of limiting the range of movement of the model, loss of system design displacement, and increasing working time, so as to avoid errors, control response time is short, and ensure accuracy.

Active Publication Date: 2017-09-05
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Considering space constraints and interference, most of the rolling motion mechanisms in the domestic trajectory capture system currently use the way of turning joints, and the rolling motion mechanism is installed at a position far from the model, thereby reducing the impact of the rolling motion mechanism on the tail of the model. Disturbance of the flow field (attached Figure 4 ), but in the rolling process of the rolling motor driving the turning joint, the model has displacements in other directions besides rolling, which needs to be compensated to make the model reach the real position, and the design displacement of the loss system limits the model itself. Range of movement with more error and increased work time

Method used

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  • Mechanism to control the roll of the separated body model
  • Mechanism to control the roll of the separated body model
  • Mechanism to control the roll of the separated body model

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Embodiment Construction

[0028] The specific embodiments of the present invention will be further described in detail according to the accompanying drawings.

[0029] Such as figure 1 , 2 As shown, the mechanism for controlling the roll of the separation body model applied to the trajectory capture system of the present invention is installed in the sleeve 3 in series by the drive control device for controlling the roll of the separation body model, and is connected to the supporting balance and the separation body through the joint 2 The support rod 1 of membrane type is connected, and the rear end of sleeve 3 is equipped with tail cone 14, like this, when the mechanism of control separation body model roll of the present invention is applied in experiment, its clogging degree is low (referring to image 3 ), and because the drive control mechanism directly controls the rotation of the support rod 1 through the joint, and the support rod 1 drives the rotation of the membrane type of the separator, ...

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Abstract

The invention provides a rolling attitude motion mechanism of a missile applied to a trajectory capture system, the main purpose of which is to realize the roll of a launch model around its own axis in a multi-body separation trajectory capture test in a wind tunnel. It includes a support rod, a joint, a sleeve, a drive control device and a tail cone. One end of the support rod is fastened to the front end of the joint in a manner concentric with the central axis, and the other end is used to install the balance and the separation body model. The joint can It is installed at the front opening of the sleeve in a freely rotating manner. The joint has a rear end shaft. When the joint is installed on the sleeve, the rear end shaft extends into the sleeve, and the drive mechanism is integrally installed on the sleeve. Inside, the drive shaft of the drive control device is fastened to the rear end shaft, so that the rear end shaft can be driven to drive the joint and the support rod to rotate, and the tail cone is blocked in the rear end opening of the sleeve . The mechanism has low clogging degree, high control precision, short control response time and high rigidity.

Description

technical field [0001] The invention relates to a mechanism for controlling the roll of a separated body model applied to a trajectory capturing system, and belongs to the field of experimental aerodynamics. Background technique [0002] The trajectory capture system is a wind tunnel test system that simulates the separation between aircraft stages in the wind tunnel test, and the mutual interference flow field between the separation body and the parent body when the aircraft bomb and external storage are separated. During the test, according to the installation in the separation body model The aerodynamic force measured by the balance is used to solve the flight mechanics equation to obtain the attitude and displacement of the separated body model in the next step. The computer inputs commands into the multi-degree-of-freedom motion mechanism, and each motion mechanism completes the position and posture of the separated body model according to the instructions. Change. [...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 胡浩黄兴中蔡琛芳秦永明张江
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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