Inter-stage separation wind tunnel test device and method based on two sets of motion mechanisms

A motion mechanism and inter-stage separation technology, applied in the field of aerodynamic wind tunnel tests in the aerospace industry

Active Publication Date: 2019-02-01
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

[0003] The purpose of the present invention is to provide a kind of inter-stage separation wind tunnel test device and test method based on two sets of kinematic mechanisms, through four degrees of freedom motion parameters to solve the complete simulation problem of aircraft front and back, stage separation motion in the vertical plane

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  • Inter-stage separation wind tunnel test device and method based on two sets of motion mechanisms

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[0050] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0051] Such as figure 1 , a kind of interstage separation wind tunnel test device based on two sets of kinematic mechanisms of the present invention includes an upper mechanism 1, an upper support arm 2, a front stage balance 3, a front stage model 4, a rear stage model 5, a rear stage balance and a balance Prop 6, lower arm 7, lower mechanism 8, upper leading screw 9, lower leading screw 10, upper motor 11, lower motor 12, upper driver 13, lower driver 14, control machine 15. The connection method of the device is that the front and rear models are respectively connected with the upper and lower drive systems to form two sets of independent motion systems. The specific connection method: the aircraft front model 4 is connected to the upper support arm 2 through the front balance 3 front and r...

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Abstract

The invention provides an inter-stage separation wind tunnel test device and method based on two sets of motion mechanisms. According to the device and method, the two sets of motion mechanisms located in a wind tunnel chamber are utilized to drive front-stage and rear-stage models of an aircraft to independently move so as to simulate flight attitudes and relative positions, two sets of balancesare utilized to measure aerodynamic loads of the front-stage and rear-stage models, a dynamic equation and a kinematic equation are solved in respective body axis systems the front stage and the rearstage of the aircraft, attitudes and relative positions of front stage and the rear stage of the aircraft are calculated to ensure that a driving system adjusts the wind tunnel test model to a targetvalue, and the above processes are repeated to realize the inter-stage separation trajectory simulation test. The device and method are capable of realizing the effective simulation of respective attitudes of the front stage and the rear stage the aircraft in inter-stage separation flight and the simultaneous measurement of interference dynamic and kinematic force, independently solving motion parameters of the front stage and the rear stage of the aircraft and truly reproducing the independent motion processes of the front stage and the rear stage of the aircraft during the inter-stage separation, and can be applied to the full speed ranges of cross-supersonic wind tunnels.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic wind tunnel tests in the aerospace industry, and in particular relates to an inter-stage separation wind tunnel test device and a test method based on two sets of motion mechanisms. Background technique [0002] At present, there are mainly three experimental research methods for inter-stage separation problems: (1) Mesh force measurement test technology is used to measure the aerodynamic force of the model under the pre-specified relative position lattice and relative attitude conditions. The aerodynamic coefficients of the subsequent model are obtained from the model disturbance flow field. Then the dynamics and kinematics models of the front and rear stages of the aircraft are established, and the aerodynamic force is obtained by interpolation means as input, and the kinematic parameters are solved under the given initial state conditions, the separation trajectory is obtained by simulation...

Claims

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Application Information

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IPC IPC(8): G01M9/02G01M9/06G01M9/08
CPCG01M9/02G01M9/06G01M9/08
Inventor 钱丰学高鹏张新明刘奇郭鹏王元靖畅利侠王红彪易国庆
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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