绳系并联支撑飞机模型绕速度矢量旋转运动设计与模拟

doi:10.7527/S1000-6893.2022.28205

Abstract

Abstract:

The wind tunnel tests of rotation around the velocity vector are important in the study on fighter spin and maneuver characteristics at high angle of attack， in which the model suspension is a key issue. This paper innovatively designs rotational methods based on the 6-DOF （degree of freedom） wire-driven parallel suspension mechanism. Firstly， two different methods with constant rotational velocity and constant airflow angles are proposed， and the relationships between the rotational parameters and the model attitude angles are derived. The correlation of the two methods is also expounded. Then， a computed torque control law with the wire length as the control variable is designed based on the dynamic equations of WDPSS. Finally， the proposed design methods are both verified through the ADAMS software simulations and the principle prototype experiments. The results show that the proposed methods allow for the fighter model to achieve complex variable-parameter rotation with variable airflow angles/constant angular velocity or constant airflow angles/variable angular velocity. Furthermore， the method of constant airflow angles can meet the 3-DOF fixed-coupling-ratio relationship， and accurately simulate the erected/inverted spin of the fighter， providing technical support for the in-depth study on spin and maneuvering characteristics at high angle of attack.

Key words: wind tunnel test, wire-driven parallel suspension, velocity vector, spin, high angle of attack, coupling ratio

CLC Number:

V216

Jiajun WANG, Xiaoguang WANG, Chulun SHEN, Qi LIN. Design and simulation of rotation around velocity vector of aircraft model with wire-driven parallel suspension system[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 128205-128205.

Figures/Tables 21

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参数	数值
质量/kg	1.093
x轴转动惯量/（10^-4 kg·m²）	6.84
y轴转动惯量/（10^-4 kg·m²）	8.52
z轴转动惯量/（10^-4 kg·m²）	8.46
机翼参考面积/（10^-2 m²）	1.99
平均气动弦长/m	0.092

i	B_i /m	P_i /m
1	（0.166， 0.42， -1.864）^T	（0， 0.027， -0.01）^T
2	（0.166， -0.42， -1.864）^T	（0， -0.027， -0.01）^T
3	（-0.554， -0.56， -1.864）^T	（-0.208， -0.078， -0.001）^T
4	（-0.554， 0.56， -1.864）^T	（-0.208， 0.078， -0.001）^T
5	（-0.406， 0.45， 0）^T	（-0.208， 0.078， 0.001）^T
6	（0.182， 0.597 5， 0）^T	（0， 0.027， 0.01）^T
7	（0.182， -0.597 5， 0）^T	（0， -0.027， 0.01）^T
8	（-0.406， -0.45， 0）^T	（-0.208， -0.078， 0.001）^T

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Design and simulation of rotation around velocity vector of aircraft model with wire-driven parallel suspension system

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