Wind tunnel dynamic force measurement test device for canard configuration rotating missile

Abstract

The invention discloses a wind tunnel dynamic force measurement test device for a canard configuration rotating missile. The device comprises a tail supporting rod, a test missile model, a steering engine driving mechanism, a force measurement balance, a fixed sleeve, an autorotation driving mechanism and a data acquisition and processing system, wherein the test missile model has a cavity and is provided with a deflectable nose control; the steering engine driving mechanism drives the nose control to deflect, and is arranged in the front of the cavity; the fixed sleeve is arranged in the back of the cavity, the rear end of the fixed sleeve is connected to the front end of the force measurement balance, and the test missile model is rotationally sleeved outside the fixed sleeve; the autorotation driving mechanism is arranged inside the fixed sleeve, and a power output shaft extends out of a front opening of the fixed sleeve and drives the test missile model to rotate; and the data acquisition and processing system is in communication connection to the force measurement balance to receive force measurement data of the force measurement balance. The device realizes autorotation of the canard configuration rotating missile and deflection of the nose control, realizes measurement of aerodynamic force and torque, and is particularly suitable for force measurement test of large length-diameter ratio test missile models in 1.2m sub-trans-supersonic wind tunnels.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a wind tunnel dynamic force measurement test device for a canard layout rotating missile. Background technique [0002] "Magnus effect" refers to the lateral aerodynamic force and moment effect perpendicular to the incoming flow and the rotation axis when the aircraft is flying at an angle of attack due to the rotational motion around the body axis and the lateral flow. Although the magnitude of the Magnus force is small, it has an important influence on the dynamic stability of the rotating projectile under the conditions of different flight Mach numbers and different angles of attack. [0003] Tactical rockets that rotate around the axis of their own projectiles during flight are divided into two categories, one is uncontrolled rotary rockets, and the other is controlled (duck rudder control, duck rudders can also be called front rudder) rotary rockets. When the test...

AI Technical Summary

Problems solved by technology

For the controlled rotating projectile with a large length-to-diameter ratio, due to the existence of the canard, the canard will produce a wash flow to the tail when there is an angle of attack, and the state of the wash flow also has a non-negligible change with the length of the projectile body. Therefore, for It is not advisable to shorten the length of the straight section of the rocket with a large slenderness ratio

In addition, if the model is made larger and the length-to-diameter ratio remains unchanged, the length of the test model will increase accordingly, but this can only reduce the range of angle of attack, and cannot meet the requirements of the model design scheme

[0004] Most of the Magnus effect test devices in today’s 1.2-meter-level wind tunnels are aimed at the self-rotation test of small aspect ratio rotating projectiles, that is, the tail support method is usually used, and a force-measuring balance is installed inside the model to measure the force of the model when blowing. Aerodynamic force and moment, the bearing structure is designed inside the test model, so that the missile or the rotating tail can rotate freely, and partially simulate the rotation effect of the missile during flight. This method has three shortcomings: 1) the speed is difficult to simulate; 2) the speed of the missile It changes with the angle of attack, that is, the speed is unstable; 3) It is difficult to simulate the control force exerted by the canard deflection on the missile

The motor is also placed in the wind tunnel and directly connected to the model, but the size of the motor must be small, and it is mostly used for the uncontrolled rotation model with a small aspect ratio; so far, it has not been obtained on the controlled rotation model with a large aspect ratio. At the same time, in order to more realistically simulate the effective combination of self-rotation and canard deflection of the controlled rotating missile in the air, the design of adding canard control on this basis is still in a blank stage

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