A full free-flying wind tunnel test device with parallel interstage separation

Abstract

The invention discloses a parallel stage separation all-free-flight wind tunnel test device, which comprises a first-stage model, a second-stage model, an upper support rod, a lower support rod, a pull pin, a rotating shaft, an upper fastening nail, a lower fastening nail, an upper spring and a lower spring. The upper spring and the lower spring are sleeved on the upper fastening nail and the lower fastening nail respectively. The upper fastening nail and the lower fastening nail pass through the first-stage model and the second-stage model along model centroids, and one end is cooperated withpositioning blind holes in the models and is fixed axially, and the other ends are respectively provided with through holes. The pull pin and the upper and lower support rods sleeve the rotating shaft and can rotate around the rotating shaft. During installation, one end of the pull pin is inserted into upper and lower fastening nail through holes, the upper spring and the lower spring are in a compressed state, and the upper support rod and the lower support rod are abutted against the two stages of models; and during separation, the pull pin is pulled out quickly due to traction of externalforce, the two stages of models are unlocked, and the upper support rod and the lower support rod continue to support the first-stage model and the second-stage model to prevent relative position ofthe two models from changing abruptly. The device can ensure quick, effective and interference-free separation when the first-stage model and the second-stage model are separated.

Description

technical field [0001] The invention relates to the support and launch of a wind tunnel test model, in particular to a parallel-connected inter-stage separation fully free-flying wind tunnel test device, which belongs to the field of aerospace engineering. Background technique [0002] The model free-flying wind tunnel test is a commonly used research method to study the dynamic aerodynamic characteristics of aircraft, and it can also be used in the research of aircraft multi-body interference. The basic method of the test is to eject the model at high speed against the direction of the airflow after the flow field in the wind tunnel is stabilized. The model will fly freely in the wind tunnel for a short time to test the safety of the separation of the multi-stage aircraft. At the same time, high-speed photography is used to monitor the model through the observation window. After shooting, the attitude trajectory of the aircraft model flying freely can be obtained, and the d...

AI Technical Summary

Problems solved by technology

Because the mass of the two stages is equal, a certain distance between the two stages often causes the center of mass of the aircraft to be located in the gap between the two stages before separation, and there is no model entity as a support to design and install the separation mechanism. The tests have brought about great technical difficulties

The first-level and second-level models must exist as a rigid whole before separation, and there must be no degree of freedom for relative movement. This requires that the model fixing mechanism must be firmly fixed. When the separation is performed, the model as a whole is in a free state and can be unlocked. The action needs to be completed by itself, and the unlocking action must be fast and effective without affecting the attitude of the model. At the same time, the wind tunnel test model is often small, and the superposition of many problems makes the realization of the full free-flying wind tunnel test technology separated between parallel stages difficult. more difficult

[0004] The full free-flying wind tunnel test technology for series inter-stage separation is relatively mature, but the full free-flying wind tunnel test technology for parallel inter-stage separation is difficult to realize due to the existence of the above problems

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