Main body and separation body track capture experiment motion distribution method for continuous on-orbit motion

Abstract

The invention discloses a main body and separation body track capture experiment motion distribution method for continuous on-orbit motion. The method comprises the following steps: acquiring the current poses of a separation body model and a main body model at the current moment to obtain the theoretical poses of the separation body model and the main body model at the next time step length, andcalculating the relative position change distances in the X, Y and Z directions; distributing the movement of the main body mechanism and the separation body mechanism according to the stroke allowance proportion; and controlling the main body mechanism and the separation body mechanism to complete X-direction, Y-direction and Z-direction movement and respective angle movement to reach the theoretical poses of the main body model and the separation body model of the next time step length. According to the method, the main body mechanism and the separation body mechanism can be prevented from moving in the same direction, the utilization rate of experiment space is increased, longer experiment time and more captured track point positions are obtained, the service life of the main body mechanism and the separation body mechanism is prolonged, and the method has the advantages of simple and rapid calculation and efficient and reliable operation.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a motion distribution method for a track capture experiment of a main body and a separate body moving continuously on orbit. Background technique [0002] At present, research on aircraft, spacecraft, and flying weapons around the world is inseparable from wind tunnel experiments. Wind tunnel experiments are an effective way to analyze the aerodynamic characteristics of objects, study airflow laws, and study the aerodynamic interaction of adjacent aircraft. The wind tunnel experiment reduces the size of the aircraft, creates a stable hypersonic flow field, and obtains the most realistic and reliable aerodynamic data to verify the aerodynamic characteristics of the aircraft. [0003] The current wind tunnel experiments are not satisfied with only obtaining the aerodynamic characteristics of the aircraft in a fixed attitude, but also need to further...

AI Technical Summary

Problems solved by technology

Because the main body model and the separation body model are in the same flow field, it is very easy to produce the same direction movement, and the degrees of freedom of the main body and the separation body mechanism are limited, the main body or the separation body mechanism will be in a certain position of the main body model or the separation body model. Stop running when one degree of freedom reaches the limit. Obviously, the utilization of the experimental space is extremely low, and the number of captured trajectory points will be greatly reduced.

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