<論文>減速機構試験装置によるパラシュートの研究

概要

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A deceleration system simulator has been developed in order to investigate aerodynamic characteristics of parachute in air-stream of the 2 mφ low speed wind tunnel of Institute of Space and Aeronautical Science, University of Tokyo, and also to simulate a controlled parachute system there in which the model parachute is controlled by extending and/or retracting 8 suspension lines independently, according to respective control signals. The performance of the simulator has been examined preliminarily in the low speed wind tunnel by using small model parachutes of 30-60 cm in deployed cross-sectional diameter, and it has been found that the simulator functionates satisfactorily. Some experiments of parachute deployment have been conducted and the results of opening load behavior have been compared with the numerical result obtained from the analysis. It has been shown that both results are in good agreement with each other. Brief qualitative discussion has been made on the feasibility of practical application of the controlled parachute system to a recovery system of rocket pay-load.
宇宙航空研究開発機構の論文