Design and Test of a Deployment Mechanism for the Composite Reflector Antenna

복합재료 반사판 안테나의 전개 메커니즘 설계 및 시험

Abstract

The dynamic characteristics of the deployable composite parabolic reflector with several panels were numerically and experimentally investigated. The deployment mechanism is designed to efficiently fit in a small volume. The parameters guiding the deployment are determined by considering; the number of panels, folding/twisting angles, and the driving forces of actuating devices. The panels are fabricated using carbon fiber reinforced plastics (CFRPs). The zero-gravity simulator is manufactured for the unfolding test. The deployment behaviors of the reflector are finally observed.

여러 패널들로 파라볼라 반사판 형상을 가지는, 전개형 복합재료 안테나의 동적 특성을 수치적 그리고 실험적으로 살펴보고자 한다. 전개 장치들은 여러 패널들이 작은 공간에 효과적으로 수납될 수 있도록 설계하였다. 반사판 패널의 개수, 패널들의 폴딩(folding)/트위스팅(twisting) 각도, 그리고 전개 작동기 등의 특성을 고려하여 전개시 필요한 설계변수를 결정하였고, 반사판 패널은 CFRP(carbon fiber reinforced plastics)으로 제작하였다. 무중력 전개장치를 제작하여 반사판 안테나의 전개시험을 수행하였고, 동적 전개특성을 관찰하였다.

Fig. 1 TRW sunflower antenna

Fig. 2 DAISY antenna

Fig. 3 Zero-gravity deployment device with trolleys and rails

Fig. 4 Zero-gravity setting with helium balloons.

Fig. 5 Zero-gravity tracking system

Fig. 6 Parabola reflector model

Fig. 7 Rotated reflector panel

Fig. 8 Folded reflector antenna panels

Fig. 9 Deploying trajectory of panels

Fig. 10 Manufactured CFRP panel

Fig. 11 Twisting/folding deployment device

Fig. 12 Deploying sequences of reflector antenna

Fig. 13 Joint device between composite panels and aluminium parts

Fig. 14 Folded composite reflector panels

Fig. 15 Deployed composite reflector panels

Fig. 16 Zero-gravity deployment device

Fig. 17 Air bushing system

Fig. 18 Zero-gravity deployment test system

Fig. 19 Inverted pendulum model

Fig. 20 Deployment angle with respect to time

Fig. 21 Deployment sequences with respect to time

Fig. 22 Measured force applied to the panel during the deployment

Table 1 Designed configuration of the reflector antenna