## 1 Introduction  
Synthetic aperture radar (SAR), proposed in the 1960s is able to obtain high-quality images regardless of day/night or whether condition of the target area [1, 2]. Due to this image acquisition performance, the demand for SAR imaging technology is rapidly increasing in various sectors including government, military, and commercial sectors [3, 4]. In general, the image acquisition performance of a satellite antenna is determined by the dimension of the antenna aperture, because the antenna transmits electromagnetic waves and receive backscattered signals from the target object. However, SAR-based antennas are mounted on a moving platform and receive backscattered signals at a moving location, the distance between the original and new position make a virtual antenna size that is wider than the size of the physical antenna. Therefore, the SAR-based antenna is advantageous to obtain the precise satellite image. Because the diameter of the physical antenna is also very important, the configuration of the satellite antenna should be the deployable configuration that is launched in the fairing of a limited volume. This type of antenna has the advantage of having high storage efficiency because it may be loaded in a storage state even in physically limited projectile pairing [5; 6; 7; 8]. Several studies have been conducted to develop a deployable reflector antenna. In 1999, [PERSON] proposed a ring-truss type of deployable mesh antenna [9]. In 2003, [PERSON] et al. proposed the beam steering method of mesh antenna and performed experimental verification for the beam steering performance [7]. In addition, [PERSON] et al. designed and verified the deployment mechanism of the ring-truss type mesh antenna numerically and experimentally [8]. The mesh antenna studied in the above three literatures can be used in the satellite antenna with a large diameter relative to its weight, but has the low stiffness property of the reflective surface, it is possible to cause relatively high surface error. The high surface error of the mesh antenna deteriorates the quality of satellite images, and the low dynamic stiffness causes a problem of delaying the photographing preparation time by causing large vibrations during the attitude controls [10]. From this point of view, it is necessary to develop a solid type deployable reflector antenna using a CFRP honeycomb sandwich structure [11; 12]. The deployable reflector antennas require high reliability for not only the deployment mechanism in the orbital environment but also the restriction force for the stowed condition in the launch environment. The deployable reflector antenna proposed in the series of papers is operated by the deployment mechanism with the constant force spring (CFS) of the hinge part in the orbital environment and maintains the stowed condition by the hold-and-release synchronizing mechanism (HRSM) at the top and the hold-and-release belt mechanism (HRBM) in the middle. Therefore, the three types of the hold-and-release mechanisms consisting of metallic material and the main reflector and main structure, which are composite material should ensure structural stability for the launch environment. Satellites are subjected to the high-level dynamic loads during the launch process. During the launch process, the combustion noise of the launch vehicle is reflected on the ground surface and transmitted into the launch vehicle, and the flow-induced noise caused by friction between the outer surface of the launch vehicle and the air is also transmitted into the fairing of the launch vehicle. This noise creates a severe reverberation sound field inside the fairing in the vehicle. In addition, this wideband air-born noise creates random vibrations in the satellite and payload. Because of the pitch maneuver to enter the mission orbit, the launch vehicle experiences a periodic load due to the fuel injection cycle of the sub engine. This periodic load causes a sinusoidal load on the satellite and payload.