微小卫星太阳帆板压紧释放机构的设计

Design of hold-down and release mechanism for solar panel of micro-satellite

为实现某型号微小卫星太阳帆板的压紧释放,研制了一种小型熔线式压紧释放机构。首先,设计了可测量预紧力的压紧机构,得到扭矩与预紧力的2倍关系,给出了预紧力的确定方法。然后,根据绳索特点,设计了具有电阻调节功能的解锁机构,增强了对电源的适应能力,满足了微小卫星快速模块化布局。最后,进行了熔断特性实验与熔断参数设计,得到熔断时间与电流的函数关系,确定了该型号卫星解锁的熔断功率为6.25 W,熔断时间为(6±1)s。开展了实验室环境与真空环境下的可靠性验证实验,结果表明:所设计的压紧释放机构工作可靠,适用于微小卫星展开机构,且具有较好的通用性与扩展性。该项研究对微小卫星太阳帆板压紧释放装置设计和空间展开机构设计具有指导意义。

To achieve the hold-down and release for a solar panel of micro-satellites, a small-scale fuse holding-down and release mechanism was developed. Firstly, the hold-down mechanism for measuring pretightening force was designed to acquire the twice relationship between torque and pretighteningforce and a determination method of pretightening force was given. Then, according to the features of rope, the unlocked mechanism with resistance regulatory function was designed to improve the adap- tive capacity of power supply and to meet the requirements of rapid modularization layout of micro-sat- ellites. Finally, a fusing characteristic experiment and the fusing parameters for the mechanism were designed to obtain the function relationship between fusing time and currents. It shows that the un- locked fusing power of this mechanism for micro-satellites is 6.25 W, the fusing time is （6±1） s. Thereliability demonstration experiment was also carried out under the environments of laboratory and vacuum. The results show that the hold-down and release mechanism designed is suitable for the un- folding mechanism of micro-satellites, which is reliable work and has better universality and expansi- bility. It offers a certain guiding significance for design of hold-down and release devices and spatial deployable mechanisms for solar panels of micro-satellites.