Currently, the aspheric mirrors used in space remote sensors are generally supported with a supporting structure containing a flexible link and a backboard. Because the supporting structure accounts for a large proportion in weight, its configuration and weight should be simplified and reduced respectively. According to the principle of three-point orientation and bipod flexure, three flexible link structures for simplifying the configuration of the support are designed. The design result is analyzed by using a finite element software. The result shows that this support configuration is able to adapt the mechanical and thermal environment in space. It can meet the required precision and can be used to support large diameter aspheric mirrors. Because the mirror backboard commonly used in the traditional configuration is removed, this support configuration is simplified. Its weight is reduced and its machining and assembling difficulties are also reduced.