In order to study the structure stability of precision support components made of the carbon fiber composites (CFRP) in the large-aperture space optical remote sensor

a CFRP joint cylinder between primary mirror and second mirror was designed and manufactured. The mechanical model of the joint cylinder was established. The material’s laying way of the component and relevant parameters were calculated based on the method of finite element analysis. The structure stability of the joint cylinder was validated through the test. First

The maximum deflection was calculated according to the angle changed between primary mirror and second mirror. The mechanical model of the joint cylinder was established according to the true load. Then

the axial elastic modulus based on the model was calculated. Following

the material’s laying way of the component was determined by the composite laminate theory. Second

the angle between the two mirror

and the modal distribution of support structure were calculated based on the software ANSYS. Finally

the structure stability was validated by the mechanic test and optical measurement method. The results show that the angle between primary mirror and second mirror was less than 10″

the first-order natural frequency of CFRP support components is greater than 75 Hz. CFRP support have better structure stability

having reached to the requirement of general technology index.