A novel compact vibration isolator was designed and constructed to attenuate the vibration of space optical payload for a optical remote sensor with a larger aperture and high resolution. The main structural parameters and arrangement forms of the isolator were researched. Firstly, the finite element method was used to analyze the relationship between main structural parameters and three-dimensional stiffness properties of the isolator. Then, the BP network was taken to predict the three-dimensional stiffness of the isolator and to search the structural parameters that accords with conditions of the isolator. A symmetric radial arrangement form of isolator was presented, along with the theoretical model and FEA simulation by combining the general structure of optical payload. Finally, a prototype of the vibration isolator was fabricated and experimental studies were carried out. Experimental results indicate that the natural frequency of the isolator system is approximately 5.31 Hz and the vibration attenuation effect is more than 20 dB when the vibration frequency is higher than 25 Hz. The maximum error of FEA simulation is less than 8% compared with the real test. It is shown that this vibration isolator can attenuate the jitter induced by spacecrafts effectively.