Aiming at the threats to spacecraft safety caused by space debris, and improving the stability and working life of spacecraft in orbit, it is proposed to use spacecraft equipped with a safety self-perceptual optical payload to detect space debris to improve the safety of the aircraft in orbit. This paper analyses the application methods and characteristics of the safety self-perceptual optical payload of space vehicles, and defines the technical indicators of the optical payload. The safety self-Perceptual optical payload includes the MWIR optical system with large field of view and the visible continuous zoom lens with large zoom ratio. The detector resolution is 1280x1024, the pixel size is 15 mu m, the focal length is 8mm, the F number is 2, and the field of view is 97.6 degrees x85 degrees of MWIR optical system; The detector resolution is 1920x1080, the pixel size is 5.5 mu m, the focal length is 15mm similar to 750mm, which has a 50 times zoom ratio, and the field of view is 38.8 degrees x22.4 degrees similar to 0.80 degrees x0.45 degrees of the visible continuous zoom lens. The two systems are athermal designed in the temperature range of -40 degrees C similar to 60 degrees C respectively to meet the environmental requirements of space applications. Safety self-perceptual optical payload could obtain, and apperceive long-range targets in the 10km range around the space vehicle, and improve the aircraft's survival ability.