Optimized Design Of Space Camera Frame Structure

The space camera is one of the important cores of space remote sensor.With the improvement of observation requirements,the aperture of space camera becomes larger and larger,and the overall mass of the camera becomes larger and larger.Therefore,while ensuring the image quality of the camera,the highly lightweight stable support structure has become the main research direction.In a certain space camera support structure as the research object,according to the development and current situation of the development of aviation remote sensors and aerial remote sensors,and reference for domestic and foreign various classic airlines main support structure of remote sensor,this paper introduces structure of airborne remote sensing,from theoretical analysis,the choice of materials,structure optimization design,the simulation analysis and experimental verification,etc to study the stability of the space camera frame.From the space environment and space of the camera by the camera to realize two imaging work into consideration,it design the camera frame not only to meet the installation requirements of various optical devices,and ensure that optical device in all kinds of mechanical environment to be able to keep the original position accuracy,stable imaging,for example in the gravity deformation,vibration,shock,noise environment,such as the framework can provide enough stiffness for the camera.According to the design requirements,to consider the choice of space camera frame material density,elastic modulus,linear expansion coefficient of factors,such as lower quality at the same time,guarantee the stability of the camera at the same time due to the shape of the frame is usually irregular,also consider the processing factors,so all aspects of performance,frame materials can choose commonly used low volume fraction of aluminum silicon carbide composite material,and materialperformance,can be widely used in various fields of carbon fiber composite materials.In the design of a space camera frame made of aluminum?base silicon carbide composite material with low volume fraction,the topological optimization of the frame structure should be carried out by using the finite element method,so as to optimize the structural form of the frame,ensure the stability of the structure and reduce the quality of the frame.In addition,the optimized frame should be simulated and analyzed to calculate the mechanical properties of the frame.In the same optical system,the application of carbon fiber composite materials in the design of support structure usually needs to start from the discussion of the properties of carbon fiber materials,including the stiffness and strength of carbon fiber materials,etc.,to study the influence of the cladding mode of carbon fiber composite materials and the connection mode of embedded parts on the stability of the frame.In addition,the finite element method is also needed to simulate and analyze the carbon fiber frame and compare the calculated results with those of the low?volume sub?frame.The results of mechanical experiments are one of the important bases for the design of space camera and also an important means to verify the accuracy of finite element simulation analysis.Therefore,it is necessary to understand the principle of vibration experiment,accurately simulate the environmental conditions of the experiment,and carry out sinusoidal vibration experiment on the space camera frame made of carbon fiber composite materials.The experimental results show that the stability of the carbon fiber frame meets the use requirements,and the accuracy of the finite element model analysis is also verified.