Safety And Envelope Analysis Of Payload Separaton

The instruments that perform specific tasks on satellite or spacecraft are called payload. After the rocket sends a payload to the orbit and the unlocking of connecting structure, the payload separates from the rocket under the separation energy. During the process of separation, to avoid a collision and significant change of angular rate is very important. Excessive angular rate will cause the posture control difficult and the payload can’t even run on the right orbit. The separation safety is a critical factor of the accuracy of orbitting.For the separation safety of payload and rocket, based on ADAMS(multibody dynamics simulation software), a payload separation system with a clamp band as connecting structure was established and the separation process was simulated. The main research includes:1, For the payload separation system with four springs as separation energy, the Newton-Euler equation for rigid body was established. Use MATLAB to solve dynamic equations numerically and compare with the ADAMS results so that the model was verified correct.2, Based on ADAMS, the separation system of the payload and the launch vehicle was established. The effects of centroid of payload, stiffness bias of separation spring, thrust oblique and the preload of clamp band to the angular rate and velocity of payload were studied so as to analyze the separation state precisely.3, Under three deviations—centroid of payload, stiffness bias and thrust oblique, the envelopement analysis for the payload was conducted. The envelope of the part embedded into the adapter was drew under three deviations above and the influence of each deviation was analyzed. The approaches in the assembly process to reduce the bad effect of these deviations were given. The envelopement analysis for the clamp band was conducted. The influence of preload, force of longitudinal restraining spring and the stiffness of lateral restraining spring was analyzed.