Research On The Structural Design And Mechanical Testing Of The Flight Model Of TX-1MiniSatellite

Minisatellite has been developed rapidly all over the world since it has large satelliteincomparable merits such as small volume, light weight, short development cycle, low cost, highfunctional density, transmitting flexible. Minisatellite’s development is an epoch-making revolutionof the international aerospace technology and space technology, and is also a new opportunity andchallenge for Chinese aerospace industry. Under this background, NUAA(Nanjing University ofAeronautics and Astronautics) started a project of TX-1structural stealth minisatellite. Thisdissertation is based on the revised design of TX-1minisatellite, researches on the related designtechnology in structure subsystem. The main work includes:1. Firstly, the plane compressive and bending properties of the aluminum honeycomb sandwichpanels which are most commonly used in the satellite structure are tested. Then based on the testresults, the factors (panel thickness, core thickness, cellular specification) which impact themechanical properties of the honeycomb plates are compared and analysed. Lastly researching on thesimplified methods in building the FEM (finite element model) of the honeycomb plates, determiningthe equivalent method for TX-1satellite by comparing the analysis results of the common equivalenttheories.2. Firstly, the initial design scheme of the Connection and Separation Mechanism is summarized.Then based on the configuration modification requirements and the test conclusion of the initialsatellite, the initial structure is modified by using FEM method and sensitivity analysis theory. Lastly,through static test, the rationality of the modification scheme is verified.3. Firstly, the initial design schemes of the primary load bearing structure and the layout ofsatellite equipments are summarized. Then based on the FEM of the Connection and SeparationMechanism, the FEM of the primary load bearing structure is built, the whole FEM of the satellite isfinished at the same time. Lastly performing design optimization for every component of the primaryload bearing structure through three optimization algorithms in NASTRAN software by using thesatellite stiffness as constraints. And the optimization results have been used as a reference scheme forthe revised design of the structure.4. After modified the minisatellite structure parameters, the optimized FEM is built. By using thePATRAN&NASTRAN software for static analysis, frequency response analysis and random vibrationanalysis, the strength and dynamic response characteristics of the structure parts are checked. The analysis results verify the rationality of the optimization scheme of the satellite structure.5. Based on the results of finite element analysis, the vibration environmental test design schemeis proposed. From x, y, z direction of the satellite, the sine-vibration and random vibration test underacceptance grade are performed. The results of the vibration environmental test show that the revisedsatellite can withstand the launch load, satellite structure design is reasonable and TX-1minisatellitecan be transferred into the launch phase.