隐身微小卫星结构设计关键技术研究
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摘要
在国防军事需求和空间资源探索的牵引下，人造卫星正朝着微型化、功能化和模块化方向快速发展。伴随微机电、新型材料等高新技术的不断革新，小型卫星和微小卫星的发展正在世界上蓬勃兴起。作为整个卫星系统的重要技术基础，结构设计技术不仅直接关系到卫星发射的成败，同时也是实现整星总体综合性能的基本保障。因此，本文以南京航空航天大学自主研制的某隐身微小卫星为背景，从卫星隐身构型设计、主承力结构设计、结构多目标优化设计以及力学环境试验设计等关键技术展开研究，具体工作如下：
1．针对微小卫星隐身构型的设计需求，根据多棱面设计思路，在满足运载给出的约束条件及总体性能需求下，提出了一种底部为六棱柱、中部为六棱台、顶部为六棱锥的钻石结构隐身构型设计方案。通过分析卫星的散射特性，采用高频散射理论对其雷达散射截面积进行了预估，并在微波暗室对全尺寸全金属卫星模型进行了C波段测试验证。通过对比分析确定了隐身构型设计方案的合理性。
2、提出了一种框架和箱板式结构相结合的微小卫星主承力结构设计方法，该方法不仅能满足主传力路径的合理性和主承力结构的刚度，而且能实现星载设备的合理布局。以某微小卫星为例，在其隐身构型的基础之上，对其主承力结构进行了系统设计，并对适配器、底板和隔板等主要承力部件进行了详细设计。
3．选取整星刚度和结构重量为目标函数，以各蜂窝夹层板的面板和蜂窝芯子厚度为设计变量，对其主承力结构进行多目标优化设计。针对复杂工程优化问题所构建的近似模型精度较低的情况，提出了一种改进的基于信赖域的近似模型管理框架。该方法的优点在于在求解过程中受近似模型精度的影响较小，通过最大最小距离法从上一步迭代过程中得到的Pareto最优解集中挑选距离最大的若干个解用于高精度模型评价，并根据信赖度值的大小对搜索限制域进行更新，从而保证得到与实际模型一致的Pareto最优解集。通过四组经典测试函数的测试后将该方法成功运用于整星主承力结构多目标优化设计中，得到了较为满意的Pareto最优解集。最后采用模糊综合评判法选取了最终设计方案，并就整星刚度和主结构质量较优化前进行了对比分析，取得了较好的优化效果。
4．通过对初始模型参数的修正得到了优化后的整星有限元模型，运用PATRAN/NASTRAN软件对其进行了静力分析，考核了优化后整星的结构强度。同时，根据卫星总体及星上单机的设计要求，对整星进行了频率响应分析和随机振动分析，获取了主承力结构各主要部件及星载设备的动态响应特性。为后续力学环境试验方案的设计提供了参考依据。
5．考虑到卫星结构设计对可靠性要求较高，在仿真分析的基础之，根据卫星在发射和飞行期间所经受的力学环境及其自身特点，提出了初样星的力学环境试验设计方案。该方案以验证初样星结构设计及其优化方法的合理性为主要目的，以获取整星主承力结构和星载设备的静动态特性及工程可靠性为主要任务。通过对整星在验收级和鉴定级条件下正弦和随机振动试验数据的采集分析，验证了有限元模型构建及近似模型管理方法的有效性和合理性。此次力学环境试验为正样星结构局部调整以及今后其他微小卫星的结构设计、力学环境试验方案的设计提供了可靠依据。
Under the needs of national military and sapce resources exploration, the satellite is developingforword to miniaturization, functionalization and modularization rapidly. By continuously renew ofthe micro electromechanical, new material and other hi-tech, the development of small satellite andmicro satellite is springing up over the world. As the important technical foundation for satellitesystem, structure design is not only directly related to the success of the satellite launch, but also is thebasic guarantee for the satellite comprehensive properties implementation. Taking the stealth microsatellite as the background, which is designed by Nanjing university of aeronautics andastronautics, the researchs were carried out form the ascepts of stealth configuration design, primaryload bearing structure design, structure multi-objective optimization design and dynamicenvironmental test design. The concrete contents are as following:
1. By meeting the needs of dimension constraints and the stealth performance, according to thepolygon design thought, a diamond-type configuration design scheme is proposed. Its bottom ishexagonal-prism, the middle is hexagonal-prismoid and the top is hexagonal-pyramid. By analyzingthe scattering characteristics of the mirco satellite, the radar scattered section is predicted using highfrequency methods. A real-size metal satellite model is made for the RCS measurement at C bands ina microwave darkroom. By comparison and analysis, the rationality of the scheme is determined.
2. A method for primary load bearing structure of the micro satellite is proposed. The method notonly meets the need of structure stiffness and rationality for the force transfer path, but alsoimplements the layout of the satellite equipments. Taking the stealth mirco satellite for example, theprimary load bearing structure is designed comprehensive, based on the stealth configuration. Thesatellite adapter, the floor, the diaphragm and other force bearing parts are also designed respectively.
3. The multi-objective optimization design is carried out for the primary load bearing structure ofthe micro satellite.Both the satellite stiffness and the primary load bearing structure mass is taken asthe objective function. The design variable contains the thickness of aluminum panels, core plates andskeleton. An improved trust-region approximation model management frame is proposed subject tothe low precision of the ordinary approximation model for comprehensive engineering problems. Theadvantages of this method are that the optimization results are little influenced by approximationmodel during the solving process. By using max-min distance means, several maximum distancesolutions evaluated by real model are selected from the last pareto optimization solutions. Then, searching area is renewed according to the evaluation result, thus the final solutions are uniform to thereal pareto solutions. The method is demonstrated by four different classical test functions andsuccessfully applied in the micro satellite structure optimization design. By comparing with the valuesof the objective function after optimization, good effect is obtained.
4. After modified the micro satellite structure parameters, the optimized FEM is built. By usingthe PATRAN/NASTRAN software for static analysis, the satellite strength is evaluated. Meanwhile,according to the general and equipments design requirements of the satellite, frequency responseanalysis and random vibration analysis are calculated in the software. From the analysis andcalculation, the dynamic response characteristics of the structure parts and equipments are obtained.Meanwhile, the results provide reference for dynamic environmental test design.
5. Considering the high reliability for satellite structure design, the mechanical environmentaltest design scheme is proposed, based on the simulated results. It takes the aim at verifying therationality of the structure design and optimization method, requiring the structure static and dynamiccharacteristics. By acquiring and analyzing the sine-vibration and random vibration test datas underacceptance and identification grade, the effectiveness and rationality of the approximation modelmanagement method and the FEM building is verified. The mechanical environmental test providereliable basis for formal satellite local adjustment and other micro satellites structure and test designin future.
1．针对微小卫星隐身构型的设计需求，根据多棱面设计思路，在满足运载给出的约束条件及总体性能需求下，提出了一种底部为六棱柱、中部为六棱台、顶部为六棱锥的钻石结构隐身构型设计方案。通过分析卫星的散射特性，采用高频散射理论对其雷达散射截面积进行了预估，并在微波暗室对全尺寸全金属卫星模型进行了C波段测试验证。通过对比分析确定了隐身构型设计方案的合理性。
2、提出了一种框架和箱板式结构相结合的微小卫星主承力结构设计方法，该方法不仅能满足主传力路径的合理性和主承力结构的刚度，而且能实现星载设备的合理布局。以某微小卫星为例，在其隐身构型的基础之上，对其主承力结构进行了系统设计，并对适配器、底板和隔板等主要承力部件进行了详细设计。
3．选取整星刚度和结构重量为目标函数，以各蜂窝夹层板的面板和蜂窝芯子厚度为设计变量，对其主承力结构进行多目标优化设计。针对复杂工程优化问题所构建的近似模型精度较低的情况，提出了一种改进的基于信赖域的近似模型管理框架。该方法的优点在于在求解过程中受近似模型精度的影响较小，通过最大最小距离法从上一步迭代过程中得到的Pareto最优解集中挑选距离最大的若干个解用于高精度模型评价，并根据信赖度值的大小对搜索限制域进行更新，从而保证得到与实际模型一致的Pareto最优解集。通过四组经典测试函数的测试后将该方法成功运用于整星主承力结构多目标优化设计中，得到了较为满意的Pareto最优解集。最后采用模糊综合评判法选取了最终设计方案，并就整星刚度和主结构质量较优化前进行了对比分析，取得了较好的优化效果。
4．通过对初始模型参数的修正得到了优化后的整星有限元模型，运用PATRAN/NASTRAN软件对其进行了静力分析，考核了优化后整星的结构强度。同时，根据卫星总体及星上单机的设计要求，对整星进行了频率响应分析和随机振动分析，获取了主承力结构各主要部件及星载设备的动态响应特性。为后续力学环境试验方案的设计提供了参考依据。
5．考虑到卫星结构设计对可靠性要求较高，在仿真分析的基础之，根据卫星在发射和飞行期间所经受的力学环境及其自身特点，提出了初样星的力学环境试验设计方案。该方案以验证初样星结构设计及其优化方法的合理性为主要目的，以获取整星主承力结构和星载设备的静动态特性及工程可靠性为主要任务。通过对整星在验收级和鉴定级条件下正弦和随机振动试验数据的采集分析，验证了有限元模型构建及近似模型管理方法的有效性和合理性。此次力学环境试验为正样星结构局部调整以及今后其他微小卫星的结构设计、力学环境试验方案的设计提供了可靠依据。
Under the needs of national military and sapce resources exploration, the satellite is developingforword to miniaturization, functionalization and modularization rapidly. By continuously renew ofthe micro electromechanical, new material and other hi-tech, the development of small satellite andmicro satellite is springing up over the world. As the important technical foundation for satellitesystem, structure design is not only directly related to the success of the satellite launch, but also is thebasic guarantee for the satellite comprehensive properties implementation. Taking the stealth microsatellite as the background, which is designed by Nanjing university of aeronautics andastronautics, the researchs were carried out form the ascepts of stealth configuration design, primaryload bearing structure design, structure multi-objective optimization design and dynamicenvironmental test design. The concrete contents are as following:
1. By meeting the needs of dimension constraints and the stealth performance, according to thepolygon design thought, a diamond-type configuration design scheme is proposed. Its bottom ishexagonal-prism, the middle is hexagonal-prismoid and the top is hexagonal-pyramid. By analyzingthe scattering characteristics of the mirco satellite, the radar scattered section is predicted using highfrequency methods. A real-size metal satellite model is made for the RCS measurement at C bands ina microwave darkroom. By comparison and analysis, the rationality of the scheme is determined.
2. A method for primary load bearing structure of the micro satellite is proposed. The method notonly meets the need of structure stiffness and rationality for the force transfer path, but alsoimplements the layout of the satellite equipments. Taking the stealth mirco satellite for example, theprimary load bearing structure is designed comprehensive, based on the stealth configuration. Thesatellite adapter, the floor, the diaphragm and other force bearing parts are also designed respectively.
3. The multi-objective optimization design is carried out for the primary load bearing structure ofthe micro satellite.Both the satellite stiffness and the primary load bearing structure mass is taken asthe objective function. The design variable contains the thickness of aluminum panels, core plates andskeleton. An improved trust-region approximation model management frame is proposed subject tothe low precision of the ordinary approximation model for comprehensive engineering problems. Theadvantages of this method are that the optimization results are little influenced by approximationmodel during the solving process. By using max-min distance means, several maximum distancesolutions evaluated by real model are selected from the last pareto optimization solutions. Then, searching area is renewed according to the evaluation result, thus the final solutions are uniform to thereal pareto solutions. The method is demonstrated by four different classical test functions andsuccessfully applied in the micro satellite structure optimization design. By comparing with the valuesof the objective function after optimization, good effect is obtained.
4. After modified the micro satellite structure parameters, the optimized FEM is built. By usingthe PATRAN/NASTRAN software for static analysis, the satellite strength is evaluated. Meanwhile,according to the general and equipments design requirements of the satellite, frequency responseanalysis and random vibration analysis are calculated in the software. From the analysis andcalculation, the dynamic response characteristics of the structure parts and equipments are obtained.Meanwhile, the results provide reference for dynamic environmental test design.
5. Considering the high reliability for satellite structure design, the mechanical environmentaltest design scheme is proposed, based on the simulated results. It takes the aim at verifying therationality of the structure design and optimization method, requiring the structure static and dynamiccharacteristics. By acquiring and analyzing the sine-vibration and random vibration test datas underacceptance and identification grade, the effectiveness and rationality of the approximation modelmanagement method and the FEM building is verified. The mechanical environmental test providereliable basis for formal satellite local adjustment and other micro satellites structure and test designin future.
引文
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