本文選題：周邊桁架 + 可展開天線��； 參考：《西安電子科技大學》2014年碩士論文

【摘要】：針對周邊桁架式可展開天線展開過程中非線性因素對展開過程性能的影響,本文對展開過程多柔體動力學分析、軌跡設計及實驗等問題做了較為深入的研究:1.應用模態(tài)綜合理論,對周邊桁架式可展開天線這種典型的多柔體系統(tǒng)進行了動力學建模,考慮摩擦、間隙、阻尼等非線性因素,并初步分析了單元展開不同步性和索網(wǎng)預張力對展開過程性能的影響。通過典型案例,分析周邊桁架式可展開天線在軌環(huán)境下的展開過程動力學響應,為有效進行展開過程軌跡設計打下了基礎。2.針對空間可展開天線沖擊過大的問題,提出了一種考慮星-天動力耦合的展開過程軌跡設計方法。首先,建立了空間可展開天線在軌展開時天線展開運動和衛(wèi)星本體姿態(tài)穩(wěn)定的耦合動力學模型;其次,利用貝塞爾曲線合成驅(qū)動索的運動軌跡,通過可展開天線的動力耦合作用得到天線展開過程中星-天系統(tǒng)的運動軌跡;然后,基于優(yōu)化方法同時選擇天線的展開軌跡及時間,在滿足衛(wèi)星本體偏轉(zhuǎn)角和偏轉(zhuǎn)角速度性能指標的約束下,確定可展開天線展開時間的下限參考值。最后結(jié)合數(shù)值仿真算例,說明了該軌跡設計方法的合理性和有效性。3.針對展開過程涉及的若干復雜非線性動力學問題,參與研制了2m口徑的周邊桁架式可展開天線實物模型。系統(tǒng)設計了展開過程動力學的實驗方案,對展開過程動力學實驗結(jié)果進行了詳細分析。4.完善了綜合設計平臺中的“展開過程動力學分析”模塊,包括可展開天線參數(shù)化多體動力學模型的建立及動力學分析和動響應預測,詳細介紹了平臺的界面、功能,并進行了算例驗證。
[Abstract]:Aiming at the influence of nonlinear factors on the development performance of peripheral truss deployable antennas, the dynamic analysis, trajectory design and experiment of multi-flexible bodies during expansion are studied in this paper. Based on the modal synthesis theory, the dynamic modeling of a typical multi-flexible system, such as the peripheral truss deployable antenna, is carried out. The nonlinear factors such as friction, clearance and damping are considered. The effects of the unsynchronicity of the element expansion and the pretension of the cable mesh on the performance of the expansion process are analyzed. The dynamic response of the unfolding process of the peripheral truss deployable antenna in orbit environment is analyzed by a typical case, which lays a foundation for the effective design of the deployable track. In order to solve the problem of excessive impact of deployable antenna, a trajectory design method for space deployable antenna is proposed in this paper, which considers the star-space dynamic coupling. First of all, the coupled dynamic model of antenna deployment and satellite body attitude stability is established when the space deployable antenna is in orbit. Secondly, the trajectory of the driving cable is synthesized by using the Bezier curve. Through the dynamic coupling of the deployable antenna, the trajectory of the star-sky system is obtained, and then, based on the optimization method, the trajectory and time of the antenna are selected simultaneously. Under the constraint of satellite body deflection angle and angular velocity, the lower limit reference value of deployable antenna is determined. Finally, the rationality and validity of the trajectory design method are illustrated by numerical simulation examples. Aiming at some complex nonlinear dynamic problems involved in the development process, a physical model of a 2m diameter peripheral truss deployable antenna is developed. The experimental scheme of unfolding process dynamics is designed, and the experimental results of unfolding process dynamics are analyzed in detail. The development process dynamic analysis module of the integrated design platform is perfected, including the establishment of parameterized multi-body dynamics model of deployable antenna and the dynamic analysis and dynamic response prediction. The interface and function of the platform are introduced in detail. A numerical example is given.
【學位授予單位】：西安電子科技大學
【學位級別】：碩士
【學位授予年份】：2014
【分類號】：TN820

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本文編號：2035505