空間飛行器分離仿真試驗臺的研究
發(fā)布時間：2019-02-26 07:50
【摘要】：在探月三期中,繞月飛行的探月飛船的軌道艙和返回艙要實現(xiàn)分離,分離的成功與否關(guān)乎飛船能否正常完成探月任務(wù)。這就需要在地面上用試驗臺模擬空間零重力環(huán)境下軌道艙和返回艙的分離運動。通過仿真試驗?zāi)軝z驗分離機構(gòu)的可靠性和分析艙段分離后的運動規(guī)律。本論文所設(shè)計的空間飛行器仿真試驗臺就是用來完成此項仿真任務(wù)。經(jīng)過權(quán)衡各種零重力模擬方法的利弊,采用了平面氣浮軸承和高精度調(diào)心球軸承相結(jié)合的方案,對核心部件十字軸和抗彎件的裝配體進行了多目標優(yōu)化設(shè)計。設(shè)計了試驗臺的整體結(jié)構(gòu),并進行校核。對動剛度較差的G艙模擬器進行了模態(tài)分析獲得了前四階固有頻率和振型,從基頻可看出G艙段模擬器的抗振性能滿足要求。對結(jié)構(gòu)設(shè)計的難點質(zhì)量慣量模擬機構(gòu)的設(shè)計方案進行了研究。由于質(zhì)量特性方程未知數(shù)多,次數(shù)高,且非線性,傳統(tǒng)的符號推導(dǎo)直接求解法只能求得部分虛數(shù)解。采用分塊求解和迭代求解的方法可以快速解得尺寸參數(shù)。分析推導(dǎo)了關(guān)節(jié)測量裝置的測量精度。采用固定一個艙段,降低模型自由度的方法,建立了地面5自由度動力學(xué)模型和空間6自由度動力學(xué)模型。采用四階/五階龍格-庫塔法求解動力學(xué)微分方程,求得數(shù)值解并分析了地面環(huán)境和空間環(huán)境兩種狀態(tài)下分離過程姿態(tài)速度變化規(guī)律。利用ADAMS軟件分別模擬空間環(huán)境和地面環(huán)境的分離過程,得到的規(guī)律和動力學(xué)方程求解的規(guī)律相符,表明動力學(xué)模型的有效性。分析了自由度缺失、摩擦阻力矩和試驗臺非完全體對分離的影響,結(jié)果表明地面分離仿真試驗臺能夠有效模擬空間分離過程。
[Abstract]:In the third phase of lunar exploration, the orbital module and the return module of the lunar spacecraft flying around the moon should be separated, and the success of the separation is related to the normal completion of the lunar exploration mission. It is necessary to simulate the separation motion of the orbital cabin and the return module in the space zero gravity environment with a test rig on the ground. Through the simulation test, the reliability of the separation mechanism can be verified and the movement rule of the separated cabin can be analyzed. The space vehicle simulation test-bed designed in this paper is used to complete this simulation task. After weighing the advantages and disadvantages of all kinds of zero gravity simulation methods, the multi-objective optimization design of the cross shaft and anti-bending assembly of the core component is carried out by using the combination scheme of the plane air bearing and the high precision concentric ball bearing. The whole structure of the test-bed is designed and verified. The first four natural frequencies and mode shapes of G-cabin simulator with poor dynamic stiffness are obtained by modal analysis. It can be seen from the fundamental frequency that the anti-vibration performance of G-cabin simulator meets the requirements. The design scheme of mass inertia simulation mechanism which is difficult in structural design is studied. Because of the unknown number, high degree and nonlinearity of the mass characteristic equation, the traditional symbolic direct solution can only obtain the partial imaginary solution. The size parameters can be quickly solved by block solving and iterative solution. The measurement precision of joint measuring device is analyzed and deduced. The dynamic models of 5 degrees of freedom on the ground and 6 degrees of freedom in space are established by using the method of fixing a segment and reducing the degree of freedom of the model. The fourth-order / fifth-order Runge-Kutta method is used to solve the dynamic differential equation. The numerical solution is obtained and the variation rule of attitude velocity in the separation process is analyzed under the two states of ground environment and space environment. The separation process of space environment and ground environment is simulated by ADAMS software, and the law obtained is consistent with the law of solving dynamic equation, which shows the validity of the dynamic model. The effects of the absence of degrees of freedom, friction resistance torque and non-completion of the test bench on the separation are analyzed. The results show that the ground separation simulation test-bed can effectively simulate the spatial separation process.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V416.8
本文編號：2430580
[Abstract]:In the third phase of lunar exploration, the orbital module and the return module of the lunar spacecraft flying around the moon should be separated, and the success of the separation is related to the normal completion of the lunar exploration mission. It is necessary to simulate the separation motion of the orbital cabin and the return module in the space zero gravity environment with a test rig on the ground. Through the simulation test, the reliability of the separation mechanism can be verified and the movement rule of the separated cabin can be analyzed. The space vehicle simulation test-bed designed in this paper is used to complete this simulation task. After weighing the advantages and disadvantages of all kinds of zero gravity simulation methods, the multi-objective optimization design of the cross shaft and anti-bending assembly of the core component is carried out by using the combination scheme of the plane air bearing and the high precision concentric ball bearing. The whole structure of the test-bed is designed and verified. The first four natural frequencies and mode shapes of G-cabin simulator with poor dynamic stiffness are obtained by modal analysis. It can be seen from the fundamental frequency that the anti-vibration performance of G-cabin simulator meets the requirements. The design scheme of mass inertia simulation mechanism which is difficult in structural design is studied. Because of the unknown number, high degree and nonlinearity of the mass characteristic equation, the traditional symbolic direct solution can only obtain the partial imaginary solution. The size parameters can be quickly solved by block solving and iterative solution. The measurement precision of joint measuring device is analyzed and deduced. The dynamic models of 5 degrees of freedom on the ground and 6 degrees of freedom in space are established by using the method of fixing a segment and reducing the degree of freedom of the model. The fourth-order / fifth-order Runge-Kutta method is used to solve the dynamic differential equation. The numerical solution is obtained and the variation rule of attitude velocity in the separation process is analyzed under the two states of ground environment and space environment. The separation process of space environment and ground environment is simulated by ADAMS software, and the law obtained is consistent with the law of solving dynamic equation, which shows the validity of the dynamic model. The effects of the absence of degrees of freedom, friction resistance torque and non-completion of the test bench on the separation are analyzed. The results show that the ground separation simulation test-bed can effectively simulate the spatial separation process.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V416.8
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