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为了研究新型连续地月转移系统的动力学及能量需求,采用Lagrange方法,在系绳为刚性杆假设的前提下,同时忽略第三体引力、地球扁率和系绳轴向变形等扰动因素的影响,建立了驱动型动量交换绳系卫星(MMET)系统的三维刚性动力学模型。对所建立的动力学模型进行了数值仿真及对比分析,仿真结果验证了所建模型的正确性。研究表明,外力矩对系统轨道运动参数影响甚小,对姿态运动参数影响明显。采用MMET方式进行载荷转移,推导出了实现载荷地月轨道转移所需的入口速度条件以及时间周期条件,并求解出了载荷在2次任务之间的时间间隔。给定初始条件下,当MMET系统以0.231 6rad/s的旋转角速度绕其质心旋转1 448.5圈,其绕地心刚好运行5圈时,载荷可顺利进入地月转移轨道。最后,对连续地月转移系统实现载荷的地月转移进行了能量对比分析,结果表明,相同条件下,MMET载荷转移方式相比于传统脉冲变轨方式在载荷转移过程中消耗更少的能量。
In order to study the dynamics and energy requirements of a new continuous ground-motion transfer system, Lagrange method is used to disregard the disturbing factors such as the gravitational force of the third body, the oblateness of the earth and the axial deformation of the tether under the premise of the rigid rod assumption of the tether , A three-dimensional rigid dynamic model of MMET system is established. The established dynamic model is numerically simulated and comparatively analyzed. The simulation results verify the correctness of the model. The research shows that the external moment has little effect on the orbital motion parameters and has obvious influence on the attitude motion parameters. The MMET method is used to carry out the load transfer. The entry speed conditions and the time period conditions for the lunar orbit transfer of the load are deduced, and the time interval between the two tasks is solved. Under the given initial conditions, when the MMET system revolves around its center of mass at 1 448.5 revolutions at a rotational angular velocity of 0.231 6 rad / s, its load can smoothly enter the Earth-Moon transfer orbit when it runs just 5 times around the center of the Earth. Finally, energy balance analysis of ground-moon transfer with continuous monthly transfer system load is carried out. The results show that the MMET load transfer method consumes less energy during load transfer compared with the traditional pulse-orbit mode under the same conditions.