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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >Advanced Guidance Scheme for Lunar Descent and Landing from Orbital Speed Conditions
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Advanced Guidance Scheme for Lunar Descent and Landing from Orbital Speed Conditions

机译：轨道速度条件下的月球下降和着陆高级制导方案

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摘要

Precise landing technology is one of the most important technologies for future lunar or planetary exploration missions. To achieve a precise landing, an advanced guidance scheme is necessary. This paper outlines a comparison of different solution methods for motion control equations utilized in guidance schemes for lunar descent, and proposes an advanced solution that allows a full depiction of descent vehicle motion from orbital states down to the final landing event. In the conventional solution methods, there exist some poor assumptions such as during descent, constant vertical gravitational acceleration is the only other force acting on the descent vehicle. This inadequate postulation limits the validity of the system solutions within a very low altitude terminal descent area; that is, close to the lunar surface. In this paper, an advanced descent solution is proposed where the centrifugal acceleration term is retained along with the gravitational acceleration term. It allows a complete representation of the descent module motion from orbital speed conditions down to the final landing state. Mathematical derivations of the new scheme are verified in terms of a conventional scheme, and comparative simulation results for a fully integrated solution, conventional schemes and a proposed advanced scheme are demonstrated to test the performance.
机译：精确的着陆技术是未来登月或行星探索任务最重要的技术之一。为了实现精确的着陆，需要先进的制导方案。本文概述了月球下降制导方案中使用的运动控制方程的不同求解方法的比较，并提出了一种先进的解决方案，可以对下降的车辆运动从轨道状态一直到最终着陆事件进行完整描述。在传统的求解方法中，存在一些较差的假设，例如在下降过程中，恒定的垂直重力加速度是作用在下降车辆上的唯一其他力。这种假设不足限制了系统解决方案在非常低的高度终端下降区域内的有效性。也就是说，靠近月球表面。在本文中，提出了一种先进的下降解决方案，其中离心加速度项与重力加速度项一起保留。它可以完整表示下降模块从轨道速度状态到最终着陆状态的运动。对新方案的数学推导根据常规方案进行了验证，并针对完全集成的解决方案，常规方案和建议的高级方案的比较仿真结果进行了测试，以测试其性能。

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