landing impact

The main work of this paper includes: Compliance control is realized to absorb the landing impact force.

本文主要研究工作包括：1.实现了机器人着地柔顺控制。

At last, combining the vertical impact model with the horizontal dragging model proposed in the thesis based on trajectory theory, a mechanical model was obtained to describe the interaction between footpad and lunar soil stimulant in landing impact process.

采用运动轨迹理论将本文提出的竖向冲击力学模型和水平拖曳力学模型结合，得到了描述着陆冲击过程中足垫与模拟月壤相互作用力学模型。

Relationship between landing Impact Force and Landing Impact Time in Simulated Parachuting

模拟跳伞着陆冲击力与冲击时间的关系

Analysis of Landing Impact Force of Aircraft Landing Gears Based on the Conception of Landing Aera

基于降落区概念的飞机起落架着陆动力学分析

Landing impact is the dynamic factor that manned spaceship will inevitably meet after the mission has been completed, and impact force may cause damages to human tissuses and organs, even death.

载人飞船完成飞行任务后，着陆冲击是必然要遇到的动力学因素，而冲击力的作用可能引起人体组织或器官的损伤甚至死亡。

Then, the problem of biped walking is studied, and corresponding control strategies are proposed to solve landing impact force and walking stability.

然后针对机器人双足行走存在的问题进行研究，并提出相应的控制策略解决机器人行走的着地冲击与稳定性问题。

Hard Landing Impact of Planet Probe

行星探测器的硬着陆撞击

The landing impact has been recognized as a significant factor in structural fatigue damage, dynamic stress on the aircraft airframe, and crew and passenger discomfort.

而这种冲击载荷被认为是造成飞机及其起落架结构发生疲劳与振动破坏、引起乘员不舒适的重要因素。

To improve the analysis accuracy of soft landing impact response for lunar lander, a method based on nonlinear transient dynamic analysis was presented.

为提高分析月球着陆器软着陆有效载荷着陆冲击响应的准确性，提出一种基于瞬态动力学的着陆器有效载荷软着陆冲击响应分析方法。

Study on Dynamic Response of Thorax under+ Gx Landing Impact by Model and Experiment

＋Gx着陆冲击人体胸部动力学响应的模型及实验研究

The commonly used soft landing cushion devices and the domestic and international mainstream landing impact simulation softwares are described.

论文论述了月球着陆器软着陆技术国内外研究现状，论述了常用的软着陆缓冲装置和国内外主流的着陆冲击仿真软件。

A rigid aeroshell for aerodynamic deceleration and landing impact will result in mass and sizes of the re_entry vehicles exceeding several times those of the payload bus.

长期以来返回式飞行器为承受再入气动载荷和着陆冲击，采用具有防热层的刚性飞行器壳体，导致返回舱的质量和外形大于有效载荷的数倍。

METHODS: Using Hybrid III dummy to put in the backing cabin of space, experiments on landing impact of all levels were carried out and related data were analyzed.

方法：通过Hybrid III型假人，在航天返回舱座椅环境中，进行不同输入量级的复合冲击实验和相关的数据分析。