Landing stability analysis for lunar landers using computer simulation experiments

Liu, Yuanyuan; Song, Sejun; Li, Ming; Wang, Chunjie

doi:10.1177/1729881417748441

Cited by 14 publications

(6 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Table 2 shows the dimension and quality parameters of main and auxiliary pillars. The validity of the dynamics modeling method has been verified by using experiment data by our research team (Liu et al , 2017).…”

Section: Dynamics Modeling Of Landermentioning

confidence: 98%

A comprehensive performance optimization method for the honeycomb buffer of a legged-type lander

Wang

2021

AEAT

Self Cite

View full text Add to dashboard Cite

Purpose In the field of planetary exploration, the legged-type lander is a common landing buffer device. There are two important performance metrics for legged-type landers: the energy absorption capacity and landing stability. In this paper, a novel method is proposed to optimize the honeycomb buffer of a legged-type lander. Optimization design variables are the dimension parameters of honeycomb and the objective functions are the evaluation parameters of the above two performance metrics. Design/methodology/approach A multi-body dynamic model of a lander and a finite-element model of the metal honeycomb are established. Based on the simulation results of the finite-element model and the quartic polynomial, the surrogate models are established to evaluate the energy absorption capacity of honeycomb. Considering both the multi-body dynamic model and the surrogate models, the study designed the optimization flow of dimension parameters of honeycomb. Besides, the non-dominated sorting genetic algorithm II is used for iterative calculation. Findings Images of surrogate models show the monotonous functional relationship between the honeycomb’s energy absorption characteristics and its dimension parameters. Optimization results show an apparent contradiction among the objective functions. Besides, according to the simulation results, this method can significantly improve the comprehensive performance of the lander. Originality/value The novel method can effectively reduce the cost of honeycomb compression tests and improve the lander’s design. Therefore, it can be used for optimizing buffers of other types of legged-type landers.

show abstract

Section: Dynamics Modeling Of Landermentioning

confidence: 98%

A comprehensive performance optimization method for the honeycomb buffer of a legged-type lander

Wang

2021

AEAT

Self Cite

View full text Add to dashboard Cite

show abstract

“…The integral effect increases the response speed for the same relative stability of the system, depending on whether the PI control effect is used in the derivative effect while resetting the permanent state error that may occur in the system. Accordingly, the PID control system provides a quick response with zero permanent state error in the system (Liu et al, 2017). If a system tuned with the PI Controller will affect large intrusive inputs within a wide range of time intervals, the PI effect alone will not be sufficient to track and correct the variations occurring in the line alone.…”

Section: Proportional-integral-derivative Control (Pid) Controlmentioning

confidence: 99%

“…In this control system, RCS actuators, actuators and LEM are the system itself. Due to the constraints of the physical design of the RCS impulse, a step function controller should be used(Apollo 9, 1999;Johannes et al, 2018;Liu et al, 2017). The force axes acting on the Lunar Excursion Module (LEM) are shown in Figure4on the LEM prototype.…”

mentioning

confidence: 99%

Lunar Excursion Module Landing Control System Design with P, PI and PID Controllers

Zenk¹,

Şenol²,

Güner³

2019

Karadeniz Fen Bilimleri Dergisi

View full text Add to dashboard Cite

The development of space technology has always been one of the most exciting areas of science. System, used in the Moon Landing of mankind, became worth examining with developing technologies. In particular, developments in control systems theory have led to significant successes in the control of highly complex systems. It is also possible to reexamine the performance of this system, which is quite costly, by using simulation methods. The vehicle is called as the Lunar Excursion Module (LEM), which brings the astronauts down to the Moon's surface from the space vehicle in the Moon's orbit. Proportional (P), proportional-integral (PI) and proportional-integral-derivative (PID) controllers were prepared for the safe descent of the lunar navigation module modeled using MATLAB / Simulink computer software. These selected controllers ensure that the individually controlled LEM operates in accordance with the rules set out in the current landing procedure in the literature. The most appropriate coefficients for the controllers were selected by using the system response curve and continuous vibration methods and their performances were compared in detail.

show abstract

“…In this paper, the physical parameters of the buffer material were obtained by using the finite element method. The multi-body system dynamics method was selected for the study of the soft-landing characteristics of the whole machine, and was compared with the theoretical calculation results [25].…”

Section: Introductionmentioning

confidence: 99%

Improving the Buffer Energy Absorption Characteristics of Movable Lander-Numerical and Experimental Studies

et al. 2020

View full text Add to dashboard Cite

To improve the soft-landing crash performance of the movable lander (ML), this study presents an investigation of a newly designed gradual energy-absorbing structure subjected to impact loads using an ML for theoretical calculation and numerical simulations. In this work, we present a novel computational approach to optimizing the energy absorption (EA) of the ML. Our framework takes as inputting the geometrical parameter (GP) as well as EA. The finite element model of the HB1, HB2, and HB3 was established and effectively verified using numerical simulation and experimental data. The relationship between the GP of the buffer material and the EA was obtained through static experiment and impact experiment, and the cushioning performance of the lander was optimized according to the ML load mass, contact speed, and EA function. According to the optimization results, we chose an outer diameter of 240 mm, an inner diameter of 50 mm, heights of HB1 = 140 mm, HB2 = 110 mm, and HB3 = 225 as the collocation, and completed the numerical simulation of three different cases. By comparing the results of theoretical calculation and numerical simulation experiments, it can be found that the overload response rates of the main body in 4 type landing, 2-2 type landing, and 1-2-1 type landing are 4.72 G, 2.61 G, and 2.33 G, respectively. It also laid the foundation for the theoretical and methodological research of the ML and manned lander in the future.

show abstract

Landing stability analysis for lunar landers using computer simulation experiments

Cited by 14 publications

References 20 publications

A comprehensive performance optimization method for the honeycomb buffer of a legged-type lander

A comprehensive performance optimization method for the honeycomb buffer of a legged-type lander

Lunar Excursion Module Landing Control System Design with P, PI and PID Controllers

Improving the Buffer Energy Absorption Characteristics of Movable Lander-Numerical and Experimental Studies

Contact Info

Product

Resources

About