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

Wang, Hui; He, Tian-Xiao; Wang, Chunjie

doi:10.1108/aeat-02-2021-0043

Cited by 5 publications

(3 citation statements)

References 36 publications

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“…Apparently, compared with the supporting leg recovery mentioned in Wang et al, 9 the proposed cable-net buffer device can simplify the cumbersome legs on the first stage into hooks, and therefore reduce the overall design difficulty and the cost of losing carrying capacity due to recovery. At the same time, when the first stage is recovered using supporting leg device according to Wang et al 29 and Wu et al, [30][31][32] the mass center of the first stage is above the legs. In this case, when the landing attitude angle or attack angle is too large, the first stage will overturn.…”

Section: Functional Principlementioning

confidence: 99%

A novel cable-net buffer device for recovering reusable launch vehicle: Design, dynamic modeling, and performance analysis

Wang,

Xiang,

Zhang

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part C:

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At present, reusable launch vehicle technology (RLV) has become a research hotspot in the aerospace field and one of the major development trends in this industry. With reference to the aircraft carrier’s arresting cable technology, this paper puts forward a novel cable-net buffer device for recovering the first stage of launch vehicle. The device can transfer load through a cable-pulley mechanism, and then complete the first stage recovery by losing the kinetic energy and gravitational potential energy of the first stage through hydraulic dampers and preloaded counterweights. In order to analyze the performance of this cable-net buffer device, the finite element software ABAQUS is adopted to establish a rigid-flexible coupling dynamic model. In this model, the cable-pulley mechanism is simulated by connector and shell elements, the damping force of the hydraulic dampers by VUAMP subroutine, and the preloaded counterweights by mass point. And then, performance evaluation indexes of this buffer device are proposed in this paper. Meanwhile, the dynamic simulation, using the established dynamic model, is carried out under different device design parameters and working condition parameters. On the one hand, the simulation results show that the tower span and damping force have remarkable effects on the buffer performance. On the other hand, among all working condition parameters, only the fall point deviation has a significant effect on the buffer performance, but this effect is less than that of the design parameters. Finally, combing the dynamic model and the surrogate model technique, this paper obtains feasible boundaries of design parameters of the device for the subsequent detailed design of it. Researches in this paper will provide new ideas for the development of RLV.

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Section: Functional Principlementioning

confidence: 99%

A novel cable-net buffer device for recovering reusable launch vehicle: Design, dynamic modeling, and performance analysis

Wang,

Xiang,

Zhang

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part C:

Self Cite

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“…Figure 1 shows the typical design structure of the LBM from a Chinese lunar lander, which includes a primary strut, two secondary struts, and a foot-pad [30,31]. The primary strut cushions the longitudinal impact load, while two secondary struts cushion the transverse impact load.…”

Section: A Reliability Series Model For the Lbmmentioning

confidence: 99%

Reliability Assessment for a Spacecraft Landing Buffer Mechanism Based on Small Sample Data

Li,

Fu,

2023

Machines

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The landing buffer mechanism (LBM) is a crucial component of aerospace landing explorations, determining the success of the entire mission. Reliability demonstration tests (RDTs) are required to ensure the LBM’s performance meets the design index. However, the RDTs of the LBM often encounter limited samples and zero-failure data, making traditional binominal test programs and reliability assessment methods based on the maximum likelihood theory unsuitable. This paper introduces a novel small-sample test verification method for the LBM, which transforms traditional binominal tests into more informative metrological tests by measuring the buffer strokes of the LBM’s subsystems. Furthermore, a confidence limit theory for the product of subsystem reliability is developed in conjunction with the reliability series model of the LBM. This theory can use the measurement data of subsystems to assess the confidence limit of the LBM’s reliability. An actual engineering application demonstrates that the proposed method can effectively handle zero-failure data and verifies that the LBM’s reliability exceeds 0.9999 with a confidence of 0.9.

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“…The buffering material used in the four-legged landing gear of vehicles is two-stage aluminum honeycomb. Aluminum honeycomb material is not only environmentally friendly, low-cost, and easy to shape, but also has the advantages of light weight, high strength, good buffering performance [1,20,21], high surface flatness, etc. ; these characteristics satisfy all the requirements for the buffering material of the legged landing gear of a vehicle [6,22].…”

Section: Introductionmentioning

confidence: 99%

The Impact Modeling and Experimental Verification of a Launch Vehicle with Crushing-Type Landing Gear

Wang

Xie

et al. 2023

Actuators

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In order to investigate the landing process of a vertical landing reusable vehicle, a dynamic model with a complex nonlinear dissipative element is established based on the discrete impulse step approach, which includes a three-dimensional multi-impact model considering friction and material compliance, and a multistage aluminum honeycomb theoretical model. The normal two-stiffness spring model is adopted in the foot–ground impact model, two motion patterns (stick and slip) are considered on the tangential plane and the structural changes caused by buffering behavior are included, and the energy conversion during the impact follows the law of conservation of energy. The state transition method is used to solve the dynamic stability convergence problem of the vehicle under the coupling effect of impact and buffering deformation in the primary impulse space. Landing experiments on a scaled physical reusable vehicle prototype are conducted to demonstrate that the theoretical results exhibit good agreement with the experimental data.

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

Cited by 5 publications

References 36 publications

A novel cable-net buffer device for recovering reusable launch vehicle: Design, dynamic modeling, and performance analysis

A novel cable-net buffer device for recovering reusable launch vehicle: Design, dynamic modeling, and performance analysis

Reliability Assessment for a Spacecraft Landing Buffer Mechanism Based on Small Sample Data

The Impact Modeling and Experimental Verification of a Launch Vehicle with Crushing-Type Landing Gear

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