Investigation on design and reliability analysis of a new deployable and lockable mechanism

Lin, Qing; Nie, Hong; Ren, Jie; Chen, Jinbao

doi:10.1016/j.actaastro.2011.12.004

Cited by 15 publications

(9 citation statements)

References 4 publications

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“…Because other connecting devices have similar properties, guide plugs are used as a representative connecting device in this study; the forces and moments on guide plugs are subsequently introduced and discussed. Each group of guide plugs has two feature points ( 1,2) The constraint on the upper segment is given as…”

Section: Variable Topological Loads Constraintmentioning

confidence: 99%

“…Research on the separation system to date has tended to focus on the specific disciplines and domains, including the separation structure design and failure analysis [1], atmospheric static pressure and aerodynamics regulation during the separation [2], multi-rigid-body motion and collision analysis via Monte Carlo simulation [3], the use of finite elements methods to evaluate the static and dynamic properties of a separation structure in an electrodynamic and flexible multi-body system [4], and the control system design of the separation structure [5].…”

Section: Introductionmentioning

confidence: 99%

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Variable Topological Method for Reliability Assessment of Aerospace Vehicle Separation

Zhou¹,

Li²,

Huang³

2019

Proceedings of the 2019 International Conference on Modeling, Simulation and Big Data Analysis (MSBDA 2019)

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During the launch of a rocket or missile, certain segments must separate from the main body, and the reliability of this separation can affect the final success of the mission. Most reports on the analysis of the specific separation structures employ specific finite element software programs; moreover, although most studies on reliability focus on the simple dynamics of the segments, few consider the separation dynamics in the distribution reliability analysis. Thus, a generalized variable topological dynamics-based aerospace separation reliability analysis method is proposed in this paper. With the exception of a few basic constraints imposed by external forces, a few internal forces in the separation structure derived from the spring oscillator assumption were also included as variable topological constraints. As the craft separated, the variable topological structure constraints changed according to the transfer conditions. The separation reliability criterion was established after modeling the separation dynamics and used to derive the reliability model and the distribution hypothesis test to estimate the separation reliability. Finally, the Monte Carlo separation simulation was conducted to verify the reliability analysis method. The results indicate that the method can effectively estimate the different phases of the separation process and verify the separation reliability of the aerospace vehicle.

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Section: Variable Topological Loads Constraintmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Variable Topological Method for Reliability Assessment of Aerospace Vehicle Separation

Zhou¹,

Li²,

Huang³

2019

Proceedings of the 2019 International Conference on Modeling, Simulation and Big Data Analysis (MSBDA 2019)

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show abstract

“…Öström et al [17] discussed the co-simulation of two models including commercial-off-the-shelf software and low-cost flight simulation model for landing gear. Lin et al [18] proposed the deployment and locking theory of mechanism and analyzed the reliability of a landing gear system from qualitative and quantitative perspectives, by constituting a fault tree. Zhang et al [19] examined the dynamic performance of a landing gear system using ADAMS, during retraction (extension) operations under various flight speeds and hydraulic fluid temperatures.…”

Section: Introductionmentioning

confidence: 99%

Efficient Driving Plan and Validation of Aircraft NLG Emergency Extension System via Mixture of Reliability Models and Test Bench

Zhu

Feng

et al. 2019

Applied Sciences

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The emergence extension system (a mechanical system) of nose landing gear (NLG) seriously influences the reliability, safety and airworthiness of civil aircrafts. To efficiently realize the NLG emergence extension, a promising driving plan of emergence extension is proposed in respect of the reliability sensitivity analyses with a mixture of models. The working principle, fault tree analysis and four reliability models are firstly discussed for NLG emergence extension. In respect of the mixture of models, the reliability sensitivity analyses of emergence extension are then performed under different flight speeds (270 Kts, 250 Kts, 220 Kts, and 180 Kts). We find dimpling torque and aerodynamic torques of forward and after doors are the top three failure factors and the start reliability is the most in emergence extension failures. Regarding the results, feasible driving plans of NLG emergence extension are developed by adjusting the aerodynamic torque of NLG forward door, and are validated by the aerodynamic torque experiment of forward door with regard to strut rotational angle under the flight speed 270 Kts. It is indicated that (1) the adverse torque generated by the new driving mechanism obviously reduces by about 24.8% from 1462.8 N·m to 1099.6 N·m, and the transmission ratio of aerodynamic torque (force) is greatly improved when the NLG strut is lowered near to 100 • ; (2) under different flight speeds (180 Kts, 220 Kts, 250 Kts, and 270 Kts), the new driving mechanism realizes the lower tasks of emergence extension which cannot be completed by the initial driving mechanism; and (3) the lowering time of the new driving mechanism shortens with the increasing flight speed. The proposed new driving mechanism is verified to be reliable for emergence extension of aircraft NLG besides normal extension and to be a promising feasible driving plan with high lowering reliability. The efforts of the paper provide an efficient driving mechanism for the design of NLG in civil and military aircrafts.

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“…Since the 1960s, multi-legged landing systems are considered the state of the art [10] for low-velocity impact during powered descent, while ballistic landing systems have been proposed as well [11]. The reliability of landing systems is critical to the success of the mission [12], both structurally [13,14] as well as functionally [9]. Many effects can contribute to a non-nominal landing procedure, such as a rougher-than-expected terrain [15] or steep slopes [16].…”

Section: Introductionmentioning

confidence: 99%

A New Mechanism for Soft Landing in Robotic Space Exploration

Seriani

2019

Robotics

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Landing safely is the key to successful exploration of the solar system; the mitigation of the connected effects of collision in mechanical systems relies on the conversion of kinetic energy into heat or potential energy. An effective landing-system design should minimize the acceleration acting on the payload. In this paper, we focus on the application of a special class of nonlinear preloaded mechanisms, which take advantage of a variable radius drum (VRD) to produce a constant reactive force during deceleration. Static and dynamic models of the mechanism are presented. Numerical results show that the system allows for very efficient kinetic energy accumulation during impact, approaching the theoretical limit.

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Investigation on design and reliability analysis of a new deployable and lockable mechanism

Cited by 15 publications

References 4 publications

Variable Topological Method for Reliability Assessment of Aerospace Vehicle Separation

Variable Topological Method for Reliability Assessment of Aerospace Vehicle Separation

Efficient Driving Plan and Validation of Aircraft NLG Emergency Extension System via Mixture of Reliability Models and Test Bench

A New Mechanism for Soft Landing in Robotic Space Exploration

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