Design Launch Vehicle Vertical Landing Guidance Law Using a Gauss Point Discrete Convex Programming

2021 ◽  
pp. 3571-3584
Author(s):  
Zhiguo Zhang ◽  
Jinglin Li ◽  
Yin Liu ◽  
Qing Xiao
Keyword(s):  
Convex Programming ◽  
Launch Vehicle ◽  
Gauss Point ◽  
Guidance Law ◽  
Discrete Convex ◽  
Vertical Landing

Design and dynamic analysis of landing gear system in vertical takeoff and vertical landing reusable launch vehicle

2018 ◽  
Vol 233 (10) ◽  
pp. 3700-3713
Author(s):  
Ming Zhang ◽  
Dafu Xu ◽  
Shuai Yue ◽  
Haifeng Tao
Keyword(s):  
General Scheme ◽  
Surface Friction ◽  
Launch Vehicle ◽  
Landing Gear ◽  
Gear System ◽  
Extreme Condition ◽  
Response Characteristics ◽  
Reusable Launch Vehicle ◽  
Vertical Landing ◽  
Vertical Takeoff

Landing gear system is a key part of the implementation of reusable vertical takeoff and vertical landing launch vehicle, where its buffing performance is directly related to the vehicle whether it can land safely or stably. According to the reusable launch vehicle general scheme, outrigger landing legs are designed, and the hydraulic absorber is used for the landing gear system. Meanwhile, a scaling principle prototype of landing gear system is developed, and the landing impact test is carried out. A dynamic simulation model of the landing vehicle has been set up, researching the influence of parameters, such as the horizontal velocity, initial inclination, surface friction coefficient, and pitch angular velocity on the landing performance. Four kinds of extreme conditions are identified, and dynamic response characteristics of landing system under each extreme condition are conducted. The simulation results are in good agreement with the experimental data. The buffing performance of the vehicle meets the design requirements, which provides a reference for the design of landing gear system of the vehicle.

scholarly journals Uncertainty Analysis for Return Trajectory of Vertical Takeoff and Vertical Landing Reusable Launch Vehicle

2020 ◽  
Vol 2020 ◽  
pp. 1-18
Author(s):  
Jian Zhao ◽  
Haiyang Li ◽  
Xiangyue He ◽  
Yuechen Huang ◽  
Jianghui Liu
Keyword(s):  
Uncertainty Analysis ◽  
Expansion Method ◽  
Approximation Problem ◽  
Launch Vehicle ◽  
Random Parameters ◽  
Reusable Launch Vehicle ◽  
Uncertainty Model ◽  
Reliability And Robustness ◽  
Vertical Landing ◽  
Vertical Takeoff

The uncertainties during the return trajectory of vertical takeoff and vertical landing reusable launch vehicle weaken the ability of precision landing and make the return process more challenging. This paper is devoted to quantifying the probability uncertainty of return trajectory with uncertain parameters. The uncertainty model of return multi-flight-phase under the uncertainties of initial flight path angle, axial aerodynamic coefficient, and atmospheric density is established using the generalized polynomial chaos expansion method. By parameterizing random uncertainties and introducing random parameters into the uncertainty model, the uncertainty analysis problem of return trajectory is transformed into stochastic trajectory approximation problem. The coefficients of the polynomial basis function are solved by the stochastic collocation method. Then state solutions, statistical properties, and global sensitivity with Sobol index are established based on coefficients. The simulation results show the efficiency and accuracy of this method compared with the Monte Carlo method, the evolution process of main output parameters under random parameters, and relative importance for random parameters. Through the uncertainty analysis of the return trajectory, the robustness of return trajectory can be quantified, which is contributed to improving the safety, reliability, and robustness of recovery and landing mission.

scholarly journals A New Optimal Guidance Law with Impact Time and Angle Constraints Based on Sequential Convex Programming

2021 ◽  
Vol 2021 ◽  
pp. 1-15
Author(s):  
Pei Pei ◽  
Jiang Wang
Keyword(s):  
Convex Programming ◽  
Optimization Problem ◽  
Impact Angle ◽  
Lateral Acceleration ◽  
Optimal Time ◽  
Proportional Navigation ◽  
Impact Time ◽  
Guidance Law ◽  
Sequential Convex Programming ◽  
Optimal Guidance

This paper proposed an optimal time-varying proportional navigation guidance law based on sequential convex programming. The guidance law can achieve the desired impact angle and impact time with look angle and lateral acceleration constraints. By treating the multiconstraints’ guidance problem as an optimization problem and changing the independent variable to linearize the problem and constraints, the original nonlinear and nonconvex problem is transformed into a series of convex optimization problem so that it can be quickly solved by sequential convex programming. Numerical simulations compared to nonlinear programming and traditional analytical guidance law demonstrate the effectiveness and efficiency of the proposed algorithm. Finally, the proposed guidance law is verified to satisfy different impact time periods and impact angle constraints.

scholarly journals Guidance Law Design for Terminal Area Energy Management of Reusable Launch Vehicle by Energy-to-Range Ratio

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Wen Jiang ◽  
Zhaohua Yang
Keyword(s):  
Energy Management ◽  
Trajectory Planning ◽  
Launch Vehicle ◽  
Reference Trajectory ◽  
Tracking Errors ◽  
Guidance Law ◽  
Reusable Launch Vehicle ◽  
Planning Algorithm ◽  
Flight Profile ◽  
Terminal Area

A new guidance scheme that utilizes a trajectory planning algorithm by energy-to-range ratio has been developed under the circumstance of surplus energy for the terminal area energy management phase of a reusable launch vehicle. The trajectory planning scheme estimates the reference flight profile by piecing together several flight phases that are defined by a set of geometric parameters. Guidance commands are readily available once the best reference trajectory is determined. The trajectory planning algorithm based on energy-to-range ratio is able to quickly generate new reference profiles for testing cases with large variations in initial vehicle condition and energy. The designed flight track has only one turn heading, which simplifies the trajectory planning algorithm. The effectiveness of the trajectory planning algorithm is demonstrated by simulations, which shows that the guided vehicle is able to successfully dissipate energy and reach the desired approach and landing glideslope target with small tracking errors.

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