Rapid Trajectory Optimization for the ARES I Launch Vehicle

This paper is concerned with ascent guidance for solid rocket, whose kinetic parameter with large deviation at each stage is a challenging problem for terminal multiconstraints. A guidance algorithm based on least square method and Newton iteration is developed at each stage to solve this problem. The angle of attack (AOA) and yaw angle of current stage are main variables and these angles of the latter stages are instrumental variables. Closed-loop iterative guidance is applied in last phase of the third stage. In the simulation part, two integrated guidance methods (IGM) containing perturbation and iterative guidance applied for different stages and one method of iterative guidance for three stages (IGTS) are analyzed to compare the performance of these guidance algorithms. The results show that the second IGM can effectively revise the influence of the thrust deviation produced by the first and second stage, whose robustness is better than the first IGM. In addition, the robustness of the IGTS is best compared with the first and the second IGM, and the range of propulsion error that the IGTS can fix is the largest among these methods.

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“…According to Taylor formula, the matrix of deviations can be expressed as follow (9) In this equation,…”

Section: Iterative Guidance Algorithmmentioning

confidence: 99%

An ascent iterative guidance algorithm for solid rocket concerned with multiconstraints

Jing

Wei

et al. 2015

The 27th Chinese Control and Decision Conference (2015 CCDC)

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“…The goal of trajectory optimal planning is to find the optimal control function ȝ(E) which consist of Į(E) and Ȗ(E) to satisfy the following equations 11,12 .…”

Section: Guidance Law Designmentioning

confidence: 99%

An online predictive reentry guidance law for reusable launch vehicles

Chen

Yan

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

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Space applications have raised the demand on autonomy, security and reliability for current reusable launch vehicle (RLV), which require guidance technology of vehicle must have strong robustness and adaptability. Based on preliminary research results, this paper outlines a method of developing an online predictive reentry trajectory planning and guidance law which use both angle-of-attack and angle-of-bank variations to control the reentry trajectory. The trajectory planning is done with the landing point prediction, which induce the energy as the integration variable instead of the time in order to solve the time uncertainty of the reentry process. The reentry dynamical model is built firstly According to the RLV mathematical model and the constraint equations. As the trajectory planning is classified as a two-point boundary value problem, Secondly the constrained optimal problem is converted to an unconstrained optimal problem by introducing augmented state vector. Finally, a numerical solution based on the simplex reflection technique (one of the optimized methods) is employed to solve the unconstrained optimal problem, and the entry online guidance law is achieved. Simulations with the vehicle and trajectory data demonstrate good performance of the guidance algorithms. The main novelty of this work is in applying a new online predictive energy-based guidance strategy that has desirable features as a reference trajectory for tracking.

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“…The method is applied to three realistic test cases for spaceplane-based launch vehicles, optimising the ascent, descent and abort trajectories and some key vehicle and mission design variables. A considerable amount of work has been devoted to the off-line optimisation of ascent and re-entry trajectories for launch systems with the inclusion of progressively more sophisticated physics and constraints examining the launch system design and performance [29][30][31][32][33], and the fast and robust generation of a guidance law with the ultimate goal to have an on-line closed loop guidance update [34][35][36][37][38][39]. This paper departs from these two streams of research, and focuses on the off-line generation of Pareto optimal trade-off solutions for a generic multi-objective optimal control problem.…”

Section: Introductionmentioning

confidence: 99%

Direct Solution of Multi-Objective Optimal Control Problems Applied to Spaceplane Mission Design

Ricciardi¹,

Maddock²,

Vasile³

2019

Journal of Guidance, Control, and Dynamics

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This paper presents a novel approach to the solution of multi-phase multi-objective optimal control problems. The proposed solution strategy is based on the transcription of the optimal control problem with Finite Elements in Time and the solution of the resulting Multi-Objective Non-Linear Programming (MONLP) problem with a memetic strategy that extends the Multi Agent Collaborative Search algorithm. The MONLP problem is reformulated as two non-linear programming problems: a bi-level and a single level problem. The bi-level formulation is used to globally explore the search space and generate a well spread set of non-dominated decision vectors while the single level formulation is used to locally converge to Pareto efficient solutions.

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Rapid Trajectory Optimization for the ARES I Launch Vehicle

Cited by 13 publications

References 2 publications

An ascent iterative guidance algorithm for solid rocket concerned with multiconstraints

An ascent iterative guidance algorithm for solid rocket concerned with multiconstraints

An online predictive reentry guidance law for reusable launch vehicles

Direct Solution of Multi-Objective Optimal Control Problems Applied to Spaceplane Mission Design

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