Optimization of Launch Vehicle Ascent Trajectories with Path Constraints and Coast Arcs

Gath, Peter; Calise, Anthony J.

doi:10.2514/2.4712

Cited by 100 publications

(39 citation statements)

References 5 publications

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“…Such a technique is -and has been -successfully used as a global optimization method for complex problems in many research fields and is also used as a suitable method for spacecraft trajectory optimization (Gath and Calise, 2001;Rajesh, 2002;Igarashi and Spencer, 2005). Other methods that are widely used in trajectory optimization problems because of their efficiency are the "gradient-based" optimizers.…”

Section: Genetic Algorithmmentioning

confidence: 99%

Thermal Protection System and Trajectory Optimization for Orbital Plane Change Aeroassisted Maneuver

Mazzaracchio

2013

J.Aerosp. Technol. Manag.

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The aim of this paper was to identify, for a specific maneuver, the optimal combination between the trajectory and the associated heat shield configuration, namely the locations and thicknesses of the ablative and reusable zones, that maximize the allowable payload mass for a spacecraft. The analysis is conducted by considering the coupling between the trajectory's dynamics and the heat shield's thermal behavior while using a highly representative model of the heat shield. A global optimization procedure and original software were developed and implemented. The analyzed mission considers an aeroassisted transfer from two low Earth orbits with an assigned orbital plane change maneuver for a given delta wing vehicle equipped with a heat shield consisting of both ablative and reusable materials. The results indicate that the aeroassisted maneuver is more convenient than a "full propulsive" maneuver in the analyzed case, even considering the increased vehicle mass due to the presence of the heat shield.

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Section: Genetic Algorithmmentioning

confidence: 99%

Thermal Protection System and Trajectory Optimization for Orbital Plane Change Aeroassisted Maneuver

Mazzaracchio

2013

J.Aerosp. Technol. Manag.

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“…The iterative guidance method was given firstly by Chandler [5]. Then the research of ascent guidance was conducted by Calise [6], Gath [7], Dukeman [8][9] and Lu [10] [11]. Optimal solution of exo-atmospheric trajectory was derived from simplified model of flight dynamics.…”

Section: Introductionmentioning

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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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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“…Many researchers have studied the problem since the 1970s. [1][2][3][4] In general, numerical solutions can be categorized into two major types: indirect, and direct methods. 5,6) Most early investigators used indirect methods to solve the ascent phase trajectory optimization problem.…”

Section: Introductionmentioning

confidence: 99%

Ascent Phase Trajectory Optimization for Vehicle with Restricted Space

Zong

Tian

Dou

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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For flight safety, space is often restricted while the vehicle climbs to the target. A general two-dimensional (2-D) vehicle model is unsuitable for ascent when space is restricted because it considers only longitudinal degrees of freedom. Requiring into ascent in three-dimensional (3-D) scenarios as well as into relationships between the 2-D and 3-D trajectories. This paper reports 2-D and 3-D ascent phase minimum time-to-climb and minimum fuel-to-climb problems in different restricted spaces. The Gauss Pseudospectral Method (GPM) is used to transform the trajectory optimization problem into a Nonlinear Program (NLP) problem that can be solved by SNOPT based on a correct initial guess. The results in different restricted spaces illustrate the effect on 2-D and 3-D flight trajectories. Numerical evidence of optimality to trajectories is verified by estimating co-state information and the Hamiltonian.

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Optimization of Launch Vehicle Ascent Trajectories with Path Constraints and Coast Arcs

Cited by 100 publications

References 5 publications

Thermal Protection System and Trajectory Optimization for Orbital Plane Change Aeroassisted Maneuver

Thermal Protection System and Trajectory Optimization for Orbital Plane Change Aeroassisted Maneuver

An ascent iterative guidance algorithm for solid rocket concerned with multiconstraints

Ascent Phase Trajectory Optimization for Vehicle with Restricted Space

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