Optimal design of launch vehicles is a complex problem which requires the use of specific techniques called Multidisciplinary Design Optimization (MDO) methods. MDO methodologies are applied in various domains and are an interesting strategy to solve such an optimization problem. This paper surveys the different MDO methods and their applications to launch vehicle design. The paper is focused on the analysis of the launch vehicle design problem and brings out the advantages and the drawbacks of the main MDO methods in this specific problem. Some characteristics such as the robustness, the calculation costs, the flexibility, the convergence speed or the implementation difficulty are considered in order to determine the methods which are the most appropriate in the launch vehicle design framework. From this analysis, several ways of improvement of the MDO methods are proposed to take into account the specificities of the launch vehicle design problem in order to improve the efficiency of the optimization process.

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A survey of multidisciplinary design optimization methods in launch vehicle design

Latin hypercube sampling applied to reliability-based multidisciplinary design optimization of a launch vehicle

Review of improved Monte Carlo methods in uncertainty-based design optimization for aerospace vehicles

Multidisciplinary design optimization of a wide speed range vehicle with waveride airframe and RBCC engine

An approach for space launch vehicle conceptual design and multi-attribute evaluation

Rapid Trajectory Optimization Using Computational Intelligence for Guidance and Conceptual Design of Multistage Space Launch Vehicles

Purpose – The purpose of the paper is to study the variation of optimal burnout angle at the end of the ascent phase and the optimal control deflection during the glide phase, that would maximize the downrange performance of a hypersonic boost-glide waverider, with variation in heat rate and integrated heat load limit. Design/methodology/approach – The approach used is to model the boost phase so as to optimize the burnout conditions. The nonlinear, multiphase, constraint optimal control problem is solved using an hp-adaptive pseudospectral method. Findings – The constraint heat load results for the waverider configuration reveal that the integrated heat load can be reduced by more than half with only 10 per cent penalty in the overall downrange of the hypersonic boost-glide vehicle, within a burnout speed range of 3.7 to 4.3 km/s. The angle-of-attack trim control requirements increase with stringent heat rate and integrated heat load bounds. The normal acceleration remains within limits. Practical implic...

Optimal trajectory analysis of hypersonic boost-glide waverider with heat load constraint

This paper presents a new design methodology for efficient conceptual design of complex systems involving multidisciplinary and computationally intensive analysis with large number of design variables. A nearly-orthogonal sampling of design space is proposed with good space filling properties to extract maximum useful information about system behavior using much lower number of trial designs. This sampled data is then used as training data for artificial neural network, which will act as a metamodel to represent the time consuming disciplinary analyses. A stage-wise interconnection of separate neural networks is also proposed for trajectory metamodel to offset dimensionality curse of neural networks. Genetic Algorithm performs global optimization by utilizing this metamodel and subsequently sequential quadratic programming performs the local optimization utilizing exact analyses. The performance of proposed methodology is investigated in this paper for the conceptual design optimization of multistage solid fueled space launch vehicle. The results show excellent approximation of highly non-linear functions using proposed sampling and drastic reduction in overall design optimization time, due to greatly reduced number of exact disciplinary analyses.

Nearly-orthogonal sampling and neural network metamodel driven conceptual design of multistage space launch vehicle

Design of launch vehicles is highly complex undertaking and it involves a number of integrated disciplines and relatively a large number of design variables, so there is need of specialized state-of-the-art design tools to control overall design process and optimize the performance of vehicle itself. In this paper we propose an integrated system design approach for multidisciplinary conceptual design and optimization of multistage Air Launched Space Launch Vehicle comprising of three-stage solid propulsion system. The vehicle performance modeling requires that analysis from four separate disciplines be integrated into the design optimization process. The disciplines of propulsion characteristics, aerodynamics, mass properties, and flight dynamics have been integrated to produce a high-fidelity system model of the entire vehicle. Genetic algorithms have been chosen as optimizer because of their robustness and their efficient capacity to explore the design space. The objective is to develop an integrated system design approach that can more efficiently (less computational time) and effectively (solution quality) facilitate integrated design analysis and optimization for Air Launched Space Launch Vehicle at conceptual design level under certain mission and flight constraints. The mission of the ASLV is to deliver a small satellite of 200kg to Low Earth Orbit with minimum possible Gross Launch Mass. The proposed design approach is meant for initial design sizing purposes but gives a quick insight on the vehicle performance prior to detailed design with minimum basic vehicle data.

http://enu.kz/repository/2009/AIAA-2009-5506.pdf

Integrated System Design of Air Launched Small Space Launch Vehicle using Genetic Algorithm

In this work, trajectory optimisation has been performed for a wing-body rocket assisted vehicle to compute the bestset of performance parameters including burn-out angle, angle-of-attack, bank-angle and throttle command that would result in optimal down-range and cross-range performance of the re-entry vehicle. An hp-adaptive Pseudospectral method has been used for the optimisation by combining the launch and rocket rocket-assisted re-entry stages. The purpose of the research is to compute optimal burn-out condition, angle-of-attack, bank-angle and optimal thrust segments that would maximise the down-range and cross-range performance of the hypersonic boost glide vehicle, under constrained heat rate environments. The variation of down-range/cross-range performance of rocket rocket-assisted hypersonic boost glide vehicle with bounds on diminishing heat rate has also been computed.

Trajectory optimisation for a rocket-assisted hypersonic boost-glide vehicle

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