Reusable Launch Space Systems

Tománek, Robert; Hospodka, Jakub

doi:10.14311/mad.2018.02.02

Cited by 11 publications

(2 citation statements)

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“…Recently, RLV is drawing more attention through successful demonstrations by private companies such as SpaceX and Blue Origin. In particular, Falcon 9, 2 the representative RLV produced by SpaceX, has successfully delivered various payloads to space many times through vertical takeoff and vertical landing (VTVL).…”

Section: Introductionmentioning

confidence: 99%

Multi-phase and dual aero/propulsive rocket landing guidance using successive convex programming

Lee

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper aims to suggest a new landing guidance algorithm for reusable launch vehicles (RLVs) to enable generation of fuel-efficient trajectories based on successive convex programming. To this end, a dual aero/propulsive landing guidance problem is first formulated to fully exploit the additional moment generated by the aerodynamic control to reduce the propulsion demand required for attitude control. As the result of the aerodynamic landing phase could greatly affect the fuel-optimal trajectory during the vertical landing phase, the formulation is further extended to the multi-phase optimal guidance problem using state-triggered constraints. The proposed guidance strategy is then obtained by solving the formulated optimal control problem based on the successive convex optimization framework using an interior point method The main contribution of this study lies in forming new RLV landing guidance problems to get an optimal trajectory and transforming the corresponding nonconvex problem into a convex optimization problem by introducing appropriate combinations for convexification techniques. Additionally, this paper introduces several practical constraints, such as the maximum slew rate of aerodynamic control fins and nozzle angles, which are not considered in previous works. In this paper, the performance of the proposed method with the potential for online computation is investigated through numerical simulations.

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Section: Introductionmentioning

confidence: 99%

Multi-phase and dual aero/propulsive rocket landing guidance using successive convex programming

Lee

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…There is a recent trend in space exploration toward reusable launch missions such as Space X (SpaceX, 2020;Tom anek and Hospodka, 2018). However, the expendable satellite launch vehicles are still the primary choice for access to space.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary design and optimization of expendable launch vehicle for microsatellite missions

Zeeshan¹,

Rafique

Kamran

et al. 2021

AEAT

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Purpose The capability to predict and evaluate various configurations’ performance during the conceptual design phase using multidisciplinary design analysis and optimization can significantly increase the preliminary design process’s efficiency and reduce design and development costs. This research paper aims to perform multidisciplinary design and optimization for an expendable microsatellite launch vehicle (MSLV) comprising three solid-propellant stages, capable of delivering micro-payloads in the low earth orbit. The methodology’s primary purpose is to increase the conceptual and preliminary design process’s efficiency by reducing both the design and development costs. Design/methodology/approach Multidiscipline feasible architecture is applied for the multidisciplinary design and optimization of an expendable MSLV at the conceptual level to accommodate interdisciplinary interactions during the optimization process. The multidisciplinary design and optimization framework developed and implemented in this research effort encompasses coupled analysis disciplines of vehicle geometry, mass calculations, aerodynamics, propulsion and trajectory. Nineteen design variables were selected to optimize expendable MSLV to launch a 100 kg satellite at an altitude of 600 km in the low earth orbit. Modern heuristic optimization methods such as genetic algorithm (GA), particle swarm optimization (PSO) and SA are applied and compared to obtain the optimal configurations. The initial population is created by passing the upper and lower bounds of design variables to the optimizer. The optimizer then searches for the best possible combination of design variables to obtain the objective function while satisfying the constraints. Findings All of the applied heuristic methods were able to optimize the design problem. Optimized design variables from these methods lie within the lower and upper bounds. This research successfully achieves the desired altitude and final injection velocity while satisfying all the constraints. In this research effort, multiple runs of heuristic algorithms reduce the fundamental stochastic error. Research limitations/implications The use of multiple heuristics optimization methods such as GA, PSO and SA in the conceptual design phase owing to the exclusivity of their search approach provides a unique opportunity for exploration of the feasible design space and helps in obtaining alternative configurations capable of meeting the mission objectives, which is not possible when using any of the single optimization algorithm. Practical implications The optimized configurations can be further used as baseline configurations in the microsatellite launch missions’ conceptual and preliminary design phases. Originality/value Satellite launch vehicle design and optimization is a complex multidisciplinary problem, and it is dealt with effectively in the multidisciplinary design and optimization domain. It integrates several interlinked disciplines and gives the optimum result that satisfies these disciplines’ requirements. This research effort provides the multidisciplinary design and optimization-based simulation framework to predict and evaluate various expendable satellite launch vehicle configurations’ performance. This framework significantly increases the conceptual and preliminary design process’s efficiency by reducing design and development costs.

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A Review on Maintenance Repair, Refurbish, and Overhaul for Reusable Launch Vehicle Management Process Toward Its Development

Noh,

Sharif,

Yusoff

et al. 2024

SpringerBriefs in Applied Sciences and Technology

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Reusable Launch Space Systems

Cited by 11 publications

References 0 publications

Multi-phase and dual aero/propulsive rocket landing guidance using successive convex programming

Multi-phase and dual aero/propulsive rocket landing guidance using successive convex programming

Multidisciplinary design and optimization of expendable launch vehicle for microsatellite missions

A Review on Maintenance Repair, Refurbish, and Overhaul for Reusable Launch Vehicle Management Process Toward Its Development

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