Optimal staging of reusable launch vehicles for minimum life cycle cost

Jo, Byeong-Un; Ahn, Ji-Whan

doi:10.1016/j.ast.2022.107703

Cited by 18 publications

(8 citation statements)

References 27 publications

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“…However, the velocity loss for each stage does not necessarily scale proportionately to the velocity increment allocated to the stage, potentially leading to a suboptimal design [12]. Other recent studies adopted a different approach [14][15][16][17]. Instead of simply adding the loss terms to v req , they obtained the ideal velocity increment for each stage under the loss-free condition.…”

Section: Considering Velocity Lossesmentioning

confidence: 99%

Simultaneous Optimization of Launch Vehicle Stage and Trajectory Considering Flight-Requirement Constraints

Ko,

Kim,

Choi

et al. 2024

Int. J. Aeronaut. Space Sci.

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A conceptual design of a launch vehicle encompasses various disciplines, such as structural design, aerodynamics, propulsion systems, flight control, and stage sizing. This paper focuses on optimizing trajectory and stage size. Traditional approaches used for the conceptual design of a launch vehicle conduct the stage and trajectory designs sequentially, often leading to high computational complexity and suboptimal results. This paper presents an optimization framework that addresses both trajectory optimization and staging in an integrated way. The proposed framework aims to minimize the lift-off mass while satisfying the constraints on flight requirements (e.g., maximum dynamic pressure and the impact points of separated parts). A case study demonstrates the advantage of the proposed framework compared to the traditional sequential optimization approach.

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Section: Considering Velocity Lossesmentioning

confidence: 99%

Simultaneous Optimization of Launch Vehicle Stage and Trajectory Considering Flight-Requirement Constraints

Ko,

Kim,

Choi

et al. 2024

Int. J. Aeronaut. Space Sci.

Self Cite

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“…In recent years, reusable rocket technology has proved its significant advantages, such as lower cost, 1 shorter launching period, 2,3 and high reliability, 4 compared with traditional rockets. Since 2015, SpaceX of America has successfully made reusable rockets land more than 100 times.…”

Section: Introductionmentioning

confidence: 99%

Calculate the ignition height of the vertical landing phase online for the reusable rocket

Cheng,

Jing,

Gao

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.

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“…The retirement of space shuttle does not mean that people all over the world stop the research on reusable spacecraft with both aviation and aerospace capabilities. In order to find an economical and safe space shuttle or system, Britain, the United States, Germany, France, Japan, and other countries have launched reusable space shuttle transportation system schemes, and Aerospaceplane research has quietly emerged [12][13][14][15]. It is generally believed that the main difference between the Aerospaceplane and the space shuttle is that the space shuttle is an aircraft that takes off vertically like a rocket and lands horizontally like a plane.…”

Section: Introductionmentioning

confidence: 99%

Impact Analysis of Different Trajectory Shapes on Optimization Based on Original Natural Algorithm

Chen,

Nan,

2024

International Journal of Aerospace Engineering

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In this paper, the reentry phase of the Aerospaceplane is taken as the research object, and the performance parameters of the reusable rocket of a private company are analyzed. Aiming at the guidance and control scheme of the spacecraft returning to the reentry trajectory in the real environment, the original natural algorithm is optimized by considering various reentry flight constraints, and the improved original natural algorithm is used to optimize the reentry trajectory of the Aerospaceplane. We obtained two types of reentry trajectories in the presence of large flight-restricted areas, the “S-type” trajectory and the “spiral-type” trajectory, and obtained data on various influencing factors. The results showed that the basic state parameters of the spiral trajectory optimized using the improved original natural algorithm after adding constraints met the constraint conditions. The aerodynamic heating rate and overload of the spiral reentry trajectory were to some extent greater than those of the S-type trajectory. Under the increasingly stringent requirements of the aerospace environment, new requirements were put forward for the thermal protection system to meet the wider environmental situation. This paper uses the improved original natural algorithm for the first time and applies it to the field of aerospace reentry and entry and adds more constraints to this algorithm for computation. Besides, for the first time, the macroscopic nature of trajectory types is used as a comparative element for parameter comparison, providing a reference basis for selecting trajectory optimization directions from the macroscopic perspective of trajectory types.

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Optimal staging of reusable launch vehicles for minimum life cycle cost

Cited by 18 publications

References 27 publications

Simultaneous Optimization of Launch Vehicle Stage and Trajectory Considering Flight-Requirement Constraints

Simultaneous Optimization of Launch Vehicle Stage and Trajectory Considering Flight-Requirement Constraints

Calculate the ignition height of the vertical landing phase online for the reusable rocket

Impact Analysis of Different Trajectory Shapes on Optimization Based on Original Natural Algorithm

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