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Launch Vehicles, Propulsion Systems, and Payloads
Published in Janet K. Tinoco, Chunyan Yu, Diane Howard, Ruth E. Stilwell, An Introduction to the Spaceport Industry, 2020
Janet K. Tinoco, Chunyan Yu, Diane Howard, Ruth E. Stilwell
With respect to LVs and spacecraft, either can be expendable or reusable, in total or by component. A reusable launch vehicle (RLV) isa launch vehicle that is designed to return to Earth substantially intact and therefore may be launched more than one time or that contains vehicle stages that may be recovered by a launch operator for future use in the operation of a substantially similar launch vehicle.(U.S. 14 CFR 401.5) Thus, an RLV is a launch system that can launch into space more than once (Tian et al. 2015) while an expendable launch vehicle (ELV) is destroyed during use or simply cannot be reused. In more specific terms, an ELV is “a launch vehicle whose propulsive stages are flown only once” (U.S. 14 CFR 401.5). Most systems today have a hybrid of reusable and expandable components.
Simulation
Published in Michael W. Carter, Camille C. Price, Ghaith Rabadi, Operations Research, 2018
Michael W. Carter, Camille C. Price, Ghaith Rabadi
For over three decades, NASA’s Space Shuttle had been the only Reusable Launch Vehicle (RLV) used to deliver cargo to space. Almost a decade prior to the end of the Space Shuttle program in 2011, NASA started evaluating options and approaches for replacement programs that were more effective in terms of cost, reliability, safety and availability. It was well understood that it was necessary to study and compare future competing designs consistently to improve upon the Space Shuttle’s cost, performance and turnaround time before pursuing the large undertaking of a new RLV. Previous estimates of the Shuttle’s operational performance proved overly optimistic, when NASA predicted originally 50–100 flights per year at $6 million per flight. These estimates were off by an order of magnitude for the flight rate and by two orders of magnitude for cost (the Shuttle flew five to ten times a year at a cost of about $600 million per flight). One of the problems of most estimates was that they tended to assume best-case scenarios and failed to take into account factors that can cause operations to take longer, flights to be delayed and costs to increase.
Commercial Space Technologies
Published in Mohammad Razani, Commercial Space Technologies and Applications, 2018
A reusable launch system (RLS, or reusable launch vehicle, RLV) is a launch system which is capable of launching a payload into space more than once.41 This contrasts with expendable launch systems, where each launch vehicle is launched once and then discarded.
An improved NSGA-II based control allocation optimisation for aircraft longitudinal automatic landing system
Published in International Journal of Control, 2019
Qi Bian, Brett Nener, Xinmin Wang
Currently, the optimisation method based on computational intelligence has triggered development in many practical engineering fields. Numerous studies have been carried out on the swarm intelligence based flight control system optimisation in the aircraft automatic landing field (Kennedy, Eberhart, & Shi, 2001). Based on the simplified brain storming algorithm, Li and Duan (2015) proposed an improved control parameter optimisation method for the F/A-18 automatic carrier landing system design. By converting the parameter design problem to an optimisation problem, a pigeon-inspired optimisation algorithm introduced by Deng and Duan (2016) was used in the field of automatic carrier landing system design. To solve the scheduling aircraft landing problem, Bencheikh, Boukachour, and Alaoui (2016) developed a memetic algorithm combining the ant colony algorithm with a local heuristic strategy. An improved gravitational search algorithm was proposed by Su and Wang (2015) to deal with the approach and landing trajectory optimisation problem for the reusable launch vehicle. Girish (2016) considered the aircraft landing time problem and presented a rolling horizon framework based hybrid particle swarm optimisation method.
Control parameter tuning for aircraft crosswind landing via multi-solution particle swarm optimization
Published in Engineering Optimization, 2018
Qi Bian, Brett Nener, Xinmin Wang
Currently, the swarm intelligence-based parameter optimization method is regarded as a powerful tool to solve large-scale optimization problems during aircraft landing approach procedures (Kennedy, Eberhart, and Shi 2001). In recent years, numerous studies have been carried out from various perspectives. Deng and Duan (2016) used the pigeon-inspired method to optimize the control parameters of the automatic carrier-landing flight control system. Li and Duan (2015) developed a control parameter optimization strategy for the F/A-18 automatic carrier-landing system via a simplified brain-storm strategy. Girish (2016) proposed a hybrid particle swarm optimization algorithm to deal with the aircraft landing problem in a rolling horizon framework. Dou and Duan (2017) conducted a Lévy flight-based pigeon-inspired algorithm for flight control parameter optimization. Bencheikh, Boukachour, and Alaoui (2016) proposed a memetic algorithm combining the ant colony algorithm to deal with the dynamic multiple runway aircraft landing problem. Su and Wang (2015) used a robust, hybrid gravitational search algorithm to optimize the approach and landing trajectory of a reusable launch vehicle. Lungu and Lungu (2014, 2016a) studied the H-inf control and dynamic inversion method for aircraft automatic landing systems. More comparisons of methods using modified swarm optimization algorithms can be found in Jakubcová, Máca, and Pech (2014).
Reentry attitude tracking via coupling effect-triggered control subjected to bounded uncertainties
Published in International Journal of Systems Science, 2018
Zongyi Guo, Jianguo Guo, Jun Zhou, Jinlong Zhao, Bin Zhao
The model in this paper comes from a control-oriented model in the reentry phase of the reusable launch vehicle (Shao & Wang, 2014), which is different from the common longitudinal model of the air-breathing hypersonic vehicle (AHV) (Parker et al., 2007). The coupling stemming from the integrated engine airframe configuration is a critical coupling to be dealt with for AHV, however, it is not the focus in this paper because of the power-free reentry phase. This article tries to see the possibility and reliability of coping with the couplings by using our proposed scheme.