“…The booster profile is shown in Figure 34; Figure 34. Partially reusable vehicle concept. 56 The fully reusable vehicle concept. It has a SABRE-powered booster and a rocket-powered upper stage.…”
“…In 2014, the Air Force Research Laboratory (affiliated to NASA, High Speed Systems Division (AFRL/ RQH)) and React Engines, Ltd. (REL) signed a cooperative research and development agreement (CRADA) to demonstrate their design and precooling technology of SABRE 56,57 (Synergy Air Breathing Rocket Engine). AFRL conducted a technical analysis with Space Works Enterprises, Inc. and designed a TSTO space vehicle that uses the SABRE as the first stage.…”
Section: Vehicle Concepts Powered By Sabre Enginesmentioning
Rocket-based combined-cycle (RBCC) powered vehicles have been widely recognized as the most promising aircraft solution that could dramatically reduce the cost of space transportation. Researchers and scientists worldwide have conducted considerable overall design researches to cope with the challenges in RBCC development including mode transition, thermal protection and thrust enhancement. According to the way to orbit and the configuration characteristics, the hypersonic aircraft powered by RBCC engine are classified as four categories: single-stage-to-orbit (SSTO) two-dimensional configuration, SSTO axisymmetric configuration, two-stage-to-orbit (TSTO) two-dimensional configuration, and TSTO axisymmetric configuration. This paper systematically presents the development of the conceptual design of RBCC-powered vehicles. Both the structural and operating key parameters like the weight distribution, the RBCC propulsion performance and take-off mode, et al. are introduced in detail. On this basis, a comparative analysis of the advantages and disadvantages of the orbit model, the configuration selection and takeoff modes are conducted. In addition, the application prospect and technology development direction for hypersonic aircraft are also discussed. At the same time, the lessons that can be drew from previous hypersonic vehicle concept design are explored.
“…The booster profile is shown in Figure 34; Figure 34. Partially reusable vehicle concept. 56 The fully reusable vehicle concept. It has a SABRE-powered booster and a rocket-powered upper stage.…”
“…In 2014, the Air Force Research Laboratory (affiliated to NASA, High Speed Systems Division (AFRL/ RQH)) and React Engines, Ltd. (REL) signed a cooperative research and development agreement (CRADA) to demonstrate their design and precooling technology of SABRE 56,57 (Synergy Air Breathing Rocket Engine). AFRL conducted a technical analysis with Space Works Enterprises, Inc. and designed a TSTO space vehicle that uses the SABRE as the first stage.…”
Section: Vehicle Concepts Powered By Sabre Enginesmentioning
Rocket-based combined-cycle (RBCC) powered vehicles have been widely recognized as the most promising aircraft solution that could dramatically reduce the cost of space transportation. Researchers and scientists worldwide have conducted considerable overall design researches to cope with the challenges in RBCC development including mode transition, thermal protection and thrust enhancement. According to the way to orbit and the configuration characteristics, the hypersonic aircraft powered by RBCC engine are classified as four categories: single-stage-to-orbit (SSTO) two-dimensional configuration, SSTO axisymmetric configuration, two-stage-to-orbit (TSTO) two-dimensional configuration, and TSTO axisymmetric configuration. This paper systematically presents the development of the conceptual design of RBCC-powered vehicles. Both the structural and operating key parameters like the weight distribution, the RBCC propulsion performance and take-off mode, et al. are introduced in detail. On this basis, a comparative analysis of the advantages and disadvantages of the orbit model, the configuration selection and takeoff modes are conducted. In addition, the application prospect and technology development direction for hypersonic aircraft are also discussed. At the same time, the lessons that can be drew from previous hypersonic vehicle concept design are explored.
“…With the maturity of related technical fields, hypersonic vehicles have received extensive attention and research as aerospace vehicles and fast-attack weapons, and a series of representative hypersonic vehicles or key projects have emerged. These include the US hypersonic flight tester SR-72 [1], the experimental spacecraft project (XS-1) [2], a twostage aerospace vehicle based on the SABRE engine [3], and a tactical-range High-Speed Strike Weapon project (HSSW) consists of Tactical Boost-Glide (TBG) programme and Hypersonic Air-breathing Weapon Concept (HAWC) [4] and the ''Hypersonic International Flight Research and Experiment'' (HIFiRE) [5] project in cooperation with the United States and Australia. Through these projects, both industry and academia have accumulated a lot of experience in the The associate editor coordinating the review of this manuscript and approving it for publication was Chaoyong Li.…”
Nowadays, aerodynamic shape optimization of the hypersonic vehicle is mostly optimized for local details such as the wing. In the overall shape optimization, the conceptual design of the vehicle is more common, in which the shape is described in fewer parameters and optimized roughly. Meanwhile, in the optimization, the capacity is considered only by the volumetric ratio, and it can hardly meet the actual payload size constraints, which is difficult to apply to engineer practice. In this paper, a rapid aerodynamic shape optimization method with payload size constraints is proposed. The analytic method combined with a clamped cubic spline curve is used to establish the parametric model with the payload size constraints. In order to ensure the accuracy and improve the optimization efficiency, the aerodynamic characteristics of the vehicle are quickly obtained based on the adaptive Cartesian grid generation method and viscosity modified Euler equations. The lift-to-drag ratio is used as the objective, and a sequence iteration method with multi-point selecting strategy is adopted to make convergence faster. In order to compare and verify the effectiveness of the proposed method, the optimal solution is compared with a reference shape obtained through a conventional multi-objective aerodynamic shape optimization with lift-to-drag ratio and the volumetric ratio as objectives. Through comparative analysis, the method proposed in this paper can find the optimal shape that satisfies the payload size constraints quickly, which can effectively improve the aerodynamic performance of the hypersonic vehicle and can be better applied to practical engineering optimization problems.INDEX TERMS Hypersonic, parametric design, surrogate model, computational fluid dynamics, optimization.
“…It can be seen that there is much research on the SABRE engine system scheme and key technology both home and abroad, but the research on the air-vehicle entry scheme based on the SABRE engine is little. In the public references, only in 2016, the United States announced the TSTO scheme based on the SABRE engine on the AIAA conference [11] .…”
Based on the composite precooling engine, a Single-Stage-To-Orbit (SSTO) scheme is proposed. The climbing process is divided into three stages. The dynamic model, the air-vehicle model and the motion model are set up, and the feasibility of SSTO is studied using the numerical simulation. In order to improve the SSTO scheme, a SSTO scheme based on launching vehicle is proposed and a Two-Stage-To-Orbit (TSTO) powered by the composite precooling engine in the first stage and the rocket engine in the second stage is proposed. The results show that if the SSTO scheme is achieved, the structural coefficient of the air-vehicle should be less than 0.13, which has great technical difficulty. By adopting the SSTO scheme based on launching vehicle, the structural coefficient can be relaxed to 0.19, and the technical difficulty will be greatly reduced. The adoption of the TSTO scheme can not only effectively reduce the technical difficulty, but also increase the payload from 15t to 20.31t.
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