Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Abstract

In the design of hypersonic cruise vehicles, great effort is demanded to improve the performances of subsystems, namely structure, aerodynamics, and propulsion. Herein, effort demanded to realize a subsystem performance is quantified by technical merit. To achieve a feasible design, excessive technical merit of any one subsystem should be avoided. Accordingly, a lowest-technical-merit (LTM) design methodology has been proposed in this work. By this methodology, the design problem could be interpreted into a parametric optimization. The solution to such an optimization corresponds to the highest feasibility. The methodology has been implemented on two cases: deriving a hydrocarbon-fueled long-range cruiser from Boeing X-51A, and a hydrogen-fueled LAPCAT scenario from PREPHA. The simulation results show that LTM could achieve optimal allocations while satisfying different payload/range performances. The design methodology could help to improve the feasibility of hypersonic cruise vehicles. Furthermore, it could also be used in the design of other systems.

Control Design for the Autonomous Horizontal Takeoff Phase of the Reusable Launch Vehicles

“…Content may change prior to final publication. (13) Simultaneous equation (13) and equation (11) to obtain the state matrix of the closed-loop system. The matrix of closedloop system is in the following form: (14) The expected closed-loop matrix is: (15) making equation 14equals to equation (15), the timevarying controller matrix can be got:…”

“…Compared with the hypersonic cruise vehicle [13,14] , the RLVs should not only adapt to the near space flight environment, but also meet the technical requirements of the airport Horizontal takeoff and landing. The small wing area of the aircraft is beneficial to reduce the drag when the aircraft is flying at high speed.…”