Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics;
北京航空航天大学飞行器设计与应用力学系；
RBCC engine performance analysis model plays an important part in scheme selection and model design for Hypersonic Flight Vehicle, RBCC engine design and performance analysis.
RBCC发动机性能分析模型在高超声速飞行器方案选择、总体设计以及RBCC发动机设计与性能分析等方面具有极其重要的作用。
This paper content is the flight vehicle stabilization loop analysis and the design.
本论文的内容是飞行器稳定回路的分析与设计。
A baseline vehicle is presented for the given flight mission, and the effects of the tank material, the thermal protection system and the design margin on the vehicle dry mass are calculated.
对给定的飞行任务，提出了基准运载器，并计算了贮箱材料、热防护系统及设计余量对运载器干质量的影响。
Design technology for integration of air vehicle fuselage, propulsion system and lifting control surfaces to optimize aerodynamic performance throughout the flight regime of an unmanned air vehicle.
为了优化无人驾驶航空飞行器在整个飞行过程中的空气动力特性而使机身、推进系统和升力控制面一体化的设计技术。
In this paper, principle, design and test result of MMW wide beam antenna on flight vehicle is introduced.
本文介绍一种用于飞行器上的毫米波宽波束天线的原理、设计方法和实验结果。
In flight vehicle preliminary design it is necessary to quickly and economically estimate the aerodynamics of a wide variety of flight vehicle configuration designs.
在飞行器的初步设计中，快速而有经济地估计出飞行器结构设计中的各种气动特性是非常必要的。
A new method of design hypersonic vehicle trajectory tracking system using fuzzy control is presented to overcome the disadvantage of flight trajectory distribution caused by separation disturbance.
针对高超声速飞行器飞行过程中因干扰造成的飞行轨迹散布问题，提出了采用飞行器飞行轨迹的模糊控制设计方法。
The paper presents a design approach based on extremum seeking for minimum power demand of formation flight of Unmanned Aerial Vehicle.
采用极值搜索方法，解决无人机紧密编队飞行中僚机所需动力最小化的问题。
This paper is mainly focusing on the flight control system design for Reusable Boost Vehicle (RBV).
增益调度法原理简单，在飞行控制系统的设计中得到了广泛应用。
The objective of this paper is to design the reentry flight control laws for the Suborbital Reusable Launch Vehicle(SRLV) based on nonlinear dynamic-inversion.
基于非线性动态逆理论，设计了亚轨道可重复使用运载器（SRLV）的再入控制律。
The essential characteristics, flight sequence, trajectory design and optimal analysis for air launch vehicle are discussed.
讨论了空中发射运载火箭的基本特点、飞行方案、发射轨道设计和优化分析方法。
The results show that optimum design of solid propulsion in single discipline doesn't stand for multi-disciplinary optimum design for flight vehicle system.
结果表明，固体推进单学科的最优设计不等价于飞行器总体多学科的最优设计；
Compared with traditional design optimization method, MDO method can gain the optimum design for flight vehicle as well as the optimum thrust-time curves of booster.
与传统设计优化方法相比，MDO方法一次设计优化就可得到满足飞行器总体设计指标的最优设计，得到内外弹道相匹配的助推器最优推力-时间曲线。
The methodologies of Multidisciplinary Design Optimization(MDO)have revolutionary impacts on design field of flight vehicle, and have become a new independent discipline.
论述分析模型参数化建模在飞机多学科优化设计中的重要意义，提出一种机翼气动与结构分析模型参数化建模方法。
According to the high performance and the miniaturized request, designed and has realized based on the DSP new unmanned aerial vehicle flight control computer hardware's design and the development.
按照高性能和小型化的要求，设计并实现了基于DSP的新型无人机飞行控制计算机硬件的设计和开发。
According to the high performance and the miniaturized request, designed and has realized based on the DSP new unmanned aerial vehicle flight control computer hardware's design and the development.
按照高性能和小型化的要求，设计并实现了基于DSP的新型无人机飞行控制计算机硬件的设计和开发。
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