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| 1 | An overview on flight dynamics and control approaches for hypersonic vehicles显示文摘With the capability of high speed flying, a more reliable and cost efficient way to access space is provided by hypersonic flight vehicles. Controller design, as key technology to make hypersonic flight feasible and efficient, has numerous challenges stemming from large flight envelope with extreme range of operation conditions, strong interactions between elastic airframe, the propulsion system and the structural dynamics.This paper briefly presents several commonly studied hypersonic flight dynamics such as winged-cone model,truth model, curve-fitted model, control oriented model and re-entry motion. In view of different schemes such as linearizing at the trim state, input-output linearization, characteristic modeling, and back-stepping, the recent research on hypersonic flight control is reviewed and the comparison is presented. To show the challenges for hypersonic flight control, some specific characteristics of hypersonic flight are discussed and the potential future research is addressed with dealing with actuator dynamics, aerodynamic/reaction-jet control, flexible effects,non-minimum phase problem and dynamics interaction. | XU Bin SHI ZhongKe | 2015 | Science China(Information Sciences)2015，58，7： | 58 |
| 2 | Variable Structure Control of Catastrophic Course in Airdropping Heavy Cargo显示文摘重型货物离机瞬间运输机数学模型发生突变,严重影响飞机空投时的安全性,对这一过程设计了变结构控制器。利用微分几何理论中的输入输出反馈线性化方法将非线性系统进行了线性化,在此基础上利用变结构滑模设计理论指数趋近律方法设计了速度与姿态的内环跟踪控制系统,并结合外环高度控制完成整个飞行控制系统的设计。数字仿真结果表明所设计的控制系统可以适用于货物离机突变过程,并对系统参数摄动具有较强的鲁棒性。 | Zhang Huiyuan Shi Zhongke | 2009 | Chinese Journal of Aeronautics2009，22，5： | 32 |
| 3 | Flight Controller Design of Transport Airdrop显示文摘在重负担的空投期间,当负担搬到抓住,飞行参数连续地变化,并且当负担放弃时,突然变化。这个过程败坏飞行质量和象负担特征的控制变得更重。基于简化空投飞行方程, backstepping 和开关控制方法被开发州的成立和骚乱 / 无常处理飞行(例如大规模飞行状况,飞行员操作错误,系统措施延期,等等) 在这份报纸的变细问题。而且,这些方法能作为一本参考书被使用飞行员在空投期间操作。与 backstepping 理论,当负担搬到抓住时,一个适应控制器为稳定运输的目的被综合,然后当条件在机身在机身的尾部从负担的存在跳到没有负担时,一个协调开关控制方法被用来控制飞机。模拟结果证明建议控制器不仅提供在空投期间的有效州的成立,而且在宽飞行条件以内完成柔韧的性能。 | CHEN Jie SHI Zhongke | 2011 | Chinese Journal of Aeronautics2011，24，5： | 18 |
| 4 | Dynamics modeling and control of large transport aircraft in heavy cargo extraction显示文摘In this paper,a novel version of six-degree-of-freedom nonlinear model for transport aircraft motion in cargo extraction is developed and validated by the theoretical mechanics and flight mechanics.In this model constraint force and moment reflecting the flight dynamic effects of inner moving cargo are formulated.A methodology for a control law design in this phase is presented,which linearizes the aircraft dynamics making use of piecewise linearization and utilizes robust control technique for interval system to achieve specified handling qualities with robustness to uncertainties.The simulations demonstrate adequate effectiveness and excellent robustness of the proposed controller. | Feng, Yanli Shi, Zhongke Tang, Wei | 2011 | 控制理论与应用(英文版)2011，9，2： | 9 |
| 5 | Application of a fourth-order relaxation scheme to hyperbolic systems of conservation laws显示文摘一个第四顺序的松驰计划被导出并且在一和二种空间尺寸适用于守恒定律的夸张系统。计划基于一第四顺序中央加权实质上非摆动(CWENO ) 为一个维的盒子的重建,它被 dimension-by-dimension 途径概括到二维的盒子。大稳定性领域 Runge-Kutta-type 解答者 ROCK4 被用于时间集成。产生方法也不要求 Riemann 解答者也不 Jacobians 的计算的使用,因此,它享受松驰计划的主要优点。高精确性和现在的方法的高分辨率的性质在一个维、二维的数字实验被表明。 | Jianzhong Chen Zhongke Shi | 2006 | Acta Mechanica Sinica2006，22，1： | 7 |
| 6 | Bifurcation analysis and stability design for aircraft longitudinal motion with high angle of attack显示文摘Bifurcation analysis and stability design for aircraft longitudinal motion are investigated when the nonlinearity in flight dynamics takes place severely at high angle of attack regime. To predict the special nonlinear flight phenomena, bifurcation theory and continuation method are employed to systematically analyze the nonlinear motions. With the refinement of the flight dynamics for F-8 Crusader longitudinal motion, a framework is derived to identify the stationary bifurcation and dynamic bifurcation for high-dimensional system. Case study shows that the F-8longitudinal motion undergoes saddle node bifurcation, Hopf bifurcation, Zero-Hopf bifurcation and branch point bifurcation under certain conditions. Moreover, the Hopf bifurcation renders series of multiple frequency pitch oscillation phenomena, which deteriorate the flight control stability severely. To relieve the adverse effects of these phenomena, a stabilization control based on gain scheduling and polynomial fitting for F-8 longitudinal motion is presented to enlarge the flight envelope. Simulation results validate the effectiveness of the proposed scheme. | Xin Qi Shi Zhongke | 2015 | Chinese Journal of Aeronautics2015，28，1： | 5 |
| 7 | Aircraft Flutter Modal Parameter Identification Using a Numerically Robust Least-squares Estimator in Frequency Domain显示文摘最近,基于频率最少平方(LS ) 评估者在识别飞机发现了宽申请拍翅参数。然而,当识别一个连续时间的模型时,频率方法经常被知道受不了数字困难特别,更宽广的频率或更高的顺序。在这篇文章,一个数字地柔韧的 LS 评估者基于向量,直角的多项式被建议解决 multivariable 系统的数字问题并且适用于测试的 flutter。这个方法的关键想法是由正确矩阵部分描述(RMFD ) 代表频率反应功能(FRF ) 矩阵在向量上为分子和分母多项式矩阵建模,并且膨胀直角的基础。作为结果,一个完美的数字条件(数字状况等于 1 ) 能为线性 LS 被获得评估者。最后,这个方法被验证由拍翅在一条风隧道和真实飞行的一个翅膀模型的测试拍翅一架飞机的测试。当它在 z 领域被建立,结果与有尤其是 LMS PolyMAX 的那些相比,它没被数字问题麻烦(例如源于一个分离时间的模型) 。确认证实了那除了克服数字问题,这个方法产出结果比得上与 LMS PolyMAX 获得的那些,或甚至更加擅长一些频率乐队。 | Tang Wei Shi Zhongke Chen Jie | 2008 | Chinese Journal of Aeronautics2008，21，6： | 5 |
| 8 | Identification of reduced-order model for an aeroelastic system from flutter test data显示文摘Recently, flutter active control using linear parameter varying(LPV) framework has attracted a lot of attention. LPV control synthesis usually generates controllers that are at least of the same order as the aeroelastic models. Therefore, the reduced-order model is required by synthesis for avoidance of large computation cost and high-order controller. This paper proposes a new procedure for generation of accurate reduced-order linear time-invariant(LTI) models by using system identification from flutter testing data. The proposed approach is in two steps. The well-known poly-reference least squares complex frequency(p-LSCF) algorithm is firstly employed for modal parameter identification from frequency response measurement. After parameter identification,the dominant physical modes are determined by clear stabilization diagrams and clustering technique. In the second step, with prior knowledge of physical poles, the improved frequencydomain maximum likelihood(ML) estimator is presented for building accurate reduced-order model. Before ML estimation, an improved subspace identification considering the poles constraint is also proposed for initializing the iterative procedure. Finally, the performance of the proposed procedure is validated by real flight flutter test data. | Tang Wei Wu Jian Shi Zhongke | 2017 | Chinese Journal of Aeronautics2017，30，1： | 4 |
| 9 | Bifurcation analysis of polynomial models for longitudinal motion at high angle of attack显示文摘To investigate the longitudinal motion stability of aircraft maneuvers conveniently, a new stability analysis approach is presented in this paper. Based on describing longitudinal aerodynamics at high angle-of-attack (a < 50 ) motion by polynomials, a union structure of two-order differential equation is suggested. By means of nonlinear theory and method, analytical and global bifurcation analyses of the polynomial differential systems are provided for the study of the nonlinear phenomena of high angle-of-attack flight. Applying the theories of bifurcations, many kinds of bifurcations, such as equilibrium, Hopf, homoclinic (heteroclinic) orbit and double limit cycle bifurcations are discussed and the existence conditions for these bifurcations as well as formulas for calculating bifurcation curves are derived. The bifurcation curves divide the parameter plane into several regions; moreover, the complete bifurcation diagrams and phase portraits in different regions are obtained. Finally, our conclusions are applied to analyzing the stability and bifurcations of a practical example of a high angle-of-attack flight as well as the effects of elevator deflection on the asymptotic stability regions of equilibrium. The model and analytical methods presented in this paper can be used to study the nonlinear flight dynamic of longitudinal stall at high angle of attack. | Shi Zhongke Fan Li | 2013 | Chinese Journal of Aeronautics2013，26，1： | 2 |
| 10 | Weak uninorm aggregation operators 显示文摘 | Li Yongming Shi Zhongke | 2000 | Information Sciences2000，124，： | 1 |
| 11 | Approximation Theory of Fuzzy Systems Based upon Genuine Many-Valued Implications-SISO Cases 显示文摘 | Li Yongming Shi Zhongke Li Zhihui | 2002 | Fuzzy Sets and Systems2002，130，2： | 1 |
| 12 | Approximation Theory of Fuzzy Systems Based upon Genuine Many-Valued Implications-MIMO Cases显示文摘 | Li Yongming Shi Zhongke Li Zhihui | 2002 | Fuzzy Sets and Systems2002，130，2： | 1 |
| 13 | The strongest schema learning GA and its application to multilevel thresholding显示文摘 | Can Li Ban Paul Shi Zhongke | 2008 | Image and Vision Computing2008，26，5： | 1 |
| 14 | Approximation theory of fuzzy systems basd upon genuine many valued implications-MIMO cases显示文摘 | Li Yong-ming Shi Zhongke Li Zhihui | 2002 | Fuzzy Sets and Systems2002，130，： | 1 |
| 15 | The strongest schema learning GA and its application to multilevel thresholding 显示文摘 | Cao Li Bao Paul Shi Zhongke | 2008 | Image and Vision Computing2008，26，5： | 1 |
| 16 | Approximation theory lf fuzzy systems based upon genuine many-valued implication-SISO Case显示文摘 | LI Yongming SHI Zhongke LI Zhihui | 2002 | Fuzzy sets and systems2002，130，2： | 1 |
| 17 | Approximation theory lf fuzzy systems based upon genuine many-valued implication-MISO Case显示文摘 | LI Yongming SHI Zhongke LI Zhihui | 2002 | Fuzzy sets and systems2002，130，2： | 1 |
| 18 | Dynamic tabu search algorithm for solving departure scheduling problem 显示文摘 | WANG LAIJUN SHI ZHONGKE LEI XIUJUAN | 2007 | Journal of southwest jiotong University ( Endlish Edition)2007，15，2： | 1 |
| 19 | Neural control of hypersonic flight vehicle model via time-scale decomposition with throttle setting constraint显示文摘 | Bin Xu Zhongke Shi Chenguang Yang ShixingWang | 2013 | Nonlinear Dyn2013，73，18： | 1 |
| 20 | Aircraft modeling and simulation with cargo moving inside显示文摘 | Chen Jie Shi Zhongke | 2009 | Chinese Journal of Aeronau- tics2009，22，1： | 1 |
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