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Conceptual design and flight test of two wingtipdocked multi-body aircraft

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Chinese Journal of Aeronautics 2022年第12期35卷 144-155页

作者： Yang MENG Chao AN Changchuan XIE Chao YANG School of Aeronautic Science and Engineering Beihang UniversityBeijing 100083China

To overcome the drawbacks such as large wing deformations,poor performance encountering gusts,limits in taking off and landing,inconvenience of transportation of High-Altitude Long-Endurance(HALE)Unmanned Aerial Vehicles(UAVs),a new conceptual aircraft called wingtip-docked Multi-Body Aircraft(MBA)has attracted lots of attentions.Aiming to investigate the feasibility of this concept,two UAV models were designed,manufactured and connected by a wingtip-docking mechanism,which only allows the relative roll motion between the two aircraft.The trim solution of the two connected aircraft is firstly obtained by solving the developed nonlinear flight dynamic equations,followed by the stability analysis based on the linearized model.The results show that the connected aircraft is inherently unstable and cannot fly without a reasonable flight control system.A set of Proportional-Integral-Derivative(PID)control laws was then developed and implemented in the two experimental aircraft.The success of the flight tests show that the flight control can effectively eliminate the unstable motion and the wingtip-docked MBA is controllable and feasible。

关键词： flight test Multi-body aircraft New conceptual aircraft PID control Wingtip-docking mechanism

Novel roll effector based on zero-mass-flux dual synthetic jets and its flight test

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Chinese Journal of Aeronautics 2022年第8期35卷 1-6页

作者： Zhenbing LUO Zhijie ZHAO Jiefu LIU Xiong DENG Mu ZHENG Hang YANG Qingyang CHEN Shiqing LI College of Aeronautics and Astronautics National University of Defense TechnologyChangsha 410073China

The autonomous and controllable Dual Synthetic Jet Actuator(DSJA)is firstly integrated into the Unmanned Aerial Vehicle(UAV),and flight tests without the deflection of rudders are carried out to verify the viability of DSJA to control the attitudes of UAV during cruising.DSJA is improved into an actuator with two diaphragms and three cavities,which has higher energy levels.Actuators,differentially distributed on both sides of the wings,are installed on the trailing edge close to the wing tips.flight tests,containing Differential Circulation Control(DCC)using double-side actuators,Positive Circulation Control(PCC)using left-side actuators and Negative Circulation Control(NCC)using right-side actuators,are implemented at cruising speed of 25 m/s.Results show that roll attitude control without rudders could be realized by DSJAs.DCC and NCC can generate the rightward roll and yaw angular velocity,prompting UAV to turn right.The stronger controlling ability can be achieved by DCC,with the maximum roll angular velocity of 15.62(°)/s.PCC can generate a rightward roll moment,but a leftward yaw moment will be produced at the same time.Leftward yaw induces the leftward rolling moment,which weakens the roll control effect,making UAV keep to yaw to the left with a small slope.

关键词： Active flow control Actuators with two diaphragms and three cavities Circulation control Dual synthetic jets flight test Roll attitude control

Preliminary study on heat flux measurement data of TT-0 flight test

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Chinese Journal of Aeronautics 2021年第5期34卷 120-128页

作者： Enwei LU Linxuan ZUO Zheng GUO Honggang ZENG Wei ZHU Feng QU National University of Defense Technology Changsha 410073China Shenyang Aircraft Design&Research Institute Shenyang 110035China Chinese Aeronautical Establishment Beijing 100012China School of Aeronautics Northwestern Poly technical UniversityXi'an 710072China

With the explosive development of aerospace science,the design of the new generation airliner at higher speeds is attracting more attentions.To achieve this goal,it is necessary to achieve accurate prediction of the aerodynamic heating/force loads and successful reduction of drag and heat flux.As a remedy for the existing studies which are based upon the CFD and wind tunnel tests,this study presents a flight test for the drag and heat reduction spike technology.The principal goals of this flight test were to provide reference for verifying the accuracy of the prediction technology on ground and promote the development of the drag and heat reduction technology.By adopting the OS-X rocket,the TT-0 test vehicle designed by Shenyang Aircraft Design&Research Institute reached a maximum Mach number of 5.8 and a maximum altitude of 38 km.Hypersonic and supersonic pressure data by pressure scanning valves and heat fluxes by gauges at different locations were obtained successfully.Also,heat fluxes obtained by in-house CFD code are illustrated in comparison with the flight data.The results indicate that the numerical errors are large in most cases.More technologies,such as more CFD codes and more numerical procedures,should be adopted to conduct studies on this issue in the future.

关键词： Aerospace science CFD Drag reduction flight test Heat reduction

UAV flight test of plasma slats and ailerons with microsecond dielectric barrier discharge

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Chinese Physics B 2018年第10期27卷 455-464页

作者：苏志李军梁华郑博睿魏彪陈杰谢理科 Science and Technology on Plasma Dynamics Laboratory Air Force Engineering University School of Automation and Information Xi’an University of Technology

Plasma flow control（PFC） is a promising active flow control method with its unique advantages including the absence of moving components, fast response, easy implementation, and stable operation. The effectiveness of plasma flow control by microsecond dielectric barrier discharge（μs-DBD）, and by nanosecond dielectric barrier discharge（NS-DBD） are compared through the wind tunnel tests, showing a similar performance between μs-DBD and NS-DBD. Furthermore, theμs-DBD is implemented on an unmanned aerial vehicle（UAV）, which is a scaled model of a newly developed amphibious plane. The wingspan of the model is 2.87 m, and the airspeed is no less than 30 m/s. The flight data, static pressure data,and Tufts images are recorded and analyzed in detail. Results of the flight test show that the μs-DBD works well on board without affecting the normal operation of the UAV model. When the actuators are turned on, the stall angle and maximum lift coefficient can be improved by 1.3° and 10.4%, and the static pressure at the leading edge of the wing can be reduced effectively in a proper range of angle of attack, which shows the ability of μs-DBD to act as plasma slats. The rolling moment produced by left-side μs-DBD actuation is greater than that produced by the maximum deflection of ailerons,which indicates the potential of μs-DBD to act as plasma ailerons. The results verify the feasibility and efficacy of μs-DBD plasma flow control in a real flight and lay the foundation for the full-sized airplane application.

关键词： plasma flow control flight test dielectric barrier discharge UAV

flight control of a flying wing aircraft based on circulation control using synthetic jet actuators

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Chinese Journal of Aeronautics 2023年第10期36卷 152-164页

作者： Zhijie ZHAO Xiong DENG Zhenbing LUO Wenqiang PENG Jianyuan ZHANG Jiefu LIU College of Aeronautics and Astronautics National University of Defense TechnologyChangsha 410073China

To achieve the nice stealth performance and aerodynamic maneuverability of a Flying Wing Aircraft(FWA),a longitudinal aerodynamic control technology based on circulation control using trailing-edge synthetic jet actuators was proposed without the movement of rudders.Effects on the longitudinal aerodynamic characteristics of a small-sweep FWA were investigated.Then,flight tests were carried out to verify the control abilities,providing a novel technology for the design of a future rudderless FWA.Results show that synthetic jets could narrow the dead zone area,improve the flow velocity near the trailing edge,and then move the trailing-edge separation point and the leading-edge stagnation point downwards,which make the effective Attack of Angle(AOA)increase,thereby enhancing the pressure envelope area.Circulation control based on synthetic jets could improve the lift,drag and nose-down moment.The variations of lift and nosedown moment decrease with the growth of AOA caused by the improved reverse pressure gradient and the weakened circulation control efficiency.Finally,synthetic jet actuators were integrated into the trailing edge of a small-sweep FWA,which could realize the roll and pitch control without deflections of rudders during the cruise stage,and the maximum roll and pitch angular velocity are 12.64(°)/s and 8.51(°)/s,respectively.

关键词： Synthetic jets Flying wing aircraft Circulation control Control mechanism flight test

Airborne laser communication technology and flight test

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Airborne laser communication technology and flight test

The Design of Control Force Measurement Device for Aircraft Quick Evaluation flight test

国防光电子论坛空间光信息与组网技术及应用研讨会

作者： Li-xin MENG Li-zhong ZHANG Xiao-ming LI Ying-chao LI Hui-lin JIANG Fundamental Science on Space-Ground Laser Communication Technology Laboratory

Reconnaissance aircraft is an important node of the space-air-ground integrated information network, on which equipped with a large number of high-resolution surveillance equipment, and need high speed communications equipment to transmit detected information in real time. Currently RF communication methods cannot meet the needs of communication bandwidth. Wireless laser communication has outstanding advantages high speed, high capacity, security, etc., is an important means to solve the high-speed information transmission of airborne platforms. In this paper, detailed analysis of how the system works, the system components, work processes, link power and the key technologies of airborne laser communication were discussed. On this basis, a prototype airborne laser communications was developed, and high-speed, long-distance communications tests were carried out between the two fixed-wing aircraft, and the airborne precision aiming, atmospheric laser communication impacts on laser communication were tested. The experiments ultimately realize that, the communication distance is 144 km, the communication rate is 2.5Gbps. The Airborne laser communication experiments provide technical basis for the application of the conversion equipment.

关键词： Airborne laser communication flight test atmospheric APT

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The Design of Control Force Measurement Device for Aircraft ...

Investigation of lateral-directional aerodynamic parameters identification method for fly-by-wire passenger airliners

2012年计算机应用与系统建模国际会议

作者： Zhang Dawei Chen Mingtai Mi Yi Liu Chaoqiang Shanghai Aircraft Design and Research Institute

The design and installation of control force measurement device for quick evaluation flight test was difficult due to not enough time and fund available. Three control force indication devices were assembled and tested. They were spring balance, control force indication glove and FlexiForce indicator. The flight test results showed that all the three devices could be used for quick control force measurement. The principle of control force indication glove was innovative. However, for the spring balance, the undirected control of the aircraft was abnormal and it might influence the quality opinion of the pilot on the handling quality of the aircraft. The load sensor on the control force indication glove must be improved. The reliability of the FlexiForce indicator also should be improved.

关键词： Control Force Aircraft Quick Evaluation Handling Quality flight test

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Chinese Journal of Aeronautics 2014年第4期27卷 781-790页

作者： Wu Zhao Wang Lixin Lin Jiaming Ai Junqiang School of Aeronautic Science and Engineering Beihang University

A new identification method is proposed to solve the problem of the influence on the loaded excitation signals brought by high feedback gain augmentation in lateral-directional aerodynamic parameters identification of fly-by-wire（FBW） passenger airliners. Taking for example an FBW passenger airliner model with directional relaxed-static-stability, through analysis of its signal energy distribution and airframe frequency response, a new method is proposed for signal type selection, signal parameters design, and the appropriate frequency relationship between the aileron and rudder excitation signals. A simulation validation is presented of the FBW passenger airliner＇s lateral-directional aerodynamic parameters identification. The validation result demonstrates that the designed signal can excite the lateral-directional motion mode of the FBW passenger airliner adequately and persistently. Meanwhile, the relative errors of aerodynamic parameters are less than 5%.

关键词： Excitation signal design flight test Fly-by-wire （FBW）passenger airliner High feedback gain augmentation Identification Lateral-directional aerodynamic parameter

Progress in flight tests of hypersonic boundary layer transition

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Acta Mechanica Sinica 2021年第11期37卷 1589-1609,I0001页

作者： Guohua Tu Jianqiang Chen Xianxu Yuan Qingtao Yang Maochang Duan Qiang Yang Yi Duan Xi Chen Bingbing Wan Xinghao Xiang State Key Laboratory of Aerodynamics China Aerodynamics Research&Development CenterMianyang621000China Hypervelocity Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang621000China Science and Technology on Space Physics Laboratory China Academy of Launch Vehicle TechnologyBeijing100076China

Boundary layer transition(BLT)can cause a sharp rise in heat flux and skin friction,which can seriously affect the flight performance and safety of hypersonic flight vehicles.Therefore,the mechanism,prediction and control of transition have become important issues that must be dealt with for the development of advanced flight vehicles,and it is also a research hotspot of particular interest to major aerospace countries.Compared to other transition research approaches,model flight tests can better present the transition problems under real flight conditions,thus have been carried out extensively over the past 30 years.The United States,Germany,France,Australia,and other countries have carried out transition research based on flight tests,such as the Pegasus wing-glove crossflow transition and the Hypersonic Boundary Layer Transition(HyBOLT)transition control flight test of the United States,the joint research project of the Hypersonic International flight Research and Experimentation-1(HIFiRE-1)circular cone and the HIFiRE-5 elliptic cone transition flight tests between the United States and Australia,the flight test of compression surface transition of the scramjet forebody(LEA)in France and so on.Although these flight tests suffered various setbacks,they still obtained valuable transition data.Recently,the United States is carrying out the concave-surface transition flight tests of Hypersonic Boundary Layer Transition(BOLT)and BOLT-II.Since its first model flight test mission for verification purpose launched successfully in 2015,several hypersonic BLT flight tests have been conducted by China Aerodynamics Research and Development Center(CARDC).The flight tests have measured valid transition data under flight conditions,obtained the transition front and its dynamical variation on blunt cones at various angles of attack and a lifting body Hypersonic Transition Research Vehicle(HyTRV).The crossflow traveling waves in high-altitude flight were measured for the first time,and our understanding of hypersonic BLT has

关键词： Hypersonic flow Boundary layer transition flight test MF-1 HyTRV