Total Energy Control System for Helicopter Flight/Propulsion Integrated Controller Design

Chen, Sheng Wen; Chen, Pang Chia; Yang, Ciann Dong; Jeng, Yaug Fea

doi:10.2514/1.26670

Cited by 23 publications

(5 citation statements)

References 20 publications

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“…(21) a relative regulator derived using Eq. (20) can guarantee that all states converge to a bounded area, that is:…”

Section: Im Rementioning

confidence: 99%

“…The blade element relative lift and drag coefficients are provided by verified wind tunnel test data [19,20] to guarantee a considerable accuracy in the flapping dynamics equations. Moreover, the rotor moment and thrust are also numerically validated.…”

Section: Main Rotor Modelmentioning

confidence: 99%

“…An eight-DOF model for the PZL Mi-2 Plus helicopter (three translations and three rotations of a rigid fuselage, main rotor speed, and engine output power) was developed to optimize autorotation profiles with different performance indices, finally comparing the results with flight test data [16]. The above-mentioned autorotation control models can be regarded as being specific for investigation of optimized profiles after engine failures; however, they are not sufficient for designing flight or engine control law during autorotation [17][18][19][20][21]. This motivates the need for more It is meaningful to emphasize the significance and necessity of autorotation power recovery simulation and control.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Engine Control Design Using Compressor Guided Vanes During Autorotation Power Recovery

Sun

Zhang

2016

Arab J Sci Eng

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In order to improve the helicopter responsive ability during autorotation power recovery maneuvers, a new turbo-shaft engine control scheme is proposed in this paper. Using rotor flapping/lagging dynamics and an induced velocity model which is capable of capturing vortex ring characteristics, an integrated helicopter and engine model was developed to simulate autorotation process. By introducing a closed-loop with compressor guided vanes, a novel two-variable engine control law is devised using Linear Matrix Inequality Pole Placement method. This allows for a rapid adaptation of the helicopter to a large and fast needed torque variation required in autorotation power recovery. The transient performances and the robustness for the closedloop helicopter-pilot system are validated for some examples appropriated to autorotation training procedure. Simulation results illustrate that, with this novel control law, the helicopter's ability to respond during autorotation is strongly enhanced when compared to traditional cases.

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“…(21) a relative regulator derived using Eq. (20) can guarantee that all states converge to a bounded area, that is:…”

Section: Im Rementioning

confidence: 99%

Section: Main Rotor Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Engine Control Design Using Compressor Guided Vanes During Autorotation Power Recovery

Sun

Zhang

2016

Arab J Sci Eng

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“…Aiming at this problem, some researchers and scholars in China use the establishment of damage models to simulate and calculate the damage probability of munitions, and then analyze the effectiveness of air defense projectiles. Cheng Jie et al evaluated the damage probability of Apache helicopter gunship by establishing a simulation damage model [1][2]. Lu Xiuhui et al take dense array against a certain type of anti-ship missile as an example, establish the damage probability calculation model of concentrated fire and airspace window fire, and compare the hit probability of maneuvering and non-movement targets [3][4].…”

Section: Introductionmentioning

confidence: 99%

Design of Simulation Software for Visualization of Munition Anti-Air Effectiveness

Cai,

Chang,

Shi

et al. 2023

J. Phys.: Conf. Ser.

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In order to realize the simulation of the damage effectiveness of air defense projectiles against air targets, this paper uses the C++ programming language to complete the development of ammunition air damage simulation model by constructing the ammunition combat model and target vulnerability digital model, and designs the visualization simulation software of ammunition air damage effectiveness based on the Unity 3D engine. The results show that the visualization and simulation software of ammunition damage effectiveness against air targets can calculate the damage effect of ammunition on air and visualize the results of missile rendezvous, combat guidance and air target damage, which provides reference for the design of air defense ammunition introduction.

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“…Therefore, the flight control design plays an important role in the optimization of the fuel consumption for an aircraft or UAV. In conventional flight control design, the autopilot and the autothrottle systems are usually considered separately [1]. The autothrottle unit is mainly used to adjust the engine throttle valve to achieve the desired flight speed, and the autopilot unit is designed to regulate the control surfaces for attitude and altitude maneuvers.…”

Section: Introductionmentioning

confidence: 99%

Design and Implementation of an Optimal Energy Control System for Fixed-Wing Unmanned Aerial Vehicles

Lai

Ting

2016

Applied Sciences

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Abstract:In conventional flight control design, the autopilot and the autothrottle systems are usually considered separately, resulting in a complex system and inefficient integration of functions. Therefore, the concept of aircraft energy control is brought up to solve the problem of coordinated control using elevator and throttle. The goal of this study is to develop an optimal energy control system (OECS), based on the concept of optimal energy for fixed-wing unmanned aerial vehicles (UAVs). The energy of an aircraft is characterized by two parameters, which are specific energy distribution rate, driven by elevator, and total specific energy rate, driven by throttle. In this study, a system identification method was employed to obtain the energy model of a small UAV. The proposed approach consists of energy distribution loop and total energy loop. Energy distribution loop is designed based on linear-quadratic-Gaussian (LQG) regulator and is responsible for regulating specific energy distribution rate to zero. On the other hand, the total energy loop, based on simple gain scheduling method, is responsible for driving the error of total specific energy rate to zero. The implementation of OECS was successfully validated in the hard-in-the-loop (HIL) simulation of the applied UAV.

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Total Energy Control System for Helicopter Flight/Propulsion Integrated Controller Design

Cited by 23 publications

References 20 publications

Engine Control Design Using Compressor Guided Vanes During Autorotation Power Recovery

Engine Control Design Using Compressor Guided Vanes During Autorotation Power Recovery

Design of Simulation Software for Visualization of Munition Anti-Air Effectiveness

Design and Implementation of an Optimal Energy Control System for Fixed-Wing Unmanned Aerial Vehicles

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