Modelica Landing Gear Modelling and On-Ground Trajectory Tracking with Sliding Mode Control

Re, Fabrizio

doi:10.1007/978-3-642-19817-5_9

Cited by 9 publications

(3 citation statements)

References 18 publications

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“…While Modelica models for a variety of aerospace applications have been successfully demonstrated (Wei et al 2015;Re 2011;Briese, Klöckner, and Reiner 2017;Milz et al 2019;Batteh et al 2018;Posielek 2018;Hellerer, Bellmann, and Schlegel 2014), to the knowledge of the authors, there are no publicly available models similar to the one proposed in this work. The authors' believe that the growing interest and on-going advancements on rocket re-usability can benefit from the availability of an open source model that allows interested parties to exploit the advantages offered by object-oriented modeling provided by Modelica tools.…”

Section: Motivationmentioning

confidence: 99%

Guidance, Navigation, and Control enabling Retrograde Landing of a First Stage Rocket

Canham¹,

Podlaski²,

Vanfretti³

2021

Linköping Electronic Conference Proceedings

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A Modelica model of a of a rocket's first stage is developed, designed to be representative of the launch vehicles in use in the United States in the late 2010s. The model uses initial conditions similar to those observed immediately after a second stage separation at 166 km altitude. A control system is developed enabling the rocket first stage to land back on Earth's surface at a predetermined landing pad in a controlled manner. The control system is evaluated based on its ability to compensate for altered initial conditions, as well as its ability to minimize acceleration forces and fuel consumption. The flight path of the simulated first stage rocket is compared to real-life telemetry data from a first stage rocket landing showing a similar trajectory.

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Section: Motivationmentioning

confidence: 99%

Guidance, Navigation, and Control enabling Retrograde Landing of a First Stage Rocket

Canham¹,

Podlaski²,

Vanfretti³

2021

Linköping Electronic Conference Proceedings

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“…Yan B 12 designed a fuzzy control law combined with the NWS and the rudder deflection to correct the taxiing direction. Fabrizio 13 proposed a sliding mode control, which was competent to follow the trajectory determined by longitudinal speed and yaw rate. Yin 14 designed a joint control law to make better use of the electric brake and rudder which is validated by the experiment.…”

Section: Introductionmentioning

confidence: 99%

The maximum taxiing safe set of the wheel-skid aircraft under optimal control of rudder

Liang

Yin

Fang³

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Directional stability during the roll-out phase is crucial to the safety and reusability of the aircraft. Because of the mechanical properties, the wheel-skid aircraft is more prone to produce course instability. To address this issue, the taxiing safe set of the wheel-skid aircraft is discussed based on the reachability theory. A dynamic model of the on-ground aircraft is established firstly, considering the complex condition of the ground loads. Then, the particular Hamilton–Jacobi partial differential equation is used to obtain the safe set. According to the safe set results, the optimal control of the rudder is built in the state space. Its effectiveness is verified by the comparison with other robust methods. In addition, three structural parameters are selected to analyze the influences on the safe set. Results indicate that the maximum safe yaw angle increases from [Formula: see text] to [Formula: see text] at 70 m/s under the optimal control of the rudder when the steering of nose wheel is locked. The safe boundary in the middle–high-speed region expands by 43.5% under the rudder control. Because of the mechanical properties, uncontrollable deflection will appear due to the asymmetric disturbances when the longitudinal velocity is lower than 42 m/s.

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“…Lemay ( 6 ) also proposed yaw controller using gain scheduling approach to manoeuvre the aircraft on ground. Chen ( 7 ) designed an aircraft-on-ground path following control law based on dynamical adaptive back-stepping method, while Fabrizio ( 8 ) developed a control system for an aircraft taxiing on ground based on sliding mode feedback control theory and feedforward control theory. Biannic ( 9 ) got the aircraft-on-ground model by using the linear fractional transformation method.…”

Section: Introductionmentioning

confidence: 99%

On-ground lateral direction control for an unswept flying-wing UAV

Zhu

Zhou

2019

Aeronaut. j.

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To solve the on-ground lateral direction control problem of the unswept flying-wing unmanned aerial vehicle (UAV) without rudder, steering system or breaking system, a control approach which uses differential propeller thrust to control the lateral direction is proposed. First, a mathematical model of the unswept flying-wing UAV on-ground moving is established. Second, based on the active disturbance rejection control (ADRC) theory, a yaw angle controller is designed by using the differential propeller thrust as the control output. Finally, a straight line trajectory tracking control law is designed by improving the vector field path following method. Experiment results show that the proposed control laws have a shorter response time, better robustness and better control precision compared with proportional integral derivative (PID) controller. The proposed controller has small computational complexity, simple parameter setting process, and uses practical measurable physical quantities, providing a reference solution for further engineering applications.

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Modelica Landing Gear Modelling and On-Ground Trajectory Tracking with Sliding Mode Control

Cited by 9 publications

References 18 publications

Guidance, Navigation, and Control enabling Retrograde Landing of a First Stage Rocket

Guidance, Navigation, and Control enabling Retrograde Landing of a First Stage Rocket

The maximum taxiing safe set of the wheel-skid aircraft under optimal control of rudder

On-ground lateral direction control for an unswept flying-wing UAV

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