Quantitative feedback control of a quadrotor

Xu, Yu; Tong, Changfei

doi:10.1109/isie.2012.6237279

Cited by 1 publication

(1 citation statement)

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“…In addition to actuator action, the pitching and rolling moments also include body gyro effect, propeller gyro effect, hub moment, and rolling moment due to translational movements [4]. Since quadrotor always flies at low speed, compared to actuator action, these moments are negligible and can be treated as disturbances [4,22]. Then the pitching moments and rolling moments can be expressed as:…”

Section: Pitching and Rolling Momentsmentioning

confidence: 99%

Flight Control of a Quadrotor under Model Uncertainties

Tong

Huai-zhong

2015

International Journal of Micro Air Vehicles

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Quadrotor type helicopters continue to grow in popularity for academic research and unmanned aerial vehicle applications. However, the model uncertainties caused by battery voltage drop, payload variation and flight condition change, have rarely been considered in control design. This work proposes a quantitative feedback theory based robust design approach to deal with these uncertainties. By analyzing the rigid body dynamics and aerodynamic forces/moments under different voltages, payloads and flight conditions, we model quadrotor dynamics as a set of linear models with parameter uncertainties, which represent a larger flight envelop than models linearized from hover condition. These model uncertainties, as well as the robust stability requirements and performance specifications of flight control system are then used for designing and tuning the controllers, to perform tradeoff between controller complexity, robust requirements, and performance specifications. We also implemented a prototype system, and conducted a serial of experiments in realtime outdoor flights to evaluate its performance. The results show good, robust, and reliable performances of the designed system in autonomous hovering, takeoff, waypoint navigation and landing flights. NOMENCLATURE INTRODUCTIONQuadrotor has become a popular unmanned aerial vehicle (UAV) platform. Compared to conventional helicopter which has the same capabilities of vertical takeoff and landing (VTOL), hovering, and low speed flying, quadrotor has three main advantages. First, quadrotor is lifted and propelled by four sensorless brushless direct current (SLBLDC) motor driven rotors, eliminating complex mechanical structure such as swashplates and linkages, thus is inherently more reliable and maintainable. Second, for given load capacity, the individual rotor of quadrotor is smaller than the main rotor of helicopter, leading to smaller damage when crashing and safer operation when flying over densely populated areas. Third, due to smaller rotors and symmetrical structure, the vibration of quadrotor is much smaller than that of helicopter. These advantages make quadrotor widely used in applications such as aerial photography, surveillance, patrolling, search and rescue, law enforcement, aerial mapping, and so on. In most of these applications, the automatic flying ability of quadrotor is demanded. However, the open-loop unstable nonlinear dynamics and limited payload of quadrotor bring both theoretical and technical challenges to control system design. Although significant progresses have been made on the control of quadrotor, most works rarely concern about the model uncertainties in practical implementation. These model uncertainties are mainly due to three factors: 1) Battery voltage drop. As will be illustrated in Section 3.2.4, the dynamics of rotors change distinctly with battery voltage. 2) Payload variation. The moments of inertia and mass of quadrotor may change with payload, bringing variation of model parameters. 3) Flight condition change. For model...

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Section: Pitching and Rolling Momentsmentioning

confidence: 99%