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This paper proposes a finite-time control law for quadrotor aircraft to achieve position tracking control in a finite time. Firstly, the position dynamical equation and the attitude dynamical equation are introduced respectively. Secondly, based on the technique of finite-time control, a finite-time position controller is designed to ensure the desired trajectory can be tracked by the real position...
The importance of carrier-based landing has been a controversial topic. The wave excites the ship to make six-degree-of-freedom motion, accompanied by atmosphere turbulence flow and ship airwake, making the carrier-based aircraft landing a great challenge. Aimed to ensure the safety of carrier-based aircraft and precision landing, a method of the constrained command filtered prescribed performance...
In the process of reentry trajectory optimization of glide hypersonic vehicle, a new adaptive detection point pseudospectral method based on detection point is proposed to solve the problem of no-fly zone constraints between adjacent collocation points. This method adaptively adjusted the number of discrete subintervals and the number of collocation points in the interval according to the maximum...
When naval vessels moving on the sea, the carrier air wake disturbance will arise. The carrier air wake makes the landing environment of carrier aircraft fair adverse, which puts forward a high demand for the high precise attitude control of carrier based aircrafts. In this paper, high precise robust attitude control problems for carrier based aircrafts with the carrier air wake disturbance are investigated...
This paper studies the attitude control problem for the longitudinal motion of a hypersonic aircraft model containing 28 inertial and aerodynamic uncertain parameters given by NASA Langley Research Center. To handle the nonlinear dynamics and uncertain parameters, ADRC for the unobservable and unmatched disturbance is designed. Besides, the properties of the closed-loop system is discussed in two...
An in-flight aerodynamic coefficient estimation method is proposed for nonlinear lateral motion of reusable launch vehicle via retrospective cost adaptive control theory. The estimated aerodynamic coefficient is then utilized for adaptive controller switch to cope with unexpected polarity change of LCDP(Lateral Control Departure Parameter) online. First, the nonlinear lateral dynamics of a reusable...
This paper focuses on the transition flight control for a small tilt rotor unmanned aerial vehicle (UAV). Aiming at the longitudinal model of a tilt rotor UAV, a novel sliding mode control (SMC) method is proposed to guarantee that the states converge to the desired sliding surfaces in finite time. Moreover, extended state observers (ESOs) are provided to enhance the system's robustness to the uncertainties...
Many challenges of modeling and control exist in the tail-sitter aircraft, including parameter uncertainty, highly coupling, nonlinearity, and external disturbance. In this paper, the model of a tail-sitter aircraft is simplified at the nominal condition to obtain the nominal linear invariant model. Then a robust controller based on the H∞ control theory is proposed to deal with the attitude tracking...
Under the coupling effect between guidance system and control system, the performance of traditional guidance and control method is limited. Therefore, integrated guidance and control (IGC) method is proposed to solve the problem. This method is characterized by the guidance loop and control loop which are considered as a whole part in accordance with the information of the relative motion between...
This paper presents a new type of vertical takeoff and landing(VTOL) aircraft, using a new type of vector propulsion scheme is different from the traditional vector propulsion scheme, which can change the three elements of thrust. This paper describes the overall layout and mechanical structure of the new aircraft. The force and moment of the flight are analyzed, and the dynamic model is established...
Morphing is usually designed to adapt the structure properties to different missions, while in this paper, it is also a method of flight control of the aircrafts. With morphing aircrafts taken as bodies with variable center of mass and inertia tensor, the centroid dynamic equations are analyzed to build the nonlinear dynamic model, which are then simplified for gull-wings with folding angles as the...
Single engine failure is a typical asymmetric problem for twin-engine carrier-based aircraft, which induces rolling and yawing divergence and aggravates takeoff performance during catapult launch. Multi-agents dynamics model integrated with aircraft, carrier and sea level atmosphere is established for the analysis of departure characteristics. Numerical simulation results reveal that lateral-directional...
Because of the high failure rate of the agricultural fixed-wing aircraft due to the terrible working environment, this paper mainly discusses applying robust fault-tolerant control algorithm and Reaction Control System (RCS) actuator to the flight control system when the multi-actuator aircraft is with actuator failures. Firstly, the self-repairing flight control system structure based on dynamic-inversion...
This paper focuses on the control problem of the aircraft with asymmetric structure damage. The contribution of this study is to present a new robust fault-tolerant control strategy based on nonlinear extended state observer and nonlinear dynamic inverse, which well balances the system performance and the tolerance of damage. Firstly, the dynamic model of the aircraft with asymmetric structure damage...
In this paper the triangular close formation flight control problem is addressed based on Lyapunov theory. Firstly, the three-dimensional nonlinear mathematical model of the formation flight control based on “leader-wing” mode was established. Secondly, both the dynamic and kinematic characteristics of the formation under the effect of aerodynamic coupling were analysed. Finally, the formation-hold...
For air-breathing hypersonic vehicle, there exits significant aerodynamic/propulsion/structure couplings due to the integrated design, which requires detailed performance limitation analysis during the concept design phase. Aerodynamic derivatives are important parameters for hypersonic vehicle while open-loop performance affects the achievable closed-loop performance, there is mutual relationship...
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