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With the regarding to the demand that the parameters vary rapidly over a wide range for the highly maneuverable technology (HiMAT) vehicle, a switched linear model with the locally overlapped characteristic is established for a full-envelope flight. Based on the mode-dependent average dwell time (MDADT) method, a stability criterion for the above switched linear model is proposed, and an application...
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...
The tilt tri-rotor UAV which combines the advantages of both rotary wing and fixed wing vehicle, offers the capability of hover, vertical take-off and landing and fast forward movement. Because of the complex structure and aerodynamics, the modeling and control of tilt tri-rotor UAV reamians a problem. In this paper, precise model of a tilt tri-rotor UAV is developed by combing system identification...
An approach using Petri net for airport apron dynamics modeling is presented. It is based on top-down, modular and resource-oriented methodology which makes the stepwise modeling possible. We divide the apron traffic system into disjoint zones and the basic net model is constructed by graph theory. The colored timed Petri net is utilized to model the traffic dynamics in each apron zones, and also...
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...
Safety and efficiency are significance for carrier aircrafts landing. One way to enhance the safety and efficiency level of the landing mission is to optimize the landing sequence. The paper mainly focuses on the carrier aircraft landing sequencing problem. In order to reduce the delay time and cost as excepted, build the optimization mathematical model, a detailed description of the design and procedure...
With regard to the objective of stealthy optimization in control surface deflection, the stealth-based multi-effectors distribution scheme is presented for flying wing in this paper. The radar cross section (RCS) of each control surface is calculated and analyzed. The stealthy efficiency data curves are obtained through comparing the deflection values with the normal state. Taking the objective of...
Aircraft scheduling is an important factor affecting the operating costs of airlines. Dispatching aircraft reasonably can not only maximize the benefits of the aircraft utilization, but also reduce flight delays. In this paper, we first transfer the scheduling model to the postman problem with the network model. Then, a scheduling model that use minimal aircrafts under the giving flight plan is put...
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 addresses the decision problem for terrain-following flights (TFFs) of aircrafts in unknown environments, where global trajectory planning methods cannot be applied directly. In such cases, the uncertainties and complexities of the terrain are needed to be dealt with especially. In order to realize the automatic generation of a terrain-following (TF) controller, a self-learning TF method...
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...
The technology of Bank-to-Turn is an important development direction of hypersonic glide vehicles' control. But there is a strong coupling between roll channel and yaw channel when the vehicle is in rolling maneuver. In this paper, a dual decoupling fusion control method is presented based on aileron-rudder cross decoupling control and model reference global sliding mode control for the problem of...
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...
In order to improve the performance of the integrated navigation system, a new navigation resource management method based on an efficiency function is proposed in this paper. Firstly, the framework of the navigation resource management method is established. Secondly, the representation of the efficiency function is given, which based on the navigation accuracy, the sensor accuracy and the navigation...
Aiming at the requirement of attack angle control of guidance weapon and the adverse effect of dynamic characteristics of control system on the guidance effect, a guidance law with terminal attack angle constraint considering the dynamic characteristics of the control system is proposed. Based on sliding-mode variable structure control theory, a three-dimensional guidance law is designed by using...
Near space aircraft enters a glide phase after the boost phase. A low glide altitude can reduce the hostile warning time to enhance penetration possibility. Therefore a lower boost phase altitude is favorable. The trajectory optimization of the boost phase for a three-stage solid rocket is an optimal control problem subject to various constraints. This problem is reformulated as a nonlinear programming...
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...
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