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In this paper, a generalized biased proportional navigation (PN) guidance law to intercept higher-speed nonmaneuvering targets at a desired impact angle is presented. Inspired by controlling the turn rate of the relative velocity vector, the biased relative PN is introduced to design the relative heading angular rate, which is required to be proportional to the LOS rate as in the case of PN but with...
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...
In this study, we present a class of nonlinear analytical solutions for the dynamics of a fixed wing unmanned aircraft vehicle (UAV). These solutions are needed for the integration and fusion of sensor data for input to guidance and control algorithms. Derivation and integration of the 3-rd order vector differential equation of motion, and its applications to various dynamical models are presented...
The recent emergence of unmanned aerial vehicles asked for both well-performing auto-flight systems and fly-by-wire architectures. Towards this end, the trajectory control module of an integrated auto-flight control system is introduced in this paper, which utilizes nonlinear second-order error dynamics of the position error and uses nonlinear dynamic inversion as a control methodology. Flight test...
Optimizing energy consumption of Micro Aerial Vehicles is one of several problems that remains to be solved in the domain of UAVs. In a recent work, a novel quadrotor was introduced that was able, when possible, to roll on the ground thanks to a tilting propeller and caster wheels. In the following work, we build upon this idea with a trirotor helicopter where all the rotors are independently tilting...
This paper discusses the scheme and design method for UCAV autonomous/semi-autonomous control system. According to the investigation of the traditional tactical flight maneuvers and the existing air combat simulators, a mission-oriented control scheme is proposed to fulfill the autonomous/semi-autonomous requirements. A library including 9 maneuvers is designed by which complex tasks could be formed...
The Ground Proximity Warning System (GPWS) and Terrain Awareness Warning System (TAWS), developed at the Naval Air Warfare Center Aircraft Division (NAWCAD), Patuxent River, is currently fielded on the F/A-18A/B/C/D/E/F/G, AV-8B, being flight tested on the T-45, and E-2D fixed-wing aircraft, and ready for deployment on the MH-60R/S rotary-wing aircraft. GPWS/TAWS is a proven survivability safety-backup...
The paper aims to investigate the effects of two genetic encoding methods while developing a model helicopter pilot and realizing smooth trajectory in flying a simple maneuver - acceleration/deceleration maneuver. It makes use of both inverse simulation and genetic algorithms to optimize the performance of the model pilot. The overall goal of is to define the maneuver and have the developed pilot...
A strategy for trajectory design, motion camouflage, is introduced within the context of orbital relative motion. At first the equations of orbital motion for this approach are developed. The control strategy is then implemented using both an impulsive and continuous approach. A number of parameters are then optimized to minimize the fuel mass. The simulation results reveal that the predator successfully...
In the entry phase, aero-environment is extremely complex for Reusable Launch Vehicles (RLVs). This brings a huge challenge to design the entry guidance law for RLVs. In this paper, an entry trajectory planning method for RLVs is researched and the algorithm is improved to ensure the continuity and smoothness of the longitudinal reference trajectory. Meanwhile, the skipping of trajectory control is...
This paper is concerned with path planning for an autonomous flight vehicle operating in a steady, uniform flow-field. We model the vehicle as a particle that travels in the horizontal plane at a constant speed relative to the ambient flow. The vehicle may turn in either direction, subject to symmetric constraints on the turn rate and the turn acceleration. The contribution of the paper is a simple...
A new approach for developing guidance and control laws for aircraft that have departed controlled flight is presented. The method leverages and produces flight trajectories similar to what pilots would perform. The method induces a periodic orbit and then escapes from the periodic orbit into normal flight. The problem is approached from the inertial reference frame in order to better define the behavior...
This paper presents a guidance algorithm for formation flight of two UAVs. Since the nonlinear guidance algorithm have good properties to follow nonlinear flight trajectory based on geometric and kinematic, the nonlinear guidance algorithm is modified as a leader-follower station keeping formation control law for two UAVs using the relation of the nonlinear guidance algorithm to the proportional navigation...
For a range correction fuze of a rocket range-extended projectile, a DSP-based trajectory calculation and correction controller that is cooperated with MCU is designed to examine the axial acceleration during the flying of a projectile, and to perform the trajectory calculation and the start-up time calculation of a correction mechanism, and to control the action of a resistance-correction mechanism...
An optimal trajectory is very important to reusable launch vehicle (RLV) which facing the critical heating and aero force in reentry environment. The trajectory planning is a typical large scale and multiconstraint optimization problem. In this paper, an optimal trajectory planning for RLV from the beginning upper atmosphere state to lower atmosphere site with the minimum accumulated heat load or...
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