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A finite time convergent sliding-mode guidance law with hysteresis switching is proposed for the guidance considering thrust constraint and second-order dynamics of divert thruster. Firstly, the mathematical model of relative movement considering the second-order dynamic delay of engine is set up according to the planar relative motion of missile and target. Secondly, based on the principle of nullifying...
A tail-controlled BTT missile with flaps control is presented. First, we derive the nonlinear system model of the six-degree-of-freedom with two inputs. Based on choosing the angle-of-attack and roll angle as output variables, the internal dynamics of the system are analyzed by using differential geometry method, and are proved to be stabilized. An autopilot is designed by using the feedback linearization...
In equipment joint support, support tasks generated by different equipment share the resource of the support sites. Compared to conventional support system, more categories of support objects leads to a sharp increase in the number and randomness of support tasks. This makes the progress of some support activities affected by the resource occupation of other activities. In other words, the availability...
As the representative of hypersonic vehicles in the near space,X-51A and HTV-2 with characteristics of high speed and irregular acceleration often adopt the way of nonballistic maneuver flight, which cannnot make an accurate estimation of state of motion. This paper focuses on four typical nonballistic maneuver models of near space targets, proposes a kind of new Modified Variable Structure Interacting...
In this article, we establish a coordinate-free description of the kinematic and dynamic models of unfixed-base manipulator by using standard ideas from Lie group and Lie algebra. We use directly the exponential product formula to formulate the kinematic equation of an unfixed-base manipulator. In order to derive the dynamic equation of an unfixed-base manipulator, geometric variations, Riemannian...
Dynamic equations describing the attitude motion of flexible spacecraft with scissored pairs of control moment gyroscopes are established. A nonlinear controller is designed to drive the flexible spacecraft to implement three-axis large-angle attitude maneuvers with the vibration suppression. Singularity of three orthogonally mounted scissored pairs of control moment gyros is analyzed. A new moore-penrose...
In this paper, Quantum-behaved Particle Swarm Optimization algorithm (QPSO) is investigated from the perspective of Estimation of Distribution Algorithms (EDAs) for the first time, which proves that QPSO is a combination of EDA and Standard Particle Swarm Optimization algorithm (SPSO). Additionally, a novel cooperative quantum-behaved particle swarm optimization algorithm (CQPSO) is proposed to prevent...
A partially linearized model for the underactuated Euler-Lagrangian system composed of two single linear inverted pendulums is obtained based on the feedback linearization method. Then, the small deviation linearization technique is applied to the partially linearized model to obtain the linear model. For the linear model which is completely controllable, we propose a method to construct a synchronization...
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