35results about How to "Suppress external interference" patented technology

A radar system for transmitting a FMCW radar sensor signal encompassing a series of frequency modulation ramps and phase-modulated with a first code sequence orthogonal to a respective other code sequence with which a time-synchronized transmitted signal of another FMCW radar sensor is phase-modulated; the radar echoes are phase-demodulated with a code sequence correlating with the first code sequence; and a distance and/or a relative speed of a localized object is identified from a Fourier analysis frequency spectrum, in a first dimension over sampled radar echo values of a frequency modulation ramp, and in a second dimension over the phase-demodulated sequence of radar echoes of the ramps of the transmitted signal; and a vehicle fleet radar system having an FMCW radar sensor in which a code set satisfying a code set orthogonality condition with a code set of a radar sensor of another vehicle is used for phase modulation/demodulation.

The invention provides a method for controlling axial direction of a high-precision magnetic bearing based on an interference observer. The method consists of a controller and the interference observer, wherein the interference observer comprises a Q filter and a rationalization generalized object inverse QGn part; the controller in a control system calculates according to displacement deviation to obtain basic control quantity so as to form a position closed loop control system; an interference value obtained by observation of the interference observer is negatively fed back into the basic control quantity to compensate exterior interference; and the formed current control quantity drives power amplification to realize high precision suspension of the magnetic bearing. The method leads differences caused by both exterior interference and objective parameter variation to be equivalent to a control input end, and introduces equivalent compensation into the control quantity to realize interference inhabitation. The method can carry out online observation and effective inhabitation against exterior interference which is not modeled or known, thereby improving control precision of suspension, and contributing to stability of the system.

A four-rotor unmanned plane finite time self-adaptive control method based on a nonsingular terminal sliding mode is provided; the method aims at a four-rotor unmanned plane system with inertia uncertainty factors and external turbulences; according to the four-rotor unmanned plane dynamic system, a nonsingular terminal sliding mode control method is employed, and self-adaptive control is combined, thus designing the four-rotor unmanned plane finite time self-adaptive control method based on the nonsingular terminal sliding mode; the nonsingular terminal sliding mode is designed so as to ensure the system finite time convergence features, thus preventing singularity problems existing in terminal sliding mode control, and effectively weakening jittering problems; in addition, the self-adaptive control is used for processing system inertia uncertainty factors and external turbulences; the method can remove the sliding mode surface singularity problems, and can effectively prevent and compensate the system inertia uncertainty factors and external turbulences, thus ensuring the system finite time convergence features.

A four-rotor unmanned plane finite time self-adaptive control method based on a fast nonsingular terminal sliding mode is provided; the method aims at a four-rotor unmanned plane system with inertia uncertainty factors and external turbulences; according to the four-rotor unmanned plane dynamic system, a fast nonsingular terminal sliding mode control method is employed, and self-adaptive control is combined, thus designing the four-rotor unmanned plane finite time self-adaptive control method based on the fast nonsingular terminal sliding mode; the fast nonsingular terminal sliding mode is designed so as to ensure the system finite time convergence features and fast convergence speed, thus preventing singularity problems existing in terminal sliding mode control, and effectively weakening jittering problems; in addition, the self-adaptive control is used for processing system inertia uncertainty factors and external turbulences; the method can remove the sliding mode surface singularity problems, and can effectively prevent and compensate the system inertia uncertainty factors and external turbulences, thus ensuring the system finite time convergence features.

The invention discloses a low prevention zone difference transmission structure employing a silicon through hole and an interlayer interconnection structure. In the low prevention zone difference transmission structure and the interlayer interconnection structure, excellent electric transmission performance of the difference silicon through hole is shielded while thermodynamics characteristics ofa difference silicon through hole transmission structure are improved. Reduction of a prevention layout zone can be caused by mismatching thermal stress when the difference transmission structure employing the silicon through hole, and integrated level improvement of transistors in a large scale array can be facilitated. In actual application of a three dimensional integrated circuit, the low prevention zone difference transmission structure and the interlayer interconnection structure normally relate to difference signal transmission between multilayer structures. Aimed at improving transmission efficiency, the invention discloses a cross-connect method for interlayer structures.

The invention relates to a flexible spacecraft multi-domain dependent robust fault-tolerant control method based on input time-varying delay, comprising the following steps: first, taking flexible vibration as external disturbance, and establishing a flexible spacecraft state space model containing external disturbance and input delay through deduction by use of a Lagrange method; then, establishing a fault model, integrating the fault model into a flexible spacecraft state model needing fault tolerance, and converting an actuator partial failure fault-tolerant control problem into an uncertain parameter robust control problem according to the fault model; and finally, designing a state feedback passive fault-tolerant controller based on a linear matrix inequality approach by combining delay-dependent Liapunov functional and uncertain parameter robust H-infinity control. The method has the advantages of simple design and easy implementation, is applicable to fault-tolerant control under the condition that a flexible spacecraft has both input delay and actuator partial failure in the field of aerospace, and can keep a system asymptotically stable and suppress external interference.

The invention provides a tail sitter type unmanned aerial vehicle transition section robust control method based on a nonlinear disturbance observer. Firstly, an H-infinity controller is designed fora nominal model of a tail sitter type unmanned aerial vehicle at a transition section so as to achieve the expected trajectory tracking performance; and then, in order to inhibit the influence by uncertainty, nonlinear characteristics and external interference and to improve the robustness of the system, the nonlinear disturbance observer is designed. Compared with other control methods, accordingto the robust control method, the dynamic and static tracking performance of the tail sitter type unmanned aerial vehicle can be improved, and under the condition of large maneuvering and strong coupling, the influence by the uncertainty, non-linearity and the external interference can be inhibited by the disturbance observer, so that the expected performance is achieved.

The present invention provides a fuel supply apparatus, wherein relative to a fuel pump inside a fuel box, a fuel filter is arranged outside the fuel box, thereby increasing the assembling property of the fuel box on vehicle body. A fuel pump (22) is configured inside the fuel box from the bottom (24) of the fuel box (20), and the fuel filter (41) is arranged at the bottom (22b) of the fuel pump (22).the rear lower end of a carrying bracket (51) carrying the fuel filter (41) is located lower than the fuel filter (41).

The invention discloses a permanent magnet synchronous motor position control method based on a boundary layer reaching law, and aims at a permanent magnet synchronous motor system with inertia uncertain factors and external disturbance. According to a dynamical system of the permanent magnet synchronous motor, a boundary layer reaching law is designed, and a permanent magnet synchronous motor position control method based on the boundary layer reaching law is designed by adopting a sliding mode control method and combining an adaptive method. The boundary layer reaching law is designed to ensure the rapidity of the system outside the boundary layer, decelerate in the boundary layer and weaken buffeting. Adaptive control is used to handle inertial uncertainty and external disturbances of the system. The invention provides a control method capable of weakening buffeting and effectively inhibiting and compensating inertia uncertainty and external interference of the system, and the finite time convergence characteristic of the system is ensured.

The invention relates to the technical field of nonlinear system control, and provides a nonlinear system adaptive event trigger control method and system, and the method comprises the steps: obtaining a reference signal and controller output at an initial moment, obtaining nonlinear system control input at the initial moment, obtaining a first auxiliary variable through an auxiliary system, and obtaining a second auxiliary variable through coordinate transformation; obtaining a second auxiliary variable, and obtaining an estimated value of a disturbance term through a nonlinear disturbance observer; a dynamic signal in a dynamic event triggering mechanism is obtained, the controller output is updated through the virtual controller and the dynamic event triggering fuzzy controller in sequence, and the controller output is returned to the auxiliary system; wherein a dynamic event triggering mechanism of the dynamic event triggering fuzzy controller dynamically adjusts a threshold parameter of an event triggering condition; based on the second auxiliary variable, an adaptive law is obtained to update the virtual controller. And the triggering frequency of a dynamic event triggering mechanism is reduced.