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127 results about "Near space vehicle" patented technology

Fault-tolerant sliding-mode control method for near-space vehicle

The invention discloses a fault-tolerant sliding-mode control method for a near-space vehicle. According to the fault-tolerant sliding-mode control method for the near-space vehicle, for the situation that the order of the magnitude of external disturbance in a quick loop and slow loop system is greatly larger than the order of the magnitude of uncertain times of the system, the nonlinear disturbance observer technology is used for processing hybrid disturbance, and unknown hybrid disturbance is estimated by a disturbance observer through known system information; in order to solve the problem that saturation of the control surface of the near-space vehicle is limited, the upper bound of the deflection angle output of a steering engine is applied to design of a control law, it is guaranteed that the input is within a certain range, auxiliary variables are designed, the deflection angle output of the steering engine is automatically adjusted through the self-adaption law, and therefore the situation that when the upper bound of the deflection angle is too large, the output is too large is avoided; a compensator is established through a radial basis function neural network and is used for fault-tolerant compensation when the steering engine breaks down, and therefore the problem that the steering engine of the near-space vehicle breaks down is solved. By the adoption of the fault-tolerant sliding-mode control method for the near-space vehicle, under the conditions of system uncertainties, unknown external disturbance, limited input saturation and a fault of the steering engine, the near-space vehicle has good control performance.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS

Dynamic-actuator aircraft attitude distributed type fault-tolerant control system

The invention discloses a dynamic-actuator aircraft attitude distributed type fault-tolerant control system. The system comprises an actuator fault detection and identification unit, an auxiliary system based on an observer and an inversion fault-tolerant control algorithm based on order filtering. According to the distributed type fault-tolerant control system, the actuator fault detection and identification unit is used for obtaining fault information of actuators in real time, the self-adaptive sliding-mode observer is obtained according to an attitude angular speed ring, the observer has strong robustness, an undetermined or interference upper bound does not need to be known, and control surface damage fault information an interference information are both hidden in the observer; a fault-tolerant controller is obtained based on an observer model. Robustness fault-tolerant control over various faults of different types under the multi-fault condition is achieved, the fault-tolerant control system is applied to near-space vehicle attitude stable control and tracking control under the condition of faults of the actuators and the control surface, flying attitude robustness fault-tolerant control is achieved, and good control performance and effect are achieved.
Owner:SHANDONG JIELIER FERTILIZER CO LTD

Method for apperceiving and reconstructing non-vision structural form of near space vehicle model

InactiveCN102542606AStrong real-timeStrong real-time performance and high transmission efficiencyUsing optical means3D modellingFiberGrating
The invention relates to a method for apperceiving and reconstructing a non-vision structural form of a near space vehicle model. The method comprises the following steps: on the basis of a distributed embedded dispersed bragg fiber grating sensing array, sensing and detecting strain information of each measuring point of a test model, and utilizing a certain curvature conversion algorithm to convert the strain information into curvature information; on the basis of a curvature interpolation, calculating the related coordinate value of each point of wings and frame of the test model according to a three-dimensional space curve fitting algorithm of orthogonal curvature information; utilizing a coordinate fuse algorithm to obtain an absolute coordinate value of each point of the model; and lastly, reconstructing the deformation state and the low-frequency vibrating form of the test model according to a computer graphic processing technology and realizing the three-dimensional visual real-time display for the change in the model form. An experimental system for the method comprises a simulated near space vehicle model, a fiber grating network analyzer with a network service function, a high-performance computer and a display, wherein the fiber grating sensing array is embedded into the surface of the simulated near space vehicle model.
Owner:SHANGHAI UNIV

Verification and simulation realization method for near space aerocraft model

The invention relates to the technology of the near space aerocraft. In order to provide a system-level consistency check novel model verification system output on the basis of the dynamic time sequence of the near space aerocraft model, give qualitative model verification based on the monte carlo method, carry out risk analysis to the model, comprehensively carry out consistency check to a model to be verified and give a visual verification criterion, the invention adopts the technical scheme that the verification and simulation realization method for a near space aerocraft model comprises the following steps of: (1) on the basis of the monte carlo simulation method, carrying out qualitative verification; (2) carrying out the qualitative model verification based on a time domain analysis method; and (3) carrying out qualitative model verification based on risk analysis, taking a model parameter as a risk to give a visual qualitative model verification criterion, giving a model comparison standard when a plurality of models to be verified exist, verifying whether the model can be safely used, and giving a safe-use range. The verification and simulation realization method for a near space aerocraft model, which is disclosed by the invention, is mainly applied to the design of the near space aerocraft.
Owner:TIANJIN UNIV

Simulation and verification method of control method of near space aircraft

The invention relates to the simulation and the verification of a control method in the field of aerospace. In order to provide a simulation and verification platform capable of supporting a near space aircraft to real-time simulation tests and performance evaluation from the design of a flight control system, the technical scheme adopted by the invention is as follows: a simulation and verification method of the control method of the near space aircraft is realized by virtue of the following devices: a simulation master control machine and a dSPACE real-time simulation machine, wherein the simulation master control machine is provided with a DS817 high-speed serial communication interface plate; and the simulation master control machine is communicated with the DS814 high-speed serial communication interface plate of the dSPACE real-time simulation machine through an optical fiber. The method comprises the following steps of: operating master control software; dividing a whole evaluation process into two parts, namely a control system efficiency evaluation process and an evaluation confirmation process, by performance evaluation software; and obtaining data, which is needed by control system efficiency evaluation, by the control system efficiency evaluation process through three steps. The simulation and verification method of the control method of the near space aircraft is mainly applied to simulation and verification in the field of aerospace.
Owner:TIANJIN UNIV

Integration design method for hypersonic slender body air vehicle and three-dimensional inward rotation air inlet channel

ActiveCN105775158ABroaden the working Mach number rangeLarge thrustGround installationsShock waveCounter flow
The invention discloses an integration design method for a hypersonic slender body air vehicle and a three-dimensional inward rotation air inlet channel, and relates to near space aerocrafts. The method comprises the following steps that a three-dimensional shock wave hook face is designated according to the design requirement; a series of basic flow fields are derived reversely according to the relation between the discrete shock wave curve and the curvature center; a slender waverider vehicle lower surface molded line and the outlet section of the three-dimensional inward rotation air inlet channel are designed, and streamline tracing in the counter flow direction is conducted in the basic flow fields; the two-dimensional projection shape of a lip of the three-dimensional inward rotation air inlet channel is designed, and a three-dimensional configuration of the lip of the three-dimensional inward rotation air inlet channel is obtained according to the shock wave relation; and the hypersonic slender body air vehicle is subjected to geometric construction based on a compression molded face. The performance of an outer waverider vehicle front body and the performance of the three-dimensional inward rotation air inlet channel are simultaneously considered by the generated slender body hypersonic air vehicle and the air inlet channel, the lift drag characteristic is high, full-flow incoming flow capture can be ensured, engine thrust is increased, outflow resistance is reduced, the operation Mach number range of the air inlet channel is widened, and natural transition of an inner waverider part and an outer waverider part is achieved.
Owner:XIAMEN UNIV

MPPT control circuit based on improved H-bridge DC-DC topology

The invention discloses an MPPT control circuit based on an improved H-bridge DC-DC topology, and belongs to the technical field of control of a solar unmanned aerial vehicle power supply system DC-DC circuit. The MPPT control circuit comprises a solar array working voltage sampling circuit, a solar array working current sampling circuit, a bus voltage sampling module, a bus current sampling module, an overvoltage protection module, a logic module, an MPPT mode driving module and a direct-through mode driving module. According to the MPPT control circuit, the working mode of the DC-DC circuit is automatically judged and selected, and two adjusting modes of Buck and Boost under the MPPT mode are enabled to be smoothly switched effectively through transition of the direct-through mode so as to guarantee the stability of the system. Unified control of the MPPT mode and the direct-through mode can be realized, the maximum output power point of a solar cell array can be tracked in real time, the utilization rate of the solar cell array can be enhanced and the power supply output capacity of an unmanned aerial vehicle power supply system can be enhanced so as to provide reference and help for energy supply of near space aircrafts represented by the solar unmanned aerial vehicle.
Owner:SHANGHAI INST OF SPACE POWER SOURCES

Convection heat-radiation system for temperature control of electronic equipment close to space vehicle

The invention discloses a convection heat-radiation system for temperature control of electronic equipment close to space vehicle, comprising an electronic equipment pressure maintaining cabin, a liquid storage tank, a pump, an in-cabin finned-pipe heat exchanger, a fan for an in-cabin radiator, an extravehicular finned-pipe heat exchanger, a fan for an extravehicular radiator, a pipeline and circulating fluid, the inlet of the pump is connected with the outlet of the liquid storage tank, the inlet of the liquid storage tank is connected with the outlet of the in-cabin finned-pipe heat exchanger, the inlet of the in-cabin finned-pipe heat exchanger is connected with the outlet of the extravehicular finned-pipe heat exchanger, the inlet of the extravehicular finned-pipe heat exchanger is connected with the outlet of the pump, and the circulating fluid working medium is filled in the pipeline; in the invention, a fluid loop coupling type convection radiator is arranged, waste heat in the electronic equipment is transmitted to the finned-pipe heat exchanger through the fluid loop and is discharged to the ambient atmosphere through the convection radiator driven by the motor; the convection radiator is used in special working environment at bottom part of a stratosphere to carry out heat radiation of high-power electronic equipment, and the structure is compact.
Owner:NANJING UNIV OF SCI & TECH

Method for tracking trajectories of hypersonic velocity near space aircraft

ActiveCN104777844AHigh precisionThe improvement did not take into account the shortcomings of aerodynamic forces in the cruising sectionPosition/course control in three dimensionsFlight vehicleRadar
The invention belongs to the technical field of radar target tracking, and particularly relates to a method for tracking trajectories of a hypersonic velocity near space aircraft. The method comprises the following specific steps of: according to earth universal gravitation, aerodynamic resistance and an aerodynamic lifting force which are applied to the hypersonic velocity near space aircraft in the cruise phase, establishing a motion model of the hypersonic velocity near space aircraft in the cruise phase; according to earth universal gravitation, aerodynamic resistance, an aerodynamic lifting force and an engine controlling force which are applied to the hypersonic velocity near space aircraft in the reentry phase, establishing a motion model of the hypersonic velocity near space aircraft in the reentry phase; according to echoed data of the hypersonic velocity near space aircraft in the cruise phase and in the reentry phase, obtaining the trajectories of the hypersonic velocity near space aircraft in the cruise phase and in the reentry phase; removing trace points which do not accord with the motion models of the hypersonic velocity near space aircraft from the trajectories of the hypersonic velocity near space aircraft in the cruise phase and in the reentry phase.
Owner:XIDIAN UNIV
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