56results about How to "Improve flight quality" patented technology

The invention discloses a building method for the universal comprehensive models of single-rotor helicopters and turboshaft engines. The method includes the building of the non-linear models of a helicopter and an engine, the static trimming of the single-rotor helicopter and the turboshaft engine, the dynamic calculation of the single-rotor helicopter and the turboshaft engine and the actual operation solution of the single-rotor helicopter and the turboshaft engine, wherein the static trimming adopts the Levenberg-Marquarat algorithm, the dynamic calculation adopts the fourth-order Ronge-Kutta method to solve the motion equation system of the helicopter and the single pass algorithm to solve the dynamic balance equation of the turboshaft engine, and the actual operation state solution adopts a modified linear quadratic regulator algorithm to carry out helicopter solution and a cascade PID (Proportion-Integration-Differentiation) plus torque feedforward plus collective pitch compensation and torsional vibration filter method to carry out engine solution and load filtration. The method can meet the test requirements of the universal models and control methods of the single-rotor helicopters and the turboshaft engines, and plays an active role in helping to shorten the development cycle and reduce the test risk and the cost.

The invention provides a quadrotor aircraft trajectory tracking control method based on nonlinear guidance, and belongs to the technical field of aircraft control. First a straight path coordinate system, an arc path polar coordinate system and an inertial coordinate system are established for a quadrotor aircraft; then the required height and the expected course angle, pitch angle and lateral acceleration for tracking a trajectory of the quadrotor aircraft are calculated; a height controller of the quadrotor aircraft obtains the required height for tracking the trajectory, an attitude angle controller obtains the expected course angle, a pitch angle controller obtains the expected pitch angle, a roll angle controller obtains the expected lateral acceleration, and finally the quadrotor aircraft flies according to a predetermined trajectory under the control of the height controller, the attitude angle controller, the pitch angle controller and the roll angle controller. The quadrotor aircraft trajectory tracking control method based on nonlinear guidance solves the problems that existing quadrotor aircraft tracking control cannot ensure constant-speed flight and response delay is large. The method provided by the invention can be used for quadrotor aircraft trajectory tracking control.

The invention relates to a self-adaptive excitation control system based on a plasma synthetic jet actuator. The system comprises a plasma synthetic jet actuator, an outer wall face pressure sensor, an intracavity pressure sensor, a computer, a high-voltage power supply, a high-pressure gas source and an airflow valve. The system is characterized in that the excitation efficacy of the plasma synthetic jet actuator can be adaptively adjusted according to the situation of an external flow field. The system has wide application range and high response speed, can be used for better mining the excitation efficacy of the plasma synthetic jet actuator, and realizes optimized positive flowing control for the external flow field.

The invention discloses a longitudinal control stability augmentation control law for an amphibious aircraft. In order to improve the longitudinal static stability of the aircraft in the take-off and landing state and restrain the weight of the aircraft in the water supply fire fighting process, the sudden gravity center change and the disturbance caused by sudden wind, on the basis of an existing assisting flight control system of the aircraft, a stability augmentation control system is interconnected with the assisting flight control system through a composite rocker arm. An irreversible type is adopted by the assisting flight control system, a gas-liquid-human sensing device is arranged, and therefore it is guaranteed that the flight control characteristics within a whole flight envelope meet the requirements of the airworthiness regulation. The stability augmentation control system makes sure that the short-period motion mode of the aircraft meets the requirements of the flight quality standard through pitching rate feedback, attack angle and overload feedback and the like.

The invention provides an aircraft height capture control method and device. The method comprises the following steps: obtaining vertical speed and height difference of an aircraft; determining the time when the aircraft starts to capture height according to the vertical speed and the height difference; and at the time above, carrying out height capture of the aircraft. According to the aircraft height capture control method and device, the problem that the time when the aircraft starts to capture the height is not accurate is solved, and furthermore, the effect of improving flight quality of the aircraft is achieved.

The invention relates to a novel redundancy integrated aircraft side bar control device, and belongs to the field of aircraft structure design. In order to solve the problems of the large volume, thelarge weight, the poor maintainability and the limited pilot leg space of an existing central rod control system of an aircraft, the novel redundancy integrated aircraft side bar control device is provided and comprises a handle, a housing, a spring load mechanism, a cross-shaped shaft assembly, a gear, an angular displacement sensor, a damper, a locking mechanism and a filter; the handle is connected to a longitudinal rocker arm in the spring load mechanism, the longitudinal rocker arm and a horizontal rocker arm in the spring load mechanism form a universal spindle coupling through the cross-shaped shaft assembly, the longitudinal rocker arm and the horizontal rocker arm in the spring load mechanism transmit horizontal and vertical swing of the handle to the angular displacement sensor through the gear, and the angular displacement sensor feeds back a movement displacement command of the handle to the aircraft. The novel redundancy integrated aircraft side bar control device is smallin size, small in weight, high in reliability and good in maintainability, can effectively reduce the complexity of an aircraft control system and improves the safety of the pilot.

The invention provides an adaptive augmentation control theory-based three-axis full authority control method for a flying wing unmanned aerial vehicle. According to the method, firstly a feedforwarddecoupling compensation controller is designed, so that the angular rate coupling can be counteracted; for a decoupled linear model, a self-adaptive augmentation controller is designed based on angular rate feedback, so that the problems that nonlinear coupling and unmodeled dynamics still exists in the model due to the fact that the feedforward decoupling controller cannot completely counteract the coupling amount are solved. Compared with an attitude control scheme, the angular rate control scheme accelerates the dynamic response speed of an inner loop, improves the damping characteristic, and expands the control surface to all available ranges. According to the method of the invention, the adaptive control part is added on the basis of the traditional PID control method, so that the consistent performance of a closed-loop system can be maintained under the conditions of uncertain dynamic and unknown parameter change of the system, and the robustness and the anti-interference capability of the system are improved.

The invention discloses a novel configuration vertical take-off and landing unmanned aerial vehicle belonging to the field of aircraft transmission system and lifting rotor, which comprises a fuselage, a rolling wing system, a vertical tail, a rudder, an aileron, a flap, a detection pod and an take-off and landing actuating cylinder. A rolling wing system is installed in the duct of the wing, andthe rolling wing system is composed of two groups of rolling wings with the same size and opposite rotating directions. The propeller shaft of each roller section is coaxial, and the full vector propulsion system of cycloidal propeller is composed of two sections of each group. The invention discloses a novel configuration vertical take-off and landing unmanned aerial vehicle, which can realize vertical take-off and landing on land-based platform and sea-based platform, and has better flying quality. The invention combines the characteristics of a rotor aircraft and a fixed-wing aircraft, andhas low dependence on take-off and landing site and strong environmental adaptability. At the same time, the whole structure of cycloidal propeller system is light and simple, which has broad militaryand civilian prospects.

The invention relates to a composite vertical take-off and landing (VTOL) efficient and high-speed aircraft. The invention provides a composite tilting wing tandem autorotation double-rotor aircraft.Two pairs of main lift rotor sets 5 are longitudinally arranged on the upper portion of an aircraft body 1, a fixed wing 2 is arranged in the middle of the aircraft body 1, two auxiliary power short wings 4 are arranged at the two ends of the fixed wing 2, ailerons 8 are arranged on the fixed wing 2, and parallel empennages 3, vertical empennages 6 and undercarriages 7 are arranged on the aircraftbody 1. The aerodynamic layout design of the composite tilting wing tandem autorotation double-rotor aircraft avoids the technical defects of the existing composite and tilting aircrafts, the tandemarrangement of the main lift suspended wings is adopted, and the rotor design defines the rotor group and the tilting power short wings according to the aerodynamic requirements of vertical take-off and landing, hovering and autorotation rotor mode cruising. The loading efficiency of the aircraft is higher than that of an existing composite helicopter, an existing tilt rotor aircraft and an existing composite multi-rotor aircraft.

The invention relates to arrangement of an aircraft capable of horizontally and vertically taking off and landing. Wings are arranged in a sweepforward mode, and wingtips on the two sides are each provided with an engine and a turnplate. An empennage is arranged by combining double tail booms with a V-shaped empennage, and an engine and two turnplates are arranged between the two tail booms. According to the arrangement, both horizontal taking off and landing and vertical taking off and landing can be achieved, in the flying process, the horizontal flying state and the vertical flying state can be switched, and longitudinal static stability of an aircraft can be kept during flat flight.

The invention discloses a time convolution network-based vibration noise suppression method for a small unmanned aerial vehicle sensor. The method comprises the following steps that: an external high-precision measurement system is utilized to obtain high-precision measurement values of an attitude angle and an angular speed during flight of a unmanned aerial vehicle, and at the same time, a gyroscope angular speed measurement value of an onboard MEMS inertial measurement unit of a flight control system under the influence of internal noise of the unmanned aerial vehicle is recorded, and a training data set and a test set after data are constructed after data cleaning and time synchronization processing are performed; a multi-layer time convolution network is built for training and testing, a trained model is called on a small embedded system for test flight verification. Experimental data shows that the time convolution network can effectively retain original signal characteristics and greatly reduce the influence of noise on a gyroscope measurement result.

The invention relates to the technical field of battery assemblies, and discloses an environment-friendly battery assembly for an unmanned aerial vehicle. The environment-friendly battery assembly comprises a battery box, mounting grooves communicating with the front surface of the battery box are formed in the left side and the right side of the battery box, and two sliding grooves which are symmetrical up and down are formed in the inner surfaces of the mounting grooves; the inner surfaces of the two sliding grooves in the mounting grooves are slidably connected with the same threaded platethrough sliding rods, the sides, away from each other, of the two threaded plates are fixedly connected with extrusion rods, and the ends, away from the threaded plates, of the extrusion rods are fixedly connected with a generator body. The input end of the side, away from the extrusion rod, of the generator body is fixedly connected with a driven disc. The driven impeller plays a role in controlling the input end of the generator body to rotate through external airflow of the unmanned aerial vehicle, and then the effect of improving the energy utilization rate and making the unmanned aerial vehicle more environmentally friendly is achieved by using surrounding airflow for power generation.