45results about How to "Improve landing safety" patented technology

The invention discloses a two-engine carrier-based aircraft with one engine off safety carrier landing control method, belonging to the flight control technology field. Through researching a flight characteristic of a carrier-based aircraft with asymmetric thrust force, the invention provides a flight state simulation method of the two-engine carrier-based aircraft with one engine off. Based on anormal two-engine aircraft flight state, different constant interference is added on a flight state variable of a flight speed, a pitch angle speed, a roll angle speed and a yaw angle speed respectively, thus a flight state of the two-engine carrier-based aircraft with one engine off is obtained. Based on a simulated flight state, vertical and lateral control law are subjected to reconstruction respectively, thus the two-engine carrier-based aircraft with one engine off safety carrier landing control method is obtained. Compared with the prior art, the method in the invention has the advantages of simple structure, reliable performance, high security of carrier landing and the like.

The invention discloses a method and a device for automatic landing leveling control of a small unmanned aerial vehicle. The landing leveling control device consists of a pitch attitude control circuit and an airspeed control circuit. Aiming at the problem that unmanned air vehicle with a simple sensor can not acquire vertical speed information and vertical acceleration speed information with required precision, the method and the device make full use of an available sensor information and calculate an expected pitch attitude g(t), an expected pitch attitude g'(t) containing correction, an expected airspeed vg(t), an expected airspeed vg'(t) containing correction, elevator control command delta Z(t), an engine chock valve command delta(t) and so on to realize control procedures in the control circuits and achieve the aim of automatic landing leveling control. Meanwhile, remote control operating personnel can operate an operating lever of an elevator and an operating lever of a chock valve in a leveling process according practical situation and carry out correction control of automatic leveling, thereby effectively improves the anti-interference capacity and landing precision of an airplane.

The invention discloses a method for controlling the automatic landing and leveling of an unmanned aerial vehicle, a control scheme combining with an open loop correction with a closed loop feedback control. Each control link in a control loop is realized by obtaining a lifting speed expected value vyg(t), a lifting acceleration expected value ayg(t), an expected pitching angle thetag(t) and an elevator skewness command Deltag (t), particularly, the lifting speed open loop integral correction vygSemi is introduced, thereby the deviation of the actual lifting speed and the expected value when the plane touches down is reduced. The correction has obvious physical meaning and strong engineering application, is easy to realize, is suitable for the automatic landing and leveling control with the requirement of high precision, and effectively improves the landing safety.

The invention discloses an aircraft automatic landing control method based on direct force control. The method comprises the steps that 1, a nonlinear model of an aircraft is trimmed and linearized, and a transverse channel and a longitudinal channel are decoupled; 2, a glide angle is determined, and an aircraft guidance law of the transverse channel and the longitudinal channel is designed, wherein the aircraft landing process of the longitudinal channel is divided into three sections, namely a level flight section, a transition section and a guide section; 3, a longitudinal control law and atransverse control law are respectively designed, wherein the longitudinal control law design comprises the design of an elevator channel, an accelerator channel and a flap channel and the moment decoupling of direct force control on the elevator; the transverse control law design comprises the design of an aileron channel and a rudder channel. According to the invention, aircraft landing controlcan be carried out under the condition of deck movement, so that the aircraft can safely land according to a preset flight path.

The invention discloses an automatic return flight laser positioning system for an unmanned plane. The system comprises a master control module, a laser position indicator and a photosensitive sensor arranged on the body of the unmanned plane, and a laser identification instrument which is positioned on a return point of the unmanned plane and allows the laser position indicator to identify and position, and the laser position indicator and the photosensitive sensor are connected with the master control module. The automatic return flight laser positioning system has the advantages of accurate return flight landing positioning, high automation level and high landing safety, allows the unmanned plane to accurately and safely land on the position of a return flight point under automatic return flight, out of control return flight and low-light return flight modes and effectively prevents casualties and loss of the unmanned plane.

The invention relates to an aircraft brake ground protection system which comprises a brake controller, brake control valves, aircraft wheel speed sensors and wheel load sensors, wherein the aircraft wheel speed sensors and the wheel load sensors are used for judging whether an aircraft is in an aerial state or a ground state. If the judging result shows that the aircraft is in the ground state, a pilot applies left and right brake instructions, the brake controller applies brake control signals to the brake control valves according to the brake instructions, and the brake control valves output brake pressure to enable the aircraft to be in a brake state; and if the judging result shows that the aircraft is in the aerial state, even if the pilot applies the left and right brake instructions, the brake controller can not apply the brake control signals to the brake control valves, and the aircraft is in a brake loosened state, thereby preventing the aircraft from landing in a braked mode because the pilot puts on the brakes by mistake in the landing process of the aircraft so as to prevent the tire skidding of the aircraft.

The invention relates to a general airplane landing radial line navigation method. The general airplane landing radial line navigation method comprises the following steps of 1, building a landing radial line by airborne navigation equipment according to airplane real-time position information provided by an airplane instrument, navigation information provided by a ground navigation station, and a received landing radial line building instruction, carrying out calculation, and displaying the landing radial line and a reverse-direction extending line of the landing radial line by cockpit display equipment, and 2, carrying out landing according to the landing radial line and the navigation information provided by the ground navigation station, guiding an airplane to the reverse-direction extending line of the landing radial line, and adjusting the airplane to make it fly or land along a direction of the landing radial line. The general airplane landing radial line navigation method solves the problem that the existing landing navigation method has a large potential safety hazard in a zone without ground navigation facilities. The general airplane landing radial line navigation method is a real-time, visual, convenient and reliable airplane navigation calculation method, improves an implementation method of real-time flight guidance of a general airplane and pilot autonomous operation display, and provides a visual and accurate landing navigation method.

A small unmanned plane undercarriage buffer relates to the field of aviation aircrafts and solves problems of low buffering efficiency, easy bounce, low reliability of a present flat spring type buffer. The small unmanned plane undercarriage buffer comprises an external cylinder, a first spring on the external cylinder, an internal cylinder having a damping hole, an air sac between the external cylinder and the internal cylinder; an upper joint, a lower joint, a piston rod extending into the internal cylinder, a piston, a damping plate, a pressure-limiting valve, a check valve, a guide sleeve and a locking cover, wherein the piston rod is orderly covered with the piston, the damping plate and the pressure-limiting plate; the piston rod is orderly covered with the check valve, the guide sleeve and the locking cover; the check valve, the guide sleeve and the locking cover are all disposed in the external cylinder; an internal-external cylinder annular oil storage cavity is formed between the internal cylinder and the external cylinder; the damping plate axially moves along the piston rod; the pressure-limiting plate limits maximum damping force to a preset valve during compression stroke; after the locking cover is tightly screwed, the guide sleeve, the check valve and the internal cylinder are axially pressed to the lower joint; the check valve controls communication between the internal-external cylinder annular oil storage cavity and a right cavity of the internal cylinder; and two ends of a first spring are respectively pressed against the upper and lower joints. The small unmanned plane undercarriage buffer possesses high buffering efficiency, uneasy bounce, stable performance and great reliability.

The invention belongs to the technical field of landing gears of vertical take-off and landing aircrafts, discloses an anti-falling collision single-leg buffer structure and a leg type landing gear, and solves the problems of falling collision and energy absorption in the landing process of a vertical take-off and landing aircraft by adopting an active control method. The undercarriage is designedbased on a bionics concept, a three-stage buffer/impact energy absorption mode of actively controlling to reduce overload peak value, buffer damping energy consumption and structure-controlled shaping deformation damage through mechanism movement is adopted, the impact peak overload is greatly reduced under the assistance of an impedance active control method, and the impact kinetic energy transmitted to the fuselage is effectively reduced, so that the structure safety is improved, and the crash survivability of passengers is improved; and meanwhile, the buffering and energy-absorbing efficiency of the undercarriage is improved, the falling collision and energy absorption requirements of the fuselage are reduced to a certain extent, and positive significance is achieved for reducing the structural weight of the fuselage.

The invention provides a rocket power fixed-point landing guidance method. The rocket power fixed-point landing guidance method mainly comprises the steps of rocket power fixed-point landing guidancemodel establishment considering aerodynamic resistance, guidance model convexity processing and second-order cone programming problem rolling time domain optimization calculation. The method aims to solve the problem of fixed-point landing guidance under the synergistic effect of thrust and aerodynamic resistance of an engine in a power descending stage of an aircraft, and converts the original rocket power fixed-point landing guidance problem into a sequential second-order cone programming problem to be solved by adopting a technology of combining lossless relaxation and sequence iteration. Acurrent guidance period instruction is calculated through rolling time domain optimization, the adaptability of the guidance method to model parameter uncertainty and motion state deviation is improved, meanwhile, fuel optimality and guidance robustness are balanced through a control margin adjustment method, and return safety and landing control precision are effectively improved.

The invention discloses a microwave guide based fixed-wing unmanned aerial vehicle autonomous landing control device and method. The microwave guide based fixed-wing unmanned aerial vehicle autonomous landing control device comprises a plurality of ground station nodes and a microwave reception processing unit; every ground station node comprises a microwave sending processing unit and a power supply management module which is used for supplying power for the microwave sending processing unit; the ground station nodes are used for receiving signals sent from an unmanned aerial vehicle and returning ground signals to the unmanned aerial vehicle; the microwave reception processing unit is arranged at the front end of the fixed-wing unmanned aerial vehicle and used for receiving and processing signals and generating corresponding action to adjust the aircraft attitude. The microwave guide based fixed-wing unmanned aerial vehicle autonomous landing control method comprises obtaining the strength of a plurality of communication signals between the current unmanned aerial vehicle and runway nodes; calculating a deviation angle of the current heading of the fixed-wing unmanned aerial vehicle and an approach runway and determining whether the unmanned aerial vehicle is aligned to the runway or not; giving out adjustment data if not. According to the microwave guide based fixed-wing unmanned aerial vehicle autonomous landing control device and method, the unmanned aerial vehicle can be adjusted according to the landing state of the fixed-wing unmanned aerial vehicle to be aligned to the runway and accordingly the success rate of the landing of the unmanned aerial vehicle is maximized.

The invention discloses real-time monitoring system and method of the tire pressure of an airplane. A power source supplies power for a control module of an undercarriage; the control module in the undercarriage supplies power for a monitoring module in an airplane wheel through a first rotating transformer and carries out interactive communication with the monitoring module in the airplane wheel through a second rotating transformer as well as carries out interactive communication with a control cabin instrument through a CAN (Control Area Network) bus; a pressure sensor monitors the pressure of wheel tires in real time and transmits data to the monitoring module in the airplane wheel; the monitoring module in the airplane wheel controls an air-release mechanism to adjust the tire pressure; and the control cabin instrument displays a tire pressure value and abnormal information and sets a pressure regulation and control instruction. The invention solves the problems existing in the cell power supply and radio-frequency communication and has the advantages of simple structure, favorable expandability and high reliability. In addition, the invention ensures that the airplane reduces the possibility of tire puncture under the conditions of different runways and loadings, thereby increasing the brake efficiency, reducing adverse shock excitation of the undercarriage, enhancing the landing safety of the airplane and reducing the airplane maintenance in ground services.

The invention relates to a sledge and wheel integrated landing gear for an unmanned aircraft. The sledge and wheel integrated landing gear comprises a supporting arm and an aircraft wheel, wherein the upper end of the supporting arm is arranged at the bottom of the unmanned aircraft body; the aircraft wheel is arranged at the lower end of the supporting arm; a sledge is arranged between the aircraft wheel and the supporting arm; the upper end of the sledge is hinged to the lower end of the supporting arm of the landing gear; and the aircraft wheel is arranged at the lower end of the sledge. The sledge and wheel integrated landing gear is scientific in design and relatively low in cost and has a simple structure and a wide application range; due to a simple mechanical structure, the landing safety of the unmanned aircraft during landing is improved effectively, the shock absorption effect is good, and the sledge and wheel integrated landing gear is suitable for various environments with complicated terrains; the unmanned aircraft can be landed steadily in a flat flying place, a rugged land and a soft grass land, and obstacles with relatively large volumes can be kept away from the aircraft during landing; and furthermore, the sledge and wheel integrated landing gear occupies a small area and has a small volume, light mass, high reliability and long service life.

The invention discloses a six-degree-of-freedom active landing buffer device for a spacecraft and a buffer control method. The buffer device is composed of a platform and buffer legs. The platform isconnected to three sets of buffer legs in the same state, and also bears the weight of a spacecraft structure. The buffer legs have three degrees of freedom, and the ends of the buffer legs can arbitrarily move in a three-dimensional space. When the spacecraft lands on rugged ground with an arbitrary attitude, the buffer device calculates the buffering force and moment required by a spacecraft fuselage according to the attitude and speed of the spacecraft fuselage. According to the configuration of the buffer legs at the moment when the spacecraft fuselage lands on the ground, the buffer forceand moment of the spacecraft fuselage are distributed to each buffer leg. By controlling the motor current of buffering leg joints, the required buffering force at the foot ends of the buffering legsis generated. The buffer device provided by the invention can maintain the spacecraft fuselage attitude stability while dissipating the kinetic energy of the spacecraft landing, and realize the softlanding of the spacecraft in any terrain environment.

The invention discloses an unmanned aerial vehicle landing method, system and device, and a storage medium, and relates to an unmanned aerial vehicle and a mobile platform. The method comprises the steps: determining a first coordinate position difference between the mobile platform and the unmanned aerial vehicle according to the obtained first position information of the mobile platform and second position information of the unmanned aerial vehicle; moving the unmanned aerial vehicle according to the first coordinate position difference until the first coordinate position difference is smaller than a preset distance threshold, wherein the mobile platform is provided with a plurality of tracking labels; acquiring tracking label images of the plurality of tracking labels; judging whether the moving posture of the mobile platform meets a preset landing condition or not according to the tracking label image; and when the moving posture of the mobile platform meets the preset landing condition, starting a landing program of the unmanned aerial vehicle to enable the unmanned aerial vehicle to land on the mobile platform. Therefore, the unmanned aerial vehicle is prevented from overturning in the landing process, the landing safety is improved, and unnecessary property loss is reduced.

The invention discloses an easy-to-carry miniature unmanned aerial vehicle and a using method thereof, and relates to the technical field of unmanned aerial vehicles. The portability and the use convenience are improved. The easy-to-carry miniature unmanned aerial vehicle comprises a vehicle body, four supporting frames distributed at equal intervals are correspondingly fixed to the outer wall ofthe periphery of the vehicle body through screws, vehicle arms are rotationally connected with one ends of the supporting frames, rotating shafts are installed on the outer walls of one ends of the vehicle arms through bearing pedestals, and wings are fixed to the outer walls of one ends of the rotating shafts through screws. The using method of the unmanned aerial vehicle comprises the followingsteps that when the unmanned aerial vehicle is taken for use, fixed sliding columns are pulled out of a second inserting groove and a first inserting groove; and the fixed sliding columns are continuously pressed, and the vehicle arms are rotated, so that the wings are stretched to designated positions. By arranging the supporting frames, the vehicle arms and other structures, the wings can be folded near the vehicle body, the overall space occupancy rate is reduced, and therefore the portability is improved; and by arranging structures such as a fixed sliding seat and the fixed sliding columns, the vehicle arms can be reliably fixed, and the structural firmness is improved.

The invention discloses a rotary acceleration type takeoff launching rack for an aircraft carrier. The rotary acceleration type takeoff launching rack comprises a launching rack upright column, launching rack arms and a lifting oil cylinder. The launching rack upright rod is an upright column is an upright column with axial acceleration and rotation functions; the telescopic launching rack arms are arranged on the upper portion of the launching rack upright column, and automatic grips are arranged at telescopic ends of the launching rack arms; the lifting oil cylinder is arranged on a column body of the launching rack upright column, and a telescopic end of the lifting oil cylinder is connected with the launching rack arms; the rotary acceleration type takeoff launching rack comprises a warning director takeoff launching rack, unmanned aerial vehicle takeoff launching racks and ship-borne fighter aircraft takeoff launching racks. The rotary acceleration type takeoff launching rack can be arranged on decks of two ship sides of the aircraft carrier, the warning director takeoff launching rack, the unmanned aerial vehicle takeoff launching racks and an island of the aircraft carrier are arranged on the same side of the aircraft carrier, and the ship-borne fighter aircraft takeoff launching racks are arranged on the other side of the aircraft carrier. The rotary acceleration type takeoff launching rack has the advantages of safety, high efficiency, simple structure, small occupied space and low manufacturing cost and energy consumption.

The invention is suitable for the field of manned vehicles, and provides a low-altitude composite aircraft. The low-altitude composite aircraft comprises an unpowered rotor mechanism, a four-rotor mechanism, a tilting-rotor mechanism and a rack used for fixing the mechanisms. The unpowered rotor mechanism is used for providing raising force for the low-altitude composite aircraft, the four-rotor mechanism comprises a left front rotor, a right front rotor, a left rear rotor and a right rear rotor with rotating shafts arranged in parallel and with the same rotating speed, the left front rotor and the right front rotor are arranged left and right and opposite in rotation direction, the left rear rotor and the right rear rotor are opposite in rotating direction, and the tilting-rotor mechanismis used for driving the left front rotor, the right front rotor, the left rear rotor and the right rear rotor at the same time to be subjected to tilting-rotor operation forwards or backwards. The low-altitude composite aircraft achieves vertical ascending and descending and is beneficial to improving of landing safety of the low-altitude composite aircraft, energy consumption is reduced, meanwhile, design is simplified, the producing and manufacturing cost is reduced, and the operation difficulty is reduced.

The invention provides a forced landing method and device and electronic equipment. In a forced landing method of an unmanned aircraft, the target forced landing site suitable for forced landing can be selected according to the image analysis result of the to-be-analyzed image obtained in real time, and the unmanned aircraft can be forced to land in the target forced landing site, so that the forced landing success rate of the unmanned aircraft can be improved, and the landing safety of the unmanned aircraft can be improved. In addition, the method can be suitable for analysis of the forced landing field in any area, and the accuracy of analysis of the unknown forced landing field is improved.