422results about How to "Smooth landing" patented technology

The present invention relates to an unmanned flying vehicle using a PCB including a main board controlling power supply and flying operation, a motor rotating a propeller by changing electric energy into mechanical energy, a PCB frame changing a signal from a remote controller and connecting the main board with the motor, a propeller generating an impellent force by from rotation by the motor, a receiver receiving a control signal of the remote controller, and a remote controller controlling a motor rotation speed of a quadrotor and direction change, and accordingly, the structure of the unmanned flying vehicle can be simplified so that the flying vehicle can be down-sized and light-weighted, and assemblability can be improved.

An intersection adapted for engagement with a toy racetrack to provide an combination jump and overcrossing intersection for vehicles traversing the racetrack. The device features first and second supports engageable with inline pairs of track thereby forming two pathways across a jump formed by a gap in the middle of the device. The first support is in a translatable engagement with the second support between a first position where vehicles crossing the gap at the same time would collide and a second position forming a second path where vehicles jumping the gap are on different trajectories.

The invention provides an unmanned aerial vehicle mixed system carried by an unmanned ship. The system comprises the unmanned ship, an unmanned aerial vehicle and a mixed communication system. The unmanned ship serves as a water domain movable platform for the unmanned aerial vehicle, and mainly comprises a ship body, a ship-borne control system arranged on the ship body, a ship-borne power device and a ship-borne application device. The unmanned aerial vehicle comprises an unmanned aerial vehicle body and a vehicle-mounted coordinating system. The unmanned aerial vehicle body is provided with a vehicle-mounted navigation device, a vehicle-mounted obstacle-avoiding device, a vehicle-mounted control device, a vehicle-mounted power device and a vehicle-mounted application device. The mixed communication system comprises a ship-borne communication device and a vehicle-mounted communication device. The ship-borne control system of the unmanned ship and the vehicle-mounted control device of the unmanned aerial vehicle body exchange data through the mixed communication system; the ship-borne control system serves as the core for the mixed communication system, and the unmanned ship and the unmanned aerial vehicle are controlled uniformly by an internal bus and a communication board card to work in cooperation. By means of the mixed system, the unmanned ship and the unmanned aerial vehicle can effectively supplement each other in water domain and space domain functions, and meanwhile the disadvantages of the water domain unmanned ship during space domain perpendicular work are compensated for.

The invention provides a bionic grasshopper jumping robot, comprising body, front leg support damping device and back leg jump device. Said front leg support damping device comprises sleeve hinged on the body, one end is on the sleeve, the other end is on the brace; the brace is equipped with compression spring. Said back leg jump device comprises body brace, transition link rod, thigh, shank and treadle sheet; body brace is fixed on body, one end is connected with thigh, the other end is connected with transition link rod, the middle part of shank is connected with transition link rod, one end is connected with thigh, terminal end is connected with treadle sheet, a spring is located between the connection point of thigh and shank and connection point of body brace and transition link point; the shanks on the two sides of body are connected together through shank link rod, the body is equipped with energy storage device, energy release device, control circuit and power. The invention is characterized by accordance with grasshopper jumping feature, simple structure, high efficiency, fast and continuous jump.

The invention discloses an attitude-adjustable moon soft lander which comprises a lander body and buffering leg components, wherein the buffering leg components are uniformly mounted on the circumferential side wall of the lander body and can realize stable landing. An attitude-adjustable effective load carrying platform is mounted inside the lander body and adopts a four-degree-of-freedom parallel connection platform which comprises an upper platform, a lower platform and five electric push rods connected with the upper platform and the lower platform, wherein displacement sensors which are used for acquiring a distance between the electric push rods and the upper and lower platforms in real time are mounted at body ends of the five electric push rods; a double-shaft tilt angle sensor used for acquiring attitude information of the upper platform is mounted on the upper platform; and the five electric push rods are controlled to realize attitude adjustment of the moon soft lander. Solar panels used for charging the soft lander are mounted on the side walls of the soft lander body through torsional springs, and the torsional springs and electromagnets mounted on the side walls of the soft lander body are used for unfolding and folding the solar panels. The attitude-adjustable moon soft lander has the benefits as follows: soft landing can be stably realized, and the attitude can be adjusted.

The invention relates to a first-child-stage parachuting-recovery carrier rocket. The first-child-stage parachuting-recovery carrier rocket is combined by two stages of rockets and comprises a recovery system arranged in a shell of a first-child-stage rocket, wherein the recovery system comprises a speed reducing device and a buffering device; the speed reducing device is arranged at the position close to the interstage section of the shell and comprises a supporting frame connected with the inner wall of the shell; a parachuting device is arranged on the supporting frame and is used for reducing the speed of the separated first-child-stage rocket in the falling process; the buffering device comprises two buffering airbags, one buffering air bag is arranged at the position close to the interstage section, the other buffering airbag is arranged at the position close to the tail section, and the two buffering airbags are used for buffering the first-child-stage rocket in the landing process. The first-child-stage parachuting-recovery carrier rocket has the advantages that the first-child-stage rocket can land smoothly without damage under the common action of the buffering device and the speed reducing device, so that non-damage recovery of the first-child-stage rocket can be realized, and the first-child-stage rocket can be secondarily utilized, so that the launching cost can be reduced.

The invention discloses a walking robot having a landing buffer function. The walking robot comprises a landing platform (1), a plurality of buffering walking mechanisms (2) surrounding the landing platform (1), a landing parachute pack (3) and a controller (4). Each buffering walking mechanism (2) comprises a multifunctional strut (21), two single-function struts (22) and a foot pad (30). When a robot lands, the multifunctional strut (21) can have the landing buffer function; and after the robot lands, the multifunctional struts (21) and the two single-function struts (22) jointly achieve a walking function. The walking robot lands stably, is flexible in gait, walks stably and is high in bearing capacity, safe and reliable, the walking capacity on complex terrain conditions can be enhanced remarkably, and the throwing in the air can be achieved.

The invention discloses a self-reset wheel-leg jumping composite mobile robot. The self-reset wheel-leg jumping composite mobile robot comprises a jumping device, a reset and wheeled driving integrated device and a torsional spring energy storage and ground falling buffer integrated device, wherein the jumping device is used for realizing the function of storing and releasing jumping energy; the reset and wheeled driving integrated device is used for realizing the functions of reset after the jumped robot falls to the ground and topples and wheeled driving; and the torsional spring energy storage and ground falling buffer integrated device is used for realizing the functions of storing jumping energy by a torsional spring and buffering the ground impact force during ground falling by using the torsional spring and an arc-shaped soleplate. The jumping motion and wheeled motion are combined to improve the maneuvering performance of the robot, namely the wheeled driving is adopted on the flat ground, the efficiency is reliable and the maneuvering performance is improved. When the robot meets steep terrains or cannot pass through barriers by the wheeled motion, the jumping motion is switched, the jumping gesture and storage energy are regulated to control the jumping height and jumping distance effectively, and the different jumping models are selected according to requirements of environment. When falling to the ground after jumping and toppling, the robot can be reset by a reset mechanism, so that the robot is in the upright state again to complete the next jumping.

The invention discloses a novel hybrid vertical / short take-off and landing (V / STOL) unmanned aerial vehicle, aiming at solving the problems of complicated structure, high cost and the like of the existing aerial vehicles. The unmanned aerial vehicle comprises a body, a main wing, take-off and landing auxiliary wings arranged on the main wing, canards arranged at the front part of the body, a vertical tail arranged at the rear part of the body, a landing gear, an accumulator battery, a control system, a power supply management system and the like, wherein the landing gear, the accumulator battery, the control system, the power supply management system and the like are arranged below the body. The unmanned aerial vehicle adopts a ducted fan to provide a lift and assist balance during vertical take off and landing, and adopts an engine to provide the main push force and to automatically generate electricity so as to effectively utilize oil-electricity complement, simultaneously the reasonable hybrid use of fuel oil and electric energy is achieved through the structure and aerodynamic configuration design of the aerial vehicle, thereby achieving vertical and short take-off and landing, reducing the control difficulty of the aerial vehicle and solving the problem of inconsistence between difficult control and short voyage of the existing V / STOL unmanned aerial vehicles; the novel hybrid vertical / short take-off and landing (V / STOL) unmanned aerial vehicle disclosed by the invention can achieve vertical / short take-off and landing, and has the advantages of flexible and steady flight, wide application range and the like.

The invention relates to an unmanned aerial vehicle (UAV) dropsonde and a method for releasing and controlling the same. A global positioning system (GPS) antennal, a GPS receiving unit, a battery, a sounding acquisition control circuit, a wireless transmission unit, a parachute, an air pressure sensor, a temperature sensor and a humidity sensor are arranged in a dropsonde shell; a transmission antenna is installed on the shell; the upper part of the shell is connected with a hanger; the upper surface of the shell is fixedly provided with contacts; the battery is connected with the GPS receiving unit, the wireless transmission unit and the sounding acquisition control circuit through a relay to form a control loop; two contact reeds connected with the contacts are parallelly connected to the control loop; the air pressure sensor, the temperature sensor and the humidity sensor are fixed outside a cabin; guide lines of the air pressure sensor, the temperature sensor and the humidity sensor are respectively connected with control contacts of a load control circuit. Electromagnet can be selected to lock or release the UAV dropsonde, and the method for releasing and controlling the UAVdropsonde has a simple principle and effective protection measurements, and can be used for effectively and directly acquiring the temperature data, the humidity data and the air pressure data of a vertical atmospheric section and sending the data back to a ground center in real time.

The present invention relates to a gimbal of an unmanned aerial vehicle and an unmanned aerial vehicle using same. The unmanned aerial vehicle comprises a body and a gimbal, the gimbal comprises a supporting mechanism and a connecting mechanism, the supporting mechanism is used to carry a carrier, and the connecting mechanism is a telescopic structure. The supporting mechanism is arranged onto the connecting mechanism. The connecting mechanism is used to mount the supporting mechanism to the body of the unmanned aerial vehicle, and can drive the supporting mechanism to cause the carrier to get close to the body of the unmanned aerial vehicle and to be received into the body of the unmanned aerial vehicle, or drive the supporting mechanism to cause the carrier to protrude out of the body of the unmanned aerial vehicle. The gimbal of the present invention can enlarge viewing angles of a shooting device carried thereby, and avoid the shielding of self-components of the unmanned aerial vehicle.

The invention discloses a telescopic landing leg expanding mechanism for a planetary probe, comprising an outer support cylinder, an inner support cylinder and a piston cylinder; internal threads are arranged on the inner wall of the outer support cylinder and are matched with external threads on the outer wall of the inner support cylinder; a rotating motor is arranged on the upper end of the inner support cylinder; the rotating motor is connected with the inner support cylinder through a linear bearing; an output rotating shaft of the rotating motor is fixed with the inner support cylinder;the piston cylinder is arranged in the inner support cylinder; a tension buffering spring and a compression buffering spring are respectively arranged between the piston cylinder and two ends of the inner support cylinder; and the outer support cylinder, the inner support cylinder, the linear bearing, the piston cylinder, the rotating motor and the output rotating shaft are positioned on the sameaxial line. The expanding mechanism realizes locking function through threaded fit; the rotating motor drives the inner cylinder to rotate; the inner cylinder rotates outwards from the threads to eject the piston rod; the motor reversely rotates to reset the inner cylinder; the buffering mode is spring buffering; the expansion radius of the landing leg is controllable; the expanding mechanism is repeatedly used; furthermore, the expanding mechanism is simple in structure and high in reliability.

The invention provides a flight control method for accurate landing of an unmanned aerial vehicle. The flight control method comprises the following steps that a target identification graph is manufactured; a matching parameter is selected when the unmanned aerial vehicle flies to a landing position; an image of a landing site is found by a camera; the unmanned aerial vehicle moves above the landing site; and horizontal distance, positive direction angle and landing speed are controlled through image identification, and finally the unmanned aerial vehicle lands on the ground and paddles are stopped. According to the flight control method for accurate landing of the unmanned aerial vehicle, the landing process is divided into a plurality of stages according to different heights, error parameters and landing speed of each stage are arranged differently, and the requirements that required flight precision and time are gradually improved with height reduction and precision improvement of the distance and angle are met; and horizontal distance control needs to be controlled by four-grade PID, by adding a control section and variable, stability, anti-interference performance and controlquality of the unmanned aerial vehicle is improved, so that accurate control is guaranteed. It is ensured that the whole process is stable, reliable and timely and the precision is high.

The invention discloses a cloud control-based automatic express delivery system employing an unmanned aerial vehicle. The system comprises a self-tightening blade (1), a satellite positioning module (2), a camera module (3), a triaxial pan-tilt (4), an unmanned aerial vehicle master control module (5), a lifting bracket (6), a high-performance brushless motor (7), an optical flow sensor (8), an ultrasonic module (9), a high-performance electron speed regulator (10), an express loading box (11), an express loading box controller (12), an infrared grating (13), a fingerprint scanning module (14), a high-precision stepper motor (15) and a lithium battery pack (16). The unmanned aerial vehicle is uniformly controlled by adopting cloud; the unmanned aerial vehicle senses the surroundings by virtue of various sensors to achieve autonomous flight; the flight security is high; and the express can be accurately delivered to the scheduled place, the identity of an express recipient is checked and photo evidence is carried out on the express recipient through the carried camera module (3) after the express is delivered, so that safe and accurate delivery of the express is ensured.

The invention discloses a self-floating seabed-based observation platform which comprises a platform housing and a support arranged inside the platform housing, wherein monitoring equipment and acoustic release transponders are mounted on the support, the platform housing comprises an upper layer platform and a lower layer platform, the support is arranged in the upper layer platform, the upper layer platform is detachably connected with the lower layer platform through a mechanical tripping gear, due to the adoption of the technical scheme, the upper platform and the lower platform are combined to form a set of internally-built flow guiding structure, after being put from a water surface, the self-floating seabed-based observation platform can effectively prevent rolling during a falling process, and that an observation platform can fall onto the bottom stably can be ensured; the two shallow water acoustic release transponders are combined together with the mechanical tripping gear, and the two-stage tripping gear is designed, namely each acoustic release transponder can be independent from the upper layer platform, and the upper layer platform and the lower layer platform loaded with equipped can are divorced for floating.

The invention discloses a high-rise escape machine and an automatic control method for escape. The invention belongs to the technical field of fire fighting equipment, and is used for self-life saving for people in tall buildings in case of fire hazards. The high-rise escape machine comprises a centrifugal mechanism (7), a braking mechanism (35), a rope recycling mechanism (36), a microcomputer controller (11), a machine frame (1), a storage battery (26), an upper pulley (5), a lower pulley (6), a safety hook (3) and a rope (4). The automatic control method of the high-rise escape machine for escape monitors the speed in the escape process in real time by using a microcomputer, and automatically controls the height of the brake point and the magnitude of the brake power of the magnetic powder brake (10) according to the height of the building and the weight of the persons, thereby realizing quick and safe escape. The invention can be widely used for office buildings, classrooms, residences and other locations.

The invention discloses a virtual reality technique-based airplane smooth landing aid system and a method thereof, belonging to the field of aviation service. The system of the invention comprises a data acquisition module, a virtual reality processing module and a display module. The method of the invention includes that: when an airplane is landing, a real-time pictures of relative position between the current airport road surface and airplane landing wheels are simulated at a control terminal by adopting virtual reality technique and combining an airport road surface real-time picture and airplane landing wheel sensor data. The real-time pictures are beneficial for a pilot to operate and judge, thus judging of the pilot on flight path and airplane position can be more visual. According to real-time relative position, optimal place, optimal angle and optimal speed for landing are obtained by terminal simulation, so as to aid the pilot to realize smooth landing of airplane.

The invention provides a detachable helicopter landing platform. The detachable helicopter landing platform is formed by splicing a plurality of triangular base plates. Telescopic supporting legs are arranged at three vertex angles of each base plate, and snapping grooves or protrusions are arranged on three edge lines of the base plates, the adjacent spliced base plates are mounted and spliced through the snapping grooves and the protrusions, and the snapping grooves and the protrusions are strengthened and fixed through one or more fixing screws. The platform has the advantages of being simple in structure, convenient to mount and easy to manufacture, and helicopters can be landed on uneven earth surfaces.

The invention relates to an unmanned aerial vehicle crash protection system and a control method and belongs to the technical field of unmanned aerial vehicles. The system is specifically characterized in that an inertial sensor is installed on a body of the unmanned aerial vehicle; a crash and slow descent device is arranged on the top of the body; and a crash protection controller as well as anemergency power supply and a parachute are arranged in a shell of the crash and slow descent device. When weightlessness of the unmanned aerial vehicle is detected, the parachute is rapidly inflated by a high-pressure helium bottle, so that the parachute can be rapidly unfolded to form. Moreover, by utilizing the characteristic of low helium density, crashing impact force of the unmanned aerial vehicle can be greatly buffered, so that the unmanned aerial vehicle can smoothly land, and damage of the unmanned aerial vehicle can be effectively avoided.

The invention discloses a flight control method and apparatus for a multiaxial flight vehicle. The method includes: detecting whether a plurality of power systems with countershaft design are abnormal by a flight control system; and when the flight control system detects that any power system is abnormal, adjusting the countershaft power system to make the multiaxial flight vehicle land stably. The method and the apparatus provided by the invention solve the problem that the multiaxial flight vehicle cannot maintain balance when any power system in the multiaxial flight vehicle is abnormal in the prior art, and the multiaxial flight vehicle still can land stably when abnormality occurs to any power system of the multiaxial flight vehicle.

The invention relates to an inclined rotating wing aircraft with telescopic wing membranes. The inclined rotating wing aircraft comprises an aircraft body, a center shaft, a main transmission mechanism, first to third power units, an outer side rod, a support rod, a main wing membrane, a flight controller, and first to third undercarriages. The inclined rotating wing aircraft disclosed by the invention is improved on the basis of the structure of the traditional four-wing aircraft, and an inclined rotating structure of an inclined rotating four-rotary wing aircraft and a wing membrane structure of a flapping wing aircraft are added. According to the inclined rotating wing aircraft, the structural state of the inclined rotating wing aircraft includes a ground sliding state, a four-rotary wing flying state and a high-altitude cruising state; when the inclined rotating wing aircraft is in a ground movement state, the undercarriages contact with the ground, the main wing membrane is open, and the forward movement, backward movement, left rotation movement, right rotation movement, climbing movement and downgrade movement of the aircraft are realized by regulating the speed of four rotary wings; the movement state of the aircraft on the ground is realized under the action of the undercarriages, and the movement state is impossible to realize by the inclined rotating four-rotary wing aircraft and the flapping wing aircraft; and the climbing movement and the downgrade movement can be realized without changing the state of the aircraft, so that the energy consumption is reduced, and the complexity of a control program is prevented.

The invention provides a constant tension highline maritime adaptive control and supply system and supply method. The system comprises a constant tension highline maritime supply subsystem and a constant tension highline maritime adaptive control subsystem; the constant tension highline maritime adaptive control subsystem is used for driving and controlling an outer index winch (3), an inner index winch (4), a highline winch (5) and a wave compensation device (6), so that a crane device (7) moves between a supply ship and a receiving ship. The system and the method have the advantages: (1) a highline adopts constant tension adaptive control, so that manual intervention s not needed in the supply process, vibration of goods on cableways is reduced and the supply efficiency is improved; and (2) wave compensation is performed on the highline by adopting a wave compensation technology, so that tension constant double closed-loop control of the highline is kept, relative movements of the two ships are compensated, safe and stable hoisting and landing of goods when the ships swing are ensured, and mutual collision between the goods and the decks of the working ship is prevented.

The invention relates to a safe and reliable intelligent unmanned aerial vehicle having an online power generation function. The intelligent unmanned aerial vehicle comprises a body, a flight mechanism arranged above the body, a wind power generation mechanism, and a support mechanism arranged below the body. An indication mechanism is arranged on the body. According to the safe and reliable intelligent unmanned aerial vehicle having the online power generation function, the included angle between blades and the wind direction is adjusted through an angle adjustment unit, thus the efficiency of power generation is improved, and the cruising ability of the unmanned aerial vehicle is guaranteed. Furthermore, the security of the unmanned aerial vehicle during landing is greatly improved through three grades of buffering, that is, primary buffering realized through repulsive acting force generated by electrifying a first coil and a second coil, secondary buffering realized by using a compressed first spring, and tertiary buffering realized by utilizing a piston to do work on an air cylinder, and the unmanned aerial vehicle is guaranteed to land smoothly.

The invention discloses a precise landing control system and method based on multi-information fusion. The system comprises: a ground end module used as a UAV accurate landing target point to transmitan infrared image to the sky to be identified by a sky end module; and the sky end module configured to acquire and identify the infrared image transmitted by the ground end module, calculate the relative position of the ground end module, detect the ground relative height, perform data fusion on a visual module, a millimeter wave radar, and the flight control information of a UAV system acquiredin real time, and send a UAV navigation control signal. The method is implemented based on the above system. The system has a long detection distance, high detection precision and a good anti-interference ability.

The escape apparatus for high-rise building is superior to available escape apparatus. The escape apparatus includes descending rope, hook in the lower end of the descending rope and person holding mechanism on the hook, and features its slowly descending device on one rack. The slowly descending device includes rope wheel with shaft on the rack, descending rope wound onto the rope wheel and with the upper end connected to the rope wheel, rocking handle on the rope wheel, upper connecting part connected to the outer end of the rocking handle, limiting nut to avoid upper connecting part fall, elastic rope connected to the lower end of the upper connecting part, balance weight connected to the lower end of the elastic rope, and self-locking unit on the rack. The escape apparatus is reliable, and can descend the escaper in the speed of 0.7-1.2 m / s.

The invention discloses a power line patrol unmanned aerial vehicle wireless charging relay station, a charging flight control system and a charging flight control method. The unmanned aerial vehiclewireless charging relay station comprises: a charging platform which is arranged on a power transmission tower and is provided with a wireless charging area for charging an unmanned aerial vehicle; anelectromagnetic locking device, wherein the electromagnetic locking device is used for generating magnetic attraction force to attract the unmanned aerial vehicle onto the charging platform when theunmanned aerial vehicle is charged, and generating magnetic repulsive force to enable the unmanned aerial vehicle to catapult and take off when the unmanned aerial vehicle takes off; a clamping device, wherein the clamping device is used for clamping the unmanned aerial vehicle in the wireless charging area in the transverse direction and the longitudinal direction; a CT power taking device, wherein the CT power taking device takes power from the power transmission line and supplies power to the charging platform, the electromagnetic locking device and the clamping device; and a controller. wherein the controller is connected with the transmitting end of the wireless charging system, the electromagnetic locking device and the clamping device in the wireless charging area. And the unmannedaerial vehicle automatically searches the nearest wireless charging relay station for electric energy supply, and long-distance uninterrupted autonomous line patrol is carried out.

The invention provides a driving assembly, a roller and a processing box. The driving assembly comprises a gear seat, a connection piece and a driving force receiving piece, wherein a containing cavity which is concave inwards is formed on the gear seat along the axial direction; the connection piece is mounted in the containing cavity; the driving force receiving piece comprises an inner end part, an outer end part and a rod body part connected between the inner end part and the outer end part; the driving part is connected with the inner end part; the inner end part drives the driving part to rotate around the axis of the connection part; the containing cavity comprises a driven power receiving part arranged at the bottom of the containing cavity and a limiting groove formed in one end part of the containing cavity; the driven power receiving part is connected with a driven part; the driven power receiving part is driven to rotate around the axis of the gear seat by the driven part; the driving assembly further comprises a positioning assembly mounted in the limiting groove; the driving assembly further comprises a positioning assembly mounted in the limiting groove and a rod body part penetrates through the positioning assembly and can do reciprocating sliding relative to the positioning assembly. The invention provides the roller and the processing box which are provided with the driving assembly. The driving assembly, the roller and the processing box have the advantages of being reliable in performance, stable in falling, stable to work and the like.

The invention relates to a bridge settlement support, which comprises a product support, further comprises an upper settlement compression device which is located on the bottom portion of the product support, the device comprises an upper settlement body and a lower bottom basin, the upper settlement body comprises a top plate, an inner support plate and a middle carrier plate, the top plate is located at the lever direction, the middle carrier plate is fixed on the lower portion of the top plate and is parallel to the top plate through the inner support plate, the middle carrier plate is equipped with a plurality of rheological channels, the inner support plate comprises a ring plate and a baffle which is fixed in the ring plate to form a plurality of cavities, and the upper portion of the ring plate is equipped with a plurality of vent holes. The lower bottom basin comprises a bottom plate and an outer support plate which is fixed on the upper portion of the bottom plate, an overflow orifice is arranged between the bottom plate and the outer support plate, the outer support plate is a ring cylinder which is tightly sleeved on the outer side of the inner support plate, an electric heating disk is laid on the bottom plate, and a compression body is filled between the electric heating disk and the middle carrier plate. The bridge settlement support has the beneficial effects that the disease of bumping at bridge-head is effectively eliminated through that the self settlement drives the floor elevation reduce.

The invention provides an aircraft mobile landing system and an aircraft mobile landing method using the system; the aircraft mobile landing system comprises a camera arranged on the aircraft and a landing target arranged on a landing platform; the landing target is provided with a light source sending lights with the preset wavelength; a controller controls the light source to flash according to a preset frequency; the camera comprises a filter sheet allowing the light with the preset wavelength to pass; the landing platform is provided with a first communication module; the aircraft is provided with a second communication module communicating with the first communication module; the system and method allow the aircraft to stably land in mobile, and the landing process has small external interferences.