227results about How to "Landing safety" patented technology

Method and system for remote control of a drone helicopter and RC plane using a handheld device is disclosed. Piloting commands and actions are performed using the handheld device, which includes a motion sensor module, with gyro-sensor and g-sensor for controlling roll, yaw and pitch of flying object under relative or absolute coordinate system. The gyro-sensor controls both heading and rotation of flying object in place around its yaw by rotating handheld device around its yaw axis; g-sensor controls pitch and roll by rotating handheld device around its pitch axis and roll axes. Upon determining free falling of flying object, throttle is thereby adjusted so as to land it safely. Flying object further has a camera, and video images are transferred wireless to be displayed on touch screen, and image zoom-in and zoom-out are provided via multi-touch of touch screen. RF and IR capability is included for wireless communication.

The invention relates generally to the control and landing of unmanned aerial vehicles. More specifically, the invention relates to systems, methods, devices, and computer readable media for landing unmanned aerial vehicles using sensor input and image processing techniques.

A traveling apparatus and a method for controlling thereof, in which an abrupt turn to make a rider fall down is prevented and stable traveling is obtained without fail, are provided.

At a step [1] whether or not a turn operation is performed by means of a barycentric position of the rider, and the barycentric position is detected at a step [2] from a load sensor. Further, a turn velocity command is generated at a step [3]. Then, the barycentric position to which the centrifugal force is added is detected at a step [4], and it is judged at a step [5] whether or not the barycentric position is close to a tire. When it is close to the tire (Yes), processing to reduce the turn velocity is performed at a step [6]. Hereupon, such computation is performed that a sensor signal ωyaw from a gyroscopic sensor is set to ωyaw←ωyaw×Gω (Gω is a value that changes in inverse proportion to the strength of the centrifugal force). When the barycentric position is not close to the tire (No), it is set to ωyaw←ωyaw at a step [7]. Furthermore, a wheel rotational velocity command is supplied at a step [8] to set tire velocity of right and left wheels to ωyaw, and a turn of a vehicle is performed at a step [9].

The invention provides a rotor-type unmanned aerial vehicle automatically adjusting a gravity center after loading and an adjustment method. The rotor-type unmanned aerial vehicle includes a machine body provided with a rotor assembly, the bottom of the machine body is provided with a testing device for supporting the machine body to test the weight and the gravity center of the machine body and a translational mechanism connected with the machine body; the translational mechanism comprises a mobile output end for fixing a load. According to the rotor-type unmanned aerial vehicle automatically adjusting the gravity center and the adjustment method, a gravity center position of the unmanned aerial vehicle is controlled through installation of the testing device and the translational mechanism on the machine body, so that the unmanned aerial vehicle can perform smooth taking-off and landing and safe landing, and the security of the unmanned aerial vehicle is improved; and the adjustment method is simple in process, enables detection and adjustment to be carried out from time to time, and is applicable to a working condition that requires to frequently modify the machine body.

The invention relates to the fields of an airplane model and an aircraft, in particular to a multi-rotor aircraft with a rolling function. The multi-rotor aircraft comprises three circular rings, a connecting arm, six power units, an energy source, a flight control system, a load, a machine body and a machine body upper cover, wherein rotating centers of three power units are in the same flat surface, the rotating centers of the other three power units are in the other flat surface, the two flat surfaces are parallel but not are coincided, and lift vectors and moment vectors generated by the six power units are mutually orthogonal. Force vector and torque in any direction can be generated by regulating the rotating speed and the direction of rotors of the six power units, the decoupling of motion and gesture of the aircraft can be realized, different motion and gesture variations can be finished by the aircraft, the aircraft can move forwards along the ground or cross obstacles by matching with the circular rings, and the aircraft has extremely high flexibility and controllability.

A safe lander consists of a flight airplane, transducer multi-path multiplexing receiver and emitter set on said airplane, digital processor/computer of land based simulator, flight control unit of land based airplane simulator, remote navigation electronic interface unit, land based airplane simulator, unique airplane identification ID and configuration unit, analysis unit of land based processing station, two-way RF communication unit of space to ground and ground to space, and remote pilot display set on land based simulator.

The invention relates to a heavy load salvage wave compensation system of a super large floating crane, which comprises a mechanical system, a hydraulic system, a monitor system, control of a hydraulic oil cylinder, control of an accumulator and the like, wherein the mechanical system consists of a lifting drum, a plurality of sets of pulley, a steel wire rope and a large tonnage lifting hook, the hydraulic system consists of an oil cylinder, the accumulator, the hydraulic oil cylinder and a hydraulic valve, and the monitor system consists of a floating crane body displacement monitor, a floating crane ship body displacement monitor and a floating crane lifting heavy weight displacement monitor. The invention solves the problems that when the super large floating crane carries out heavy load salvage, and at the moment that a heavy weight is lifted out of water, because the heavy weight has large volume, seawater forms an eddy current to enable a floating crane ship body to be inclined and swing, and a lifting weight also swings along with the floating crane ship body and can not be controlled, solves the problems that when a large structure is lifted on the sea, waves influence the floating crane ship body to lead to difficult butting of marine platforms to ensure goods to be safely fall on a ship deck or safe offshore platform installation and allows that the ship has certain inclination to be suitable for tough working conditions of marine operation.

The invention discloses a vision localization landing tail end-based unmanned aerial vehicle landing method. In the method, a used unmanned aerial vehicle airport consists of a plurality of gate position Markers; each unmanned aerial vehicle obtains Markers in a visual range through a visual module and verifies the ID of each Marker in the visual range, so as to estimate the own position to land accurately. According to method provided by the invention, the unmanned aerial vehicle airport can provide landing services for a plurality of different unmanned aerial vehicles, and provide single-vehicle stopping platforms for various small platforms such as vehicle roofs and balcony lamps, and through a uniform framework, completely autonomous flight landing in the whole unmanned aerial vehicle scheduling can be realized at low cost, so that the method has a good popularization prospect.

The invention relates to a Mars complex terrain region safe landing trajectory generation method with minimum fuel consumption, and belongs to the technical field of planet landing. The method comprises the steps that a Mars powered lowering kinetic model is built at first, a navigation function is built according to the target landing terrain, obstacle avoidance control force obtained through the navigation function can effectively avoid collision between a lander and an obstacle, and the lander is safely landed to a target landing point. According to the Mars complex terrain region safe landing trajectory generation method with minimum fuel consumption, the obtained obstacle avoidance control force is introduced into a Mars powered lowering kinetic equation, the control force is partially used for achieving obstacle avoidance, and landing trajectory optimization is carried out on the improved kinetic equation, so that obstacle avoidance is achieved, and meanwhile fuel consumed by the powered lowering trajectory is saved. The Mars complex terrain region safe landing trajectory generation method can not only take the target landing area terrain into consideration, but also effectively reduce fuel consumption, and overcomes the defects that obstacle avoidance cannot be achieved and fuel consumption is large in traditional optimization trajectory and obstacle avoidance.

A system for enabling the safe landing of an aircraft during an in-flight emergency is provided. The system includes a plurality of onboard devices for releasably securing a plurality of wings to a fuselage, and a non-electric module for activating said onboard devices. Said onboard devices are released to separate said wings from the fuselage.

The invention discloses a wireless ultraviolet light-based helicopter landing boosting system. The system comprises an emission end and a receiving end; the emission end and the receiving end are communicated by an atmosphere channel; the emission end is arranged at the floor of a landing field; voice data image input equipment is integrated in the emission end and is connected with a coder; the coder is in control connection with an ultraviolet LED (light emitting diode) light source by a driving circuit; the receiving end is mounted on a helicopter and comprises a photoelectric detector connected with a photoelectric converter; the photoelectric converter is connected with voice data image output equipment by a decoder. The wireless ultraviolet light-based helicopter landing boosting system and landing boosting method have the advantages of strong antijamming capability, good hidden performance, portability, wide view field receiving and the like by using the ultraviolet communication technology, and can perform all weather operation.

The invention provides a speed-reducing and stopping device for aircraft landing, and is particularly applicable to landing of a carrier-based aircraft. The speed-reducing and stopping device consists of an electromagnetic runway, a magnetic tail plate and a control system, wherein the electromagnetic runway is arranged in an aircraft landing runway; and the magnetic tail plate is arranged at the tail of the aircraft and can be unfolded or folded. In an aircraft landing process, the magnetic tail plate is unfolded, an electromagnet is electrified, and the direction of a magnetic pole of the magnetic tail plate is opposite to the direction of a magnetic pole of the electromagnetic runway; when the aircraft is close to the runway, the magnetic tail plate is attracted with the electromagnet of the runway, the aircraft is stopped from moving forwards, and the speed of the aircraft is sharply reduced, so that the aircraft can be safely landed within a short time and by a short distance. After the aircraft is stopped, the power of the electromagnet is failed or the current direction is changed, and the magnetic tail plate is separated from the electromagnetic runway and is folded, so that the aircraft can move to an objective position.

The invention provides a parachute fixed-wing unmanned aerial vehicle (UAV) autonomous fixed-point recovery method comprising the following steps: setting a recovery point and a recovery course, and judging whether the setting has recovery conditions; when autonomous recovery is needed, generating an approach descending route and making an aircraft fly along the approach descending route; generating a recovery route, and making the aircraft fly along the recovery route; correcting the recovery route according to the measured wind speed and direction on the aircraft, and making the aircraft fly along the corrected recovery route; and finally, making an engine stop and opening a parachute when the aircraft approaches the recovery point. By adopting the method of the invention, the procedure of aircraft recovery operation is simplified greatly, the operating burden of UAV operators is lightened, the autonomy of UAVs is enhanced, and the dependence of UAVs on communication conditions is reduced.

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 relates to a novel thin-interbedded horizontal well landing geosteering method. The horizontal well landing geosteering method includes the following steps: (1) constructing a horizontal well landing geosteering comparison model; (2) vertically correcting an LWD (Logging While Drilling) curve of a curve section; (3) carrying out error judgement and determining structure errors in real time by means of the fine comparison of the landing geosteering comparison model; and (4) determining a trajectory adjustment according to the structure errors scheme. The method realizes the transformation from conventional mark comparison to digitalized continuous comparison, and has the dual characteristics of real-timeliness and accuracy; and the digitized comparison profile of a landing section is established before drilling, the LWD curve is digitized in real time in the process of landing, and is finely compared with the profile after the vertical depth is corrected, the structure is corrected in real time, a result is judged according to the structure errors, the trajectory design is updated in real time, and thereby accurate landing can be realized.

The invention discloses a helicopter guiding system based on wireless ultraviolet light and multi-dimensional codes. The helicopter guiding system comprises four emitting ends and four corresponding receiving ends based on the wireless ultraviolet light and the multi-dimensional codes, and all the emitting ends and the receiving ends communicate correspondingly through atmosphere channels. The invention further discloses a helicopter guiding method based on the wireless ultraviolet light and the multi-dimensional codes. According to the helicopter guiding device and method, the ultraviolet light is used for positioning and guiding in the landing process of a helicopter, the ground gradient, wind speed, the wind direction, ground constitution, barriers and other environment information are sent to a helicopterist through the portable emitting ends to help the helicopter to land smoothly, the limitation that landing conditions are judged only by the helicopterist in the air through the eyes is broken through, a guarantee is added for safe landing of the helicopter, and the helicopterist is helped to safely and accurately land the helicopter under complex environment conditions.

The invention discloses a carrier-based aircraft automatic landing control method based on robust preview control. Future information and current information on a glide slope track and longitudinal deck movement are used for preview control of a carrier-based aircraft, so as to achieve the tracking of the height of a glide slope and the compensation of the longitudinal deck movement, and meanwhile lateral offset can be effectively suppressed and eliminated to enable the carrier-based aircraft to main lateral stability. The future information is used for feedforward control, the current information is used for feedback control, average operation can be performed in advance for the control surface and a throttle of the carrier-based aircraft to achieve the purposes of tracking and compensation, the instantaneous energy can be reduced, the response speed is accelerated, and the carrier-based aircraft can be ensured to safely land on an aircraft carrier.

The invention relates to an unmanned aerial vehicle recovery damping airbag. The unmanned aerial vehicle recovery damping airbag comprises a vehicle body, airfoils and an airbag buffer device, the airfoils are fixedly mounted on the vehicle body, and the airbag buffer device is mounted on the vehicle body and comprises a collection box, an air inlet and outlet pipeline, an air inlet fan and an airbag body. The unmanned aerial vehicle recovery damping airbag is specifically structurally characterized in that the collection box with a lower opening is fixedly mounted on one airfoil, the air inlet and outlet pipeline is mounted between the collection box and the vehicle body, one end of the air inlet and outlet pipeline is connected with the air inlet fan fixedly mounted on the vehicle body, and the other end of the air inlet and outlet pipeline extends into the collection box and is hermetically connected with the airbag body folded in the collection box. The airbag comprises an inflatable bag body made of inelastic, soft and airtight materials, and the airbag buffer device can not only absorb and release sufficient impact energy and reduce landing impact load of an unmanned aerial vehicle, but also avoid rebound during landing, so that the unmanned aerial vehicle can descend and ground stably during landing and lands safely.

The invention relates to an emergency device used after an airplane fails, in particular to an airplane emergency landing device. The emergency landing device comprises an airplane urn entering device, a combined retarding device and a stumbling rope device. When the airplane is landed on a landing buffering mattress, the mattress is sunken, anti-rebound protective covers distributed at the four sides of the mattress are unfolded to the center of the mattress, magnets on the anti-rebound protective covers are attracted to the fuselage, the fuselage is locked by hasps on the anti-rebound protective covers, and the airplane cannot bounce through the airplane urn entering device. The combined retarding device comprises a spring buffering mechanism, a hydraulic actuating cylinder pressure reducing mechanism and a damping block pressure reducing mechanism, and plays multiple roles in buffering and reducing the pressure of the emergency landing device. Through the airplane emergency landing device, the airplane can be safely landed when an undercarriage fails in the air, so that the life and property safety of passengers is ensured. Meanwhile, a new landing mode is created, the emergency landing device can be used for short-distance landing of a fighter and even a transport plane, and the manufacturing cost of an aircraft carrier is reduced.

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 discloses a helicopter landing system. The helicopter landing system comprises a landing auxiliary mechanism installed at the bottom of a helicopter body, and a parking apron arranged on a ship deck. The landing auxiliary mechanism comprises an electromagnet attracting to a helicopter undercarriage. The parking apron is round. A plurality of evenly distributed electromagnetic devices are arranged in the parking apron. The helicopter landing system further comprises a slideway arranged on the ship deck. The parking apron is installed on the slideway. When landing, a helicopter slides to a preset position along the slideway. After landing, the helicopter slides to a helicopter warehouse along the slideway. The helicopter landing system is simple in structure and convenient to use and has good reliability and wide applicability and universality. The helicopter can land safely and stably under the circumstance of strong light and poor sea conditions. Helicopter of different models and sizes can be suitable for the helicopter landing system after improved slightly.

A rotorcraft that utilizes both a main compound rotor and a plurality of tiltrotors is disclosed. The main rotor and the thrusters can provide vertical lift for vertical take-off and landing of the rotorcraft. The thrusters of the rotorcraft can articulate to a horizontal position to facilitate horizontal flight. The main rotor of the rotorcraft can continue to provide vertical lift for the rotorcraft in horizontal flight, as well as operate in an autorotation mode. In the event of a failure of the main power source of the rotorcraft, the main rotor in autorotation mode can safety land the rotorcraft. In the autorotation mode, the main rotor can create electrical energy that is stored in a battery and can be used to power the plurality of thrusters. The rotorcraft can also be configured in an anti-torque mode, where the thrusters cancel out the torque of the main rotor.