35results about How to "Ensure safe landing" patented technology

The invention discloses a method for controlling automatic carrier landing based on a preview control, which belongs to the technical filed of automatic carrier landing, guiding, and flight control. The invention discloses a method for controlling automatic carrier landing based on the preview control by utilizing known glide path information and predictable longitudinal deck motion information during an automatic carrier landing process. The glide path information is calculated in advance based on the relative position and the relative motion of the carrier and the warship. The deck motion information is estimated by a particle filter based deck motion predictor. At the same time, the interference of warship wakes is considered in the design of a controller. The method for controlling automatic carrier landing based on the preview control can ensure the accuracy and robustness of the landing under the interference of the deck motion and the warship wakes during the carrier landing process.

The invention provides an inertial anti-skid braking system and a control condition determination method. The inertial anti-skid braking system provided by the invention adopts the structure that a floor switch is added to an inertial anti-skid braking system in the prior art, the positive pole of an electric apparatus contact of the floor switch is connected with the positive pole of an electric apparatus contact of an inertial sensor, and the negative pole of the electric apparatus contact of the floor switch is connected with the negative pole of the electric apparatus contact of the inertial sensor. The floor switch on an airplane undercarriage is logically synthesized with accessories of the braking system, and the braking pressure is locked in the air, so that before touch-down of an airplane or when the braking airplane wheel does not rotate fully although the airplane touches down, the inertial anti-skid braking system cannot apply braking pressure to the braking airplane wheel; and after ground protection fails, the anti-skid braking system conducts normal braking on the braking airplane wheel.

The invention discloses an unmanned aerial vehicle parachute automatic release unit. The unmanned aerial vehicle parachute automatic release unit structurally comprises a support rack, wing cabins, anti-collision racks, blades, a parachute automatic release unit body, a unmanned aerial vehicle body and a camera and is characterized in that the support rack is welded to the bottom of the unmanned aerial vehicle body and connected with the ground, the wing cabins are arranged in the middles of the anti-collision racks, arranged on the outer side of the unmanned aerial vehicle body and electrically connected with the unmanned aerial vehicle body, the anti-collision racks are fixed outside the wing cabins and fixedly connected with the unmanned aerial vehicle body to form an integral structure, the blades are arranged on the upper portions of the wing cabins and rotatably connected with the same, and the parachute automatic release unit body is mounted at the top of the unmanned aerial vehicle body and movably connected with the same. The unmanned aerial vehicle parachute automatic release unit has the advantages that when an unmanned aerial vehicle loses balance and stops powered flight, an internal parachute can be popped up through a wind power transmission structure, the unmanned aerial vehicle can safely land, a protective shell mounted inside the release unit can reduce impact force on the unmanned aerial vehicle body, the parachute can be automatically retracted when the unmanned aerial vehicle is recharged and used, and recycling, time saving and use convenience are achieved.

The invention discloses a special shock-absorbing tripod for an aerial camera, which comprises a primary shock-absorbing device, an intermediate connecting piece and a secondary shock-absorbing device sequentially connected from bottom to top, and is characterized in that the secondary shock-absorbing device includes a top The connecting piece, the top connecting piece is cylindrical, the bottom surface of the top connecting piece is provided with three expansion assemblies along the circumference, and the expansion assemblies are provided with connecting assemblies between each two, and the expansion assemblies and the connecting assemblies form As for the shock-absorbing sleeve, one end of the intermediate connecting piece is connected to the primary shock-absorbing device, and the shock-absorbing head at the other end of the intermediate connecting piece is set in the shock-absorbing sleeve and can move along the axial direction of the shock-absorbing sleeve. The present invention adopts the arrangement of the primary shock absorbing device and the secondary shock absorbing device, wherein the secondary shock absorbing device adopts the mode of wrapping the shock absorbing head with the shock absorbing sleeve, and realizes two shock absorbing for landing through two different structures, which is very good It solves the problem of excessive impact force when landing, and ensures the safe landing of the drone.

The invention relates to the technical field of unloading devices, in particular to a self-unloading type mechanical automation fragile product unloading device which comprises a movable base, a height adjusting mechanism is arranged above the movable base, and an adjusting conveying mechanism is arranged above the height adjusting mechanism. The adjusting conveying mechanism comprises a first movable block, by means of the design, the device can automatically convey goods, a reciprocating mechanism is arranged below the adjusting conveying mechanism, a placing mechanism is arranged below the reciprocating mechanism, and a shifting mechanism is arranged on the right side of the upper portion of the reciprocating mechanism. According to the self-unloading type mechanical automation fragile product unloading device, manual carrying by people is not needed, the labor amount of people is reduced, the bottom end, the front portion and the rear portion of goods can be supported in the conveying process, the goods can be conveyed stably and not prone to deviation, smooth conveying of the goods is guaranteed, and the stability of the device is improved.

The invention discloses an aerial camera capable of ensuring safe landing, which comprises a main body of the aerial camera and a camera arranged at the bottom of the main body of the aerial camera. A plurality of groups of shock-absorbing tripods are arranged under the main body of the aerial photo. The intermediate connecting piece and the secondary shock absorbing device, the secondary shock absorbing device includes a top connecting piece, the top connecting piece is cylindrical, three expansion components are arranged on the bottom surface of the top connecting piece, and connecting components are arranged between two expansion components, The expansion assembly and the connection assembly form a shock absorber, one end of the intermediate connector is connected with the primary shock absorber, and the shock absorber at the other end of the intermediate connector is set in the shock absorber and can move along the axial direction of the shock absorber. In the present invention, the shock-absorbing tripod is set as a primary shock-absorbing device and a secondary shock-absorbing device, wherein the secondary shock-absorbing device adopts the method of wrapping the shock-absorbing head with a shock-absorbing sleeve, and achieves shock absorption for landing through different structures, which is very good Solved the problem of excessive impact force when landing, and ensured the safe landing of the drone.

The invention discloses an electric automatic equipment maintenance protection device and a use method thereof, and belongs to the technical field of maintenance protection. The electric automatic equipment maintenance protection device comprises an iron tower, and is used for providing protection for maintenance personnel when the personnel climb the iron tower; the electric automatic equipment maintenance protection device further comprises a parachute and a control device; a maintaining worker performs operation carrying the parachute; and the control device is used for controlling the parachute to open. The electric automatic equipment maintenance protection device has the advantages that the parachute can be controlled to open; safe landing of the maintenance personnel is ensured; safe loopholes occurring during falling of the maintenance personnel are avoided; life safety of the maintenance personnel is ensured; and the electric automatic equipment maintenance protection device has the features of being simple in structure, reasonable in design and easy to manufacture.

The invention discloses an aerial camera with a professional tripod. The aerial camera comprises an aerial camera main body and a camera arranged at the bottom of the aerial camera main body, wherein multiple sets of wings with propellers are arranged on the aerial camera main body; a damping device is arranged at the bottom at one end of the wings; the damping device comprises a connecting plate and a damping tripod; the connecting plate is connected with the bottom of the wings; the damping tripod comprises three sets of adjusting components which are distributed along the peripheral direction of the connecting plate; each adjusting component comprises a base; a left expansion link and a right expansion link are hinged on the base; the left expansion link and the right expansion link are arranged in V shape; and the other ends of the left expansion link and the right expansion link are both hinged with the connecting plate. According to the invention, the damping device is arranged, the V-shaped damping tripod is arranged and a triangular structure is formed between the damping tripod and the connecting plate, so that the damping and stabilizing functions are achieved and the safe landing of the aerial camera is guaranteed.

The invention discloses a method for autonomous site selection and landing of an unmanned aerial vehicle integrating LIDAR point cloud and image data. The method includes generating a color point cloud image based on the fusion of lidar point cloud data stream and image data stream; calculating at least one smooth area in the color point cloud image, taking the smooth area closest to the UAV as the initial landing point, and controlling the UAV Move to the initial landing point; in the process of moving to the initial landing point, perform visual analysis on the semantic information corresponding to all smooth areas, and filter to obtain at least one safe smooth area; determine the safe smooth area closest to the current position of the drone as The final landing point, control the drone to land to the final landing point. The invention realizes that without relying on unreliable sensor information such as GPS and IMU, the optimal landing point in the area is independently selected for landing over various terrains, and the landing point with potential safety hazard can be quickly and effectively screened.

The invention relates to a runway center line light which comprises a light source, a reflector and a prism. The light source is arranged in the reflector; the prism comprises a light-in surface and a light-out surface which inclines with respect to the light-in surface; the light source is dead against the light-in surface; the rays of the light source converge onto the light-in surface through the reflector and are refracted out with deflection from the light-out surface; the angle between the light source and the ground is 53 degrees to 58 degrees; the distance between the light-out port of the reflector and the light-in surface is 19.5mm to 22.5mm; the refraction angle of the prism is 51 degrees to 56 degrees; and the size of the light-out port is 53mm X 42mm to 56mm X 45mm. The distance between the highest point of the light-out port of the light-out surface of the prism and the horizontal ground is less than 6.35mm, which satisfies the high requirements of airports. Therefore, the runway center line light can be applied in the airports with high demands to pilot the taking-off and landing of airplanes and thereby ensures safe taking-off and landing of the airplanes.

The invention discloses a descending deceleration device for an aerial photography unmanned aerial vehicle, which includes a body, a flight impeller and a speed reducer. Four flight impellers distributed in a rectangular shape are fixed on the outside of the body, and a speed reducer is arranged between every two flight impellers. , and the four reducers are fixedly connected to the surface of the body through the fixed seat, the inner walls of the four reducers are connected with the outer wall of the decelerating hemisphere, and the bottoms of the inner walls of the four decelerating hemispheres are connected to the surface of the center of gravity ball through four connecting rods Fixedly connected, the surfaces of the four decelerating hemispheres are all provided with six vents, and one side of the inner wall of the six vents is hinged with a windshield. When the aerial photography UAV of the present invention rises, the decelerating hemisphere ensures the air circulation through the vent, the reducer does not affect the ascent of the aerial photography UAV, and the windshield closes the ventilation opening when the aerial photography UAV descends, and the reducer increases the aerial photography UAV to descend When the resistance is reduced, the speed of the aerial photography UAV is reduced, and the safety of the aerial photography UAV is ensured.

The invention provides an inertial anti-skid braking system and a control condition determination method. The inertial anti-skid braking system provided by the invention adopts the structure that a floor switch is added to an inertial anti-skid braking system in the prior art, the positive pole of an electric apparatus contact of the floor switch is connected with the positive pole of an electric apparatus contact of an inertial sensor, and the negative pole of the electric apparatus contact of the floor switch is connected with the negative pole of the electric apparatus contact of the inertial sensor. The floor switch on an airplane undercarriage is logically synthesized with accessories of the braking system, and the braking pressure is locked in the air, so that before touch-down of an airplane or when the braking airplane wheel does not rotate fully although the airplane touches down, the inertial anti-skid braking system cannot apply braking pressure to the braking airplane wheel; and after ground protection fails, the anti-skid braking system conducts normal braking on the braking airplane wheel.

The invention discloses an anti-falling device for a building-type machine room-less elevator and a use method thereof, which comprises a car and an elevator shaft body, and the car is arranged in the elevator shaft body. When the traction force of this device disappears, the second spring, the rotating rod and the guide wheel are used together, so that the hinge rod drives the splint to move upwards and fits closely with the side wall of the elevator shaft body, and an anti-skid layer is set on one side of the splint. This effectively increases the frictional resistance between the splint and the elevator shaft body, so that the car can be effectively fixed in the elevator shaft body, avoiding serious injury to the people inside the car due to landing, and even if the inside of the car is fully loaded and heavy, the setting of the splint can also Effectively reduce the descending speed of the car, and under the setting of the first rack, pinion and second rack, when the car slowly falls and touches the ground, the setting of multiple first springs can effectively The buffer function provides double protection for the internal personnel and effectively ensures that the personnel land safely.

The invention relates to an aircraft arm and a variable-pitch aircraft. The aircraft arm comprises an arm plate, a driving part, a propeller assembly, a driving sleeve assembly and an actuating assembly; the driving part is arranged on the arm plate, and the driving part is provided with a driving shaft; the propeller assembly comprises a rotor head and a propeller, the rotor head is in driving connection with a driving shaft, and the propeller is rotationally arranged on the rotor head; the driving sleeve assembly is movably arranged on the driving shaft in a lifting manner and can drive thepropeller to rotate; and the actuating assembly is arranged on the arm plate and is in driving connection with the driving sleeve assembly. The propeller rotates around the axis of the propeller, so that a forward propeller posture can be quickly converted into a reverse propeller posture, stored rotating kinetic energy is converted into thrust in the direction away from the ground, and thereforethe purposes of further slowing down the falling speed of the variable-pitch aircraft and ensuring safe forced landing of the variable-pitch aircraft are achieved.

A soft landing obstacle avoidance simulation test system comprises a six-freedom-degree motion simulation device, a high-simulation lunar surface simulation sand board screen, a GNC simulation computer, a sensor and executing mechanism simulation interface box, a dynamic emulation computer and a ground test general control computer. Three-axis rotation and three-dimensional translational motion relative to the lunar surface of a prober are simulated through the six-freedom-degree motion simulation device. The landform of the lunar surface for the prober to land on and the characteristics of lunar surface reflection to a sensor are simulated through the high-simulation lunar surface simulation sand board screen. Guidance, navigation and control calculation is performed by the GNC simulation computer according to the output of the sensor and executing mechanism simulation interface box and measured information of the landing navigation sensor to acquire executing mechanism control instructions, the executing mechanism control instructions are sent to the dynamic emulation computer for orbit and posture dynamic calculation and parameter update, and six-freedom-degree motion parameters are generated to be used for driving the six-freedom-degree motion simulation device. The ground test general control computer is responsible for control over the whole test system and data management.

A method for scan-selecting safety landing region of moon craft at hovering stage includes obtaining 3-D information of moon surface by utilizing sensor of moon surface-imaging defining region occupied by moon craft-landing as unit area being defined as landing center, moving said landing center as per fixed distance from inside to outside to judge whether each landing region on landing center issatisfied with landing condition or not and moving said landing center continuously to make judgment if it is not or otherwise moving moon craft to relevant position for landing.

The invention discloses an automatic parachute detachment device for an unmanned aerial vehicle. Its structure includes a support frame, a wing compartment, an anti-collision frame, blades, a parachute automatic detachment device, a body, and a camera. The support frame is welded to the bottom of the body and connected to the ground. Connection, the wing compartment is set in the middle of the anti-collision frame and outside the fuselage and electrically connected, the anti-collision frame is fixed outside the wing compartment and fixedly connected with the body to form an integrated structure, and the blades are set on the upper part of the wing compartment and connected by rotation , The parachute automatic disengagement device is installed on the top of the body and connected flexibly. The utility has beneficial effects: when the unmanned aerial vehicle loses balance and stops power flight, the internal parachute can be ejected through the wind transmission structure to ensure that the unmanned aerial vehicle lands safely and is separated from the device. A protective shell is installed inside the device to reduce the impact on the body. When the drone is recharged and used again, the parachute can be automatically retracted, recycled and time-saving, and convenient to use.

The invention discloses a radar altimeter for on-orbit detection and landing. On the basis of the existing pulse compression radar altimeter, a data processing unit is further connected with a second digital filtering unit, a second direct digital synthesizer, The attenuator is electrically connected to the second filter amplifier; the timing unit is also electrically connected to the second direct digital synthesizer and the second analog-to-digital conversion unit; the second antenna is electrically connected to the attenuator, and the attenuator is electrically connected to the second low-noise amplifier connected, the second low-noise amplifier is electrically connected to the second mixer, the second mixer is electrically connected to the second filter amplifier, the second filter amplifier is electrically connected to the second analog-to-digital conversion unit, and the second analog-to-digital conversion unit The unit is then electrically connected to the second digital filtering unit. The invention not only has the ability to measure the height of the planet's surface on the orbit, but also has the ability to provide the height measurement and the speed measurement for the lander's landing process.

The invention provides a power reduction initial point parameter optimization method based on terrain of moon surface, The method particularly comprises the following steps: a first step, setting a moon latitude and a selenocentric distance of a power reduction initial point, wherein RL is an average moon radius in a certain local area where range finding is introduced; a second step, in a period between near-moon braking and around-moon rail reducing, optimizing the moon latitude and the selenocentric distance of the power reduction initial point, and introducing the optimized result into a third step; and the third step, in the period between around-moon rail reducing and power reduction, if a fact that the selenocentric distance error or / and moon latitude deviation are larger than allowable envelope in design, optimizing the moon latitude and the selenocentric distance of the power reduction initial point according to the manner of the second step until the moon latitude and the selenocentric distance of the power reduction initial point are set in the allowable envelope in design, and hereon utilizing the optimized moon latitude and the selenocentric distance of the power reduction initial point as initial parameter of a power reduction period. The initial parameter determined by the method can ensure a detector to safely fall into a preset target area in soft landing process.