34results about How to "Guaranteed a safe landing" patented technology

The invention aims at providing a high-altitude self-rescue apparatus which is safe and quick, convenient to use and has low cost for high-rise residential buildings and office buildings. The high-altitude self-rescue apparatus can be used for realizing the return-rope-free bidirectional escape through reciprocating movement at both ends of a steel wire rope; and breaking can be realized only through mechanical friction so as to ensure the normal work of the high-altitude self-rescue apparatus when a building has power failure. A transmission wheel series with an eccentric moving block can guarantee that relative sliding does not happen between the steel wire rope and the main transmission wheel, namely the transmission is effective. A centrifugal braking system of the descent control device can descend both children and adults at a constant speed.

The invention relates to a smart UAV suitable for mountain flight and stable to land. The smart UAV comprises a main body, a plurality of support mechanisms and a plurality of terrain exploration mechanisms. Each terrain exploration mechanism comprises a side bar, a second motor, a second drive shaft and a terrain exploration component. The terrain exploration component comprises a turntable, a third motor and a plurality of terrain exploration units. Each support mechanism comprises a drive unit, a support rod, a hinge block, a hinge unit, an air pump, a cylinder, a piston and a buffer unit.When the smart UAV suitable for mountain flight and stable to land lands on a mountain with complex terrain, the terrain exploration components drive a distance sensor to move and rotate in order to detect the terrain on the landing ground. Moreover, the driving units adjust the angles of the cylinders and the air pumps control the movement of the pistons. The buffer units are configured to improve a cushioning property when the UAV lands, thereby further ensuring the safe landing of the UAV. Thus, the UAV can safely land in a mountainous area with complex terrain.

The invention discloses a longitudinal track motion estimation and compensation method based on a motion platform, and belongs to the technical field of control law design of a full-automatic landing system on the basis of the motion platform. In order to guarantee the fact that an airplane can track an ideal landing point synchronously, a landing guidance system must be compensated synchronously. The method aims to the last stage of a motion platform landing stage, the influences of sailing motions and swaying motions of the motion platform on the landing of the airplane are taken into comprehensive consideration, and estimation and compensation of motions of a motion track (the ideal landing point) are carried out. In the longitudinal aspect, the longitudinal motion signals of the motion track are introduced into a longitudinal guidance system after estimation and compensation so that the dynamic performance of the system can be improved, errors are restrained, and the tracking precision of the airplane is improved.

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 a controllable-descend-speed type tower escape descend control knapsack. A head protecting device is fixed to the middle of the upper end of the rear wall of a knapsack body protector, and tightening bands used for binding the knapsack body protector and a human body are arranged on the two side walls of the knapsack body protector correspondingly. A controllable-descend-speed type descend control device is fixed to the interior of the front wall of the knapsack body protector, and a safety hook used for being hooked to a steel ring in a position near a window of a tower is fixed to the end of a rope coiled round the controllable-descend-speed type descend control device. A sleeve stay in the controllable-descend-speed type descend control device extends through a trouser leg on one side of the knapsack body protector and is fixed to the bottom of a corresponding protecting foot cover, and the descend speed is regulated in the modes that the controllable-descend-speed type descend control device is manually regulated; and the controllable-descend-speed type descend control device is controlled through the sleeve stay after the human feet kick downwards. According to the controllable-descend-speed type tower escape descend control knapsack, on the premise that the controllable-descend-speed type descend control device has a deceleration function, the descend speed can be controlled and regulated through the sleeve stay, the phenomenon that the head and limbs of the human body are knocked or scratched in the descend escape process is avoided, the application safety performance is high, materials are low in price, and the manufacturing cost is low.

The invention discloses an operating method of an equipment airborne multistage airbag cooperative shock absorber. The multistage airbag cooperative shock absorber comprises an upper airbag, an airbagtube column and a lower airbag. In an equipment airborne landing process, the upper airbag can discharge gases and relieve pressure outside by virtue of an upper airbag exhaust valve, gases can be discharged to the airbag tube column by virtue of a combined exhaust valve I, and the airbag tube column expands to realize first-stage shock absorption; the airbag tube column can discharge gases and relieve pressure outside by virtue of an airbag tube column exhaust valve, gases can be discharged to the lower airbag by virtue of a combined exhaust valve II, and the lower airbag expands to realizesecond-stage shock absorption; the lower airbag can discharge gases and relieve pressure outside by virtue of a lower airbag exhaust valve to realize third-stage shock absorption; after equipment airborne safe landing, the airbag device can be vented and is convenient to contain and store. According to the multistage shock absorption method of the multistage airbag cooperative shock absorber, airborne equipment can be prevented from directly contacting with the ground, multistage release of the pressure inside the airbag can also be realized, airbag blasting is avoided, and safe landing of theairborne equipment is ensured.

The invention provides a soft landing mechanism buffer for a landing probe, which is used for buffering the impact of the spacecraft. The invention is mainly composed of an outer cylinder, a metal tie rod, an inner cylinder, a cutter, a support plate, a support rod, etc., adopts a piston structure, and tightens the metal pull rod between the support rod and the support plate, and the metal pull rod can be located inside The center of the barrel or around the outer wall of the inner barrel. Another structure of the present invention is a buffer structure with bidirectional buffer function. The invention absorbs the impact energy through the yield deformation of the metal tie rod, is less affected by the space environment, has stable performance, reliable operation and compact volume.

The invention discloses a composite wing aviation aircraft and a flight control method thereof, A composite wing aerocraft includes a fuselage, The left wing and the right wing are symmetrically arranged on the side of the fuselage, the flight controller is arranged inside the fuselage, the integral plastic frame is connected above the fuselage, the top end of the frame is provided with a rotor, the tail part of the fuselage is provided with a propeller connected with the output shaft of the engine, and the rotor is connected with the output shaft of the engine through a clutch transmission mechanism. As that composite-wing aeronautical aircraft comprise a rotor and a fixed wing, the take-off distance is shorten and the flight speed and the flight efficiency are improved through driving control and rotational speed control of different stages of the rotor. The composite-wing aeronautical aircraft comprise a rotor and a fixed wing.

The invention discloses an equipment airborne multi-stage airbag cooperative buffering device. The equipment airborne multi-stage airbag cooperative buffering device comprises an upper airbag, an airbag tube column and a lower airbag; the upper airbag can exhaust air to the outside to reduce pressure by using an upper airbag exhaust valve and can also exhaust air to the airbag tube column by usinga combined exhaust valve I, and the airbag tube column expands to realize primary buffering; the airbag tube column can exhaust air to the outside to reduce the pressure by using an airbag tube column exhaust valve and can also exhaust air to the lower airbag by using a combined exhaust valve II, and the lower airbag expands to realize secondary buffering; and the lower airbag can exhaust air tothe outside to the reduce the pressure by using a lower airbag exhaust valve to realize three-stage buffering. According to the equipment airborne multi-stage airbag cooperative buffering device, through multi-stage buffering of the airbag cooperative buffering device, airborne equipment can be prevented from directly touching the ground multi-stage releasing of the pressure in the airbag can alsobe realized; and therefore, the airbag is prevented from exploded and safely landing of the airborne equipment is guaranteed.

The invention relates to an automatic oiling type emergency hydraulic system of an airplane, comprising a hydraulic system and an electrical system. An oil path is switched through a switching valve; an emergency accumulator in an oil path of an assisted hydraulic system fills oil and supplies the pressure to the emergency accumulator; horizontal stabilizers are continuously operated to enable the pressure of the emergency hydraulic system to change; and an emergency electric pump is started to supply the pressure to the emergency system and fill oil and supplied pressure to the emergency accumulator. Hydraulic oil of the emergency hydraulic system comes from the assisted hydraulic system without being added from the outside and the whole process can be automatically finished; and the emergency hydraulic system maintains the pressure and automatically discharges the hydraulic oil which returns to an assisted oil tank. The emergency hydraulic system is fully coupled with the assisted hydraulic system so as to greatly reduce the workload for maintenance. When a main hydraulic system and the assisted hydraulic system have faults and fail, the operation safety of the horizontal stabilizers can be ensured and the airplane can safely land by the emergency hydraulic system.

The invention discloses a working method of an airborne occupant multi-stage airbag cooperative buffer seat. The multi-stage airbag cooperative buffer seat comprises an upper air chamber, a middle airchamber and a lower air chamber; the upper air chamber, the middle air chamber and the lower air chamber are arranged by stacking from top to bottom, the upper air chamber can exhaust to the outsidethrough an upper air chamber exhaust valve for decompression, and can exhaust to the middle air chamber through a combined exhaust valve, and the middle air chamber is expanded to achieve first-stagebuffer; the middle air chamber can exhaust to the outside through a middle air chamber exhaust valve, and can further exhaust to the lower air chamber through a second combined exhaust valve, and thelower air chamber is expanded to achieve secondary buffer; the lower air chamber can exhaust to the outside through a lower air chamber exhaust valve to achieve three-stage buffer; the multi-stage buffer method of the multi-stage airbag cooperative buffer seat can prevent a human body from colliding secondly with the interior of a fighting vehicle, achieve multi-stage release of the internal pressure of the airbag buffer seat, and prevent the airbag buffer seat from blasting, thereby effectively ensuring a safe landing of an airborne occupant.

The invention discloses a multi-stage airbag cooperative buffering seat for an airborne occupant. The seat comprises an upper air chamber, a middle air chamber and a lower air chamber which are stacked from top to bottom; the upper air chamber can discharge air and release pressure through an air discharge valve of the upper air chamber and also discharge air to the middle air chamber through a first combined air discharge valve, and the middle air chamber expands to achieve first-stage buffering; the middle air chamber can discharge air and release pressure to the exterior through an air discharge valve of the middle air chamber and also discharge air to the lower air chamber through a second combined air discharge valve, and the lower air chamber expands to achieve second-stage buffering; the lower air chamber can discharge air and release pressure to the exterior through an air discharge valve of the lower air chamber to achieve third-stage buffering. Through multi-stage buffering of the multi-stage airbag cooperative buffering seat, not only can secondary collision between the human body and chariot interior parts be prevented, but also the multi-stage release of pressure in the airbag buffering seat can be achieved, the airbag buffering seat is prevented from being blasted, and therefore safe landing of the airborne occupant is effectively ensured.

The invention discloses a longitudinal track motion estimation and compensation method based on a motion platform, and belongs to the technical field of control law design of a full-automatic landing system on the basis of the motion platform. In order to guarantee the fact that an airplane can track an ideal landing point synchronously, a landing guidance system must be compensated synchronously. The method aims to the last stage of a motion platform landing stage, the influences of sailing motions and swaying motions of the motion platform on the landing of the airplane are taken into comprehensive consideration, and estimation and compensation of motions of a motion track (the ideal landing point) are carried out. In the longitudinal aspect, the longitudinal motion signals of the motion track are introduced into a longitudinal guidance system after estimation and compensation so that the dynamic performance of the system can be improved, errors are restrained, and the tracking precision of the airplane is improved.

The invention discloses an FADS fault judgment and control method for an energy management section of a vehicle. The method comprises the steps of acquiring atmospheric data measurement data and inertial measurement data under wind interference; analyzing a characteristic difference between the atmospheric data measurement data and the inertial measurement data; establishing mathematical representation of the safety boundary of the atmospheric data measurement data according to the distribution rule of the flight profile height, speed, course, wind speed and wind direction; judging whether theatmospheric measurement information is in a safety boundary range or not according to the coverage degree of the safety boundary of the atmospheric data measurement data on the atmospheric measurement data, and judging that an atmospheric data sensing system breaks down when the atmospheric measurement information is not in the safety boundary range; and when the atmospheric data sensing system breaks down, carrying out longitudinal control according to key state boundary protection or carrying out rolling control according to sideslip angle boundary protection. Under the condition of an FADSfault or no atmospheric data measurement information in the unpowered return process, the carrier can still be safely and reliably controlled, and safe landing of the spacecraft is guaranteed.

The application provides a method and a device for determining the safe landing of an unmanned helicopter after engine shutdown. The method includes the following steps: acquiring multiple groups of flight data on an altitude-velocity diagram of an unmanned helicopter after engine shutdown; determining safe landing conditions for the unmanned helicopter after engine shutdown; and determining a safe landing control strategy of the unmanned helicopter after engine shutdown based on the current flight data of the unmanned helicopter after engine shutdown and the safe landing conditions. Accordingto the embodiment of the application, a basis is provided for the safe landing of the unmanned helicopter through the determined safe landing conditions, and a safe landing control strategy of the unmanned helicopter after engine shutdown is determined to ensure the safe landing of the unmanned helicopter after engine shutdown.

The invention discloses a non-rebound aircraft landing buffer system and a non-rebound aircraft landing method. The landing buffer system comprises an aircraft, an air bag, a landing bottom plate, a rope and a rope control mechanism. The landing bottom plate is detachably arranged at the bottom of the aircraft; the rope control mechanism comprises a rotating shaft, an energy storage assembly and a limiting assembly, the rotating shaft is rotationally connected to the aircraft, one end of the rope is fixedly connected with the landing bottom plate, and the other end of the rope is wound around the rotating shaft so as to drive the rotating shaft to rotate forwards when the landing bottom plate falls; the energy storage assembly is arranged on the rotating shaft so as to store energy when the rotating shaft rotates forwards and release energy to drive the rotating shaft to rotate reversely to recycle the rope in a winding mode after the landing bottom plate lands; and the limiting assembly is arranged on the rotating shaft so as to limit the rotating shaft after the landing bottom plate lands, and the rotating shaft can only rotate reversely. The system and the method are applied to the field of aircraft recovery, can effectively avoid hard landing and rebound of aircrafts in the use process, ensures safe landing of the aircrafts, has good universality, and can adapt to various terrains.

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 a tower crane cockpit automatic lifting and danger protection device, which includes a fuselage, the fuselage includes a cockpit, a direction control chamber, a disengagement ejection transmission chamber, and a support transmission chamber. The ejection mechanism is equipped with an automatic lifting structure, which saves unnecessary waste of time and energy for the driver. When the driver encounters an unexpected situation, such as fainting, the cockpit can also be lowered to rescue the driver in time. When the body senses When the tower crane is extremely unstable, the automatic trigger device causes the body to descend quickly. If the descent is not timely enough, it will be ejected out of the warehouse. At the same time, it will trigger the opening of the parachute and start the aircraft, automatically adjust the descending speed and direction, and trigger the supporting device when it is about to land to ensure a safe landing. To ensure the integrity of the overall body and the safety of personnel, the body can also be used for secondary use.

The invention relates to an automatic oiling type emergency hydraulic system of an airplane, comprising a hydraulic system and an electrical system. An oil path is switched through a switching valve; an emergency accumulator in an oil path of an assisted hydraulic system fills oil and supplies the pressure to the emergency accumulator; horizontal stabilizers are continuously operated to enable the pressure of the emergency hydraulic system to change; and an emergency electric pump is started to supply the pressure to the emergency system and fill oil and supplied pressure to the emergency accumulator. Hydraulic oil of the emergency hydraulic system comes from the assisted hydraulic system without being added from the outside and the whole process can be automatically finished; and the emergency hydraulic system maintains the pressure and automatically discharges the hydraulic oil which returns to an assisted oil tank. The emergency hydraulic system is fully coupled with the assisted hydraulic system so as to greatly reduce the workload for maintenance. When a main hydraulic system and the assisted hydraulic system have faults and fail, the operation safety of the horizontal stabilizers can be ensured and the airplane can safely land by the emergency hydraulic system.

The invention is suitable for the technical field of magnetic suspension compressors, and provides a control method and a control device of a magnetic suspension compressor system and a storage medium, and when the input power supply loses power, a direct-current bus capacitor is charged through back electromotive force generated when a rotor of a magnetic suspension compressor rotates, and the magnetic suspension compressor system is controlled. The direct-current bus voltage is kept stable for a period of time, power supply of the bearing controller can be guaranteed under the condition that hardware cost is not increased until the rotating speed of the rotor is reduced to the range where the bearing can safely land, safe landing of the bearing is guaranteed, and the bearing is prevented from being damaged due to the fact that the bearing controller loses power and the bearing rotating at a high speed directly falls.

The invention discloses an automatic stop valve capable of controlling the oil leakage amount. The end face of an oil outlet end of a traveling valve is attached to the end face of the oil inlet end of a flow dividing valve, and a plug is located in the traveling valve and close to the oil inlet end; a stopper is installed at the oil outlet end, and a screw plug is installed at the oil inlet end; a center hole of the screw plug is an oil inlet hole; a sleeve is located between the stopper and the screw plug; a shunting valve assembly is positioned in the sleeve; and one end of a reset spring is installed in a reset spring installation groove in the inner end face of the stopper, and the other end of is attached to the end face of the oil outlet end of the flow dividing valve. The valve is installed at the bottom of the oil inlet end of the flow dividing valve and is in sliding fit with the sleeve; a stop block is mounted at the port part of the oil inlet of the flow dividing valve; and a spring is sleeved on the stop block. The stop valve is installed at the front end of an airplane wheel, when an airplane wheel cylinder base is damaged and oil liquid leaks, after oil liquid with the designed value volume of the stop valve flows through, an oil way can be automatically cut off, continuous leakage of the oil liquid in a hydraulic pipeline is effectively avoided, and safe landing of an airplane is guaranteed.

A carrier energy management section FADS failure judgment and control method, comprising the following steps: obtaining atmospheric data measurement data and inertial measurement data under wind interference; analyzing the characteristic difference between the atmospheric data measurement data and the inertial measurement data; Establish the mathematical representation of the safety boundary of the air data measurement data according to the distribution law of profile height, speed, heading, wind speed and wind direction; judge whether the atmospheric measurement information is in the safety boundary according to the coverage degree of the air data measurement data safety boundary to the atmospheric measurement data Range, when the atmospheric measurement information is not within the safe boundary range, it is judged that the air data sensing system is faulty; when the air data sensing system is faulty, the longitudinal control is performed according to the critical state boundary protection or the roll control is performed according to the sideslip angle boundary protection. In the case of FADS failure or no atmospheric data measurement information during the unpowered return process, the vehicle can still be safely and reliably controlled, ensuring the safe landing of the spacecraft.

The invention discloses an aerial survey unmanned aerial vehicle capable of improving balance through buffering, and belongs to the field of unmanned aerial vehicles, the aerial survey unmanned aerial vehicle comprises a lower rack disc, an upper shell is arranged above the lower rack disc, folding movable joints are arranged at the two ends of one side of the upper shell, and an unmanned aerial vehicle driving body is arranged on the inner side of the upper shell; supporting frame rods playing a supporting role are connected to the two side faces of the folding movable joint, a balance tail rod used for keeping balance is arranged on the rear side face of the upper machine shell, and a protection elastic piece playing a protection role during landing is arranged at the tail end of the balance tail rod. The unmanned aerial vehicle has the characteristics that the size of the whole fuselage of the unmanned aerial vehicle is small, interference airflow formed at the tail of the fuselage can be dispersed through a flow guide structure of the fuselage, the stability of the unmanned aerial vehicle in the flight process is guaranteed, and the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle is high in practicability and high in practicability. And meanwhile, the unmanned aerial vehicle can be protected while the unmanned aerial vehicle is lowered.

The invention discloses an autonomous approach route planning method for gliding unmanned aerial vehicles. The method allows a gliding unmanned aerial vehicle to enter a landing area in an optimal gliding manner, height is reduced and course is regulated by means of variable-radius finger-of-eight hovering, and when descending to a set landing window height, the unmanned aerial vehicle can meet the requirements of set landing courses. Firstly, a route composed of a tangent segment, an arc segment and a figure-of-eight hover segment is planed preliminarily according to current location and route limits of the unmanned aerial vehicle, and the unmanned aerial vehicle is controlled to fly along the route; when the unmanned aerial vehicle reaches the set landing direction, the radius and circle number of the hover segment are dynamically adjusted according to the difference between the current height of the unmanned aerial vehicle and the set landing window height; when reaching a set landing height range, the unmanned aerial vehicle meets the requirements of landing route. The method is used to plan the routes to allow for autonomous approach with no effects of objective condition, such as weather, climate and wind interference, and is widely applicable.

The invention belongs to the technical field of aviation scheduling, and discloses a man-machine interaction coordinated flow scheduling method for a high-moving-speed vehicle, which comprises the following steps: S1, inputting information of a climate early warning scheme, a flight model, flight crew, personnel on duty, an expert team and the like, a contact number, flight scheduling information, other information and the like into a total information storage system through an input end; according to the invention, a climate early warning scheme, flight models, flight crew, personnel on duty, expert teams and other information, contact numbers, flight scheduling information, other information and the like are input into the total information storage system through the input end, so that a scheduling center can conveniently retrieve and use the information at any time, through the implementation of a climate early warning scheme, the personnel dispatching center dispatching desks of all departments can be guaranteed to be uniformly deployed in extreme weather such as heavy fog, thunderstorm or storm wind, panic and panic are avoided, safe landing of the forced landing aircraft is guaranteed, the airport is prevented from being damaged, and the emergency early warning effect is good.

The invention discloses a working method for equipping an airborne multi-stage airbag cooperative buffer device. The multi-stage airbag cooperative buffer device includes an upper airbag, an airbag column and a lower airbag; The air valve exhausts and relieves pressure to the outside, and it can also exhaust air to the airbag column through the combined exhaust valve, and the airbag column expands to achieve a first-level buffer; the airbag column can exhaust pressure outward through the airbag column exhaust valve , the lower airbag can also be exhausted through the joint exhaust valve two, and the lower airbag can be inflated to realize the second level of cushioning; the lower airbag can exhaust the pressure to the outside through the lower airbag exhaust valve to achieve the third level of buffering; after the equipment is airborne and landed safely , the airbag device can be deflated, which is convenient for storage and storage; the multi-stage buffer method of the multi-stage airbag cooperative buffer device in the present invention can not only prevent the airborne equipment from directly touching the ground, but also realize the multi-stage release of the internal pressure of the airbag to prevent the airbag from bursting. And make sure the airborne equipment lands safely.