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 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 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 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 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.