32 results about "Airplane crash" patented technology

The present invention discloses a method and apparatus for minimizing accelerations during impacts such as those encountered in motor vehicle accidents, helicopter and airplane crashes, explosions, and the like. The preferred embodiment takes the form of a helical spring-like member (100), designed to experience plastic deformation over a desired deformation length, under a given impact load threshold. The spring-like member is preferably installed in a mechanical linkage that is flattened under impact, straining the spring-like member in a predictable fashion. The operating characteristics of this system [namely the stress-strain curve, and thus the deformation length, impact load threshold, and acceptable load range for the system to be protected] can be easily controlled by varying the device dimensions and installation configuration.

The invention belongs to the technical field of avionics and in particular relates to a flying parameter recorder capable of floating on the water. The flying parameter recorder comprises an upper separable component and a lower mounting frame which is directly fixed on an airplane, wherein a recorder component is arranged in the separable component filled with a foaming material; an electric initiator is arranged on the mounting frame; after the airplane crashes into the water, the electric detonator in the flying parameter recorder is detonated to be on fire, so that the separable component and the mounting frame fixed on the air plane can be separated from each other, and the separable component is pushed out and floats on the water. Under the common action of a water sensor, a battery box, a relay and a throwing separation device, the flying parameter recorder can enable the separable component to be popped out of the mounting frame to be popped out of the airplane body after falling into the water, so that the separable component can be prevented from sinking to the bottom of the water together with the airplane and can be easily found by searching staff.

The invention belongs to the technical field of aircraft processing. Specifically, the invention relates to an emergency lifesaving device for a fuselage after an airplane crash, which includes an aircraft fuselage, the aircraft fuselage includes a cockpit, and the lifesaving device also includes The parachute, the accommodation box installed on the fuselage at the rear end of the cockpit, the ejection device for ejecting the parachute, the connection device and the controller for connecting the fuselage and the parachute, the fuselage is located at the rear end of the accommodation box and is equipped with an opening and closing assembly , the ejection device includes an ejection plate and an ejection assembly, the connection device includes a front end connection assembly for connecting the front end of the fuselage and the parachute and a rear end connection assembly for connecting the rear end of the fuselage and the parachute, the ejection assembly Both the switch and the switch components are electrically connected with the controller. After the aircraft is out of control, it can prevent the aircraft from being blown up, avoid large losses, avoid large safety accidents, and reduce the consequences of the aircraft crash.

The method provides a dry vertical shaft storage system for spent fuel of a nuclear power station and a storage method thereof. The system comprises a loading subsystem, a storage subsystem, a reloading subsystem, a transferring subsystem, a residual heat discharge subsystem, a negative pressure ventilation subsystem, a fuel suction subsystem and an air blowing subsystem. The system saves a water-cooling system and a water purification system on the basis of the water storage method; the storage vertical shaft is arranged underground, so that the influence of an external event can be effectively prevented, such as airplane crash; when the spent fuel needs to be transferred, a spent fuel storage tank can be taken out of a storage depot, and then directly loaded in a spent fuel shielding transport cask through lifting equipment so as to be conveniently transported; a plant and structural equipment are not polluted by radioactive materials, so the spent fuel storage depot can be normallydisassembled and retired after the spent fuel storage tank is transferred; radioactive decontamination is not needed and the spent fuel storage depot can be conveniently retired; and the storage tankcan be processed in different phases to reduce initial cost according to the operation of the power station.

The invention provides a heuristic optimization method and device for a communication topology of an unmanned-manned aerial vehicle formation. The method comprises the steps of S1, acquiring a formation communication graph according to a two-dimensional lasting formation shape into which the unmanned-manned aerial vehicle formation requires to form; S2, when the unmanned-manned aerial vehicle formation has a communication fault, building a first reconstructed formation communication graph according to the type of the communication fault; S3, acquiring a first optimal reconstructed communication topology corresponding to the first reconstructed formation communication graph according to a communication topology reconstruction algorithm; S4, acquiring a second optimal reconstructed communication topology according to the first optimal reconstructed communication topology, a plurality of location configurations of the unmanned-manned aerial vehicle formation and the communication topology reconstruction algorithm, wherein the second optimal reconstructed communication topology meets a preset condition that n>[abs(V)*(abs(V)-1)] / 2, and the second optimal reconstructed communication topology is a re-optimized communication topology of the unmanned-manned aerial vehicle. According to the invention, a large-scale unmanned-manned aerial vehicle formation can be ensured to avoid an airplane crash accident when a communication fault occurs and recover the formation shape, and the communication cost for keeping the formation is low at the same time.

The invention provides an electromagnetically driven black box throwing mechanism, which includes an ejection assembly, an actuation assembly and a base, the ejection assembly is arranged at the center of the base, and at least two groups of the actuation assemblies are evenly distributed Around the black box, all actuating components are arranged on the side of the base, the base is installed on the aircraft body, and the ejection component is connected to the bottom of the black box. When the aircraft is flying safely, the actuating components press Tightly lock the black box. When the plane crashes, the actuating component operates to unlock the black box. At the same time, the ejection component moves to eject the black box to separate the black box from the aircraft body. An electromagnetically driven black box throwing mechanism according to the present invention is installed on the aircraft body to press the black box tightly during the safe flight of the aircraft. Perform ejection to separate it from the aircraft body in advance.

The invention belongs to the on-board computer technology field, to be specific, relates to a safety-critical software health management method. The safety-critical software health management method comprises the following steps: 1) a safety-critical software health monitoring table can be created; 2) a safety-critical software diagnosis criteria table can be created; 3) a safety-critical software health management decision blueprint can be created; 4) whether the safety-critical software is faulted can be determined by querying a health monitoring table; 5) a fault phenomenon can be determined according to the health diagnosis criteria table; 6) the fault treatment can be carried out according to the fault treatment rules made by the health management decision blueprint. The safety-critical software health management method is advantageous in that the fault isolation and the fault recovery of the safety-critical software can be realized by creating the health monitoring table, the health diagnosis criteria table, and the health management decision blueprint, and therefore the problems such as airplane crash, casualties, property damages, and severe environmental damages, which are possibly caused by the incorrect function or the failure of the safety-critical software, can be prevented.