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 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 normally disassembled 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 tank can be processed in different phases to reduce initial cost according to the operation of the power station.

The invention discloses an airplane with an abnormal emergency landing safety and protection device, comprising a fuselage, and the backside of the fuselage is provided with a parachute which can pop out of the fuselage when the airplane crashes; the head part and the bottom part of the fuselage are provided with airbag devices which can pop out of the fuselage when the airplane crashes; the airbag device comprises an airbag and a rapidly inflating device; the rapidly inflating device is communicated with the airbag through a pipeline; the pipeline is provided with a check valve; the rapidly inflating device is a nitrogen compressed gas generator or a sodium azide solid tablet gas generator or the combination of the nitrogen compressed gas generator and the sodium azide solid tablet gas generator; the invention can not only reduce the impact when the airplane crashes, but also increase the waterborne buoyancy force of the airplane and improve the safety performance.

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 discloses a ground control system capable of flight control of a plurality of unmanned aerial vehicles (UAVs). The ground control system includes a multi-UAV flight control navigation platform, a ground station software control platform and a remote controller auxiliary module, wherein the multi-UAV flight control navigation platform includes a plurality of different types of UAVs, and includes a flight control stability augmentation module, an obstacle avoidance module, a tracking identification module, a sensor detection module, a blade motor output module, a data analyzing andpackaging module B, a wireless data transmission module and a GPS / INS integrated navigation module; and the ground station software control platform includes an interactive user command input module,a status and map display module, a task assignment cooperative control module, a data analyzing and packaging module A, a warning and alarming module, a data storage and playback module and a remotecontroller auxiliary module. The ground control system capable of flight control of a plurality of UAVs supports a multi-UAV formation cooperative task control flight path planning function, and is provided with the obstacle avoidance module which can effectively reduce airplane crash accidents caused by communication between ground stations and UAVs during autonomous flight.

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 discloses an unmanned aerial vehicle provided with a falling guard device and a falling guard method thereof, belonging to the field of UAV (unmanned aerial vehicle). The UAV comprises a judgment module for judging whether the UAV is in a falling state or not, a controller for sending out ejection signals when judging that the UAV is in the falling state and an ejection mechanism for separating a part of the UAV from the UAV in an ejecting manner, wherein the controller is respectively connected with the judgment module and the ejection mechanism; the ejection mechanism is connected with the part separated in the ejecting manner. According to an idea that lighter parts and heavier parts in the aerial vehicle are separated automatically, the damage of the aerial vehicle in an airplane crash can be lowered, the safety of the aerial vehicle in the air is improved from another aspect, parachutes are installed on the heavier parts with regular shapes, the damage is further reduced, and the situation that the parachutes twine the heavier parts is avoided.

The present invention discloses an automatic airplane black box surfacing apparatus, and relates to an airplane black box addition facility. At present, when the airplane crashes into the sea, the black box falls into the sea along with the airplane, and it is difficult to fish the black box or the black box can not be fished if the black box is positioned in the deep sea area. According to the automatic airplane black box surfacing apparatus of the present invention, the black box (2) is embedded in a hard foam floating body (5); when the plane crashes into the water, an automatic water contacting and separation device (1) is started, such that the airplane black box (2) is separated from the airplane body; the airplane black box (2) surfaces with the effect of the hard foam floating body (5); meanwhile, a radio position indicator (3) automatically starts, and transmits a position signal; the search person can rapidly find the accident site and recover the black box according to the signal transmitted by the radio position indicator.

The invention relates to a high-magnitude strong-impact test method and belongs to the technical field of aviation airborne electronic equipment. The test method is used for simulating that a fixed protection recorder installed on an airplane bears high-magnitude strong-impact during airplane crash. A test product undergoes changes with reduces speeds to generate strong impact, so that the large probability working condition of the protection recorder undergoing strong impact damage can be reflected during airplane crash, and the method has indoor actionability. According to the method, high-pressure gas serves as a power source, the test product is driven to be accelerated to a regulated speed in a specially-made guide device by utilizing the high-pressure gas to instantly release high pressure; at the time, a spring support is separated from the test product through a separating device for the spring support and the test product, and the test product independently impacts a load generating medium at the regulated speed to generate strong impact with the regulated load. By implementing the high-magnitude strong-impact test method, strong-impact verification of magnitude of over 6,000g / 5-8ms half sinusoidal waves can be achieved.

The invention discloses a high-magnitude and strong impact test method, and belongs to the technical field of aviation airborne electronic equipment. According to the test method, the situation that a fixed type protection recorder installed on an airplane bears high-magnitude and strong impact when the airplane crashes is simulated, a tested product produces strong impact when bearing the change of reducing of the speed, the large probability working condition of the protection recorder when the protection recorder bears the strong impact damage can be reflected well when the airplane crashes, and indoor implementation is achieved. According to the method, a high-pressure gas medium serves as a power source, high pressure is released instantly through the high-pressure gas, the tested product is pushed to accelerate until the standard speed is reached in a specific guiding device, a bullet support and the tested product are separated through a separating device of the bullet support and the tested product, the tested product independently collides with a load generating medium with the required speed, and the strong impact with the required load is produced. By means of the high-magnitude and strong impact test method, the verification problem of the strong impact with the magnitude with the half-sine wave of 6000 g / 5-8 ms can be solved.

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 discloses an electronic switching unit without energy consumption for a standby power supply of a model airplane receiver. Along with the constant development and popularization of model airplane activities, amateurs who are high on large-level model airplanes become more and more, but a lot of amateurs are only equipped with the cognitive level on that airborne equipment of small-class model airplanes consumes power and usually ignore or forget the state of charge of the battery of the model airplane receiver during outfield flight, so that non-maneuvering accidents caused by the power shortage of the receiver usually occur. According to the power consumption characteristics of the model airplane receiver and a steering engine as well as the technical requirements for a battery pack, the invention solves the problem that when the model airplane receiver is short of power in the air, the standby power supply can be quickly and directly switched to for the emergency power supply of the receiver, and can effectively control airplane crash accidents caused by the power shortage of the battery pack of the model airplane receiver. The electronic switching unit is formed by that a design idea of computer online emergency power supply, which is quick in response, is borrowed, a micro-power consumption voltage detector is used as a core, a P-channel high-power field effect transistor is used as a switching actuating element for a main power supply and the standby power supply, a few discrete electronic elements are used as supplement elements, and a circuit not only has simple and direct and reliable structure, but also has no need of debugging.

The invention relates to airplane flying safety equipment, in particular to a retarding device when an airplane loses power and rapidly crashes and auxiliary equipment thereof. The invention provides airplane safety equipment, which solves the technical problem that a vertical impeller drives a rotary air compression impeller to compress the air downwards, so that the retarding effect can be generated when the airplane loses power, and the airplane slowly lands and does not vertically crashes. The size and the number of the retarder are designed according to the size and the weight of the airplane to support the weight of the airplane, so that the dropping speed can be reduced when the airplane drops, and the airplane can safely land to the ground. According to a compact and scientific design, the airplane crash retarder can be used for any airplane.

The embodiment of the invention provides a novel unlocking separation mechanism, and belongs to the technical field of avionics. The novel unlocking separation mechanism specifically comprises a base,a recorder connecting seat and a spring unlocking mechanism, wherein the base is of a hollow tubular structure, one end of the base is provided with a shape memory alloy power source, and the side wall of the other end of the base is circumferentially provided with a plurality of first through holes; the recorder connecting seat is used for fixing a throwing recorder, and second through holes areformed in the positions, corresponding to the first through holes, of the side wall of the recorder connecting seat in the circumferential direction; and the spring unlocking mechanism comprises a thrust spring arranged on the outer wall of the base in a sleeving mode and a limiting steel ball used for limiting and locking the recorder connecting seat and the base. The novel unlocking separationmechanism can separate the throwing recorder from an aircraft body at the key moment of aircraft accidents, so that the throwing recorder escapes from the severe crash environment, and the survival capacity of the throwing recorder is improved.

The invention relates to a detachable initiating explosive device cutting and separating combined structure capable of bearing a large bending moment load, and overcomes the defects that in the prior art, under the working condition of single-point fixed connection of a large target object, the bending moment load bearing force is insufficient, stability and reliability are poor, and at present, an initiating explosive device combination structure capable of bearing a large bending moment load and fixing a target object at a single point, arranging a cable after disassembly, cutting the cable and separating the target object at the same time do not exist. The target objects such as a flight recorder and the like can be fixed at a single point, and meanwhile the recorder cable can be rapidly arranged and installed; when an aircraft works, the large bending moment load generated by a target object can be effectively borne, when the aircraft wrecks, a target object connecting cable can be cut off, the target object is thrown and separated, meanwhile, a delay mechanism is designed, and the function of the whole device has time sequence.

A polyhedral object enabling an accident airplane crash site to be found out quickly is composed of top planes, a plurality of inclined faces and a plurality of vertical lateral walls. After an accident airplane crashes into a sea (or a high mountain or a dense forest ) and disintegrates, multiple polyhedral objects float on the water surface of the sea and gather together to form a piece (when the accident airplane crashes into the high mountain or the dense forest, the polyhedral objects are scattered all around in the high mountain or the dense forest), the top planes and the inclined faces can reflect light, airplane radar signals and satellite electronic signals, and therefore the efficiency at which the accident air plane is found out through searching can be increased.

The invention provides an electromagnetically-driven black box throwing mechanism, and the throwing mechanism comprises ejection assemblies, actuating assemblies and a base, wherein the ejection assemblies are arranged in the center of the base, the actuating assemblies are evenly distributed on the periphery of a black box, all the actuating assemblies are arranged on the side of the base, and the actuating assemblies are arranged on the periphery of the black box; the base is installed on the aircraft body, and the ejection assembly is connected with the bottom of the black box; when the aircraft flies safely, the actuating assembly tightly presses and locks the black box; when the aircraft breaks down, the actuating assembly operates and unlocks the black box, and the ejection assemblyacts to eject the black box to enable the black box to be separated from the aircraft body. The electromagnetically-driven black box throwing mechanism is installed on an aircraft body, the black boxis pressed in the safe flight process of an aircraft, and after the aircraft breaks down, the unlocking can be driven under the action of an instruction, and the black box is catapulted to be separated from the aircraft body in advance.

The invention discloses an airborne standby power switching device for a model airplane receiver. The airborne standby power switching device is characterized by being composed of a 6V main power supply, a 4.75V voltage detecting circuit, a 6V main power indicating circuit, a level switching and driving circuit, a standby power switching circuit and a standby power supply. The airborne standby power switching device for the model airplane receiver, disclosed by the invention, aims at solving the problem that when a battery pack of a large-level model airplane receiver is short of power, a serious accident occurs and the like; the airborne standby power switching device adopts a high-practicability standby power preparation technique for the model airplane receiver, and can be used for achieving the technical goal of power-consumption-free rapid switching of the standby power supply of the receiver; and in case that the large-level model airplane receiver is short of power in the air, the airborne standby power switching device can automatically and directly switch the standby power supply so as to finish the supply of standby power for the model airplane receiver through the standby power supply, and effectively avoid the accidents such as model airplane crash due to the power shortage of the battery pack of the model airplane receiver; and the airborne standby power switching device can be used as a model airplane airborne configuration for ensuring the safety flight of a model airplane.

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.

The invention discloses a solar energy-based unmanned aerial vehicle positioning apparatus and a control method. The apparatus includes a cylindrical cage-like body and an airbag. The airbag is connected to the cylindrical cage-like body, and the apparatus further includes a solar cell panel, a positioning module, a lithium battery, a data transmission module, and a control module that are disposed in the cylindrical cage-like body. A gyroscope is built in the control module, and can determine an attitude of an aircraft. When it is determined that the aircraft crashes, the airbag is opened. When it is determined that the apparatus lands and is in a relatively stationary state after the aircraft crashes, a power supply mode is selected according to states of the solar cell panel and the lithium battery, and a positioning signal of the positioning module is sent through the data transmission module. The apparatus is firm, has good protection performance and an ultra-long endurance fieldpositioning capability, and can send positioning information for a long time, thereby greatly reducing difficulty of finding the aircraft and minimizes a loss after an unmanned aerial vehicle crashes.

A process for aircraft retrieval and aircraft crash site remediation may include establishing a perimeter at an aircraft crash site. The process may include containing wreckage in a containment unit that is adapted to prevent release of hazardous materials into the environment. The wreckage may include wreckage of an aircraft from the aircraft crash site. The process may include washing at least some of the wreckage in a decontamination unit. The process may include packaging the washed wreckage in a container.

Systems and methods for determining object location may include a memory and a processor. The processor may be configured to collect seismic data and geophysical data to determine object location. The processor may be configured to determine one or more seismic attributes associated with a plurality types of noises based on the seismic data and the geophysical data using one or more machine learning algorithms. The processor may be configured to eliminate unwanted noises from noise classifications based on the one or more seismic attributes. The processor may be configured to predict the object location by comparing time and velocity data of the object with recorded timing and velocity data. The processor may be configured to validate the object location by comparing the determined noise with image data. The systems and methods may be used in, for example, detecting missing planes such as Malaysian Airlines Flight 370.

The invention discloses a separated aircraft protection device, method and system. The separated aircraft protection device comprises a protection device, and a drone flight module, a fixing module and a control module which are respectively connected with the protection device. The airplane protection method of the separated airplane protection device comprises the following steps: receiving an airplane alarm; enabling the separated airplane protection device to fly to a proper position of an airplane and is fixed at the position; starting the protection device to protect the airplane from landing. The airplane protection system comprises a server and one or more separated airplane protection devices, the server formulates an airplane protection scheme according to airplane alarm information, and the one or more separated airplane protection devices are mobilized to cooperatively complete airplane landing protection. According to the separated airplane protection device, method and system, when an airplane breaks down, the separated airplane protection device is used for providing protection for airplane landing, the possibility of airplane crash is reduced, the safety of the airplane is improved, and personal and property losses caused by flight accidents are reduced.

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 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.

The invention belongs to a test technology, and provides a six-degree-of-freedom airplane land falling collision emergency evacuation test system and method, so that the test is closer to a real falling collision scene, the authenticity of the emergency evacuation test is improved, and technical support is provided for modeling of an emergency evacuation simulation model. The method comprises the following steps: step 1, a six-degree-of-freedom motion platform simulates pitching and rolling attitude adjustment after an airplane falls and collides, and a window of a passenger cabin section [6] simulates an external scene after an airplane accident; step 2, a participant wears a wearable wireless sensor to simulate emergency evacuation after the aircraft accident, moves from the interior of the passenger cabin section [6] to a front boarding gate [4] and an on-wing emergency exit [7], and evacuates from the aircraft through a main slide [3] and an on-wing slide [9]; and step 3, the wearable wireless sensor sends the physiological state test participation and the motion trail of the participant, and the physiological state test participation and the motion trail are sent to a system background through the multi-channel wireless data receiver [3].