215 results about "Aircraft safety" patented technology

A system and method for operating an aircraft such that any hostile persons taking over the cockpit, for instance, terrorists or a disgruntled pilot, cannot control the flight path of the aircraft to enter restricted airspace, such as ‘no fly’ zones, or any authorized pilots while operating an aircraft cannot unintentionally enter any no fly zone areas.

A method provides alert information, regarding an aircraft wheel braking system, to an operator of an aircraft during an aircraft landing. An input of a target deceleration rate for the landing aircraft is received prior to the aircraft having landed on a ground surface. At least one sensor electronically collects information relevant to a real-time deceleration rate of the aircraft after the aircraft has landed on the ground surface, and the real-time deceleration rate of the aircraft is calculated. The target deceleration rate is compared to the calculated deceleration rate to determine an effectiveness of the aircraft wheel braking system. A visual, audible, or tactile alert is optionally provided to the operator of the aircraft, and data from this system could also be used as an input for various other aircraft safety systems. A system for performing the method is also provided.

An improved system and method are disclosed for facilitating target aiming and aircraft control by flight crews using electronic displays. For example, an aircraft display system is disclosed that includes a database for storing target location and boundary data, a processing unit, a position and direction determination unit for use in determining the position of an aiming symbol on a display, a graphics display generator, and a visual display. The processing unit determines whether or not a selected target to be displayed is obscured or covered by the aiming symbol to be displayed. If any portion of the target is obscured or covered by the aiming symbol, then the processing unit directs the graphics display generator to generate graphic control signals for the visual display, which increase the transparency of the portions of the aiming symbol that obscure or cover the target. Notably, the transparency of any symbol (or portion of a symbol) can be increased if that symbol obscures or covers a target being displayed or viewed. Thus, the visibility of targets viewed using onboard visual displays is significantly enhanced, whereby the targets are obscured by the symbols used to aim and control the aircraft. Advantageously, target aiming and aircraft control are facilitated, which reduces pilot workload and navigation errors, and thus results in increased aircraft safety.

The invention discloses a 2D + 3D large aircraft shape defect detection and analysis method based on deep learning, and the method is characterized in that the method comprises the steps of collectinga multi-view 2D image and 3D point cloud data; obtaining a complete aircraft point cloud model through registration; extracting feature points of the image and the point cloud, and performing 2D-3D correspondence according to feature matching; estimating the pose of the camera according to the 2D-3D corresponding relation; according to the camera pose, realizing assignment from the texture colorof the 2D image to the 3D point cloud; determining point cloud semantic segmentation according to the point cloud color and the coordinate information; and detecting and analyzing aircraft appearancedefects according to the point cloud semantic segmentation. The invention discloses the 2D + 3D large aircraft shape defect detection and analysis method based on deep learning. Vision sensor equipment and an optical three-dimensional detection system measurement technology are used for processing and analyzing collected 2D + 3D data, shape defects on a large aircraft can be accurately and effectively detected and extracted, the conception is reasonable, and in practice, automatic application can be achieved in aircraft safety inspection and other scenes.

A system for enabling the safe landing of an aircraft during an in-flight emergency is provided. The system includes a plurality of onboard devices for releasably securing a plurality of wings to a fuselage, and a non-electric module for activating said onboard devices. Said onboard devices are released to separate said wings from the fuselage.

An aircraft safety seat that has a supporting structure and a bucket seat supported by the structure, the bucket seat has a seat and a back which are lined together, the back being installed on the structure so as to slide generally downwards, wherein at least one connection rod connected by its first end to the support and by its other end to the seat, the connecting rod being generally horizontal when in normal use, and being suited for pivoting downwards by its first end under the effect of a force exerted downwards on the seat, against the action of a shock absorber.

The invention relates to a safe landing system and a method for rescuing airplanes, wherein, a carrying device (1) uses a landing-guiding device (2) to detect flight information, such as location, direction and speed, etc. of the airplane (4) and then based on the flight information, the airplane (4) is guided to be matched with the carrying device (1) till the carrying device (1) and the airplane (4) synchronously move to the same horizontal position and direction to cause the airplane (4) to downwards move gradually onto the carrying support (103) of the carrying device (1). Then the engine of the airplane (4) is turned off and the carrying device (1) is decelerated by a brake device (102) to be completely stopped. The safe landing system and the method for rescuing the airplanes can rescue the airplane (4) which breaks down for the duration of the flight and can not successfully open a belly to lower down a take-off and landing device and airplane wheels. By adopting the safe landing system and the method for rescuing the airplanes, the airplane (4) can land safely to not only ensure the safety of human life, but also avoid the economic loss of plane crash.

The invention discloses a gust generating device for wind tunnel experiments, which relates to the field of aircraft aerodynamic experiment research, can realize gust load slowing down and actively control the gust flow field environment required for wind tunnel experimental research, and is useful for the structural design of aircraft and improving the safety of aircraft Sex and comfort provide an important theoretical basis. The invention includes: the gust generator is a longitudinal gust generator, which can generate a stable simple harmonic flow field in the vertical direction, and is mainly composed of a driving mechanism, a blade cascade swing mechanism, a control system and a frame. The invention is applicable to the field of experimental gust generation.

The invention belongs to the boring and processing technology, and relates to a device capable of collecting borings. A main body structure of a quick collector for borings is a hemispherical housing; a central hole for allowing a bore bit to get in and out is formed in the center of the hemispherical housing; one side of the bottom of the hemispherical housing is an open type, and is in contact with a component surface to form a sealed space; a borings collecting hole is formed in the hemispherical housing; and a negative-pressure absorbing device is connected outside the borings collecting hole, and is used for absorbing away borings. The quick collector for the borings disclosed by the invention can be used for limiting the borings within a limited area, so that a great deal of splash is avoided, the borings can be automatically cleaned, independent cleaning is not required after boring, the boring operation is greatly convenient and aircraft safety is improved.

The invention discloses an aircraft safety take-off control method. The method comprises the steps of 10, obtaining information of an angle between an aircraft body and the horizontal plane through an angle sensor; 20, judging whether the obtained information of the angle is smaller than or equal to the maximum safety angle threshold value or not; 30, controlling the aircraft to take off if the obtained information of the angle is smaller than or equal to the maximum safety angle threshold value. The invention further discloses an aircraft safety take-off control device. By the adoption of the technical scheme, whether the aircraft is horizontally placed or not can be accurately judged, and the aircraft can safely take off.

The invention discloses an aircraft safe landing method and a landing device. A landing car is adopted to reduce the speed and the kinetic energy of an aircraft to reach zero within short time to solve such safe landing problems of the aircraft due to undercarriage failures; the landing car includes a frame, multiple sets of wheels, a stop plate A, buffer pads A, a platform, multiple rows of stop devices and a control room; multiple buffer pads A stacked and connected in sequence are mounted on the stop plate A; an airport control center controls the landing speed, angle and direction of the landing car and the aircraft forcedly landed by the failures, gradually lowers the speed of the landing car; meanwhile, an ejector rod is hoisted; a platform rotates around a rotating shaft; an angle alpha of the platform is gradually changed from zero degree to a certain degrees, and meanwhile, the aircraft is decelerated; an aircraft head or an aircraft body or other part and the buffer pads A are deformed; and the buffer pads A coat the surface of the aircraft, so that the resistance is further increased, the speed of the aircraft is reduced to zero, the landing is safe, and the harm to the aircraft and persons therein is eliminated or reduced.

A security mechanism identifies users, so as to restrict access and operation to authorized users, such as to persons authorized to access and fly a particular aircraft. The security mechanism comprises one or more security devices to identify the user attempting to gain access or operate the controller; and one or more monitoring devices to determine whether or not the user identified is authorized to have access or operate the controller. Methods of safely operating aircraft are also described. The methods include protocols for limiting access to the aircraft and assuming remote control of the aircraft if a possibly hostile situation is detected.

An aircraft system comprising a deflector assembly including, a base having mounting apertures; an inner ring concentrically positioned within an outer ring, the inner ring and the outer ring have an annulus defined therebetween via a base plate, a plurality of rods attached within the annulus and culminating at an apex creating a conical profile; and a forward-mounted cone-shaped deflecting member. The base plate comprises a through hole allowing airflow through the deflector assembly to supply an airplane engine. The aircraft safety device system further comprises at least one locking latch for removably securing the deflector assembly to a housing of the airplane engine. The aircraft safety device is mountable inside a lip of the housing of the airplane engine. Further, the aircraft safety device provides protection for airplane engines from air born animate and inanimate objects.

The invention discloses a non-centralized safety interval autonomous keeping system for a pilot, which is characterized by comprising a conflict probability module, a graded warming module and a dynamic release module. The input part is composed of four kinds of data of aircraft performance, a flight status, an airspace situation and a flight intention, and the output part is aircraft operation parameters. The system uses the aircraft safety interval autonomous keeping as a research object, problems of conflict detection and conflict release between aircrafts, the aircraft and a ground obstacle and the aircraft and the special restricted airspace existing in intensive flights under different performance, different missions and different priorities of heterogeneous aircrafts in a civil aviation operation condition can be solved. Key technologies such as conflict detection among multiple aircrafts, conflict release strategy optimization and flight conflict autonomous graded evaluation in the civil aviation operation condition are broken through, and a set of complete non-centralized safety interval autonomous keeping system for the pilot is brought forward.

A security mechanism identifies users, so as to restrict operation to authorized users, such as to persons authorized to fly a given aircraft. The security mechanism comprises a controller operable by a user; one or more security devices to identify the user attempting to operate the controller; and one or more monitoring devices to determine whether or not the user identified is authorized to operate the controller.

A method for policing and managing the operation of a flying, unmanned aircraft in the event of usurpation of control of, malfunction of, or ill-intentioned use of, this aircraft includes the steps of (a) detecting inappropriate operation of the aircraft; (b) transmitting a takeover command to the aircraft to interrupt control of the operation of this aircraft by a first pilot and relinquish control of the aircraft to a second pilot; and (c) transmitting control commands to the aircraft to control its operation by the second pilot, until the need for alternate pilot control of the aircraft has ended or until the aircraft has landed safely.

The invention relates to a patrol aircraft safety control system, which comprises a ground control device, an emergency air bag device, an aircraft and a main control chip and a slave control chip for controlling the aircraft, wherein the aircraft is provided with an image acquisition unit, a flight control unit, a wireless transmitting and receiving device and a memory electrically connected with the main control chip respectively; the ground control device comprises a wireless transmitting and receiving module, an aircraft remote control module and a flight path module; the aircraft is also provided with a speed sensor, a GPS positioning device, a six-axis inertial sensor and an ultrasonic sensor electrically connected with the input end of the slave control chip, and the output end of the slave control chip is electrically connected with a rotor control device, a speed reducing protection device, and a gas generating device. The aircraft can perform patrol automatically according to the made flight path, the aircraft reduces the speed once fault happens, the air bag can be ejected in time, and the process is safe and reliable.

The present invention relates to an aircraft double-redundancy anti-skid control system, which comprises an anti-skid controller, an electromagnetic hydraulic lock, a brake control valve and a wheel speed sensor. According to the present invention, during a normal anti-skid control process, the main anti-skid control plate card of the anti-skid controller, the brake control valve, and the main electrical coil of the wheel speed sensor are in a working state, the standby anti-skid control plate card and the standby electrical coil are in a warm standby state, the anti-skid control system automatically switches to a standby working state when any one of the main anti-skid control plate card, the brake control valve and the main electrical coil of the wheel speed sensor produces failure, and no influence is generated to the main anti-skid control when any one of the standby anti-skid control plate card of the anti-skid controller, the brake control valve and the standby electrical coil of the wheel speed sensor produces failure, such that the operation reliability of the anti-skid control system is improved, and the aircraft safety is effectively improved.