1101results about "Aircraft indicators" patented technology

An aircraft includes a flight deck including a flight deck door configured to be moved between an open position and a closed position, a first monument, second monument, and a secondary barrier door moveably secured between the first monument and the second monument. The secondary barrier door is configured to fold into a stowed position in which a path to the flight deck is open, and unfold into a deployed position in which the path to the flight deck is closed.

The invention relates to the technical field of aircraft power supply systems, and discloses an intelligent power distribution and fault diagnosis method for an aircraft power supply system, which comprises the following steps: acquiring a real-time current signal and load working condition information of an aircraft power supply bus, a double-domain composite entropy feature is constructed by extracting a time domain entropy transition index representing the energy domain stability of a current signal and a phase synchronization index representing the time structural domain stability; according to the method, dual inspection of the energy domain and the time structure domain is carried out on the current signals, and cooperative judgment is carried out in combination with the load working condition, so that sensitive capture of real fault forebodes is realized; and meanwhile, tolerance is dynamically shown on normal loads in the airplane operation process, the restriction between safety and usability in the prior art is effectively avoided, and predictive health management is made possible.

A door assembly configured to be mounted in an opening of a cabin area of an aircraft. The door assembly includes a door configured to be movable between a deployed position across the opening and a stowed position out of the opening. A lock is mounted to the door and movable between a locked position and an unlocked position. An engagement assembly is mounted to the door and movable between an engaged position and a disengaged position. The engagement assembly includes a plunger, a lock mechanism, and an elongated member that extends between the lock and the lock mechanism. In the engaged position, the lock mechanism and the elongated member position the plunger in an extended position outward from the door. In the disengaged position, the lock mechanism and the elongated member position the plunger in a retracted position relative to the door.

The invention discloses an aircraft nozzle protection device and an aircraft, and relates to the technical field of aircraft nozzle protection.The aircraft nozzle protection device comprises an annular shell and a cover plate, the annular shell is arranged outside an aircraft engine in a sleeving mode, and the cover plate is arranged on the outer side of the annular shell; the first side of the cover plate is rotationally connected with the annular shell, the second side of the cover plate is connected with the annular shell and the engine jet pipe in an unlocking mode, when the aircraft is ejected out of the barrel, the engine jet pipe is static, the second side of the cover plate is locked with the annular shell, and when the aircraft is ejected out of the barrel, the engine jet pipe swings, the second side of the cover plate is unlocked from the annular shell. The first side of the cover plate rotates around the annular shell by the preset angle and then is separated from the annular shell, the cover plate bears huge airflow impact force generated by fuel gas when the aircraft is ejected out of the barrel, the situation that an engine jet pipe is damaged by high-temperature and high-pressure fuel gas is avoided, an ejection bottom plate in the launching barrel does not need to be used, and space is saved; and the mass and cost of the launch canister and the aircraft are reduced.

The invention relates to the technical field of multi-rotor aircrafts, in particular to a blade protection cover detection method, device and equipment and a medium. The method comprises the steps that if it is determined that a multi-rotor aircraft is in a stable hovering state based on the detected moving speed, the detected accelerated speed and the detected angular speed; if yes, acquiring the detected climbing speed and the blade rotating speed of the multi-rotor aircraft; the nominal weight of the multi-rotor aircraft is obtained, and the theoretical climbing acceleration is obtained according to the blade rotating speed and the nominal weight; obtaining a theoretical climbing speed and a disturbance climbing acceleration according to the detected climbing speed and the theoretical climbing acceleration; and determining whether the model of the multi-rotor aircraft is matched with the model of a blade protection cover mounted on the multi-rotor aircraft according to the theoretical climbing speed and the disturbance climbing acceleration. According to the scheme, whether the model of the multi-rotor aircraft is matched with the model of the blade protection cover installed on the multi-rotor aircraft or not can be determined, an operator can be conveniently reminded to replace the unmatched blade protection cover in time, and the user experience is improved.

The invention discloses an arresting protection device of a rear propeller type aircraft and the aircraft, and relates to the field of aircrafts. The arresting hook is hinged below the tail part of the aircraft fuselage; the telescopic limiting and buffering mechanism is mounted on the fuselage and located between the arresting hook and the propeller, and the telescopic limiting and buffering mechanism has a retraction state and an extension locking state; the trigger mechanism is arranged on the telescopic limiting buffer mechanism. Therefore, by increasing the first angle a of the arresting hook swinging upwards for the first time, the impact force of the arresting hook on the fuselage is effectively reduced, and lightweight design of the telescopic limiting buffer mechanism and the fuselage bearing area is facilitated; the telescopic limiting buffer mechanism can be switched among different states to limit the upward swinging angle of the arresting hook, so that the arresting cable is always located below the lowest rotating plane of the propeller, collision with the propeller is avoided, safety of the propeller and the aircraft body is guaranteed, and safety of the aircraft with the rear propeller in the recovery process is improved.

The invention discloses a liquid-phase sweating cooling thermal protection structure based on atomization jet flow, and relates to the field of heat reduction and resistance reduction of active flow control of aerospace high-speed aircrafts, the liquid-phase sweating cooling thermal protection structure comprises a coolant cabin, and cooling spray holes are formed in the cabin wall of the coolant cabin; an atomization vibrating body is fixedly connected to the position, located at the cooling spray hole, of the cabin wall of the cooling agent cabin, the atomization vibrating body can make contact with a cooling agent in the cooling agent cabin, and a driver used for enabling the atomization vibrating body to vibrate is further included. The liquid-phase sweating cooling device works on the basis of the ultrasonic atomization principle, through the effect of the piezoelectric ceramic atomization piece, the liquid coolant generates atomization jet flow and enters a boundary layer outside the aircraft, use of a liquid pumping driving device is avoided, and the light weight degree of the liquid-phase sweating cooling device is improved.

The invention relates to a concave angle asymmetric double-layer negative Poisson's ratio superstructure and application thereof. A concave angle asymmetric double-layer negative Poisson's ratio superstructure comprises bearing pressing plates symmetrically arranged at the upper end and the lower end and a plurality of unit cell elements arranged between the two pressing plates, and is characterized in that the unit cell elements are arranged at equal intervals in the transverse direction and the vertical direction respectively to form an m * n array, each unit cell unit comprises a double-layer concave corner body, transverse connecting rods on the two sides and a vertical connecting rod on the upper portion, the lower portion of each double-layer concave corner body is an outer flat plate cell wall, and the ends of the transverse connecting rods between every two transversely adjacent unit cell units are connected into a whole. And the end parts of the vertical connecting rods between the vertically adjacent unit cell elements are connected with the outer flat plate cell walls into a whole. The deformation mode of the superstructure is influenced by the impact speed, when the speed is increased, the deformation mode transits from overall deformation to local deformation, different local deformation zones are generated, the superstructure has different horizontal contraction processes at different impact speeds, the negative Poisson's ratio effect is reduced along with the increase of the speed, and the local deformation zones are reduced. The superstructure can be applied to anti-impact protection parts of automobiles, airplanes and unmanned aerial vehicles and anti-impact protection parts of wearable protection devices.

A computer implemented method in a communications network for determining location information about an actual location of a drone comprises obtaining (302) a reported location of the drone at a first time point and obtaining (304) a measurement of radio conditions between the drone and a node in the telecommunications network, at the first time point. The method then comprises predicting (306) radio conditions at one or more locations related to the reported location of the drone, and determining 308 the location information about the actual location of the drone based on the measured radio conditions and the predicted radio conditions.

A portable flight navigation tool has a tablet computer with GPS, and memory with an aviation database with international operating rules including transoceanic flight rules, a moving-map database with tracks, coastal airport identifiers and locations, and predefined reporting point locations for transoceanic operations. The navigation tool includes machine readable code for displaying the operating rules, reading locations from the GPS while indicating them on a moving map display, and a trip database with a planned transoceanic route for an individual flight configured by entry of waypoints or names and selection of predefined tracks. The tool has a checklist database and displays checklists for pre-departure, coast-out flight phase, waypoint-reached, and a coast-in flight phases; and may provide a heading and next-waypoint timing for rhumb-line routes from GPS failure locations to the next waypoint of the active route. The tool links as a primary / secondary pair with another like tool.

An aircraft section, between a cockpit and a cabin, comprises an aisle to access to the cockpit from the cabin, and a monument extending in a longitudinal direction and a transverse direction. The monument includes a first lavatory, a second lavatory adjacent thereto in the transverse direction and comprising the aisle, a wall separating the first lavatory from the second lavatory, a boundary wall delimiting the first lavatory and a portion of a rear wall of the cockpit, and a second boundary wall delimiting the second lavatory and a second portion of the rear wall of the cockpit. The boundary walls are parallel or continuous. The monument further includes an outer door movable between an open position, where the cockpit aisle is accessible from the cabin area, and a closed position, where the cockpit aisle is blocked with respect to the cabin area.

A device to control movement of fluid that is emitted from an aircraft engine that is mounted to a wing of an aircraft. The device includes a support member positioned on an exterior of the aircraft and having an elongated shape with a first end connected to the wing and a second end connected to the fuselage. The support member has a first sectional size. A deflector shield is mounted to the support member and positioned on the exterior of the aircraft. The deflector shield has a larger sectional size than the support member. The deflector shield has an outer edge that extends around the support member and is positioned radially outward from the support member.

A ground collision avoidance method in an ownship vehicle is disclosed. The method includes: retrieving position measurements for the ownship vehicle and for a dynamic obstacle; retrieving mapping data from an airport map database that includes coordinate data for airport travel pathways; adjusting a position measurement for the ownship vehicle and a position measurement for the dynamic obstacle based on coordinate data retrieved from the airport map database and historical aircraft movement data; predicting a series of future positions for the ownship vehicle that are constrained by airport surface operation rules; predicting a series of future positions for the dynamic obstacle that are constrained by airport surface operation rules; calculating whether a potential collision is imminent; and causing a collision alert to be displayed when the processor has determined that a potential collision between the ownship vehicle and the dynamic obstacle is imminent.

The invention relates to the technical field of airborne signal detection, and discloses an airborne signal anomaly detection and predictive maintenance system based on an AI model, which comprises a hardware part and a software part, the hardware part comprises a signal acquisition module, a data storage module, a data transmission module, an edge calculation module and a display alarm module; the software part comprises a data preprocessing module, an AI model construction module, an anomaly detection module, a fault prediction module and a maintenance decision module. According to the invention, through an integrated hardware architecture and an intelligent software algorithm, real-time acquisition of airborne signals, accurate anomaly detection, fault prediction in advance and intelligent making of a maintenance plan are realized, and the operation reliability and maintenance efficiency of airborne equipment are improved.

Embodiments provide an aircraft with one or more tilting fan assemblies that are configured to tilt between a forward flight position and a vertical lift position. The aircraft may also include a plurality of lift fan assemblies for vertical movement. The tilting fan assemblies may be coupled to the fuselage or wings of the aircraft via one or more tilting mechanisms. A control system coupled to the aircraft may control the one or more tilting mechanisms to move the tilting fan assemblies between the forward flight position and the vertical lift position. The tilting fan assemblies may be coupled to one or more support structures that are coupled the fuselage or wings of the aircraft.

Principles described herein allow for wings to be optimized for aerodynamic and structural efficiency while reducing planform compromises required to address wing tip stall problems. All-moving outboard wings allow the outboard wing local angle of attack to be changed relative to the inner wing region to avoid tip stall at high aircraft angles of attack, such as that which is required for low-speed flight. During high-speed cruise flight, at low aircraft angle of attack, the outboard wing local angle of attack can be increased to achieve an ideal elliptical lift distribution.

A method of operating a propeller system for an aircraft, the propeller system comprising a propeller, the method comprising: receiving propeller speed information, the propeller speed information indicating propeller speed; receiving a target propeller speed; performing a propeller speed threshold adjustment process, the propeller speed threshold adjustment process comprising adjusting a propeller speed threshold as a function of the target propeller speed; comparing the propeller speed to the propeller speed threshold; and in response to propeller speed exceeding the propeller speed threshold, performing an overspeed protection process.

The present disclosure provides techniques for machine learning-based monitoring of restricted objects. A set of images depicting an exit on an aircraft is accessed, and at least one image of the set of images is processed using a first machine learning model to determine an orientation of at least a portion of an individual relative to the exit. In response to determining that the orientation is towards the exit, it is determined whether one or more alert criteria are satisfied, where the one or more alert criteria comprise a threshold period of time. In response to determining that the one or more alert criteria are satisfied, one or more alerts indicating the exit are generated.

A folding wingtip aircraft includes a wing that includes a primary portion and a wingtip. The folding wingtip aircraft includes a folding wingtip system configured to rotate the wingtip relative to the primary portion. The folding wingtip aircraft also includes a flight control computer. The flight control computer is configured to, in response to a first determination that a wingtip position of the wingtip is not in a folded position when a second determination indicates that a last completed command by the folding wingtip system was a fold command, set error codes for the folding wingtip system. The flight control computer is also configured to change a setting to indicate that the folding wingtip aircraft is grounded based on the error codes.

An electric vertical take-off and landing (eVTOL) aircraft can enhance energy efficiency, safety, and operational range. A deployable wing structure can provide aerodynamic lift during horizontal flight, reducing reliance on energy-intensive propellers. Integrated flexible solar panels capture solar energy, contributing additional power and optimizing energy management. The wing system also includes an emergency descent mode, doubling as a glide-assist device for controlled landings during critical failures. The system offers modular configurations for various missions, ensuring adaptability and improved flight performance. The eVTOL can be implemented with systems and methods for mitigating motion sickness. The systems integrate tactile feedback systems into wearable devices and environmental components. Sensors detect motion and environmental changes, and a computing device can generate corresponding tactile feedback signals. Tactile actuators embedded in the devices or components provide non-visual motion cues, such as pressure, vibration, and haptic feedback, to resolve sensory mismatches between the vestibular and proprioceptive systems.

Methods and systems are provided for a transportation vehicle. One method includes retrieving data associated with one or more seat attributes associated with one or more passenger seats of an aircraft; identifying a first attribute associated with a passenger seat that does not meet a configurable threshold condition defined for the first attribute for aircraft takeoff, landing or both take-off and landing; determining an action associated with the first attribute that can modify the first attribute to comply with the threshold condition for aircraft takeoff, landing or both take-off and landing; and executing the action associated with the first attribute to meet the threshold condition with the aircraft takeoff, landing or both take-off and landing.

The present invention discloses a method and system for real-time perception of the state of an aircraft's rudder surfaces. The system includes an embedded pressure sensor, an embedded processor, a signal transmission module, and an angle comparison module. The embedded pressure sensor uses a silicon chip and is arranged at specific positions on the front edge and upper and lower surfaces of the aircraft's rudder surface to monitor the pressure signal on the rudder surface in real time. The actual airflow angle and surface flow conditions of the rudder surface are solved based on these surface dynamic pressure information, and compared with the rudder control instructions input by the flight control system to determine whether the rudder angle has reached the specified position and whether flow separation has occurred on the rudder surface. The system and method for real-time perception of the state of an aircraft's rudder surfaces with embedded pressure measurement proposed by the present invention provide a beneficial monitoring means and feedback method for rudder manipulation and flow control during the flight of the aircraft, thereby avoiding aircraft safety accidents caused by rudder jamming or failure.

The invention belongs to the field of information surveying and mapping, and particularly relates to a geographic information surveying and mapping unmanned aerial vehicle which comprises a surveying and mapping unmanned aerial vehicle body, a surveying and mapping camera device, a protective baffle and a filter switching mechanism, and the filter switching mechanism comprises a supporting table, a driving assembly, a connecting arm, a mounting sleeve plate, a filter, a wiping assembly and a protective cover plate. The supporting table and the driving assembly are both installed at the bottom of the surveying and mapping unmanned aerial vehicle body, one ends of the multiple connecting arms are fixedly connected to the output end of the driving assembly in a circumferential array mode, the mounting sleeve plate is fixedly connected to the other ends of the connecting arms, the filter is installed on the inner wall of the mounting sleeve plate, and the two wiping assemblies are symmetrically installed at the bottom of the supporting table. One end of the protective cover plate is fixedly connected to the inner side wall of the supporting table, and the bottom of the protective cover plate is in abutting connection with the top of the mounting sleeve plate. Therefore, the problems that in the background technology, existing filter switching depends on manual operation or the switching precision is low, so that surveying and mapping work is interrupted, and the imaging edge is blurred are solved.

The invention discloses a flight crew monitoring method and system and a computer readable storage medium, and relates to the technical field of flight crew state monitoring. The monitoring method comprises the steps that monitoring equipment is controlled to monitor the state of a flight crew to obtain monitoring state information, and the monitoring equipment is configured to be not needed to be worn by the flight crew; and determining an alarm strategy based on the monitoring state information in combination with the flight state information of the aircraft. By means of the mode, the state of the flight crew can be monitored to guarantee flight safety, the flight crew does not need to wear monitoring equipment, the time consumed by the flight crew to wear the monitoring equipment can be saved, and the psychological burden of the flight crew can be reduced.

The utility model discloses an automatic balancing device and an aerial operation robot. The automatic balancing device comprises a connecting seat, a motor and a flying disc, wherein the connecting seat is used for being connected with a foot stool of the aerial operation robot; the motor is fixedly mounted on the connecting seat, the flying disc is fixedly connected with a rotating shaft of the motor, and the flying disc is used for rotating under the driving of the motor so as to provide power for balancing the aerial operation robot. The automatic balancing device is compact in structure and controllable in cost, is mounted on a foot stool of the aerial operation robot, and is used for resisting center-of-gravity shift caused by crosswind or movement on an overhead line, so that interference of the center-of-gravity shift on operation of the aerial operation robot on the overhead line is avoided; the walking stability and safety of the aerial operation robot on the overhead line are remarkably improved.

A system and method for providing airport docking guidance for an aircraft includes supplying, from an airport gate database, airport gate data parking data indicative of gate position points and a gate aircraft parking headings. Aircraft data is supplied from an aircraft data source. Position error data is supplied from a position error receiving system. Airport gate data for one airport gate is retrieved. A processing system processes the aircraft data and the position error data to determine, for the one airport gate, an aircraft position point, an aircraft position deviation, and an aircraft heading deviation. The position error data may be supplied from a ground-based position error transmission system that at least selectively determines, from airport gate data and a ground-based position measurement system, the position error data and transmits the position error data.