597results about "Aircraft indicators" patented technology

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 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.

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.

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.

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.

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.

The invention discloses a structural health monitoring method for a high-temperature and ultrahigh-pressure reactor based on an unmanned aerial vehicle platform, the unmanned aerial vehicle platform carries a non-contact thermal imaging module and a contact ultrasonic detection module, and the structural health monitoring method comprises the following steps: receiving and processing data from the non-contact thermal imaging module, identifying a suspected abnormal area on the surface of the reactor; generating a control instruction based on the identified suspected abnormal area, and guiding the unmanned aerial vehicle platform to move the contact type ultrasonic detection module to a corresponding position for contact type detection; and the data processing module is used for receiving and processing data from the contact type ultrasonic detection module so as to verify and evaluate the suspected abnormal area. According to the technical scheme provided by the invention, full-coverage structure health assessment can be carried out on the high-temperature and ultrahigh-pressure reactor through the remote unmanned aerial vehicle platform, and potential internal defects and surface abnormalities can be accurately identified.

A calibration assembly for a guided vehicle. The calibration assembly includes an orientation marker that operably engages with a first guidance apparatus of the guided vehicle. The calibration assembly also includes an imaging assembly that operably engages with and is in electrical communication with a second guidance apparatus of the guided vehicle. When the imaging assembly captures the orientation marker at a translated position for at least one cycle, the imaging assembly calibrates a rotational displacement between a first guidance direction of the first guidance apparatus and a second guidance direction of the second guidance apparatus based on an angular displacement of the orientation marker measured between a zeroed position denoting the first guidance direction and the translated position.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircraft driven by an electric propulsion system and in other types of vehicles. In some embodiments, an aircraft is disclosed, the aircraft comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command for the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on at least one dynamically changed torque command.

The invention discloses a method for arranging the mounting position of an aviation airplane wheel thermal fatigue early warning device, and relates to the technical field of airplane braking airplane wheels. The method comprises the following steps: acquiring a first lowest temperature corresponding to 10% attenuation of tensile strength of an airplane wheel assembly material, and acquiring a second lowest temperature corresponding to 20% attenuation of tensile strength of the airplane wheel assembly material; based on the temperature of each thermal display unit on the thermal fatigue early warning devices, a plurality of thermal fatigue early warning devices are arranged at equal intervals on the circumference with the stress smaller than 85% of the tensile strength of the airplane wheel assembly material by calculating the fixed rim of the airplane wheel assembly under the radial-lateral design load working condition. The thermal display units with different melting point temperatures are respectively arranged, and whether the airplane wheel is overheated or not is judged by visually observing the use temperature of the airplane wheel.

The application is a divisional application of the original application with the application number 2021108483611. The application discloses a waterproof unmanned aerial vehicle. The unmanned aerial vehicle comprises a shell and a second sealing partition. A flight control cavity is formed in the shell. The second sealing partition is arranged in the upper shell of the shell and arranged in the horizontal direction. The second sealing partition divides the flight control cavity into an upper sealing cavity and a lower sealing cavity. The upper sealing cavity is provided with an upper opening for mounting components. A detachable cover plate assembly is arranged at the upper opening. The cover plate assembly seals the upper opening. The internal cavity of the unmanned aerial vehicle is divided by the sealing partition. The sealing partition blocks the diffusion of water into the internal cavity of the unmanned aerial vehicle, avoids the problem that water enters one cavity and then enters other cavities, and seals the battery mounting port by the battery sealing cover to prevent water from flowing in from the battery mounting port.

Operation control unit controls flight driving mechanism such that drone performs an operation by which detection values of sensors included in sensors included in drone match a target value. Detection unit detects, when a plurality of drones perform an operation by which detection values of the sensors included in sensors included in the plurality of drones match a target value, a difference in an operation result of each of drones. Clustering unit classifies a plurality of drones, including drone in which clustering unit is included, into at least one cluster based on differences in operation results detected by detection unit. Correction unit corrects the detection values of the sensors based on the operation results of drones included in a maximum cluster of the classified clusters.

The embodiment of the utility model discloses an environment situation indicating device based on cockpit windshield indication. The device comprises a controller and an indicating module which are connected. Wherein the controller is used for determining an environment situation indication strategy and driving one or more indication sub-modules of the indication module according to the environment situation indication strategy, so that one or more indication sub-modules at a specified position generate an environment situation indication effect matched with the environment situation indication strategy; the indication module comprises a plurality of indication sub-modules, each indication sub-module is arranged at a preset position of a windshield of a cockpit, and each indication sub-module is used for being driven by the controller to generate an environment situation indication effect.

Aircraft having a security system at the interface between a first domain and a second domain. The aircraft (10) comprises a first domain (12, 14) having lower security requirements, including at least one system (42, 44) for generating an input video stream (20), and a second domain (16) having higher security requirements, including at least one system for processing and / or displaying an output video stream (22) obtained from the first domain (12, 14). It includes a video stream security system (18) forming a video interface between the first domain (12, 14) and the second domain (16), the security system (18) being configured to receive the input video stream (20) according to the first video transmission protocol and to generate the output video stream (22) from the input video stream (20), according to a second video transmission protocol. Figure for the abbreviation: Figure 1

The cable support capable of monitoring the clamping state in real time is characterized in that a cam rod is provided with a large-section section and a small-section section, at least two blind holes are formed in the large-section section, and at least two arc-shaped grooves are formed in the side face, close to the tail end, of the small-section section; a sunken part deeper than the groove body is arranged in the arc-shaped groove; the ball can move along the arc-shaped groove and reside in the sunken part; the connecting sleeve is provided with at least two conical grooves corresponding to the axial positions of the arc-shaped grooves, and the balls are embedded into the conical grooves. The nut is matched with the external thread part of the connecting sleeve, and the ball can be embedded and sunken when the cam rod is rotated; at least two kidney-shaped holes are formed in the side wall of the shell in the axial direction, the studs penetrate through the kidney-shaped holes and the blind holes, and the studs are used for axially guiding and preventing relative rotation of the cam rod and the shell; the spring is arranged in the shell and sleeves the small-section section; one end of the force sensor abuts against the shell, and a gap for a clamped part is reserved between the other end of the force sensor and the connecting sleeve. The force sensor is integrated, real-time monitoring of clamping force is achieved, and the clamping force can be accurately adjusted and designed.

The application discloses an air crossing robot, which comprises a flying mechanism and a buffer mechanism, wherein the flying mechanism comprises a flying body and a support connected with the flying body, and the buffer mechanism comprises a ring-shaped protection component movably connected with the support, the ring-shaped protection component is arranged around the flying body, and the ring-shaped protection component can rotate around its axis. The buffer mechanism of the air crossing robot can effectively separate the yawing moment in the phase-cut direction, thereby reducing the amplitude of the change of the flight posture of the air crossing robot, and in combination with the specific structure of the ring-shaped protection component, the collision duration can be prolonged, and substantial impact buffering is provided. Experiments show that the trend of the inclination of the air crossing robot after being hit is greatly reduced by being equipped with the buffer mechanism.

The invention relates to an emergency lighting element (1) comprising a planar, electrically operated radiation source (2) for the planar emission of electromagnetic radiation from its front surface (3). A long-lasting phosphor layer (10) is provided over the entire surface of the front surface (3) of the radiation source (2). The radiation source (2) is designed to emit electromagnetic radiation in the visible range, and the long-lasting phosphor layer (10) is designed to partially transmit the radiation, wherein the emission of the radiation source (2) and the transmission of the long-lasting phosphor layer (10) are coordinated such that the emission of electromagnetic radiation in the visible range by the emergency lighting element (1) is at least 50% higher when the radiation source (2) is switched on than when the radiation source (2) is switched off.

A propulsion system (20) includes a propulsor (26), an engine (22), an electrical assembly (24), and an emergency energy protection assembly. The engine (22) includes a fuel system (38). The fuel system (38) includes a fuel control unit. The electrical assembly (24) includes a battery (66), a motor control unit (64), an electric motor (62), and an electrical distribution system (68). The electrical distribution system (68) includes at least one contactor electrically connected between the battery (66) and the motor control unit (64). The at least one contactor is switchable between a closed state and an open state. The engine (22) and the electric motor (62) are coupled with the propulsor (26). The emergency energy protection assembly includes an emergency actuator. The emergency actuator is actuable in an actuated state to control the at least one contactor to switch to the open state, control the motor control unit (64) to deenergize the electric motor (62), and control the fuel control unit to stop fuel flow for the engine (22).

Tracking a maintenance compliance window of opportunity is provided. The method comprises receiving an alert in response to an aircraft system exceeding an operational threshold or failing to transmit a report. A lead time countdown to a compliance deadline is started in prescribed units. Elapsed and remaining units, out of a total number of allotted units in the lead time, are calculated based on reports from sources defining an operating cycle of the aircraft system. The countdown is displayed in a user interface as a normalized sliding scale of elapsed percentage of total number of allotted units in the lead time. The remaining units out the total number of allotted units are also displayed in the user interface. The countdown is ceased in response to the first of: resolution of the alert or the countdown reaching the compliance deadline, wherein the lead time has completely elapsed.

An optimized protection device configured to open a low-voltage electrical line in the event of an HVDC disturbance, while directing the potential occurrence of a secondary electric arc. Advantageously, it is thus possible to increase the safety of the systems by optimally isolating an electrical line in the event of HVDC disturbances above a predetermined magnitude.

A system and a method include a control unit configured to determine a position of an aircraft within an airspace from tracking information received from a tracking sub-system. The control unit is further configured to associate weather conditions with the position within the airspace. The weather conditions are detected by one or more sensors of the aircraft.

The system includes a crew task determination module (40) and a crew resource determination module (44), designed to determine, for each crew member, at least one theoretical reference cognitive state of the crew member based on the task list assigned to the crew member, using a resource model. It also includes a crew operational state determination module (62), designed to determine an indicator of the crew member's ability to perform the task(s) on the task list assigned to the crew member, based on the crew member's actual cognitive state determined from physiological measurements of the crew member and measurements of the crew member's interaction with the aircraft, and from the crew member's theoretical reference cognitive state determined by the crew resource determination module (44).

An aircraft propulsion system includes a core engine that includes a core flow path through a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate power used to drive the main compressor and a propulsive fan. A water augmentation system includes a tank where water is stored and at least one location where water is communicated into the core flow path, and a controller programmed to operate the water augmentation system according to a selected mode of operation, a detected quantity of water and other conditions impacting engine operation.

The utility model provides an automatic yaw attitude adjusting mechanism for a photoelectric pod, which relates to the field of adjusting mechanisms and comprises an automatic horizontal adjusting mechanism, and a first suspension arm and a second suspension arm are arranged on two sides of the bottom of the automatic horizontal adjusting mechanism. A plurality of threaded holes are formed in the top ends and the bottom ends of the first lifting arm and the second lifting arm, bolts are inserted into the bolt holes in a penetrating mode, the top end of the first lifting arm and the top end of the second lifting arm are connected with the horizontal automatic adjusting mechanism through the bolts, and the pitch posture automatic adjusting mechanism is installed at the bottom ends of the first lifting arm and the second lifting arm through the bolts. A plurality of elastic telescopic pieces are located in a plurality of threaded holes respectively, a spring is in a compressed state, one end of a pressing column abuts against the head portion of a bolt, the other end of the pressing column abuts against the head portion of the bolt, and the other end of the pressing column abuts against the head portion of the bolt. Therefore, the bolt is not easy to loosen in long-time use.

The invention provides a linkage protection method and system for a battery and an electronic speed controller of a high-voltage unmanned aerial vehicle and a medium, and the method comprises the steps: synchronously collecting the multi-dimensional state data of a battery management system and the electronic speed controller based on a preset period, and fusing the data into an operation state sequence set; meanwhile, a safety threshold group set is dynamically adjusted in combination with environment temperature information; then, identifying an abnormal state by sequentially comparing each state parameter with a threshold range, and further calculating a dynamic change trend of an abnormal parameter to evaluate a risk level; meanwhile, the risk level is intelligently improved based on a preset parameter association rule; then, integrating all the abnormal information into an abnormal level distribution diagram, and inputting the abnormal level distribution diagram into a fault level instruction obtained by a fault analysis model; and finally, executing a corresponding hierarchical control strategy. Therefore, serial comparison and comprehensive analysis of multi-parameter thresholds are realized, and the continuous operation capability and task reliability of equipment are guaranteed on the premise of ensuring the safety of a flight control system.