29 results about "Aircraft Pilots" patented technology

The invention discloses an aircraft simulation data generation and situation deduction method based on a flight plan, and the method comprises the steps: firstly constructing an analysis model which is used for receiving a flight plan generated by a front end and carrying out the preprocessing, and then carrying out the aircraft situation deduction based on the information of each flight segment. The method comprises the following steps: generating an independent aircraft class, attaching different state attributes to the aircraft class, establishing an aircraft climbing and descending model, and continuously updating the state attributes of the aircraft class according to real-time deduction data. And finally, designing cyclic output of the aircraft simulation situation data once every 4 seconds. The method aims at providing assistance for work of a controller and improving situation awareness and real-time state monitoring of the aircraft in the operation stage. Meanwhile, an aircraft driver is assisted to make a decision autonomously, and control over the aircraft by the driver and information interaction between the driver and a controller are enhanced; and enough reaction time can be reserved for a driver and a controller at the emergency moment.

The invention provides a method for systematically monitoring aircraft pilot and air traffic control (ATC) radio communications to detect predefined aviation-specific keywords indicative of operational conditions affecting flight safety or efficiency, such as turbulence, icing, or visibility constraints. Detected keywords and semantic equivalents from voice transmissions are transformed into structured data formats. These structured data are correlated with Automatic Dependent Surveillance-Broadcast (ADS-B) data, including precise aircraft position, altitude, heading, and speed. Leveraging this integrated data, the system generates automated, quantitative visualizations, such as condition-specific heatmaps or other graphical representations, illustrating spatial distributions of reported in-flight phenomena like turbulence, icing, or hazardous conditions. These visualizations enable air traffic controllers, pilots, and aviation stakeholders to rapidly assess and disseminate real-time observations and historical patterns of flight hazards, thereby significantly enhancing situational awareness, operational safety, and decision-making effectiveness without manual input or subjective interpretation, improving overall aviation operational efficiency and safety.

The present invention provides an aviation pilot seat with a lightweight and high-load side-slip adjustment mechanism, the seat comprising a leg assembly and a guide rail assembly, a seat assembly mounted on the leg assembly, the seat assembly comprising a seat cushion and a side-slip adjustment mechanism arranged under the seat cushion. The left and right support plates of the seat are rationally split, optimized by simulation and verified by tests, which can not only provide a safe and reliable side-slip adjustment function for the aircraft pilot, but also maintain the force and strength requirements of the seat. The integrated design cleverly avoids the cantilever load condition before side-slipping, achieves the optimal force structure, and maximizes the lightweight and high-load design goal of the seat, without affecting the verification of various load tests of the seat. Even during a crash impact, the seat can still firmly restrain the pilot; in order to prevent the pilot from operating incorrectly, a front-back adjustment limiting mechanism is added after the side-slip adjustment to prevent the front-back adjustment from hitting the cabin side wall after the side-slip adjustment.

The invention discloses a civil aviation flight safety management method and system based on QAR data, and belongs to the technical field of flight safety management, and the method comprises the steps: obtaining a plurality of flight parameters in the QAR data of a civil aviation aircraft; according to a plurality of flight parameters in the civil aircraft QAR data, generating a safety score of the aircraft; classifying the flight parameters, judging the potential safety risk of the aircraft, and generating an abnormal flight parameter score; generating a safety risk score of the aircraft according to the historical safety score and the abnormal flight parameter score of the aircraft; according to the safety risk score of the aircraft, an aircraft driver is pre-warned; by comprehensively acquiring and processing the flight parameters in the QAR data, scientifically evaluating the safety score of the aircraft, accurately judging the potential safety risk and dynamically generating the safety risk score, timely early warning is finally realized, the efficiency and accuracy of civil aviation flight safety management are effectively improved, and a powerful guarantee is provided for flight safety.

A method for piloting a pre-existing aircraft comprising the following steps:integrating an alternative piloting system (1) into the pre-existing aircraft;connecting the aircraft (200) and a ground station in which a ground pilot (207) is positioned;when the aircraft is in a normal state, having the aircraft piloted by a nominal crew;using detection means to detect the occurrence of an emergency situation and, when the occurrence of the emergency is detected:making the ground pilot (207) operational, so that the ground pilot can produce an aircraft ground piloting set-point;transmitting the ground piloting setpoint to the aircraft;using the alternative piloting system to acquire and transmit the ground piloting setpoint to the aircraft flight control system.

The application provides a formation cooperative task allocation method based on a hierarchical mixed auction algorithm, wherein a manned aircraft first makes a tactical decision by quantifying attribute values of tasks in a battlefield to determine priorities of different types of tasks, and then the tasks are distributed to corresponding types of unmanned aircrafts for task auction allocation solution, so as to improve the solution rate of the algorithm and the rationality of the allocation scheme, the target function is improved by introducing a coverage factor and a penalty term, the rationality of the task allocation is optimized, and a task re-allocation mechanism is formulated, namely, the manned aircraft performs real-time dynamic re-allocation of the tasks according to the residual resources of the unmanned aircrafts and the execution cost. The application takes advantage of the human intelligence of the manned aircraft pilots, can not only quickly find the unmanned aircrafts most suitable for the selected tasks, but also realize dynamic task allocation in a complex and changeable environment, balance the task load of the unmanned aircrafts, and reasonably use the unmanned aircrafts in the unmanned aircraft cluster as much as possible.

The invention provides a nonlinear control method suitable for high-maneuverability and large-overload flight, and the method comprises the steps: obtaining an unfiltered compensation control law instruction based on a current-beat state disturbance estimation item of an aircraft, a current-beat input disturbance estimation item of the aircraft and a current-beat constant disturbance estimation item of the aircraft; multiplying the state signal of the current shot of the aircraft by the full-state feedback gain matrix to obtain an unfiltered full-state feedback instruction; multiplying a current shot control instruction of an aircraft pilot by the control gain matrix to obtain an unfiltered main control law control instruction; summing the unfiltered full-state feedback instruction and the unfiltered master control law control signal to obtain an unfiltered master control law instruction; summing the non-filtered compensation control law instruction and the non-filtered main control law instruction to obtain a non-filtered flight control instruction; the unfiltered flight control instruction passes through a low-pass filter to obtain a filtered flight control instruction; and controlling the aircraft to realize high-maneuverability and large-overload flight through a nonlinear steering engine based on the filtered flight control instruction.

The invention relates to a training aircraft pilot physiological state monitoring and early warning system, and belongs to the technical field of aviation physiological monitoring and early warning. The system comprises a data acquisition and preprocessing module, an autonomic nervous system toughness evaluation module, a dynamic toughness index fusion module and an early warning generation module. The system obtains a multi-mode physiological signal and a flight parameter of a pilot; by calculating a cross-modal phase synchronization index, a state space trajectory convergence rate and a brain function network modularization coefficient, evaluation is carried out from three dimensions of cardiopulmonary coupling strength, system recovery capability and cognitive load state; carrying out weighted fusion on the multi-dimensional indexes to form a comprehensive dynamic toughness index, and determining an early warning grade according to the comprehensive dynamic toughness index; according to the method, comprehensive evaluation indexes are constructed, so that the defect that a traditional method depends on a single physiological index and is easily interfered is overcome, the false alarm rate is remarkably reduced, and the robustness and reliability of an early warning result are enhanced.

The utility model discloses a fuel receiving rod device for confirming air refueling butt joint. The fuel receiving rod device comprises a turbine power generation device, an LED lamp bead, a contact and a cable. The turbine power generation device, the LED lamp bead, the contact and the cable form an open circuit, when air refueling butt joint succeeds, the contact is connected, the whole circuit forms a closed circuit, the LED lamp bead is lightened, and butt joint success indication is provided for a fuel receiver pilot. According to the oil receiving rod device, a signal indicating successful butt joint is clearly fed back to an oil receiving aircraft pilot in the form of lamplight, and butt joint can be confirmed without waiting for a fuel oil channel with stable flow to be constructed between the oil receiving rod and the refueling taper sleeve.

A monitoring system (100) comprising a measuring unit (81) is described. The monitoring system (100) serves to monitor an aircraft pilot (99) in an aircraft with regard to the gaseous components in the breathing gas supply and the proportions of gases in the bloodstream of the pilot (99).

The invention discloses a manned aircraft piloted by a small unmanned aerial vehicle, and belongs to the technical field of manned flight equipment. The aircraft comprises a cabin, a large multi-rotor module, a small multi-rotor module, a connecting rod, a universal hinge and an undercarriage, the large multi-rotor module is fixed on the cabin and is mainly used for generating lift force; the small multi-rotor module is connected with the cabin through a connecting rod and a universal hinge, is positioned in front of the cabin, and is mainly used for controlling the flight attitude of the aircraft; a remote controller is arranged in the cabin, and a driver can remotely control the small multi-rotor module through the remote controller. The characteristics of low equipment failure rate and high stability of the small unmanned aerial vehicle are utilized, the overall failure risk of the manned aircraft is reduced, meanwhile, navigation is conducted through the small multi-rotor-wing module in front, the control experience of a driver is enhanced, and the flight safety is improved.

A method for assisting the driving of a rotorcraft, the aircraft comprising at least two engines, the first engine being able to be placed in a standby state to ensure that the second engine operates in a fuel economy mode (so-called ECO mode), a method for assisting the driving of a rotorcraft, in the method, a determined number of flight hours between two overhauls is achieved by limiting wear of the second engine in the ECO mode, an engine control temperature (TCPME) associated with the second engine is calculated in the flight computer as a function of a predefined maximum power (PME) in the ECO mode of the second engine, the engine control temperature represents a current damage state of the second engine and is displayed on the flight screen to attract the attention of the aircraft pilot to allow it to remain below the engine control temperature.

According to the aircraft anti-collision system for the airport ground obstacles and the anti-collision method used in the aircraft anti-collision system, lag or errors of information transmission can be eliminated, improper driving behaviors of an aircraft driver can be effectively corrected in time, and collision detection, early warning and braking can be completed through independent equipment of an aircraft. The aircraft anti-collision system of the present disclosure includes: detection units installed at a plurality of high-risk collision positions of an aircraft and including at least a pair of monitoring devices; the analysis processing unit is used for judging the relative motion collision trend between the airplane and the obstacle and sending feedback instructions of different risk levels according to the relative motion collision trend; the alarm unit is used for sending corresponding alarm prompt information to an aircraft pilot according to different risk levels of the feedback instruction; and the brake control unit is used for sending a deceleration instruction to an aircraft brake system when the feedback instruction with the high risk level is received and control operation is not carried out according to the alarm prompt information.

The invention discloses an aircraft pilot control device joint debugging system, which belongs to the technical field of aviation equipment, and comprises an acquisition measurement and control system and a test tool, and a pilot control device is fixed on the test tool and is connected with the acquisition measurement and control system through an adapter cable. The acquisition measurement and control system comprises a function generator, a digital multimeter, a main control board, an industrial personal computer and the like, the main control board is used for transforming voltage, supplying power to the driver control device, automatically switching a sensor test channel and acquiring a sensor feedback signal of the driver control device, and the function generator is used for outputting a signal with a certain amplitude and a certain frequency; the digital multimeter is used for calculating the feedback signal into an angle value, and then the industrial personal computer judges whether the angle value meets the standard or not and generates a report file. According to the invention, automatic measurement and display can be realized, the debugging time of the whole control device is reduced to 0.2 hour from the original 8 hours, the debugging efficiency is improved, the labor intensity is reduced, and the production cycle is guaranteed.

The invention belongs to the field of air refueling long-distance convergence guidance, and particularly relates to an air refueling long-distance convergence guidance system and method. The system comprises an instruction response module, a data acquisition module, a route planning module and an auxiliary guide module. The long-distance meeting guidance system carries out route planning according to information such as the position and the speed of the refueling and receiving aircraft and meeting function requirements, and finally an airborne display device assists a refueling aircraft pilot in completing a long-distance meeting task. The method disclosed by the invention is of great significance for completing a flexible and hidden air refueling task in a confrontation environment and expanding the task execution range of the oil receiver aircraft.

The invention relates to the technical field of training aircraft flight training monitoring and man-machine interaction, in particular to a training aircraft pilot operation behavior monitoring and correcting system. Comprising a multi-modal data acquisition module used for acquiring student physiological-cognitive data and training plane flight state data in real time; the student mental model dynamic construction module is used for generating a real-time cognitive load index; the manipulation behavior track prediction module is used for generating a predicted manipulation deviation degree; the feed-forward calibration instruction generation module is used for determining a calibration instruction transmission mode in response to the predicted manipulation deviation degree generated by the manipulation behavior trajectory prediction module, and generating a calibration instruction corresponding to the calibration instruction transmission mode; and the personalized parameter calibration module is used for cognizing the influence factors and determining a low load threshold value and a high load threshold value of a calibration instruction transmission mode. According to the invention, the safety margin of flight is obviously improved, the training period of trainees can be effectively shortened, and the training efficiency and quality are improved.

The invention discloses a man-machine cooperative flight multi-dimensional cognitive state quantitative evaluation method for a low-altitude aircraft, and the method specifically comprises the steps: synchronously collecting the electroencephalogram, eye movement, skin electricity, heart rate and other multi-dimensional physiological data of a driver and the flight data of the aircraft; based on coupling of electroencephalogram, eye movement and flight data, a quantitative model of the driver three-dimensional space cognitive load is constructed; for specific emergencies, on the basis of analysis of event electroencephalogram related potential components and in combination with driver sight line, the duration of a key instrument is obtained again, and a situational awareness damage index is generated; and fusing the indexes with task management pressure indexes obtained based on the skin and the heart rate to obtain a multi-dimensional cognitive state comprehensive evaluation result, and dynamically adjusting man-machine interaction logic or an automatic driving takeover strategy according to the multi-dimensional cognitive state comprehensive evaluation result. According to the method, the cognitive state of the low-altitude aircraft driver in the complex three-dimensional environment can be objectively and quantitatively evaluated, and technical support is provided for man-machine collaborative optimization and definition of the safety boundary of the low-altitude aircraft.

An aircraft (12) piloting system (10) comprising a throttle (16), a flight parameter sensor system (18), and an engine control unit (22) controlling thrust parameters of an aircraft (14) engine (12). The piloting system (10) includes a flight control unit (20) connected to the engine control unit (22), the sensors (18), and the throttle (16); the flight control unit (20) generating a thrust control vector from a flight control law and sending a digital signal including the generated thrust control vector to the engine control unit (22); and the engine control unit (22) controlling said thrust parameters of the engine (14) according to the generated thrust control vector received.

The invention belongs to the technical field of aircraft seat slide rail assembly, and discloses a clamp for aircraft pilot seat slide rail assembly and a using method thereof, the clamp comprises a pipe frame, a first mounting seat, a second mounting seat, a first connecting rod, a second connecting rod, a third connecting rod, a fourth connecting rod and a fifth connecting rod, and the pipe frame adopts a truss structure design and is provided with four first mounting positions and two second mounting positions, the support is designed to be of a bent structure and is fixedly connected to the first mounting position, a pressing plate is movably connected to the outer side face of the support, and a limiting pin is arranged on the lower surface of the support; the plate is fixedly connected to the second mounting position, an angle plate is fixedly connected to the plate, and the angle plate and the lower surface of the support are located on the same horizontal plane. The problem that the aircraft pilot seat sliding rail is inconvenient to assemble is solved.

The invention relates to an aircraft seat device, in particular an aircraft pilot seat device, for mounting in an aircraft, comprising a stand unit (14a; 14b), which has two mutually spaced seat feet (16a, 18a; 16b, 18b); a seat main part (30a; 30b), which has a seat base (32a; 32b) and a backrest (34a; 34b), the seat main part (30a; 30b) being connected, in lateral regions (36a, 38a; 36b, 38b), to the two seat feet (16a, 18a; 16b, 18b); and a height adjustment device (100a; 100b), by means of which the seat main part (30a; 30b) is attached to the seat feet (16a, 18a; 16b, 18b) at an adjustable height. According to the invention, the height adjustment device (100a; 100b) has a gear unit (102a; 102b), by means of which the seat main part (30a; 30b) can be continuously adjusted between a lower position and an upper position, the gear unit (102a; 102b) having at least one adjustment gear (104a, 106a; 104b, 106b) which is functionally positioned between the seat main part (30a; 30b) and the stand unit (14a; 14b).

1. The name of the present design product: display screen for displaying pilot control graphical user interface of compound wing vertical take-off and landing aircraft. 2. The use of the present design product: for displaying graphical user interface. 3. The design points of the present design product: the graphical user interface displayed on the display screen. 4. The picture or photograph best indicating the design points: front view. 5. The design claimed contains color. 6. The rear view, left view, right view, top view and bottom view are omitted as they are conventional designs. 7. The use of the graphical user interface: displaying pilot control interface of compound wing vertical take-off and landing aircraft.

An system and method for providing navigational assistance to an aircraft pilot in real time. A series of photos with a fixed field of view are captured and combined to create a panoramic image using an inexpensive still camera mounted on an electric pan motor. The panoramic image is layered with stored terrain data having identical location, and any abnormalities (such as ground or airborne obstructions) are identified. AI software may be used to determine if / what corrective action is required to avoid a collision or other dangerous outcomes.

This invention provides, in some embodiments, an impact- and blast-resistance improved aircraft pilot chair, which is able to provide improved protection to a pilot, from exposure to significant G forces and / or exposure to projectiles including projectiles penetrating the aircraft and / or effects of pilot chair ejection and / or effects of aircraft crash

A force application device for an aircraft control stick in provided. The device includes a mechanical joint, a force motor, a rheological brake, and a control device. The mechanical joint receives a lever of an aircraft pilot stick and is rotatably movable. The force motor includes a motor shaft extending along a third axis, the rotation of the motor shaft being linked to the rotation of the mechanical joint. The force motor exerts a resistive torque on the motor shaft. The rheological brake includes two facing parts, and has a volume delimited by the two facing parts, the volume being adapted to contain a rheological material. One of the parts is arranged on the motor shaft and rotatably movable about the third axis relative to the other of the parts. The control device applies an electromagnetic field within the volume so as to vary shear strength of the rheological material.

A monitoring system (100) with a measuring unit (81) is described. The monitoring system (100) serves to monitor an aircraft pilot (99) in an aircraft with regard to the gaseous components in the breathing gas supply and to the proportions of gases in the pilot's (99) blood circulation.

1. Name of this design product: Aircraft cockpit elbow rest. 2. Purpose of this design product: Installed on the side of the aircraft pilot as an elbow rest. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture.

A monitoring system comprising a measuring unit is described. The monitoring system may serve to monitor an aircraft pilot in an aircraft with respect to the gaseous components in the breathing gas supply and to levels of gases in the bloodstream of the aircraft pilot.

The invention relates to a system and method for detecting and protecting an aircraft against inappropriate piloting by a pilot potentially experiencing spatial disorientation due to a somatogravic illusion. The method comprises: obtaining (401) flight information and state information; estimating (402) a current value of a perceived degree of longitudinal pitch from said flight information; calculating (403) a difference between said current value of the perceived degree of longitudinal pitch and a current value of an actual degree of longitudinal pitch; and when this difference is greater than or equal to a predetermined longitudinal pitch deviation threshold, then determining (406) whether a piloting action performed by said at least one pilot is inappropriate from the aircraft state information; and when the piloting action performed is inappropriate, then activating (408) a protective measure.It is possible to detect flight conditions conducive to the occurrence of somatogravic illusions, as well as signs of spatial disorientation in pilots leading to inappropriate aircraft piloting. Figure to be published with the abbreviation: Fig. 4.

The invention provides an aircraft driver health state early warning device and method. The health state early warning device comprises a central processing unit, a camera, a data acquisition module, a data storage module, a data analysis module, a sound-light alarm module, a data server and an application program. The camera is installed in an aircraft cockpit and used for monitoring the health state behavior of an aircraft driver and transmitting collected image information of the health state of the aircraft driver to the data collection module. According to the invention, real-time data monitoring and automatic alarm can be carried out on the health state behavior of an aircraft driver in an aircraft cockpit, and meanwhile, real-time image information data of the health state behavior of the aircraft driver can be transmitted to application software on the data server for real-time monitoring and automatic alarm; and the personal safety of personnel on the aircraft is ensured.