10 results about "Aircraft Pilots" patented technology

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.

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 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.

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).

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.

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.