35 results about "Flight simulator" patented technology

This application relates to a joystick device and a flight simulator. The joystick device includes a housing, a joystick shaft, and a connecting wire. The joystick shaft is connected to the housing and has a through hole that connects the interior and exterior of the housing. The connecting wire is movably disposed in the through hole; the connecting wire has a first end and a second end, the first end being disposed inside the housing and the second end extending outside the joystick shaft. The housing contains a wire receiving space, within which at least a portion of the connecting wire is bent and movably disposed. At least two rib assemblies are provided on the inner wall of the housing, and the first end of the connecting wire is fixed by engaging two adjacent, spaced-apart rib assemblies. By using two rib assemblies to hold and fix the connecting wire, and by providing a wire receiving space within the housing for bending the connecting wire to allow for its extension and retraction, the structure is simple and occupies little space.

This invention proposes an efficient system and method for processing objective data from helicopter flight simulators. The system includes a data preprocessing module for preprocessing acquired complete flight data, including data fusion and time-series correction; a data segmentation module for segmenting the raw simulator objective data based on helicopter configuration, control variable changes, and flight status to obtain segmented data; a batch processing module for providing a batch processing entry point for multiple sets of segmented data, simultaneously importing multiple sets of segmented data and multiple data parameters into one or more other processing modules for processing; an outlier removal module for identifying and removing outliers from the batch-processed segmented data; a curve fitting module for correcting the data after outlier removal; and a filtering module for recovering the true information as much as possible from the segmented data containing interference.

The present application relates to the technical field of aircraft operating mechanism, in particular to a drive-control integrated aircraft side stick operating mechanism, which comprises a box body, a controller and a driver, a roll transmission shaft is rotatably supported in the box body, a U-shaped decoupling mounting seat is fixedly connected to one end of the roll transmission shaft, a pitch shaft is horizontally supported in the U-shaped decoupling mounting seat, a base is fixedly sleeved on the pitch shaft, a handle connecting rod and a handle assembly are sequentially connected to the upper end of the base, a roll motor drives a rocker arm I through a rocker arm II and a transmission connecting rod I, the rocker arm I is hinged to the roll transmission shaft, a pitch motor drives a fixed head through a rocker arm III and a transmission connecting rod II, and the fixed head is fixedly arranged at the end of the pitch shaft. The present application provides a drive-control integrated aircraft side stick operating mechanism with high integration, ultra-small volume, double-channel synchronous force sensing, microsecond-level real-time bus communication and plug-and-play, which is particularly suitable for the demand of high-fidelity, high-reliability and small-sized operating device of high-level flight simulator.

This invention belongs to the field of flight simulator maintenance technology, specifically relating to a machine learning-based predictive maintenance method for flight simulators. It addresses the problems of existing maintenance methods relying on periodic inspections and passive repairs, delayed fault warnings, and high false alarm / missing rate. This invention acquires historical operational data, sensor time-series data, fault records, and environmental parameters from the flight simulator, and performs preprocessing including cleaning, labeling, and feature fusion. It constructs a composite health feature set containing statistical features, dynamic health status values, and aircraft material reliability parameters. A hybrid prediction model (random forest feature selection + LSTM time-series prediction + adaptive correction reliability assessment) is used to train the model. Combining prediction result fusion analysis and multi-level decision rule post-processing, maintenance work orders and spare parts demand plans are output. This invention improves the accuracy and timeliness of fault prediction, realizing a shift from passive response to proactive prediction in maintenance, significantly reducing maintenance costs and the risk of unplanned downtime.

The application relates to a control rocker capable of realizing rotation return, a flight simulator, wherein the control rocker comprises a shell, a connecting part rotationally connected with the shell, the connecting part comprising a rocker shaft and a shaft sleeve, the shaft sleeve being fixedly connected with the rocker shaft, and a rotation return structure being arranged on the shaft sleeve and used for returning the connecting part relative to the shell.

This invention relates to a coaxial multi-pointer instrument and a flight simulator. The instrument includes a housing, a top cover, and a bottom cover. A display component, a pointer drive component, a control module, and a measurement component are disposed within the cavity formed by the housing, top cover, and bottom cover. The display component is located behind the top cover and displays the rotation of the pointers. The pointer drive component drives different pointers to rotate. The measurement component is located within the pointer drive component and measures the motion signals of the corresponding components, inputting these signals to the control module. The control module adjusts the control of the pointer drive component based on the received motion signals. This invention uses readily available micro-motors and gear sets, resulting in low overall cost. The motors in the pointer drive component can be miniature, enabling coaxial two or more pointers within a small space. Digital closed-loop control facilitates integrated control and the development of simulation components for older pointer instruments in flight simulators.

This invention belongs to the field of simulation testing, specifically relating to an emergency escape device and method for a full-motion flight simulator. It aims to solve the problems of existing simulator escape devices requiring manual deployment, poor stability during escape, and uncertain attitude, increasing climbing difficulty. The invention includes: a fixed end of a telescopic device mounted on the simulator; the telescopic end of the telescopic device can be locked or unlocked with a locking device; the locking device is mounted on a ladder; the ladder is detachably fixed to a cylindrical shaft; the cylindrical shaft bearing is mounted on a leveling device, which is also mounted on the simulator. This invention provides a device specifically for emergency escape training. The structure of this invention enables automatic ladder deployment and retraction, facilitating easy access, exhibiting high stability, adapting to various scenarios, and maintaining a horizontal position without shifting with the simulator's attitude.

The application discloses a flight simulator support connection point bearing capacity evaluation method, comprising the following steps: determining the real-time ratio of shear stress value and normal stress value according to the fused root stress distribution data, classifying the ratio by using a support vector machine, and outputting a weld stress classification grade; evaluating the shear stress dominant type failure of the current root stress distribution data by using a dynamic load amplification factor, fusing an additional displacement amount into the dynamic load amplification factor, and outputting a root weld failure risk grade; extracting a root bending moment value according to the combination of the root weld failure risk grade and the cantilever length, processing the bending moment value by a simulation method to analyze the influence of shortening the cantilever length on the forward movement of the center of gravity, and obtaining a simulated bending moment distribution diagram; and based on the simulated bending moment distribution diagram, comparing the position offset of the ratio of the shear stress value and the normal stress value on the classification hyperplane before and after optimization, and outputting a verification grade.

The application provides a kind of airspeed maintaining control method, device and equipment of helicopter flight simulator, it is related to helicopter flight control technical field, this method includes: in the case where airspeed maintaining function in helicopter flight simulator is opened, based on the current airspeed reference value of helicopter flight simulator and interpolation table, the current expected pitch angle reference value of helicopter flight simulator is determined;Interpolation table is used to characterize the corresponding relationship between current airspeed reference value and current expected pitch angle reference value;Based on current expected pitch angle reference value and current airspeed reference value, control the helicopter flight simulator to fly at the current airspeed reference value.The application can solve the problem that after airspeed reference value adjustment, pitch angle reference value is fixed, which leads to airspeed reference value and pitch angle reference value mismatch, affecting airspeed maintaining control effect, so that airspeed control can reach the set airspeed reference value, reduce the steady-state error of airspeed maintaining.

This application belongs to the field of aviation safety technology and relates to an accident reproduction method and system based on QAR data and simulator-based anti-flight maneuvering, aiming to solve the problems of low reproduction accuracy and poor compliance in existing technologies. The method includes: acquiring an accident QAR dataset; locking the accident timeline nodes and filtering a subset of key parameters; using an anti-flight simulator and optimizing the simulator's anti-flight control strategy based on the key parameter subset and timeline nodes to generate preliminary reproduction data; calculating the timeline and physical deviations between the preliminary reproduction data and the accident QAR dataset, and dynamically fusing the two deviations based on the timeline nodes to generate dynamic correction coefficients; calibrating the simulator's anti-flight process using the dynamic correction coefficients to obtain calibrated reproduction data. This application, by constructing a technical system of data preprocessing, anti-flight optimization, and closed-loop dynamic correction, achieves deep coupling between QAR data and the simulator, improving the accuracy, objectivity, and compliance of accident reproduction.

This invention discloses a method and related equipment for optimizing the sensor layout of the main arm of a dynamic flight simulator, relating to the field of flight simulators. It includes: acquiring a three-dimensional geometric model of the main arm and performing point cloud segmentation to generate a candidate measurement point set; acquiring acceleration signals under uniformly accelerated rotation conditions, and determining the number of equivalent low-order modes based on the number of times the peak value significantly increases; iteratively correcting the initial dynamic model using sensor data, and reconstructing the motion state of the dynamic flight simulator through infinite-dimensional state matrix replacement, thereby improving the positioning accuracy of extreme strain points and solving the problem of calculation deviation in traditional models. An observability matrix is ​​constructed based on the equivalent state matrix and the observation matrix. Under the condition of satisfying constraints, the sensor layout is encoded into a binary vector, constructing an objective function that considers both observability indicators and the constraints on the number of measurement components. An intelligent optimization algorithm is used to solve the objective layout. Measurement components are arranged and measurement data is collected based on the optimization results, achieving optimal monitoring accuracy with the fewest measurement components.

This utility model discloses a cable management structure for positioning a wire harness within the inner cavity of a rotating cylinder. The cable management structure includes a cable management base and a cable tie. The cable management base is positioned against the inner wall of the rotating cylinder; the cable tie is connected to the cable management base and is used to position the wire harness within the base. The wire harness rotates with the rotating cylinder relative to the rotating frame, preventing loosening or shifting of the wire harness; preventing poor contact, signal fluctuations or interruptions, and ensuring the control precision and display accuracy of the flight simulator. This utility model also discloses a base equipped with the cable management structure and a flight simulator equipped with the base.

This application provides a motor assembly, a force feedback base, and a flight simulator. The motor assembly includes a mounting plate, a first motor, and a first magnetic encoder plate. The mounting plate has a first side and a second side arranged opposite to each other, and a through hole passing through the first and second sides. The first motor includes a first motor body, a first output shaft, and a first magnet. The first motor body is located on the first side of the mounting plate, the first output shaft is connected to the first motor body and extends through the through hole to the second side of the mounting plate, and the first magnet is located at the end of the first output shaft. The first magnetic encoder plate is located on the second side and fixed to the side of the first magnet opposite to the mounting plate, spaced apart from and opposite to the first magnet. The motor assembly of this application has a compact structure, stable operation, and low cost. Furthermore, the front-mounted first magnetic encoder plate facilitates installation compared to the rear-mounted design, requiring less space.

The application discloses a flight simulator joystick A-axis reset structure and relates to the technical field of flight simulator joysticks. The flight simulator joystick A-axis reset structure comprises an A-axis and a shell. A limiting seat is arranged on the upper end of the A-axis. The upper end of the limiting seat is matched with the shell. The limiting seat and the shell are fixedly connected through a connecting assembly. An adjustable torsional spring is arranged in the shell. One end of the adjustable torsional spring is close to one side of the limiting seat. The shell is fixedly arranged in a handle assembly. A potentiometer is arranged on the upper end of the shell. A compression spring is arranged on the upper end of the potentiometer. A base wire shaft is arranged at the bottom end of the A-axis. The bottom end of the A-axis is provided with a fixing mechanism which facilitates the fixed connection between the A-axis and the base wire shaft. The application connects the A-axis and the base wire shaft through a connecting knob and a knob base, thereby facilitating the installation and dismounting of the A-axis. The limiting shaft and the bearing are arranged to balance the force and adjust the rotation of the central shaft.

The application verifies the flight program by the linkage simulation verification mode of the flight simulator and the control simulator, and comprises the creation of the static structure of the airspace where the flight program is located, the compilation of the dynamic air traffic control operation scene, the compilation of the flight simulator flight practice plan and the control training plan, the real-time simulation verification of the controller and the pilot, the operation index analysis after the flight, etc. A reasonable and sustainable flight program operation analysis method is provided in the air traffic control field, and a reference direction is provided for the comprehensive flight program verification, so that the problem of incomplete verification content of the existing simulation verification and the field verification flight test is solved, the problem of lack of flight program operation evaluation method and means is solved, the targeted suggestions for the optimization and improvement of the flight program design are provided, and thus the problem of low flight program utilization rate is solved.

The application relates to the technical field of computers and discloses a flight simulator motor degradation monitoring and early warning method and system, an electronic device and a storage medium, which comprise establishing a health baseline atlas and storing reference data under a motor health state; in the running process of the simulator, characteristic parameters are extracted, compared with the health baseline atlas, and a partition degradation index of each stroke partition is calculated; vibration signals and acoustic signals are collected, a sound anomaly quantization index is calculated and generated; under the same motion instruction, the characteristic parameters are synchronously collected, a transverse difference rate is calculated, an adaptive threshold is dynamically determined, a load intensity is determined according to a partition degradation index history record, a degradation integral is calculated and updated based on the load intensity and a duration, and a remaining available life is predicted; an active excitation detection sequence is injected at a preset trigger opportunity, data is collected to generate a health detection report, grading early warning logic is executed by comprehensively considering various indexes, and early warning information is output. The application can improve the operation reliability of a flight simulator motion system.

1. The name of the design product: six degrees of freedom motion platform. 2. The use of the design product: six degrees of freedom motion platform for aerospace, ship simulation training industry, which can be applied to aircraft flight simulator, ship navigation simulator, large-scale entertainment simulation equipment field. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view.

The utility model discloses a flight simulator operating load test frame, including installation frame, the installation frame lower four corners respectively are provided with universal wheel, the installation frame top is through fastening bolt no.

1. Name of the product in this design: Flight Simulator. 2. Purpose of this design: for flight simulation training, education, and entertainment. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

A foot pedal simulation device and a transport aircraft simulator belong to the field of flight simulators. The foot pedal simulation device includes a frame and four foot pedal components. Two foot pedal components are located in the driver's seat and the other two are located in the co-pilot's seat. A support shaft is fixedly mounted on the frame. The upper ends of the two foot pedal components in the same pilot's seat are rotatably connected by a connecting shaft. The two ends of the connecting shaft are fixedly connected to the support shaft by mounting cranks. A synchronous shaft is rotatably mounted on the frame. The synchronous shaft is connected to a servo motor. Two differential cranks are fixedly mounted on the synchronous shaft at intervals along its axial direction. The differential cranks include two staggered hinge parts. Each hinge part is hinged to a synchronous connecting rod. The synchronous shaft is connected to the four foot pedal components through four synchronous connecting rods, which can control the linkage of the two foot pedal components located on the left and right sides in the same pilot's seat. It can also make the two foot pedal components in another pilot's seat perform the same actions synchronously, making the simulation more realistic.

The application provides a replaceable cabin flight simulator, and relates to the technical field of flight simulation, which comprises a visual display device, a rear cabin body and a cabin part. The rear cabin body comprises a rear cabin body fixed part and a rear cabin body movable part. The visual display device is connected with the rear cabin body fixed part. The bottom of the visual display device and the rear cabin body is provided with a rear-opening channel. The cabin part and the rear cabin body movable part are arranged in the channel. The front end of the cabin part is detachably connected with the visual display device. The rear end of the cabin part is detachably connected with the front end of the rear cabin body movable part. The rear cabin body movable part is detachably connected with the rear cabin body fixed part. The technical scheme solves the technical problem of the deficiency of the cabin replacement technology of the existing flight simulator.

This invention belongs to the field of flight simulation and motion control technology, and relates to a method and system for coordinated vibration control of multiple actuators in a flight simulator. It collects flight attitude / state / event information, generates low-frequency attitude commands for a six-degree-of-freedom platform, and matches them with virtual vibration sources. Based on the airframe-cabin transfer relationship, it constructs multi-sensor point frequency-band target vibration responses and ergonomic perception weights. Based on the excitation of the previous control cycle and the current measured response, it online corrects the frequency response matrix and combines actuator travel margin to form vibration resource constraints. Under these constraints, it optimizes the optimal vibration excitation for the platform, seat, joystick, foot pedals, etc., in the current control cycle, converts it into a time-domain signal, and executes it synchronously. The platform implements decoupled superposition of low-frequency attitude and high-frequency vibration. This invention enables dynamic allocation and migration of vibration energy across actuators according to real-time capabilities, reduces the risk of channel saturation, and significantly improves the consistency of body sensation and training realism across multiple parts.

This invention relates to a coaxial multi-layer knob, control panel, and flight simulator. The coaxial multi-layer knob is used in the control panel of an aviation instrument in a flight simulator. Each layer is one or a combination of encoders, potentiometers, or band switches, and each layer has the same or similar structure, arranged in a serial coaxial manner. It includes single-layer encoder buttons, single-layer potentiometer buttons, multi-layer buttons of the same type, buttons of different types in combination, and additional switch buttons. The knob of this invention has a compact structure, low cost, simple interface, and the number of layers can be freely combined according to actual needs. The spring parameters and the number of pins are adjustable, therefore, the torque of the knob can be flexibly adjusted, and the settings are clear.

This utility model relates to the field of flight simulator technology, specifically a flight simulator joystick, including a base, with a hollow rod hinged to the upper end of the base. An auxiliary mechanism is provided on the outer side of the hollow rod, including an anti-slip component disposed on the outer side of the hollow rod. The anti-slip component includes an airbag fixedly installed on the outer surface of the hollow rod. A support component is disposed on the outer side of the hollow rod, including a sliding ring slidably connected to the interior of the hollow rod. A support ring is movably sleeved on the outer side of the hollow rod. In this utility model, the height of the palm rest can be adjusted by sliding it up and down along a groove, adapting to different hand sizes of the operator. This makes it easier for those with smaller hands to grip, effectively supporting the palm heel and improving support, preventing reduced micro-operation precision due to insufficient support. Simultaneously, by adjusting the grip diameter of the joystick, it can be adapted to different hand sizes of the operator.

The present application belongs to the field of aviation technology, and relates to a kind of airplane stall recovery method based on proximal policy optimization algorithm.The present application collects the different trajectories of the airplane by running flight simulator, and the improved proximal policy optimization agent uses the flight trajectory of the airplane to learn the control strategy, and the state parameters of the airplane are transmitted to the agent through UDP protocol.The control strategy of the agent is transmitted to the flight simulator through UDP, and the ratio of beta distribution parameters is calculated using beta distribution to provide help for training planning.A smooth airplane stall recovery reward function is designed to improve the training efficiency of the system.Finally, combined with adaptive learning rate, the sample efficiency of flight trajectory is fully utilized to improve the learning ability of the system.

This invention discloses a flight simulator flap handle control mechanism. The flight simulator flap handle control mechanism includes: a pull handle, a sector wheel, a fixed shaft, a locking nut, a pressure sleeve, a disc spring, and a friction plate. The pull handle is rotatably mounted on the fixed shaft via the sector wheel. One side of the sector wheel comprises the locking nut, the pressure sleeve, the disc spring, and the friction plate. The opposite side of the sector wheel comprises the friction plate and the shoulder of the fixed shaft. The beneficial effect of this invention is that by adjusting the locking nut, the frictional damping of the friction plate on the sector wheel can be changed, making the operating feel and force of the pull handle closer to that of a real aircraft.