A system and method for predicting aircraft nonlinear instability includes the steps of: (1) a pre-built aircraft state parameters for all possible flight conditions, (2) real time measuring flight parameters to determine aircraft state, (3) calculating the inertial coupling frequencies and periods as well as the nonlinear instability threshold based on the nonlinear instability theory recently developed by the inventor, (4) providing a first warning signal if the threshold is approached, (5) providing a second warning signal if the threshold has been exceeded.

The invention relates to a virtual reality high-altitude flight experience device with centrifugal weight system which includes a base, a balance steering device and a safety seat. The base includes a bottom plate, a steering seat, an annular cover plate and a steering rod. The balance steering device includes a cylinder composed of two curved plates, an end cover, a second hydraulic cylinder, a weight, a baffle, a bearing, a rotating shaft, a third hydraulic cylinder and a controller. The safety seat includes a back plate, a horizontal plate, a bumper and a VR helmet. The virtual reality high-altitude flight experience device with centrifugal weight system of the present invention has simple and reasonable structure, easy to operate, low cost, safe and reliable, strong sense of reality, and high degree of intelligence, etc. which effectively solves the problem of poor experience in the existing flight experience devices.

The invention relates to a virtual reality high-altitude flight experience device with centrifugal weight system which includes a base, a balance steering device and a safety seat. The base includes a bottom plate, a steering seat, an annular cover plate and a steering rod. The balance steering device includes a cylinder composed of two curved plates, an end cover, a second hydraulic cylinder, a weight, a baffle, a bearing, a rotating shaft, a third hydraulic cylinder and a controller. The safety seat includes a back plate, a horizontal plate, a bumper and a VR helmet. The virtual reality high-altitude flight experience device with centrifugal weight system of the present invention has simple and reasonable structure, easy to operate, low cost, safe and reliable, strong sense of reality, and high degree of intelligence, etc. which effectively solves the problem of poor experience in the existing flight experience devices.

A system and method for predicting aircraft nonlinear instability includes the steps of: (1) a pre-built aircraft state parameters for all possible flight conditions, (2) real time measuring flight parameters to determine aircraft state, (3) calculating the inertial coupling frequencies and periods as well as the nonlinear instability threshold based on the nonlinear instability theory recently developed by the inventor, (4) providing a first warning signal if the threshold is approached, (5) providing a second warning signal if the threshold has been exceeded.

Systems, methods, and computer products according to the principles of the present inventions may involve a training system for a pilot of an aircraft. The training system may include an aircraft sensor system affixed to the aircraft adapted to provide a location of the aircraft, including an altitude of the aircraft, speed of the aircraft, and directional attitude of the aircraft. It may further include a helmet position sensor system adapted to determine a location of a helmet within a cockpit of the aircraft and a viewing direction of a pilot wearing the helmet. The helmet may include a see-through computer display through which the pilot sees an environment outside of the aircraft with computer content overlaying the environment to create an augmented reality view of the environment for the pilot. A computer content presentation system may be adapted to present computer content to the see-through computer display at a virtual marker, generated by the computer content presentation system, representing a geospatial position of a training asset moving within a visual range of the pilot, such that the pilot sees the computer content from a perspective consistent with the aircraft's position, altitude, attitude, and the pilot's helmet position when the pilot's viewing direction is aligned with the virtual marker.

A method for determining an attenuation of a wind caused by a simulated obstacle and experienced by a simulated vehicle in a simulation, comprising: receiving a wind direction and an initial speed for a simulated wind; generating a line of sight vector having a source position, a given direction and a given length, the given direction being one of opposite to the wind direction and identical to the wind direction; determining a distance between the simulated obstacle and the simulated vehicle using the line of sight vector, the distance being at most equal to the given length of the line of sight vector; determining a wind attenuation gain using the distance between the simulated obstacle and the simulated vehicle; determining an actual speed for the simulated wind using the initial speed of the simulated wind and the gain for the wind attenuation; and outputting the actual speed.

An interactive computer simulation system, station and method for training a user in the performance of a task through a training activity. A tangible instrument module allows a user to interact with the tangible instrument module for controlling a virtual element. A plurality of performance metric datasets representing results of the interactions between the user and the tangible instrument module is obtained. During execution of the interactive computer simulation, in the plurality of performance metric datasets, a plurality of actual maneuvers of the virtual element are detected during the training activity, one or more standard operating procedures (SOPs) are identified for the training activity from a plurality of the individually detected actual maneuvers. In real-time upon detection of the SOPs, information for display in the interactive computer simulation related the SOPs.

A method for determining an attenuation of a wind caused by a simulated obstacle and experienced by a simulated vehicle in a simulation, comprising: receiving a wind direction and an initial speed for a simulated wind; generating a line of sight vector having a source position, a given direction and a given length, the given direction being one of opposite to the wind direction and identical to the wind direction; determining a distance between the simulated obstacle and the simulated vehicle using the line of sight vector, the distance being at most equal to the given length of the line of sight vector; determining a wind attenuation gain using the distance between the simulated obstacle and the simulated vehicle; determining an actual speed for the simulated wind using the initial speed of the simulated wind and the gain for the wind attenuation; and outputting the actual speed.

A method, includes saving in-flight data from an aircraft during a simulated training exercise, wherein the in-flight data includes geospatial locations of the aircraft, positional attitudes of the aircraft, and head positions of a pilot operating the aircraft, saving simulation data relating to a simulated virtual object presented to the pilot as augmented reality content in-flight, wherein the virtual object was programmed to interact with the aircraft during the simulated training exercise and representing the in-flight data from the aircraft and the simulation data relating to the simulated virtual object as a replay of the simulated training exercise.

In an aspect of the present disclosure is a system for simulating an electrical vertical takeoff and landing (eVTOL) aircraft, including a fuselage comprising one or more pilot inputs, each of the pilot inputs configured to detect pilot datum; a concave screen facing the fuselage; a plurality of projectors directed at the concave screen; a computing device communicatively connected to the plurality of projectors, the computing device configured to: receive the pilot datum detected by the pilot inputs; generate a simulated eVTOL flight maneuver as a function of the pilot datum; and command the plurality of projectors to display one or more images based on the simulated flight maneuver.