4 results about "Flying qualities" patented technology

The invention belongs to the technical field of aviation flight training, particularly relates to a multi-module collaborative flight simulator control panel and method, and solves the problems that an existing system is low in interaction efficiency, subjective in evaluation, lagged in early warning and time-consuming in comment. The system depends on traditional IOS hardware, and is provided with an intelligent voice interaction module which recognizes teacher voice through ASR, generates an instruction through intention recognition and three-level slot completion, and cooperates with double-layer flight stage recognition logic to guarantee interaction accuracy; the flight quality monitoring module operates a rule engine and an enhanced LSTM neural network in parallel, and outputs a comprehensive flight quality score in combination with an adaptive fusion algorithm; the real-time reminding module dynamically adjusts the early warning priority according to the event level and the flight stage, and multi-mode early warning is provided; and the intelligent comment module fuses the multi-source data and generates a personalized structured report according to the priority of the template. According to the invention, intelligent interaction, quantitative evaluation and automatic commenting of training are realized, and the training efficiency and evaluation objectivity are improved.

This invention provides a method for flight potential assessment that integrates flight performance and multimodal data, belonging to the field of flight potential assessment technology. The invention first constructs a standardized simulated flight assessment task framework, decomposes the scenario, and standardizes the steps. Flight parameters and multimodal physiological and psychological data are collected and sliced ​​according to step alignment. Flight quality parameters and physiological and psychological parameters are defined, and a mapping between standardized operation steps and capability elements is established to form capability representations. Flight performance is stratified and scored to obtain completion and quality scores. Flight performance features are constructed and physiological and psychological features are extracted. A quantitative correlation is established using actual flight mission performance as the core criterion, and fusion weights are determined to synthesize capability element scores. Statistical norms are established based on test data from the subject group, and the assessment results are output. This invention improves the structure and objectivity of the assessment.

The embodiment of the invention provides an aircraft tail floor mopping risk assessment method, and relates to the technical field of aviation safety. The method comprises the steps of obtaining flight data of a target flight; extracting risk assessment features from the flight data; the risk assessment features comprise flight state features, operation behavior features and time sequence analysis features; the time sequence analysis feature is used for representing a change trend or a dynamic sequence of one or more flight parameters in a preset flight stage; inputting the risk assessment features into a risk assessment model to obtain a predicted grounding pitch angle output by the risk assessment model; the risk assessment model can represent a linear relation and a non-linear relation between the risk assessment characteristics and the grounding pitch angle; and determining tail floor mopping risk information of the target flight based on the predicted grounding pitch angle. The method and the device can be used in flight quality monitoring and pilot training evaluation processes, and are used for solving the problems of dependence on artificial experience and low evaluation accuracy in the prior art.

The invention discloses an accelerator control method, device and equipment for flight equipment, and the method comprises the steps: determining an accelerator control state at the current moment according to the current accelerator position of an accelerator control part and a preset soft stop point position; and in the soft stop state, according to the collected and determined external applied force, the soft stop distance between the accelerator position and the soft stop point position at the next moment is calculated, and the accelerator control component is controlled to conduct precision according to the soft stop distance. And in the non-soft locking state, compensation force is generated according to the position of the control component, and a driver is assisted to control the accelerator. The interaction condition between an automatic accelerator control system and a driver in an active driving mode is fully considered, and the most appropriate auxiliary accelerator control is provided according to different control states. The driving experience of a driver is effectively improved, the flight quality of the flight equipment is also improved to a certain extent, and good life and health guarantee is provided for members in the flight equipment.