12 results about "Flight envelope" patented technology

The application relates to the technical field of aircraft design, and discloses a continuous variable-camber rigid wing driven by multiple rudders and a control method thereof, wherein the continuous variable-camber rigid wing comprises a wing leading edge section, multiple rigid wing sections, a distributed rudder driving mechanism and a transmission mechanism; the multiple rigid wing sections comprise a first wing section, a second wing section and a third wing section which are sequentially hinged through rotating shafts; the distributed rudder driving mechanism is arranged in the wing leading edge section and is used for independently driving the deflection of each rigid wing section; and the transmission mechanism is connected between the distributed rudder driving mechanism and the corresponding rigid wing section and is used for converting the output motion of the distributed rudder driving mechanism into the deflection motion of the corresponding rigid wing section. According to the application, the rigid wing is segmented, multiple rudders are used for independent driving, an advanced aerodynamic analysis model and a closed-loop feedback control are combined, the wing camber is self-adaptively, continuously and accurately regulated within a full flight envelope, and thus the optimal aerodynamic performance can be maintained at all times.

This invention provides an online monitoring method and system for airborne flight runaway precursors of civil aircraft based on flight test data. The method includes: constructing a set of input flight parameters for identifying airborne flight runaway precursors; acquiring daily operational data and flight test data of the target aircraft model; and extracting physical feature information of airborne flight runaway by referencing the aerodynamic mechanism model and extreme flight envelope boundary of the target aircraft model. Based on the domain adaptation concept, an offline precursor recognition model is constructed that integrates physical feature information embedding, meta-learning, and multi-instance learning. Based on knowledge distillation technology, the recognition capability of the offline precursor recognition model is transferred to a lightweight network constructed from gated recurrent units to generate an online precursor monitoring model, enabling real-time precursor probability calculation and early warning. Finally, an intelligent agent model based on a dual-delay deep deterministic policy gradient algorithm is constructed to verify the effectiveness of the online precursor warning. This invention overcomes the cross-domain data gap and meets the requirements of online lightweight computation.

The application provides a kind of low airspace collaborative management method and system based on digital twinning, comprising: based on the real-time state data of aircraft obtained, analyzing aircraft maneuverability, flight envelope characteristic parameters, characteristic parameters include maximum speed, maximum acceleration, minimum turning radius, utilize kinematics and dynamics model, depict different aircraft movement law;Combined with real-time flight data of aircraft, through digital twinning technology, real-time synchronization aircraft motion trajectory and attitude change in virtual environment, accurately reproduce aircraft dynamic behavior, provide high-fidelity digital model for flight conflict detection, flight path prediction;For aircraft motion characteristic difference, construct multi-level, multi-granularity digital twinning model, digital twinning model includes airspace structure model at macro level, aircraft group behavior model at mesoscopic level and single aircraft dynamic model at micro level.

This invention discloses an active vibration control system and method for tiltrotor aircraft wings, comprising: an actuator assembly consisting of piezoelectric laminated actuators symmetrically arranged within the wing; acceleration sensors, including a wing acceleration sensor located at the outer end of the wing and a fuselage acceleration sensor located in the cockpit; and an adaptive control unit for acquiring sensor signals and outputting control commands. A dual-loop control and flight state tracking strategy is employed: the first control loop implements dynamic characteristic control for the wing-rotor system to suppress transient responses; the second control loop implements steady-state response control for the airframe structure to suppress steady-state harmonic vibrations at the rotor pass frequency and its integer multiples. The flight mode is determined based on the rotor speed and nacelle tilt angle, and the weights of the dual-loop control are dynamically adjusted. This invention achieves adaptive vibration suppression of the tiltrotor aircraft throughout its entire flight envelope, balancing transient and steady-state response control, improving flight quality and extending the lifespan of critical equipment.

The application belongs to the technical field of aero-engine control, and provides a reference rotating speed scheduling method and device for acceleration and deceleration of an aero-engine. The method comprises the following steps: training an agent dynamics model to learn transient state transition relationship through time sequence data (containing state variables and fuel actions); in a simulation environment constructed by the model, taking state variables and environmental parameters as inputs and fuel flow as actions, generating original control outputs through reinforcement learning strategy optimization, and the optimization process is based on a reward function and meets engineering constraints such as turbine inlet temperature, surge margin, rotating speed and fuel change rate; implementing governance processing on the original outputs to ensure that they meet the actuator dynamic limit; and taking the reference rotating speed sequence after the governance as a set point input into an inner loop tracking controller, and only using fuel as an actuator to complete the acceleration and deceleration transition by the controller. The application realizes intelligent rotating speed scheduling which is safe, smooth, constraint-compliant and only relies on a single actuator, and is suitable for the whole flight envelope.

This invention relates to the field of scene generation technology, specifically to an automatic generation method for simulated training scenarios of aviation emergencies based on generative adversarial networks. The method includes: receiving aviation emergency videos input by a target user; generating a target scene image containing a global situational image and local instrument images based on the aviation emergency video; generating emergency semantic text corresponding to the target scene image; constructing a basic terrain model based on basic aviation geographic data; constructing a flight envelope model based on aircraft performance parameters; and initializing an emergency parameter matrix; obtaining a first emergency feature vector and a second emergency feature vector based on meteorological environmental data, the basic terrain model, fault types, and the flight envelope model, combined with the emergency parameter matrix. This invention improves the automation level of training data generation by automatically generating target scene images containing global situational images and local instrument images using aviation emergency videos, meteorological data, geographic data, and aircraft status data.

This invention discloses an atmospheric data system design method and atmospheric data sensing system based on a simplified bird configuration. The method includes: establishing a dimensionless generalized aerodynamic model suitable for the shape of a bird-configured aircraft, and constructing a standard database of surface pressure distribution of the target aircraft within its complete flight envelope; based on the standard database, with the atmospheric parameter calculation accuracy as the optimization objective, and under given engineering constraints, using a global optimization algorithm to automatically optimize the number and spatial location of pressure gauges; based on the optimal layout of the pressure gauges, implementing a hybrid-driven atmospheric parameter calculation algorithm, which first estimates initial values ​​through a data-driven approach, and then iteratively optimizes under the constraints of the dimensionless generalized aerodynamic model, outputting the calculation results; during the calculation process, integrating a fault diagnosis and fault tolerance mechanism based on reverse verification of machine learning models and physical models to achieve online identification of faulty sensors and system reconfiguration.

The application discloses a kind of high-efficiency high-precision calculation method for flight envelope fluid-solid temperature field, belong to heat transfer field.Method is:1) for the transition stage in flight envelope, fluid-solid coupling temperature field is obtained by using conjugate heat transfer calculation of transition stage;2) after the completion of conjugate heat transfer calculation of transition stage in flight envelope, fluid-solid decoupling is extracted;3) for the steady-state stage in flight envelope, the efficient calculation of finite element reduction is carried out to solid temperature field, and the full-time-domain solid temperature field of stable stage is obtained;4) the solid temperature of last time is extracted, and the fluid-solid temperature field is re-coupled, and the parameter is used as the initial field of fluid-solid coupling temperature field calculation of next transition stage;5) for the second transition stage, conjugate heat transfer calculation of fluid-solid coupling temperature field is carried out again, and 1) is repeated;By analogy, the fluid-solid transient temperature field calculation of whole flight envelope is completed.The application can quickly obtain the temperature field of transient process, reduce the consumption of calculation resources while ensuring the calculation precision, and greatly improve the calculation efficiency.

The application discloses an aero-engine thrust estimation method based on physical mechanism and multi-task learning fusion, and belongs to the technical field of aero-engine modeling and state estimation. The application proposes a physical information guided multi-task long short-term memory network architecture. Firstly, singular value elimination based on physical effective domain is performed on full flight envelope sensor data to guarantee time sequence continuity; secondly, a shared time sequence feature extraction layer and a multi-task prediction head are constructed to synchronously output net thrust, fuel consumption rate and rotor transient power difference; finally, a double physical punishment term is constructed based on macroscopic energy conservation and microscopic rotor dynamics equation, and a maximum value normalization relative residual mechanism is introduced to calculate a joint loss function for network optimization. The application guarantees extremely high thrust reconstruction precision, gives a black box model strict thermodynamic and dynamic physical self-consistency, and provides a high-reliability virtual sensor feedback for engine direct thrust control.

The application discloses a kind of based on energy flow's new energy aircraft comprehensive thermal management system performance evaluation method and system, and relates to thermal field. Including: establishing loss analysis model;Determine minimum loss, compare with actual loss, obtain thermal management system external characteristic index;Determine the design matching degree of all electric energy equipment of each cooling branch, adjust the selection of all electric energy equipment of each branch in combination with energy flow coupling value index;After unit value processing to take-off, climb and cruise condition, classification is carried out, energy flow operating value index is established, the operation of the determined thermal management architecture under the whole flight envelope is evaluated, and the final thermal management selection scheme is determined.The application is used to improve the accuracy of aircraft thermal management system conceptual design stage architecture trade-off, and can also be used for effective monitoring of the operating state of thermal management system under flight condition.

This application discloses a method for identifying aerodynamic parameters of a tail-saddle unmanned aerial vehicle (UAV) and applying it to a data processing device. The method includes: obtaining a propeller thrust coefficient function; obtaining steady-state flight data collected by airborne sensors when the tail-saddle UAV is in steady-state flight at different pitch and sideslip angles; calculating propeller thrust based on the steady-state flight data and the propeller thrust coefficient function; calculating aerodynamic forces by combining dynamic equations and decomposing them into lift, drag, and sideslip forces; calculating aerodynamic coefficients at different angles of attack and sideslip angles; and obtaining the aerodynamic coefficient function based on a polynomial model and least squares fitting. This application does not require specialized equipment such as wind tunnels, but only relies on low-cost airborne sensors to complete aerodynamic identification covering the entire flight envelope in a real flight environment, reducing the cost of engineering applications.

The invention relates to a method for the automated recovery of an aircraft (100) to a normal flight envelope, after the detection of one or more flight parameters or one or more flight conditions of said aircraft (100) outside a flight envelope peripheral to the normal flight envelope, and based on suitable information from sensors and / or one or more computers of the aircraft, configured to deliver information representative of the flight conditions of said aircraft, by operating an automated control of flight controls. Fig. 3