234 results about "Flight dynamics" patented technology

The invention provides the application and design for embedding a bionic honeycomb-shaped active safety escape capsule into an aircraft. The application and design comprise the following related technologies including redesign of a main machine body of the aircraft for the embedded type bionic honeycomb-shaped active safety escape capsule, internal space layout design of the main machine body of the aircraft for the embedded type bionic honeycomb-shaped active safety escape capsule, design of an escape capsule embedded type shell and the shape, analysis of influences of the embedded escape capsule on the overall load of the aircraft, integral analysis and determination of flight aerodynamic load data, selection of an escape capsule material, escape capsule ejection mode analysis and ejection device design, logic design of launch motion of the escape capsule, internal space structure analysis of the escape capsule; active safety design of space landing of the escape capsule, description of flight dynamics influences of the escape capsule on the aircraft during and after separation, and design of an active help seeking system of the escape capsule. In this way, the application and design for researching and manufacturing the bionic honeycomb-shaped active safety escape capsule embedded into the aircraft are achieved.

In a flight simulator program, a flight dynamics editing module enables the user to input parameters for modifying an existing aircraft design or creating an aircraft design. Starting with the type and purpose of aircraft, the user is able to specify parameters defining the configuration, and various other aspects of the aircraft, including the number and type of engines, properties of the flight controls, type of landing gear, etc. Once the user has input the parameters, an aerodynamic coefficients generator module included with the flight simulation program determines aerodynamic coefficients for the aircraft design, using classical formulas and determining the coefficients in an appropriate order. The aerodynamic coefficients and certain parameters input by the user are then output as two flight model data files, in a format usable by the flight simulator program, so that the user can evaluate the aircraft design by flying it within the simulation.

The invention relates to a flight dynamic information data integrator and a processing method, belonging to the field of civil aviation technology. The flight dynamic information data integrator comprises a power-supply system, a microprocessor, an input control display unit, a communication unit, a data receiving unit, a data processing unit and a data storage unit; wherein, the data receiving unit is internally provided with a receiving process program module which can realize real-time physical reception of the transmitted data and executes data decompression, data source feature recognition and classification treatment to realize data interchange and share. The processing method of the integrator comprises dynamic information of production departments such as air traffic control (ATC), airports and airline companies are integrated into a platform database for supplying data service; standard flight information is formed by integrating the received related data of the flights and then stored in a data center; meanwhile, the integrative process is monitored, and the integration results are analyzed. The invention can realize data interchange and share, and provides complete, accurate and timely data service.

An apparatus and method to control the attitude, heading course, altitude and position of a lighter-than-air airship. In one aspect, a hybrid airship including a lighter-than-air gas filled envelope, a thrust vectored front propulsion system, a back rotary wing system and a onboard control system. In one aspect, at least one system to modify the on board mass, a system to control the internal pressure, at least a power battery pack and a radio link communications for unmanned piloting. Said hybrid airship has improved maneuverability, safely flights and is capable to fly as Lighter-than-air airship and Heavy-than-air aircraft.

The invention discloses a test system and control method for a full state blowing experiment of a tilting rotor, and the test system and the control method comprise an unmanned tilting rotor platform,a power system, a transmission system, a data calibration system, a data link system, a ground test and control system, a control system and a control method. The test system and control method for the full state blowing experiment of the tilting rotorhave the ability to calibrate, test and control the integrated blowing experiment of the tilting rotor blowing model. The ground test and control system communicates commands with an on-board control system through a wireless data link to complete the full state blowing experiment under the matching of different blowing speeds and nacelle angles, which is particularly suitable for studying the interference relation between the tail flow and the wing / fuselage in the dynamic state of the rotor and to provide a reliable parameter basis for analyzing the aerodynamic interference mechanism of the tilting rotor and optimizing the nonlinear flight dynamics modeling of the tilting rotor. The integrated control system has the advantages of simplewiring, high experimental efficiency and perfect test state, and effectively improves the efficiency of the full state blowing experiment of the tilting rotor.

An aircraft has wings configured to twist during flight. Inboard and outboard propulsion devices, such as turbofans or other propulsors, are connected to each wing, and are spaced along the wing span. A flight controller independently controls thrust of the inboard and outboard propulsion devices to significantly change flight dynamics, including changing thrust of outboard propulsion devices to twist the wing, and to differentially apply thrust on each wing to change yaw and other aspects of the aircraft during various stages of a flight mission. One or more generators can be positioned upon the wing to provide power for propulsion devices on the same wing, and on an opposite wing.

The invention discloses a dynamic scheduling method for multi-runway flight getting in and out. The method comprises the following steps that flight delay cost is analyzed, and a flight delay cost minimization objective function for multi-runway flight getting in and out scheduling is provided; theoretic delay time is calculated, and flight delay time of different aircraft types is converted into delay time of unit delay cost; fairness of multi-runway scheduling is analyzed, and the objective function considering the fair factor is built; ordinary constrain conditions of multi-runway flight dynamic scheduling are provided; the multi-runway flight scheduling constrain conditions considering flight delay are designed; the dynamic scheduling problem of multi-runway flight getting in and out is solved by adopting the genetic algorithm, dynamic scheduling of multi-runway flight getting in and out is achieved, and the purposes of improving the runway using rate and reducing the flight delay cost are achieved. According to the method, influence on multi-runway scheduling caused by flight delay is sufficiently considered, and the purposes of improving the runway using rate and reducing the flight delay cost are achieved.

The invention relates to an initiative claim settlement service system for the flight delay insurance. The initiative claim settlement service system comprises a service processing core module, a product management module, an insurance policy data management module, a flight dynamic database module, a user information management module, a user information collecting addition module and a payment processing module. The initiative claim settlement service system is connected with an external marketing system, an external flight dynamic database server and a third-party payment platform through ports, so that when the dynamic states of a flight guaranteed by the flight delay insurance change, relevant information can be rapidly and accurately obtained, whether insurance policies are given out or not and whether claim settlement conditions are met or not can be automatically judged, settlement can be rapidly carried out on the insurance policies meeting the claim settlement conditions, and complex procedures for automatically searching delay proofs by travelers and inconvenience caused by automatically searching the delay proofs by the travelers are saved; in other words, the insurance claim settlement service cost is reduced, and the service time length is shortened; meanwhile, the user perception and the user satisfaction are improved, and the healthy development of the market of the flight delay insurance is facilitated.

A hybrid-type satellite simulation system and a method thereof are disclosed. The system includes: a satellite modeling unit including a satellite model and a software model having flight dynamics and space environment data; a satellite operation unit for generating a telecommand, transmitting the telecommand to the satellite simulation system, receiving simulation result as a telemetry, analyzing the simulation result and displaying the analyzed result; a simulator kernel for managing and controlling the satellite simulation system; a TCP / IP interface processing unit for performing an interface function of TCP / IP level between the simulator kernel and a satellite onboard computer; an onboard computer interface processing unit for performing an interface function between the satellite onboard computer and the TCP / IP interface processing unit; and a satellite onboard computer including flight software for controlling a satellite.

The invention discloses an estimation method of an atmosphere angle of attack and an angle of sideslip in a high-angle-of-attack flight status. Under the premise that the structure of an aircraft is not changed and additional measuring devices and hardware devices are not added, the parameters output by the existing onboard strapdown inertial navigation system, a GPS (Global Position System) system, a flight control system and a fuel measuring system are fully used for resolving the angular acceleration, the rotational inertia, the product of inertia, the coefficient of a moment equation set and the total mass of the aircraft; based on a flight dynamics model, by establishing an extended Kalman filter, and integrating the processes of resolving the flight dynamics model and the status estimation together, accurate estimation of the current angle of attack, the angle of sideslip and the true airspeed is realized, and then the current air speed and the change rate of the air speed are resolved and input into the extended Kalman filter as the feedback information so as to finish the real-time accurate estimation of the angle of attack and the angle of sideslip of next time; the real-time accurate estimation of the angle of attack and the angle of sideslip is realized by a recursive resolving mode, measurement range and measurement precision of an atmosphere data system are improved, and adaptability to complex flight environment is also improved.

The invention provides a flight dynamic information display method, system and equipment and a storage medium. The method comprises the steps that flight information is acquired; a flight display interface with a flight information area is provided, and a take-off information bar, a stopping information bar and an arrival information bar are displayed in the flight information area along the timeaxis in sequence; current flight information is acquired, and flight information which is displayed in the flight information area is updated; whether or not a current flight has a new event of landing preparation or course reversal is judged. According to the flight dynamic information display method, based on the time dimension, all flight states of take-off, arrival, stopping, landing preparation and course reversal in the process are arrayed in sequence, an airport gate, a check counter, a baggage turntable, an exit and predicted take-off / arrival time are integrated, and according to the flying progress, a user can conduct quickly position and focus on the flight dynamic information of an airport according to a used scene; stopping, landing preparation and course reversal data is supplemented, more sufficient data information is provided on a complex flight scene, and the method helps the user to successfully complete travel.

A method and apparatus is provided that provides accurate navigation for spin-stabilized projectiles in a GPS-denied environment using low cost measurement sensors, by application of flight dynamics in real-time state estimation algorithms.

The invention discloses a flight dynamic entity information updating method and a system thereof; wherein, the method comprises: searching the correspondent flight number in the flight plan information in the flight dynamic entity according to the flight number mark in the Aeronautical Fixed Telecommunications Network (AFTN) message, determining the flight dynamic entity corresponding to the flight number is the flight dynamic entity to be updated, searching the correspondent taking-off airport and / or landing airport in the flight plan information according to the taking-off airport and / or landing airport information in the AFTN message and updating the leg information in the FPL information or the flight actual information of the flight dynamic entity to be updated corresponding to the taking-off airport and / or landing airport information of the flight plan information. The invention can precisely associate the flight dynamic entity to be updated and can precisely position the specific leg in the flight dynamic entity to be updated, thus realizing correctly and effectively updating the flight dynamic entity information.

The invention discloses an air-ground amphibious intelligent vehicle, aiming at overcoming the problem that in the prior art, the vehicle only can run on the ground. The intelligent vehicle consists of a lower ground intelligent vehicle, a middle control system and an upper flight dynamic system, wherein the flight dynamic system comprises four sets of flight dynamic devices with same structures, a connecting rod fixing disc (6), a connecting rod fixing block (7), a carbon fiber connecting rod (17), a motor fixing block (18) and a motor fixing frame (19). The flight dynamic device comprises a propeller (1), a bullet propeller clamp (2), a brushless motor (3) and an electronic speed regulator (4). The four sets of flight dynamic devices are arranged symmetrically by the carbon fiber connecting rod (17) and the like relative to the centers of gravity of the air-ground amphibious intelligent vehicle. The flight dynamic system and a PCB (12) in the middle control system are connected into a whole by studs (15) which are distributed uniformly, and the PCB (12) and a ground intelligent vehicle therebelow are connected into a whole by the studs (15) which are distributed uniformly.

The invention discloses a dynamics modeling and analyzing method for an aerospace vehicle and belongs to the technical field of flight dynamics modeling and simulation analysis of aircrafts. According to the dynamics modeling and analyzing method, the variable-span and variable-sweepback aerospace vehicle is simplified and is composed of a fuselage, a left wing inner side, a left wing outer side, a right wing inner side and a right wing outer side, wherein the fuselage, the left wing inner side, the left wing outer side, the right wing inner side and the right wing outer side are independent rigid bodies. The deformation movement of wings relative to the fuselage is represented through a set of constraint equations, so that the freedom degree of a dynamics model is reduced; the aerodynamic force exerted on the aerospace vehicle is simplified to act on the fuselage only, and the dynamics model is established through the Kane method; related items derived from the deformation movement are extracted from the dynamics model to form additional force and additional force moment so that the influence on the dynamics characteristics of the aerospace vehicle by the inertia force and inertia moment caused by the deformation moment can be represented. The dynamics model of the aerospace vehicle is simplified through the dynamics modeling and analyzing method, and integral items and derivation terms of the inertia moment do not appear in the equations. In this way, dynamics modeling and simulating can be easily performed on the aerospace vehicle, and meanwhile accuracy is high.

The invention discloses a landing point forecasting system for space launch rocket. According to the invention, the landing point forecasting system is connected to a spaceflight test and control network. Rocket debris and rocket flight position and speed information are extracted from data provided by a radar data processing system. Rocket debris separation time is extracted according to information provided by a remote measurement data processing system. Initial separation point data is obtained through fitting simulation. A rocket debris flight dynamics model is established through combination of flight environment mathematics modeling and aerodynamic characteristics analysis. Through landing point influence factor analysis, landing point accurate forecasting is performed, so that a landing area search range is reduced and rocket debris recycling efficiency is improved.

The invention discloses a real-time dynamic flight path planning method based on linear programming. The real-time dynamic flight path planning method based on linear programming comprises the following steps: obtaining a coordinate point set included by obstacle boundary coordinate points according to morphological characteristic coordinates of an obstacle in a navigation coordinate system; obtaining a dynamic parameter constraint set of an aircraft according to an established discrete time model; and obtaining a flight path coordinate point set in the navigation coordinate system according to an optimal flight path target function on the basis of the coordinate point set included by the obstacle boundary coordinate points and the flight dynamic parameter constraint set. By virtue of the real-time dynamic flight path planning method based on linear programming, the technical problem in the prior art that the flight path cannot be automatically planned is solved; furthermore, the technical effect of automatically planning the flight path is achieved.

A method for controlling a path of a rotary-wing drone wherein said method comprises:Establishing a first-order temporal relation between flight control parameters and flight dynamics for said rotary-wing drone comprising:An Explicit Discrete Time-Variant State-Space Representation of a translation control of said rotary-wing drone;An Explicit Discrete Time-Variant State-Space Representation of a course control of said rotary-wing drone;Controlling the path of said rotary-wing drone by:Estimating a course of said rotary-wing drone on the basis of said Explicit Discrete Time-Variant State-Space Representation of a course control of said rotary-wing drone;Estimating a position of said rotary-wing drone on the basis of said Explicit Discrete Time-Variant State-Space Representation of a translation control of said rotary-wing drone;said steps of estimating being performed independently.

The invention relates to a small light unmanned aerial vehicle semi-physical simulation system and a simulation method, which relates to the field of testing technologies of an unmanned aerial vehicleflight control system and solves a problem that the existing unmanned aerial vehicle simulation system cannot authentically and effectively reflect the practical function of inertial navigation in the flight control system, cannot effectively reflect the dynamic performance of an actuator and cannot perform quantitative analysis and online parameter adjustment and the like on a simulation test result. The small light unmanned aerial vehicle semi-physical simulation system comprises a simulation upper computer, a real-time simulation machine, a three-axis simulation turntable upper computer, athree-axis simulation turntable, a rudder angle acquisition unit and a simulation vision unit, wherein the real-time simulation machine comprises a PXI controller and a communication and data acquisition function module, and the PXI controller comprises a PharLap real-time operating system, an unmanned aerial vehicle flight dynamic model and a CustomDevice driver. The small light unmanned aerialvehicle semi-physical simulation system performs simulation on an attitude angle in the simulation process of the unmanned aerial vehicle flight dynamic model by using the three-axis simulation turntable, provides an unmanned aerial vehicle attitude change testing environment under a ground environment, performs a hardware-in-loop testing on the physical inertial navigation system and improves thefidelity of the simulation.

The invention discloses a non-linear load calculation method of a flying wing unmanned aerial vehicle, which comprises the steps of solving flight attitude parameters. A multi-degree-of-freedom coupling flight dynamics simulation model is adopted for aerodynamic and dynamic flight calculation of the aircraft based on aerodynamic non-linear coefficients in solving the flight attitude parameters, Atthe same time, an objective function is established to optimize the flight attitude parameters which do not meet the requirements by using the optimization algorithm, and the output flight attitude parameters are used as the input of the nonlinear concentrated load calculation. As for that aerodynamic non-linearity characteristic of the whole aircraft of the unmanned aerial vehicle (UAV), the invention adopt a flight dynamics simulation model of multi-degree-of-freedom coupling to solve the flight attitude parameters of three-axis couple non-linearity on the basis of the aerodynamic non-linearity coefficient; Thus, the nonlinear load calculation of flying-wing UAV is realized, which has good practicability.

The invention provides a simulation method of multi-engine helicopter power system dynamic matching. A device according to the method provided by the invention includes a multi-engine helicopter flight simulator and a simulation control program of the multi-engine helicopter power system dynamic matching; the simulation control program of the multi-engine helicopter power system dynamic matching is installed in a main calculation computer of the multi-engine helicopter flight simulator; communication between subsystems of the multi-engine helicopter flight simulator is performed through the Ethernet, and data exchange can be completed through adopting the TCP / IP protocol; coordinated work situations of multiple engines can be automatically matched and calculated, power matching output simulation of the multiple engines in stagnation, cool rotation, starting and spatial flight can be realized, and the fidelity of helicopter simulation can be improved; flight dynamics and kinematics mathematical models which are generally applied to helicopters are selected, and simulation of dynamic matching of the power systems of helicopters in different models can be realized through establishing performance data forms of the power systems of the helicopter in different models and design parameters of the helicopter.

The invention relates to a mobile flight dynamic notifying system based on an iPhone mobile platform. The system consists of an iPhone client system and a service end system. The client system comprises an iPhone client application module. The service end system comprises a journey extracting module, a message subscribing module, a message parsing module and a message pushing module.

The invention discloses a solving method of a tilt transient process of a tilt rotorcraft. The method comprises the steps of 1, building a flight dynamics model applicable to the calculation of the tilt transient process of the tilt rotorcraft; 2, building an appropriate boundary condition, path constraint and performance index according to different flight missions, and transforming the tilt transient process of the tilt rotorcraft into a nonlinear dynamic optimal control problem; 3, designing a numerical optimization algorithm to solve the nonlinear dynamic optimal control problem in the step 2, and obtaining the tilt transient process of the tilt rotorcraft. The solving method of the tilt transient process of the tilt rotorcraft is high in computational efficiency, fast in convergence and high in computed result reliability, and can be used for researching the optimal tilt transient process of the tilt rotorcraft.

The invention discloses a multi-source heterogeneous flight accident track data fusion method, relates to a flight accident data processing method and belongs to the technical field of data processing. The multi-source heterogeneous flight accident track data fusion method comprises the steps of firstly performing unified time reference correction on various data sources, then recognizing and eliminating abnormal flight data by using a wavelet algorithm, then performing data supplement on sparse flight parameter data by using a least square algorithm and flight dynamics model data, and finally performing heterogeneous fusion on a variety of heterogeneous flight data based on probabilistic graphical model method so as to generate a final flight accident track. Under the unified probabilistic framework, comprehensive data fusion is performed on the flight accident track by using different configurations and different sources of flight data and flight dynamics models of the corresponding aircraft models, and the estimation accuracy and the update frequency of the flight accident track are improved.

The invention discloses an oil-drive variable-pitch quad-rotor unmanned aerial vehicle which comprises a power-transmission system, a rotor-operation system and a rack system. Both the rotor-operation system and the power-transmission system are fixed to the rack system. The oil-drive variable-pitch quad-rotor unmanned aerial vehicle mainly solves the problems that a conventional electric multi-rotor vehicle is poor in wind resistance and the like, the load is small, and the flight time is short and the problems that purchasing, using and maintaining cost is high and the use and maintenance technical doorsill is high due to complexity of the mechanical structure, the structural dynamic characteristic, the flight dynamic characteristic, the aerodynamic characteristic and a flight control system of a conventional helicopter.

Systems and methods are contemplated for favorably improving flight dynamics of aircraft, including enhanced aerodynamic braking and improved flight maneuverability. Air braking systems selectively position a first set of blades at a negative thrust pitch to product a net negative thrust across first and second sets of blades, while balancing torque of the drive shafts to zero. First and second sets of IBC blades can be driven by the same shaft or torque-linked shafts. Flight maneuver systems operate a powerplant at a high power mode, and dissipate the energy from the high power output by positioning a first set of IBC blades at a low efficiency pitch while maintaining constant thrust. As increased or rapid flight maneuverability is required, the first set of blades is positioned toward a high efficiency pitch to instantly increase thrust to the aircraft without requiring a related increase in energy output from the powerplant.

The invention discloses a compound identification method of an unmanned helicopter flight dynamical model and belongs to the field of unmanned helicopter dynamical modeling, and the method is characterized in that an unmanned helicopter, a flight control computer, a sensor group, an airborne data broadcasting station, a ground data broadcasting station, a ground station, a remote controlled transmitter and a remote controlled receiver are utilized, wherein a remote controlled command of a ground pilot is in charge of stimulating the unmanned helicopter; an automatic control command of the flight control computer is used for maintaining the unmanned helicopter at the predetermined flight speed, and ensuring the flight safety; and the remote controlled command and the automatic control command are combined by the flight control computer to obtain a steering engine command, so as to manipulate the unmanned helicopter to finish an identification test. In the compound identification methodprovided by the invention, the remote controlled command of the ground pilot and the automatic control command of the flight control computer are simultaneously introduced, so as to ensure the remotecontrolled command and the automatic control command to be mutually matched, thus the flight dynamical model of the unmanned helicopter can be accurately and safely identified.

The invention provides a scheduled flight dynamic intelligence real-time broadcasting method, which comprises the following steps of: (1) carrying out grammar and semantic validation and message decoding processing on messages to obtain flight plan data; (2) using the flight plan data to newly build the scheduled flight plan or to interfere the flight dynamic state of the scheduled flight, generating various kinds of character reminding information at the same time, and displaying the character reminding information; (3) during the display, using a basic sound library and an industrial field library to synthesize the character reminding information into voice in real time and performing the broadcasting. The method has the advantages that the real-time visual character reminding and synchronous voice broadcasting can be realized on various scheduled flight dynamic states, newly built scheduled flight plans, message sending reminding and message receiving reminding; the workload of a controller can be further reduced; the work efficiency is improved; the fault operations such as wrong operation, forgotten operation and missed operation due to busy work and work fatigue of the controller can be reduced; and better popularization values are realized.

The invention discloses a 4D trajectory displaying method based on World Wind. The 4D trajectory displaying method based on World Wind comprises the following steps of disposing flight dynamic data of an aircraft; converting projection coordinates of the aircraft so as to obtain the projection position; introducing control airspace GIS data so as to obtain an airspace background; combining the projection position of the aircraft and the airspace background so as to obtain the projection position of the aircraft with the combination of the airspace background; and displaying the flight dynamic data of the aircraft in the form of comprehensive information and the like. According to the method disclosed by the invention, the three-dimensional airspace background of a display subsystem is rendered by utilizing a World Wind platform; the dynamic information of the aircraft is displayed by adopting a transparent target layer, and the position of the aircraft at the target layer is consistent with the three-dimensional airspace background by adopting a space conversion mode, so that relatively intuitive airspace dynamic information can be provided for managers, and the effectiveness and reliability of air traffic control can be improved.

The invention discloses a radar track and flight information comprehensive display system, which communicates with a EUROCAT-X system and a flight information system, and comprises a data on demand (DOD) data preprocessing end, a server and a client. The radar track and flight information comprehensive display system acquires various track data of an airplane from the EUROCAT-X system, acquires flight plans and flight dynamic information from the conventional flight and message system, and corresponds flights in the two sets of systems by related correspondence and association methods to realize reference display.