43 results about "Flight (process)" patented technology

The invention discloses an online prediction method for stagnation point heat flow in the flight process of an aircraft. The method comprises the following steps: 1) before actual flight, carrying out one-dimensional heat flow identification through a sequence function method by utilizing temperature data of each measuring point in a structure, and training a neural network three-dimensional correction model in combination with actually measured heat flow; 2) simplifying the Fay-Riddell stationary point heat flow engineering estimation formula, taking the actually measured heat flow and the incoming flow condition of a given trajectory as an input sequence, and correcting various coefficients in the simplified formula through a least square method to obtain a preliminary stationary point heat flow prediction formula; and 3) during actual flight, taking the stationary point identification heat flow updated in real time as new heat flow data, and performing real-time fitting through a least square method to obtain a prediction formula updated in real time to predict a stationary point heat flow value in future 10 seconds. The heat flow error indicated by the method is within 15%, and the invention comprises the rapidity of engineering estimation, so that real-time and accurate heat flow indication in the flight process can be realized.

The invention discloses a 360-degree omni-directional overload flight simulator. The center of gravity of a trainee is in the front of the center of the gravity of an airplane like in the real flight process. The 360-degree omni-directional overload flight simulator comprises a vertical lifting system, a first movement system, a second movement system and a flight cockpit system, wherein an intelligent control system has control over a front-and-rear pitching motor and a left-and-right rotating motor, the center of gravity of the trainee is in the front of the center of gravity of the airplane like in the real flight process, and the pilot can feel transverse movement and rotation at the same time; the intelligent control system converts various rotation overload motions of the vision into electric signals, and controls a stepping motor to synchronously move in the X direction, the Y direction and the Z direction. When the 360-degree omni-directional overload flight simulator is used, the training cost can be reduced, the training effect can be ensured, and the airplane driving training time of trainees such as trainee pilots can be shortened.

The invention provides a flight verification auxiliary system based on a flat plate, and belongs to the field of flight verification. The system comprises a verification platform and auxiliary systemdata synchronization module, an equipment database management editing module, a verification plan making module, a verification result management module, a verification log management module and a calculation auxiliary module which are arranged on mobile equipment. A verification platform and an auxiliary system data synchronization module communicate with the flight verification platform throughTCP / IP to realize batch file transmission between the flight verification platform and the auxiliary system;. A flight verification platform is provided with a data synchronization module. An auxiliary system on a portable tablet personal computer is used for assisting a checker in completing flight checking work, the workload of the flight checker in the flight process is greatly reduced, the probability of misoperation is reduced, and the flight checking efficiency is improved.

A multi-type fuze flight process parameter measurement device, the device includes the following modules: fuze characteristic acquisition module, ignition signal acquisition module, accelerometer and signal acquisition module, rotational speed information acquisition module, data processing module, data recording module, power supply module and communication modules. The invention mainly measures the parameters of the fuze flight process, which involves relevant electrical characteristics and environmental characteristics, provides data support for analyzing the specific conditions of the fuze during flight, guides the development and production of the fuze, optimizes the dynamic test process of the fuze, and improves the measurement accuracy , which greatly shortens the design cycle of the fuze, and its structure and internal assembly can be adapted to multiple types of fuzes, such as mortars, shoulder-fired rockets, and grenades.

The invention relates to a flight path-based aviation ad hoc network clustering method and a computer readable storage medium, and belongs to the technical field of aviation communication. The clustering method comprises the following steps: 1) pre-storing geographical cluster information corresponding to a corresponding geographical position on an aircraft flight path; wherein the geographical cluster information comprises a geographical cluster identifier and an intra-cluster position; 2) in the flight process of the aircraft, acquiring the current geographical position of the aircraft in real time; 3) searching matched geographical cluster information according to the current geographical position; and 4) updating own geographical cluster information according to the geographical cluster information matched in the step 3). According to the invention, the geographical cluster information corresponding to the corresponding geographical position on the flight path of the aircraft is stored before the aircraft flies. The updating of the geographical cluster information can be realized only by acquiring the current geographical position in the flight process of the aircraft, so thatthe problems of poor communication real-time performance and low efficiency caused by real-time calculation of clustering related information in the flight process of the aircraft are avoided.

The present invention discloses a multi-sensor information fusion-based airplane journey scoring method and system, wherein the multi-sensor information fusion-based airplane journey scoring method comprises the following steps of S1 obtaining various types of sensor information during the flight process of an airplane, and classifying the sensor information according to the information types; S2 according to the classification types, obtaining the transfinite events corresponding to each type of sensor information separately, and according to the transfinite events, carrying out the normalization calculation on each type of sensor information to obtain the airplane journey score of each type of sensor information; S3 carrying out weighted fusion on the airplane journey scores of various types of sensor information to obtain the final airplane journey score. By the multi-sensor information fusion, the method can fully utilize the advantages of multiple sensors to make up the insufficiency of the single sensor, and enables the comprehensiveness and the accuracy of the information to be improved.

The invention discloses a pilot operation quality assessment method based on curve fitting. The method comprises the steps that S1, influence factors for judging whether a flight is affected or not are determined according to analysis on historical flight data; S2, spare control points and dense control points in the flying process are acquired for each type of influence factors, curve fitting is performed, and an optimal flight curve for each type of influence factors is obtained; S3, a flight error is calculated according to the difference between an actual flight curve and each optimal flight curve, and pilot operation quality is assessed according to the flight errors of all the influence factors. Through the method, the influence of environmental factors on the actual flight curve of a plane in the flying process can be fully considered, abnormal values can be fully considered during curve fitting, and therefore pilot operation quality can be effectively assessed.

The invention provides a dynamic simulation test method for a power system. Step 1, parameters of a trajectory of the power system to be verified and flight test conditions are obtained; step 2, a throat of a direct connection test bed is designed according to a range of flight Mach numbers; step 3, a simulated total temperature Ttm is given according to a state of flight and heating capacity of the direct connection test bed; step 4, an iso-simulated total temperature curve under the simulated total temperature Ttm is determined according to the determined simulated total temperature Ttm anda simulated total temperature formula; and step 5, according to the determined total temperature Ttm, test temperature of the direct connection test bed is adjusted, and the obtained iso-simulated total temperature curve is used to carry out a dynamic simulation test. The dynamic simulation test method for a power system of the invention can quantitatively simulate a flight process of an aircraftand evaluate dynamic working characteristics of an engine system, simplifies steps of the direct connection test bed during the test, shortens a test period, and reduces the test cost.

The invention relates to a free flight analog simulation platform. The free flight analog simulation platform comprises an analog setting system, a data information system, a permission setting system, and an actual scene analog system. The implementation method of the platform includes the steps that first, a flight rule is designed, wherein in the actual scene analog module, an airplane flight process model is built on the basis of the core through that the distance is equal to the number generated when the speed is multiplied by the time; a conflict avoidance rule is designed, wherein in the actual scene analog module, the courses of airplanes are obtained through an equation of motion of the airplanes, the course included angle is calculated, and which encounter condition happens to the airplanes is judged so that corresponding avoidance measures can be taken. The free flight analog simulation platform is mainly used for the teams researching free flight to collect data and provides relevant data for free flight analog, analog logs are output, the analog data can be visually displayed for users, the users can conveniently calculate collision risk in free flight so that factors for influencing safety of free flight can be researched, and technical support is provided for achieving free flight.

The invention discloses a multichannel coordinated loading system flight by flight spectrum experiment method which is technically characterized in that (1), during flight system simulation, the occurrence probability of an A working condition during first flight is e, wherein the e is larger than 0 and smaller than 1; (2), the occurrence probability of the A working condition during first flightis the e, because the e is smaller than 1, the A working condition is not simulated in the system for the first time, and this time the cumulative probability is e; (3), because the A working condition is not simulated in the first flight system, the probability of the A working condition during second flight is the sum e+e of the last cumulative probability and the original probability, namely 2*e; (4), the probability of the A working condition during third flight is the sum of the second cumulative probability and the original probability of the A working condition; (5), during the Nth flight, the total time of the A working conditions simulated before is an integer taken from N*e, the alpha is set as the time of the A working conditions, and the beta is decimal part of the N*e, that isalpha / N is approximately equal to the e. According to the multichannel coordinated loading system flight by flight spectrum experiment method, all working conditions of an aircraft in the flight process are fully simulated.

The invention discloses a flight test flow state distinguishing method based on friction resistance change rules. The method comprises the following steps: (1) calculating the axial force coefficientCA_identification of an aircraft corresponding to each flight moment in the whole flight process of the aircraft by adopting an aerodynamic identification method; (2) calculating the wave resistance Cap_calculation corresponding to each flight moment in the whole flight process of the aircraft according to an aerodynamic data table of the aircraft; (3) performing subtraction on the axial force coefficient CA_identification of the aircraft corresponding to each flight moment in the whole flight process of the aircraft and the wave resistance Cap_calculation, so as to obtain a friction resistance Caf_identification changing curve for the whole flight process of the aircraft; (4) dividing a friction resistance curve into two sections by taking the minimum point in the friction resistance curve as a boundary, dividing each section of the friction resistance curve into a plurality of sub-intervals, and calculating the friction resistance variation delta Caf_identification in each sub-interval; and (5) finding out the biggest influence factor of the delta Caf_identification, and if the flow state change causes the dominance of the friction resistance variation delta Caf_tran to the deltaCaf_identification, judging that the surface flow state of the aircraft changes so that transition from laminar flow to turbulent flow occurs.

The invention provides an aircraft flight safety control method and system and a server. The method comprises steps that a first safety threshold and a second safety threshold are set for at least oneflight parameter in the flight process of an aircraft; at least one flight parameter value of the aircraft in the flight process is acquired; safe operation is carried out based on the at least one flight parameter value, when the at least one flight parameter value is between the first safety threshold and the second safety threshold or equal to the second safety threshold, a blow-up system of the aircraft is released from insurance; when the at least one flight parameter value is greater than the second safety threshold, the blow-up system is made to blow up the aircraft. The method is advantaged in that through setting the safety range for the flight parameters of the aircraft in the flight process, the pipeline for guaranteeing the safe flight of the aircraft can be formed, so faultsof the flight process of the aircraft can be better handled and dealt with, and damage to ground facilities and personnel can be avoided.

According to the various aspects of multiple embodiments, it provides equipment and methods from multiple independent systems (such as flight management systems and ground air traffic control) in the entire flight history.During the flight process, many trajectory differences (such as flying intentions, controllers interference, or actual flights caused by predictive errors and predictive trajectories) will form interference. Therefore, dynamic monitoring of these deviations and controlling a dynamic synchronizationcycle.A dynamic trajectory synchronization algorithm attempts to return each system in these systems to the balance whenever a disturbance causes imbalance.The disturbances include the deviation of the atmospheric conditions and the predictive atmospheric conditions, the changes in pilot preferences, and a variety of unpredictable events that require the movement of the controller (such as the needs of the interval with other aircraft or the changes in flow weather, special use airspace or scheduling requirements).

The invention discloses a mobile time-slot aviation control method based on 4D track, establishes a mobile time-slot model, uses modern computer, network technology and big data processing technology, and performs a large number of calculations and predictions in the flight control work by the computer system to provide a visual mobile time slot model for tower flight controllers, and change the previous control mode that relied on human mental calculation, visual judgment, and manual guidance and command into a global (full flight process) and visualized time slot allocation control model. The use of mobile time slot management methods in military and civil aviation radar control systems can greatly reduce the difficulty of flight deployment, reduce errors caused by human factors, and improve the level of control automation.