43 results about "Flight (process)" patented technology

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.

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 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 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.