32 results about "Flying qualities" patented technology

A step-motion actuator using piezoelectric material to launch a flight mass which, in turn, actuates a drive pawl to progressively engage and drive a toothed wheel or rod to accomplish stepped motion. Thus, the piezoelectric material converts electrical energy into kinetic energy of the mass, and the drive pawl and toothed wheel or rod convert the kinetic energy of the mass into the desired rotary or linear stepped motion. A compression frame may be secured about the piezoelectric element and adapted to pre-compress the piezoelectric material so as to reduce tensile loads thereon. A return spring may be used to return the mass to its resting position against the compression frame or piezoelectric material following launch. Alternative embodiment are possible, including an alternative first embodiment wherein two masses are launched in substantially different directions, and an alternative second embodiment wherein the mass is eliminated in favor of the piezoelectric material launching itself.

The invention discloses an image matching method suitable for automatically detecting the flight quality of the aerial photography. The method comprises the steps that firstly, images are preprocessed, denoising and filtering are respectively carried out on two digital images to be matched, and the two digital images to be matched are obtained with the aerial photography measuring method in the measured area and are two-dimensional images; secondly, SIFT characteristic extracting is carried out, the SIFT characteristic extraction is respectively carried out on the two digital images through a data processor, all characteristic points of the two digital images and SIFT characteristic descriptors of all the characteristic points are obtained; thirdly, a kd tree is established to carry out the bi-directional search to determine matching points; fourthly, gross error removing is carried out according to the RANSAC algorithm. According to the method, the steps are simple, design is reasonable, the achieving process is convenient, robustness and the using effect are good, and the method can effectively solve the problem that according to an existing method, matching is prone to failure matching or error matching.

The present invention provides a high-speed wind tunnel high-angle-of-attack pitching dynamic stall test device. The device is driven by a motor, and the flywheel is driven to rotate through a belt drive wheel. The central axis of the flywheel drives a synchronous transmission gear set to transmit kinetic energy to the main drive. The four-link motion system consists of the main drive wheel, the connecting rod and the rotating window, which realizes the conversion of the flywheel rotation into the reciprocating oscillation of the rotating window, and then drives the fixed aircraft model to achieve pitching motion at a large angle of attack. The high-speed wind tunnel pitching dynamic stall test device with large angle of attack of the present invention overcomes the difficulties of strong vibration during operation of the existing high-speed wind tunnel, small space in the test section, low structural response frequency of the test section, and large environmental noise, etc., and can provide The dynamic aerodynamic test results of the aircraft model under the conditions of large angle of attack (up to 75°), large amplitude (‑15°~75°), and high frequency (0~6Hz) are used for aerodynamic optimization design, flight quality evaluation, and control rate design Provide key test basis.

The invention discloses a cruise stage fuel consumption prediction method for aircraft mass change. The method comprises the following steps: step 1, considering the influence of mass change and crosswind, and constructing a cruise stage fuel consumption model; step 2, aiming at the model constructed in the step 1, establishing an objective function and constraint conditions; and step 3, solving the optimal solution of the objective function to obtain the optimal fuel mileage under each mass and the corresponding optimal cruise height and maximum cruise Mach number. According to the prediction method, a cruise fuel consumption prediction model based on aircraft mass change can be established, and the optimal cruise height and the optimal cruise speed corresponding to the maximum fuel mileage of different aircraft masses are determined through optimization calculation by the model.

The invention discloses an unmanned aerial vehicle semi-aviation transient electromagnetic receiving coil flight parameter measuring device and method. The device comprises a receiver, an attitude resolving module, a nine-axis attitude sensor, a GPS, a radar altimeter, a transient electromagnetic receiver and flight quality inspection software. The receiver comprises a receiver shell and an annular receiving coil arranged in the receiver shell, the receiving coil is connected with the bottom of the unmanned aerial vehicle through four anti-torsion ropes, and self-rotation of the coil in the flight process can be effectively reduced. The attitude resolving module, the nine-axis attitude sensor and the GPS are all fixedly arranged at the circle center of the receiving coil; the course angleof the receiving coil can be accurately obtained; the attitude of the receiving coil is calculated in real time, a radar altimeter is fixedly arranged below the circle center of the receiving coil, height information for calculating a vertical magnetic component in the data inversion process can be provided, and flight quality inspection software monitors the flight quality by dynamically playingback flight parameters of the receiving coil on site.

The invention discloses a Beidou positioning system-based flight control operator flight quality evaluation system and method. The Beidou positioning system-based flight control operator flight quality evaluation system includes a Beidou positioning system, an unmanned aerial vehicle, a ground station, a wireless data transmitting module and a data wireless receiving module; the Beidou positioning system includes a mobile station and base station; the mobile station and the wireless data transmitting module are arranged on the unmanned aerial vehicle; the mobile station is connected with the wireless data transmitting module; the base station and the wireless data receiving module are arranged at the ground station; the base station is connected with the wireless data transmitting module; and the ground station is connected with the base station. The system and method of the invention can evaluate the flight quality of the flight control operator of the unmanned aerial vehicle and achieve authentic and accurate evaluation results and has an important reference value in an unmanned aerial vehicle flight control operator flight quality evaluation process.

The invention discloses a lunar-earth high-speed reentry and return flying quality evaluation method, which comprises the following steps of firstly, reading flight stage mark parameters in a remote signal, confirming mission profiles, start time and end time which are corresponding to the flight stage mark parameters, and extracting sub flying targets in one-to-one mapping with the mission profiles; secondly, confirming a constraint condition set of each sub flying target and an index set corresponding to each constraint condition, respectively carrying out number normalization on quantitative indexes and qualitative objects; finally, confirming an ability function value of each constraint condition and an ability quantized value of each mission profile, and calculating a lunar-earth high-speed reentry and return flying ability quantized value. The lunar-earth high-speed reentry and return flying quality evaluation method realizes scientific evaluation of the autonomous flight ability in the processes such as a lunar-earth transition section, a navigation establishment section, a reentry section and a springing section, and solves the problem that the target completion ability of a flying machine is not easy to quantitatively evaluate during the lunar-earth high-speed reentry and return full-mission simulation flight test.

The invention discloses an apparatus for balancing an aircraft by utilizing fixed spoilers. The apparatus comprises the fixed spoilers, movable spoilers, a self balancing device substrate and a rotor. The fixed spoilers arranged on the apparatus generate fixed balancing torque, and the movable spoilers are also arranged to generate variable balancing torque. An between each of the movable spoilers and the rotor is in a range of 10-170DEG, so the movable spoilers can increase the balancing torque and can reduce the balancing torque as needed, and the disadvantage of no torque change of traditional fixed spoilers is avoided. The fixed spoilers and the movable spoilers are utilized to simply and conveniently realize the real time adjustment of the balancing torque of the rotor aircraft in order to improve the flight quality and stability of the rotor aircraft.

The invention discloses an unmanned plane flying quality inspection system. It is very important for accurately inspecting unmanned plane flying quality. The unmanned plane flying quality inspection system is developed according to inspection requirements on flying quality of an unmanned plane for aerophotography. The unmanned plane flying quality inspection system can calculate flying image quality parameters such as a degree of overlapping, a swing angle, course flexibility and flying height difference by an interactive fast computing method. The unmanned plane flying quality inspection system has innovativeness in swing angle and overlapping degree calculation and can produce reliable results. Under the condition of satisfying engineering production, through a side length measurement method, an overlapping degree calculation formula is deduced, course and lateral direction overlapping degrees of unmanned plane images are acquired accurately and the problem of inaccuracy of the calculation result of the overlapping degree of flying images is solved.

The invention discloses a flight quality adaptive evaluation method, which comprises the following steps of: firstly arranging flight actions to be evaluated, then selecting flight action entries of related standards from historical flight data, and establishing a standard action reference library; constructing a depth variational self-encoding network, then calculating distance measurement by adopting a dynamic planning mode on the sorted flight action to be evaluated and corresponding standard action compression characteristics obtained after processing of the depth variational self-encoding network, and then calculating similarity measurement between the flight action to be evaluated and the standard action; and then, according to similarity measurement between a flight action to be evaluated and a standard action, global information and local information are considered at the same time, a multi-view fusion scoring rule is formed, so that a scoring model is constructed, namely, the completion condition of a single action is considered, and scoring is performed in combination with performance in a complete flight sortie. Therefore, the multi-view automatic comprehensive evaluation of the flight action quality is realized.

The invention discloses a device for balancing the torque of a rotor craft. The device comprises fixed spoilers, movable spoilers, a self-balancing device base body and a rotor. According to the invention, the fixed spoilers are configured so as to generate fixed balancing torque; moreover, variable balancing torque is generated according to the added movable spoilers. Because the angle between the movable spoilers and the rotor is 10-170 degrees, the movable spoilers not only can increase the balancing torque, but also can reduce the balancing torque as required, which can not be realized by the traditional fixed spoilers. According to the invention, the balancing torque of the rotor craft can be adjusted in real time simply and conveniently by utilizing the fixed spoilers and the movable spoilers, and the flight quality and the stability of the rotor craft can be improved.

The invention belongs to the technical field of aero-engine manufacturing and repairing, and discloses an anti-loose high-temperature alloy lock washer which comprises a ring part. Two locking claws are arranged on each of the left side and the right side of the ring part, a lock claw is arranged at the bottom of the ring part, the length of the lock claw is 4-8 mm, and the lock washer is made ofGH3044. According to the anti-loose high-temperature alloy lock washer, the failure rate of falling of heat shield nuts in the using process of an aero-engine of a certain type is effectively lowered,the stability of the engine and assembling efficiency of operators are improved, the flight quality is guaranteed, and regular checking, fault repairing and repeated test-run costs are saved.

The invention discloses a novel configuration vertical take-off and landing unmanned aerial vehicle belonging to the field of aircraft transmission system and lifting rotor, which comprises a fuselage, a rolling wing system, a vertical tail, a rudder, an aileron, a flap, a detection pod and an take-off and landing actuating cylinder. A rolling wing system is installed in the duct of the wing, andthe rolling wing system is composed of two groups of rolling wings with the same size and opposite rotating directions. The propeller shaft of each roller section is coaxial, and the full vector propulsion system of cycloidal propeller is composed of two sections of each group. The invention discloses a novel configuration vertical take-off and landing unmanned aerial vehicle, which can realize vertical take-off and landing on land-based platform and sea-based platform, and has better flying quality. The invention combines the characteristics of a rotor aircraft and a fixed-wing aircraft, andhas low dependence on take-off and landing site and strong environmental adaptability. At the same time, the whole structure of cycloidal propeller system is light and simple, which has broad militaryand civilian prospects.

The invention provides a flying quality data monitoring method, which comprises the following steps of acquiring full-range flying data; dividing the full-range flying data into staged flying data corresponding to various flying stages according to preset flying phases; determining flying events of various flying stages according to preset event setting conditions and the staged flying data of various flying stages; and generating a flying event flying quality analysis report according to the flight events of various flying stages, so as to carry out flying quality analysis on the flight events. The invention also provides a flying quality data monitoring device. By dividing the full-range flying data according to the flying stages, thereby refining the setting process of the flying events, so that the technical personnel can set the flying events of various flying stages simply and conveniently. The invention solves the technical problem of large workload of setting monitoring parameters of flying quality data in an existing flying quality data monitoring method and device.

The invention relates to a high-intensity motor rotor for a model airplane, which is low in manufacturing cost, has collision resistance and is uniform in mass distribution. The high-intensity motor rotor for the model airplane comprises a head cover and a rotating shaft fixedly connected inside a shaft hole on the head cover; a connection screw of the head cover is provided with a hollow passagecoaxially formed with the shaft hole and communicated with the shaft hole; the outside part of the rotating shaft passes through the shaft hole to be inserted in the hollow passage; a plurality of ring-shaped grooves are formed at intervals on the outer peripheral wall of the rotating shaft; and the rotating shaft is fixedly connected with the shaft hole into one whole body by super glue filled inthe ring-shaped grooves. According to the invention, the rotating shaft in a motor is designed into a long shaft from a short shaft in the prior art and is inserted in the hollow passage in the connection screw, so that deformation resistance and fracture resistance of the connection screw are greatly improved. The rotating shaft is fixedly connected with the head cover by epoxy resin, so that machining and assembling efficiency of the head cover is greatly improved, and rotor mass can be guaranteed to be uniformly distributed in a direction of taking the axis as the symmetry axis so as to obtain high flight quality. The high-intensity motor rotor for the model airplane is simple in structure, low in manufacturing cost and few in assembling working time, and can be widely applied to a model external rotation motor.