70 results about "Landing performance" patented technology

The invention discloses an automatic carrier-landing guiding method of a carrier-borne unmanned aircraft and belongs to the technical field of automatic carrier-landing guiding for carrier-borne aircrafts. The method comprises the following steps of determining a reference flight path at a capturing phase according to the initial course information and the positional information of the unmanned aircraft, determining a reference flight path at a tracking phase by considering the influence of deck movement, acquiring a flight-path error at the capturing phase by adopting a direct sightline method, and obtaining a flight-path error at the tracking phase by adopting a dynamic coordinate-system changing method; calculating longitudinal and transverse control-signal instruction values according to the flight-path errors, and guiding the carrier-borne unmanned aircraft to fly along the reference flight paths. The automatic carrier-landing guiding method of the carrier-borne unmanned aircraft provided by the invention has high realizability and operability, so that the carrier-landing performance of the unmanned aircraft under a specific carrier-landing environment is improved; the deck movement is directly led into a carrier-landing tracking-phase guiding algorithm, so that the addition of a deck-movement compensator to a controller is avoided, the complexity of a flight control system is lowered, and the reliability of a carrier-landing system is improved.

The invention discloses differing embodiments of methods, aircraft, and apparatus for determining the landing conditions of a runway. In one embodiment, braking data may be collected from an aircraft which has landed on the runway; a braking performance measurement of the aircraft may be calculated based on the braking data; and a normalized braking performance measurement may be determined based on the braking performance measurement. The invention may be utilized to predict the expected braking performance of various types of aircraft on the runway. The invention may provide landing performance information to a broad host of users, and / or may be used as a basis for the development of a new aviation standard for the reporting of runway braking action.

The invention discloses a height-lift device provided with combined jet structure on a wing flap, comprising a wing leading edge slat, a main wing and the wing flap; wherein, the upper surface of the wing flap is provided with the combined jet structure which is provided with an air compressor used for controlling the flow and the speed of ejective airflow so as to adjust the influence of the airflow on the taking-off or landing performances of a plane. The high-lift device can obviously improve the flow quality above the wing flap of the plane, avoid the separation of the wing flap, improve the taking off, landing and stall performance of the plane, improve the maximum lift and furthermore, and achieve the taking off and landing of the plane at comparatively low speed.

The invention provides a vertical landing track design method for an unmanned aerial vehicle, which belongs to the field of flight control and comprises the following steps of: 1, building a balance equation of the unmanned aerial vehicle landing stability state according to the kinematics relationship of the unmanned aerial vehicle; 2, adopting a non-linear plan method for designing the verticallanding track of the unmanned aerial vehicle in a glissade stage; 3, designing the height track in an index form in a leveling stage and solving the non-linear equation to obtain the vertical landingtrack of the unmanned aerial vehicle according to the designed track angle trimming value and the elevation instructions in the leveling stage; and 4, integrating the landing tracks in the glissade stage and the leveling stage to obtain the vertical landing track of the whole unmanned aerial vehicle. The method has the advantages that the safety margin of the incidence angle and the operation margin of an elevator are improved, the precise and safe landing of the unmanned aerial vehicle is convenient to guide, the method is applicable to the landing control algorithm considering all of the height, the pitch angle and the descending speed, in addition, the landing performance is fully analyzed, and mathematic software is adopted for effective design to avoid the traditional experience trial and error.

A display system is provided for displaying runway landing data. The system includes a processor and a display device. The processor is adapted to receive data representative of an aircraft landing operation and is operable, in response thereto, to supply one or more image rendering display commands. The display device is coupled to receive the image rendering display commands and is operable, in response thereto, to render an image representative of a runway and a segment of the runway that will be used to land and stop the aircraft during the aircraft landing operation. A method for displaying the runway landing data is also provided.

The invention discloses differing embodiments of methods, aircraft, and apparatus for determining the landing conditions of a runway. In one embodiment, braking data may be collected from an aircraft which has landed on the runway; a braking performance measurement of the aircraft may be calculated based on the braking data; and a normalized braking performance measurement may be determined based on the braking performance measurement. The invention may be utilized to predict the expected braking performance of various types of aircraft on the runway. The invention may provide landing performance information to a broad host of users, and / or may be used as a basis for the development of a new aviation standard for the reporting of runway braking action.

A display system is provided for displaying runway landing data. The system includes a processor and a display device. The processor is adapted to receive data representative of an aircraft landing operation and is operable, in response thereto, to supply one or more image rendering display commands. The display device is coupled to receive the image rendering display commands and is operable, in response thereto, to render an image representative of a runway and a segment of the runway that will be used to land and stop the aircraft during the aircraft landing operation. A method for displaying the runway landing data is also provided.

The invention provides a rotor type aircraft water landing model test method. Firstly, a test device is installed, and electrical signal connection and test are completed. Then, a hydrodynamic high speed test trailer moves in an orbit and drives a model to move, when the speed of the model reaches the running speed required by the test and is stable, data acquisition equipment is started, after the normal working of the data acquisition equipment is determined, a model connection component is controlled to loosen the model, and the model freely separates and goes into water to slide. After the model goes into the water, the hydrodynamic high speed test trailer brakes and slows down until parking. After the test process is ended, the effectiveness of collected test data is analyzed, valid test parameters are recorded, and the valid test parameters comprises model weight, center of gravity, forward speed and sinking speed at the instant of going into water, a pitch angle, a roll angle and a yaw angle in a model initial state, and a pitch angle, a roll angle and a yaw angle, overload of center of gravity, cockpit overload, bottom pressure of the model after the model goes into the water. According to the method, a reliable basis is provided for effectively evaluating the water landing performance of a rotor type aircraft.

The present invention relates to a method for detecting landing quality of an aircraft, comprising: determining whether a vertical speed rate is greater than a first preset value or a vertical acceleration is greater than a second value when the aircraft landing; collecting landing data; generating a landing message based on collected landing data in response to that the vertical speed rate is greater than the first preset value or the vertical acceleration is greater than the second value when the aircraft landing; storing or transmitting the landing message; and determining the landing quality of the aircraft based on the landing data in the landing message.

The invention relates to a dynamic numerical simulation method for an external flow field of a multi-element airfoil of an airplane. The method comprises the steps that 1, an airplane model with a leading edge slat, a trailing edge flap and the multi-element airfoil is established and imported into fluent software; 2, a vertical descending motion function of the airplane model is constructed and imported into the fluent software; 3, a turbulence model is selected; 4, simulation parameters are set, including fluid parameters, airfoil material parameters, work environment parameters, boundary condition parameters, a dynamic mesh updating model, a solution method and solution precision; 5, the fluent software is run, and a flow parameter variation diagram, including a speed, pressure and temperature variation diagram, of fluid around the airfoil in the vertical descending process of the airplane is acquired. Compared with the prior art, dynamic numerical values of the external flow field in the landing process of the airplane can be effectively acquired, and reference can be conveniently provided for assessment of rising and landing performance of the airplane and design of a high lift device.

The invention discloses a landing operation performance evaluation method based on flight data. The method comprises that a QAR system collects landing distances, landing loads and landing elevation angles of multiple flights of the same type within certain historical period, and predicts parameter distribution; the risk values of abnormal landing events including distant landing, heavy landing and tail strikes are calculated; a landing operation performance evaluation model is established according to the risk values of the three abnormal landing events and weights thereof; and the evaluation model is used to calculate a landing operation performance evaluated value of certain flight, and an evaluation result of a landing operation performance level is output according to a division standard of the landing operation performance levels. According to the method, the landing operation performance of the single flight is evaluated in an integrated manner, the risks of landing events of the single flight or in certain period can be predicted, and the landing performance of the whole fleet or airline can be evaluated and compared. In addition, the invention also provides a landing operation performance evaluation device based on flight data.

The invention provides an unmanned aerial vehicle using distributed ducted power and capable of short-distance take-off and landing and relates to the technical field of unmanned aerial vehicles. Theunmanned aerial vehicle has two fuselages. A front wing connects and traverses the fronts of the two fuselages, and a rear wing connects and traverses the tail portions of the two fuselages. Verticaltail wings are respectively installed directly above the tail portions of the two fuselages. An oil-electricity hybrid power scheme is adopted to prolong endurance of the unmanned aerial vehicle, andreduce weight, vibration and the oil consumption rate of a power system. Ducted power assemblies distributed on the upper surfaces of trailing edge flaps of the wings suction boundary layer airflow onthe upper surfaces of the wings so as to increase the aerodynamic efficiency of the wings. Distributed arrangement of the power system avoids a problem that malfunction of one engine causes a runawayunmanned aerial vehicle, thus improving safety of the unmanned aerial vehicle. The trailing edge flaps drive the ducted power assemblies to deflect so as to change a thrust direction, thus shorteningsliding distances in take-off and landing stages of the unmanned aerial vehicle, improving take-off and landing performance of the unmanned aerial vehicle, and expanding the application range of theunmanned aerial vehicle.

The invention relates to an aviation aircraft, and in particular relates to a hovering type folding wing lifting body aircraft based on a variable centroid technology. According to the technical scheme, the hovering type folding wing lifting body aircraft based on the variable centroid technology comprises a lifting body airframe (1), a variable centroid mechanism (2), a vectored thrust mechanism (3) and a wing rotation folding mechanism (4), wherein two front wings (41) and two rear wings (42) which are connected with the lifting body airframe (1) are in a wing combination type serial wing layout. By adopting the hovering type folding wing lifting body aircraft based on the variable centroid technology, the problems of take-off and landing performances and multi-attitude flight performance of a fixed wing aircraft are solved, and the functions of vertical / short-distance take-off and landing, thrust vectoring and small-space flight of the fixed wing aircraft are realized.

The object of the invention is to provide an inflatable tire with good rolling resistance, wet land performance and wear-resistance, wherein the generation of groove cracks on the surface of the tire is inhibited. The inflatable tire is an inflatable tire with a surface, and the surface comprises a drive surface and a base part. The drive surface is prepared by a rubber combination for the drive surface, and the rubber combination comprises a preset amount of silicon dioxide that has a 70-300m2 / g BET specific surface area, a preset amount of carbon black and / or inorganic filler, and 0.5-5 parts in weight of release agent, wherein the release agent comprises at least one of a group that consists of fee fatty acid metal salt, fatty acid amides and amide ester. The base part is prepared by a rubber combination for the base part, and based on the weight parts, the rubber combination comprises a preset amount of carbon black and / or silicon dioxide that has a 70-300m2 / g BET specific surface area.

A pneumatic tire in the invention inhibits deterioration of noise performance and improves mud land performance. A pneumatic tire (1) is provided with a tire shoulder longitudinal furrow (3) and a tire shoulder horizontal furrow (8). The tire shoulder longitudinal furrow (3) is formed to be trapezoidal wave-shaped sawteeth. In the tire shoulder horizontal furrow (8),the angle of a straight line connecting an intersection point (P1) of a furrow central line (8G) and the tire shoulder longitudinal furrow (3), and an intersection point (P2) of a furrow central line (8G) and a grounding terminal (Te) relative to the tire axial direction is 5-20 degrees. The width of the tire shoulder horizontal furrow (8) is gradually increased, the ratio Wo / Wi of the furrow width (Wo) at the grounding terminal (Te) to the furrow width (Wi) at the part communicated with the tire shoulder longitudinal furrow (3) is 1.5-3.0. One party side furrow intersection part (20) of a one party side furrow wall (8A) of the tire shoulder horizontal furrow (8) in the tire shoulder horizontal furrow (8) and the tire shoulder longitudinal furrow (3) is closer to the axial inner side of the tire than the other party side furrow intersection part (21) of the other party side furrow wall (8B) of the tire shoulder horizontal furrow (8) in the tire shoulder horizontal furrow (8) and the tire shoulder longitudinal furrow (3).

Disclosed is a short take-off vertical landing aircraft comprising a fuselage, main engines, a vertical fin, and main wings, upper wings, end wings and canards which are arranged at both sides of thefuselage; the outer sides of the end wings are provided with extension wings; the two extension wings are provided with ailerons; the two upper wings are provided with elevators; the tail portions ofthe two end wings are provided with rudders; the lower parts of the two end wings are provided with forward direction stretching support structures, and each forward direction stretching support structure is provided with a main engine, a main engine propeller and a propeller dip angle driving device; the lower portion of each end wing is provided with a retractable main undercarriage; and the rear portion of the vertical fin is provided with a backward stretching support structure, and the backward stretching support structure is provided with an attitude-adjusting engine propeller. The shorttake-off vertical landing aircraft not only has short distance take-off and vertical landing performance, but also takes into account flight performance of high speed, long endurance and large voyage, and so on.

The invention belongs to the field of plane design, and provides a plane lift-enhancing device high-velocity and high-velocity comprehensive optimum design method based on multiple subjects for solving the problems that in an existing lift-enhancing device design process, by means of a mechanism and pneumatic reciprocated iteration, consumed time is long, expenses are high, and plane performance can hardly be improved through a cruiser wing variable camber. Take-off performance, landing performance, cruising performance and the mechanism weight serve as optimization targets, parameterized control points of lift-enhancing device multi-section wing types, mechanism design parameters of the lift-enhancing device drive mechanism, required take-off configuration deflection angles, required landing configuration deflection angles and cruising stage variable camber deflection angles are optimized so that the configuration of the optimal comprehensive performance can be obtained. The method has the advantages that the requirement for the weight of the drive mechanism, the requirement for trajectory kinematics, the requirement for the high-velocity cruise variable camber and the requirement for low-velocity take-off and landing are all met while the system is optimized, and the method is suitable for various mechanism types, free of specific trajectory formulas and high in flexibility.

The invention relates to a rubber composition used for tread positions of sport tires suitable for highways and drifting racing. The rubber composition is characterized by being composed of, by weight, 100-137.5 parts of styrene butadiene, 40-70 parts of carbon black, 20-30 parts of white carbon black, 1.5-2.5 parts of zinc oxide, 0.5-1.5 parts of stearic acid, 0.5-1.5 parts of homogenizing agent, 2-3 parts of Si-69, 1.5-2.5 parts of static protective agent, 1.5-2.5 parts of antiager, 1-3 parts of promoter, 1-3 parts of sulfur and 0.1-0.3 part of antiscorcher. The rubber composition takes requirements on performance in two aspects into consideration, has excellent wet land performance and dry land holding power and realizes harmonization of high controlling performance and low rolling resistance.

The invention provides an air vehicle adopting a double-pointed-cone fish tail type front edge aerodynamic layout. The air vehicle comprises a vehicle body and an engine. The vehicle body comprises head pointed cones, a transition section, air inlet channel pointed cones and a blended wing body. The two head pointed cones are adopted and symmetrically arranged on the two sides, so that the low-pressure area of the head of the air vehicle is effectively enlarged, the trim capability of the whole vehicle is improved while the lift force is increased, and the trim resistance of the whole vehicle is reduced; by designing the transition section in the gap between the head pointed cones and the blended wing body, the vortex core central position on the inner sides of the head pointed cones is controlled, unfavorable interference between vortexes is reduced, the air flow energy of the upper surface is supplemented at the same time, and the lift force is increased; the air inlet channel pointed cones are arranged in the middle of the transition section, and then the vortex lift force of the upper surface of the air vehicle and high-angle-of-attack air inlet efficiency are improved; besides, the shielding effect on an air inlet channel is achieved through the head pointed cones and the transition section, and the hidden performance is improved; by means of the design of a plane groove surface between an air inlet channel lip and a tail jet nozzle on the lower surface of the air vehicle, the purpose of increasing the lift force is achieved. By means of the aerodynamic layout scheme, the hidden performance, taking-off and landing performance, subsonic speed and transonic speed maneuvering characteristics, the supersonic cruise performance, the poststall maneuver performance and other indexes can be well considered.

The invention discloses an amphibious aircraft which comprises an aircraft body, wings, short engine compartments, floating barrels, an empennage and an undercarriage. The wings are fixed to a hump onthe back of the aircraft body. The short engine compartments are installed at the head ends of the wings. The floating barrels are arranged on the two sides of the middle portion of the aircraft bodyand located below the wings. The empennage is arranged on the tail portion of the aircraft body. The undercarriage is installed at the bottom end of the aircraft body. The floating barrels are provided with protrusions, and containing cavities with openings are formed in the leeward faces of the protrusions. It can be guaranteed that when the aircraft glides at a high speed on the water surface,the longitudinal and transverse stability and the water surface take-off and landing performance are good, and the stability of the aircraft in the flight process is improved as well.

The invention provides a jet flow control plane for a blended wing body configuration aircraft. The control plane is located at the back of the aircraft body, and is extended and retracted through a driving mechanism, so as to be coupled with the engine jet flow at the front of the control plane, thus improving the pitch-up moment for rising and landing of the aircraft. Compared with a traditionalblended wing body configuration tail control plane, the jet flow control plane for a blended wing body configuration aircraft has a higher control plane efficiency, and can significantly increase theavailable pitch-up moment. At the same time, since the moment arm is long, the required pitch-up moment can be achieved with a small lift loss, and the overall adverse effect on the rising and landing performance is small. The driving mechanism can be accommodated in the aircraft body, thus having no influence on the cruising performance.

The invention discloses a method for evaluating the power augmentation effect of an outward blowing type flap layout aircraft. The method comprises the following steps: 1) establishing a power augmentation aircraft performance calculation model; 2) calculating a performance integral characteristic speed; 3) establishing a non-reference velocity point aerodynamic force increment correction model; 4) completing calculation of non-reference velocity point aerodynamic force according to the aerodynamic force increment correction model in the step 3; 5) calculating the takeoff distance of the aircraft; and 6) according to the calculation result of the step 5), evaluating the aircraft power augmentation effect. The method is suitable for calculation of the take-off and landing performance of thepower augmentation aircraft of the outward blowing type flap layout aircraft, evaluation of the power augmentation effect and optimization of the layout configuration of the augmentation device, andan effective design tool is provided for layout and type selection of the power augmentation aircraft.

The invention discloses a proof machine. The proof machine is composed of a wing (1), an undercarriage (2), a connection rack (3), a head (4), a tiltable intermediate section wing and main power system (5), a vertical empennage rotor wing (6), a vertical empennage (7), a tailplane (8), a rotor wing (9), a frame (10) and a wing rotor wing (11). The proof machine employs a unique tiltable intermediate section wing body / main power system and a variable pitch posture adjusting power system and is comprehensively applied to a single-tailboom aerodynamic layout so as to ensure that an airplane has quite good short-distance / vertical rising and landing performance and stable hovering performance, and is provided with excellent air cruise capability of a fixed wing airplane at the same time. The integrated tilt design of the intermediate section wing body and main power system can satisfy the need for tilting by a power system, and can also reduce the shield effects by the frame and the wing on propeller slip-stream during a tilting process.

The invention discloses a cross-domain hypersonic aerodynamic layout of a sharpened leading edge vortex wave integrated fixed wing. The planar shape of the cross-domain hypersonic aerodynamic layout comprises but is not limited to sharp-end double sweepback, elbow double sweepback, single sweepback, a gradually-changed leading edge, an S leading edge and other appearances. The lower surface is a waverider surface obtained through streamline tracking in a flow field with shock waves; the upper surface is a free flow surface or a smooth continuous curved surface which protrudes upwards moderately; the wings contract to form sharp trailing edges, and the fuselage contracts to form a sharp body or a small rear body. Under the hypersonic speed working condition, the layout is a waverider or a similar waverider, shock waves on the windward side are attached to the sharpened leading edge through the sharpened leading edge waverider effect, and the high lift-drag ratio is obtained; in the subsonic flight stage, stable small separation vortexes generated by appendage flowing or front edge sharpening under the condition of a small attack angle are utilized to obtain a high lift-drag ratio; and in the low-speed take-off and landing stage, by means of the vortex effect that airflow is rolled up from the lower surface to the leeside under the medium-large attack angle, high nonlinear vortexlift force under the low-speed horizontal take-off and landing working condition is obtained, and the high lift force is obtained to improve the take-off and landing performance.

The invention discloses an aerodynamic layout of an aircraft with a blended wing body and belongs to the technical field of aircrafts. The aerodynamic layout is designed for solving the problems that an existing aircraft with a blended wing body is insufficient in lift force and large in flight drag. The aerodynamic layout of the aircraft with the blended wing body involves the blended wing body and a rear wing; a fuselage and a wing of the blended wing body are blended to constitute a front wing; the rear wing is a horizontal tail, and the two sides of the horizontal tail are connected with the two sides of the front wing through connecting parts respectively. On the basis of wing and fuselage blending, the horizontal tail is added to serve as the rear wing so that the lift force of the aircraft with the blended wing body can be increased; in addition, the arrangement area of a high-lift device and the arrangement area of an operating device are increased so that the maximum lift coefficient can be increased and the take-off and landing performance of the aircraft can be improved.

The invention relates to the technical field of unmanned ground-effect wing ships, in particular to a ground-effect flight control device of an unmanned ground-effect wing ship. The device comprises a ship body, ground-effect wings are symmetrically arranged on the left side and the right side of the ship body, pontoons are arranged on the ground-effect wings, a plurality of ground-effect flight height measuring devices are arranged at the bottom of the ship body in the length direction, and ground-effect flight height measuring devices are arranged at the bottoms of the pontoons. The stern is provided with a first steering gear, the first steering gear is used for controlling the elevator, the ground-effect wings are provided with second steering gears, and the second steering gears are used for controlling the ailerons. A unique ground-effect flight height measuring device is adopted to measure the minimum ground-effect flight height from the ship body and the pontoon to the water surface in real time so as to ensure that the measured ground-effect flight height of the unmanned ground-effect wing ship is real-time and accurate; and according to the invention, the extended control panel is retracted and clung to the bottom of the ship body or the pontoon, so that the original shape of the bottom of the ship body or the pontoon is kept, and adverse factors possibly influencing the take-off and landing performance of the unmanned wing-in-ground-effect ship are eliminated.

The invention discloses a method for evaluating landing indexes of extraterrestrial object soft landing detectors under a low sampling frequency condition. The method comprises the following steps of(1) autonomously calculating a landing index in real time by utilizing a satellite-based algorithm after an extraterrestrial object soft landing detector starts a soft landing process; (2) storing thelanding index according to a certain frequency and certain periodicity when the extraterrestrial object soft landing detector satisfies a landing condition; (3) downloading the landing index data stored by the soft landing detector after the ground confirms that the soft landing detector safely lands on an extraterrestrial object; and (4) analyzing and assessing the landing index data downloadedby the ground, if the landing index satisfies a soft landing task index requirement totally issued by the detector, judging that the landing index is qualified, and otherwise, judging that the landingindex is unqualified. According to the method, the obtaining of satellite-based landing states at the landing moments is realized, so that a reliable technical way is provided for the final landing state determination and landing performance assessment.

Systems and methods that optimize landing performance are provided. The system determines a number, N, of equipment configurations (a combination of a brake setting and a thrust reverser configuration) supported by the aircraft. The system determines a deceleration airspeed to achieve a target taxi speed and, for each of the N equipment configurations, determines a respective deceleration distance. In various embodiments, the system further updates the deceleration distances by one or more of a brake's condition, aircraft historical data, brake warranty and life cycle data, and environmental conditions. The deceleration distances are used to identify a number P of exit-ways that can be used at the runway. Total costs (including brake usage and fuel cost) for each of the P exit-ways is determined, and the equipment configuration that delivers the lowest total cost delivers the optimize landing performance.

The invention relates to an overall aerodynamic layout of a double-engine unmanned aerial vehicle. The overall aerodynamic layout of the double-engine unmanned aerial vehicle is characterized in thatthe unmanned aerial vehicle comprises a vehicle body (1), a large-size radome (2), a wing (4), short cabins (3), propellers (5), a V tail (6) and a blocking hood (11); the section of the vehicle body(1) is in a ship shape, the span-chord ratio of the wing (4) is 15:25, and the vehicle body (1) and the wing (4) are in fused transition in shape; a flap (7), a flaperon (8) and an aileron (9) are arranged on the wing (4), and a lifting rudder (10) is arranged on the V tail (6); and engines are mounted on the inner section of the front edge of the wing through the short cabins (3), and the propellers (5) are mounted at the front ends of the short cabins. The unmanned aerial vehicle adopting the short-distance taking-off and landing layout can meet the overall, aerodynamic, structural and taking-off-and-landing-performance requirements and has the advantages of being wide in flying speed range, high in lift-to-drag ratio, short in taking-off and landing distance and the like, and the short-distance taking off and landing unmanned aerial vehicle layout can be used for aerodynamic layout design of scouting and attaching integrated unmanned aerial vehicles, attaching-type unmanned aerial vehicles, scouting-type unmanned aerial vehicles and special unmanned aerial vehicles.