71 results about "Wing loading" patented technology

The invention discloses a static strength test method of a large vane used for wind power and electrical power and a test system thereof. The test method comprises the following steps: keeping the vane flat, fixing one end of the root of the vane through a fix support of the test system, vertically loading the vane with a crane, wherein the loading mode is as follows: single point loading through the crane is converted into multi-point loading through a load distributing beam; and then, transmitting the multi-point loading to the vane through a vane loading clamp. The lifting point of the crane, the load distributing beam and the vane loading clamp are connected together through slings provided with load sensors, a strain piece and a displacement sensor are arranged on the vane, and stress, shape change and displacement data information respectively collected from the loading process are used for determining whether the static strength of the vane meets the requirements of design or not. The test method of the invention has the advantages of low area limit, low test cost, convenient process operation and accurate test result; and the test system of the invention has the advantages of simple manufacturing, convenient assemble, low cost and long service life.

The invention discloses a weight loading ring-piece type corrosive wear tester, consisting of a stand, a weight loading system, a friction force measuring system, a transmission system and a crucible resistance furnace system. The weight loading system is internally provided with a lifting rotary plate; during loading, the weight tray is located in the low order; during unloading, the lifting rotary plate is rotated; the weight tray is risen to a high-order for bearing a weight; one end of a first wire rope in the weight loading system is horizontally led out and then wound on a pinion of a force-increasing roller; one end of a second wire rope is fixed and then wound on a bull wheel of the force-increasing roller; and the weight is suspended on the sagging end. In the invention, a ringlike sample and a block-like sample are used as the friction pair, liquid metal is used as the corrosive medium, the behavior of the solid friction pair for bearing corrosion and wear at the same time in the liquid metal can be simulated, the load, temperature, rotating speed and liquid metal supply test parameters can be changed, the friction force can be measured and high load-applied accuracy and high measuring precision are ensured.

The structural strength of an aircraft wing is continuously tailored along its length to closely match continuously varying imposed wing loads. The wing comprises upper and lower skins each formed from panels joined together. Each of the skin panels includes a stiffening web sandwiched between and joined to the inner and outer facesheets. The web has a repeating pattern and at least one dimension that continuously varies along the length of the panel.

The invention belongs to the field of aviation fatigue tests, and particularly relates to a wing load applying device for a large aircraft strength test. The wing load applying device comprises a brace system, a loading platform, a plurality of platform move actuator cylinders and a plurality of loading actuator cylinders. According to the wing load applying device, through the controllable adjustment of platform positions of the movable loading platform controlled by a computer according to wing deformation of load during aircraft stopping on ground and below 1 g load during flying, as well as the loading by the actuator cylinders arranged on the platform, load applying directions and values under the situation of large deformation of large aircraft wings are ensured, so that test loading and test precision are improved; through the accurate applying of wing load, balance of a conventional whole aircraft test is ensured, so that inaccurate structure test of constraint components, which is caused by unbalance of load is avoided; and the loading of wings under large deformation can be realized by using conventional actuator cylinders, and large-stroke special actuator cylinders and tandem actuator cylinders can be omitted, so that the experiment implementation difficulty is reduced and a test cycle is ensured.

The invention discloses a shield segment testing machine. The shield segment testing machine is characterized by being composed of a self-balancing counter-force core tube, a cylinder force application device, an axial force loading device, a loading beam and a base, the base is located at the bottommost, the self-balancing counter-force core tube is located in the center of the base, a shield segment ring is located at the edge of the base, the loading beam stands vertically on the outer side of the shield segment ring, the two ends of the cylinder force application device are connected with the self-balancing counter-force core tube and the loading beam respectively, and the axial force loading device is located on the shield segment ring. The self-balancing counter-force core tube adopted on the shield segment testing machine is simple and economical, and can also achieve unbalanced loading on shield segments. Twelve-point loading is adopted in the radial direction and the axial direction, multi-point loading can be achieved, and the stress characteristic of a lining structure under the normal use state can be well simulated.

The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area than the front wing. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform.

An adaptive guidance system (AGS) regulates the altitude and heading of a parasail to arrive at a target at a prescribed altitude. Since the altitude profile depends both on unknown wing loading, and wind magnitude and direction, the AGS estimates the glide slope and wind on the fly and provides a command to a stability augmentation system (SAS) that results in the desired glide slope and heading by performing a sequence of maneuvers and sensing the response. According to one embodiment, the SAS operates in the linear region and includes a PID controller that uses the difference between the actual heading and heading command to create an actuator output. The actuator output is limited by a position / rate limiter that imposes the physical limitations of the response time of the actuator / servos and position limits to prevent entering the nonlinear region. Alternatively, an adaptive SAS operates in both the linear and nonlinear region and includes a neural network (NN) that receives an error signal (difference between a reference model and actual heading) which is used to adapt the weights of the NN.

The invention discloses a vertical take-off and landing fixed wing long-endurance air vehicle. The vertical take-off and landing fixed wing long-endurance air vehicle comprises a fuselage in horizontal position in flight; the head part of the fuselage is provided with a pair of canard type wings; the tail part of the fuselage is provided with a pair of wings; a vertical empennage is arranged below the tail part of the fuselage; the lower parts of the wings are provided with at least two pairs of distributed power plants, wherein the number of the power plants is even, and the revolving shafts of the power plants are arranged along the axis of the fuselage; the head part of the fuselage is provided with a vertically distributed through hole; and an elevating control power plant is arranged in the through hole, and the revolving shaft of the elevating control power plant is arranged in vertical. According to the vertical take-off and landing fixed wing long-endurance air vehicle, the elevating control power plant is used for changing rotating aped of variable pitch propellers and elevating control moment force needed by screw pitch output in the whole flight envelope; the number of fixed pitch propellers is larger, and rotating speed of each propeller can be controlled individually, so that rolling and yaw control adjustable minimum pulse-width is smaller, and control accuracy is higher.

Gauge or stabilizer wheels are located at the outer front portions of disk wing frames and are connected for operation with other disk wheels on the main and wing frames. The front stabilizer wheels bear much of the wing loading and allow the wing primary depth control wheels to be positioned further to the rear of the machine. The front stabilizer wheels can be hydraulically controlled for on-the-go forward depth control adjustments and provide frame support when the disk is in a field transport position.

The invention relates to a test method for a central wing box. A test piece, a test piece support system, a simulated side wall panel support system, a simulated fuselage frame support system, a simulated floor beam support system and an outer wing loading system are included. The test method reduces the cost and can carry out comprehensive test assessments on the strength of the central wing box.The method can simulate the boundary condition and the stress state of the central wing box in an airframe without the need of processing fuselage barrel sections for support more really.

The present invention discloses a hybrid-driven underwater glider. The hybrid-driven underwater glider comprises a submarine body, a master control system, an ups and downs adjustment mechanism, an attitude adjustment mechanism, a main propulsion propeller, wing-borne propellers, a power management system, an attitude sensing system, a high performance battery, a mission sensing system and a satellite positioning communication system. The master control system controls the ups and downs adjustment mechanism to realize the buoyancy adjustment of the underwater glider, controls the attitude adjustment mechanism to realize the attitude control of the underwater glider, and achieves the gliding motion of the glider by virtue of the self buoyancy and attitude inclination. The master control system controls the wing-borne propellers and the main propeller to realize full-speed linear propulsion motions, differential steering motion control, and emergency braking and back-up driving motions. The hybrid-driven underwater glider can be widely used in applications, such as water resource information exploration of waters for long voyage.

A flying toy capable of moving by flapping of wings includes an actuation mechanism, for the wings, comprising a crank drive rotated by a means providing the driving force, two flexible wings arranged symmetrically with respect to the vertical plane of symmetry of the toy and connected, at the wing bases, to the actuation mechanism. The wing bases are mounted oscillating about axes arranged on both sides of the vertical plane of symmetry of the toy. The toy includes a control means, that receives a control signal indicating a left turn, increases the tension on the right wing and reduces it on the left wing. For a right turn, the opposite action is performed.

The invention belongs to the field of aviation fatigue test and in particular relates to a vertical wing loading method for a full scale fatigue test. The method disclosed by the invention comprises the following steps: performing weighting on a pressure core under multiple load conditions according to the damage degree, and determining the position of a loading actuator cylinder. The vertical wing loading method for the full scale fatigue test provided by the invention is obtained on premise of meeting requirements of shear force, bending moment, torque and design load conditions of each control plane of the wings, and can be widely applied to designing vertical wing loading points for the full scale fatigue test of various aircrafts.

The invention belongs to the aircraft strength test technology, and relates to a chuck-type wing loading device, which includes a pulling plate bolt, a pulling plate, a loading chuck, a loading wood block, a square rubber pad, a chuck compression bolt, a chuck connecting bolt, a bush, a spring washer, a rear spar, a wing profile, a rear spar actuator cylinder, a front spar and a front spar actuator cylinder. The invention is solid in mounting, the test load is accurately applied, the front spar load applying and the rear spar load applying are not influenced by each other, the device weight is accurately deducted, and the device does not increase the vertical stiffness of the wing profile.

The structural strength of an aircraft wing is continuously tailored along its length to closely match continuously varying imposed wing loads. The wing includes upper and lower skins each formed from panels joined together. Each of the skin panels includes a stiffening web sandwiched between and joined to the inner and outer facesheets. The web has a repeating pattern and at least one dimension that continuously varies along the length of the panel.

An umbrella system relating to the general protection of fixed outdoor umbrellas, especially during windy conditions. The umbrella system uses a supportive shaft equipped with a resiliently deformable region allowing omni-directional bending under wind loading. A preferred embodiment of the deformable region comprises a helical spring.

A building construction has a foundation, walls and a roof structure, the walls being wrapped by a reinforcement fabric, with the reinforcement fabric being connected to the foundation and the roof structure to tie the roof structure to the foundation for increased resistance to natural disasters. The connection of the reinforcement fabric to the roof structure includes a top rail having a connector plate attached to the roof structure and having an upwardly oriented opening, and a wrapping member about which the reinforcement fabric can be wrapped, the wrapping member having a geometry corresponding with the geometry of the upwardly oriented opening in such a manner that the wrapping member is prevented from rotating in the opening.

An aircraft wing comprising an upper surface; and two or more spoilers pivotally attached to the upper surface, wherein at least two adjacent ones of the spoilers are separated by a gap, and wherein the width of the gap is: greater than 1 cm; and sufficiently small to choke the flow of air through the gap such that for at least one flight regime with the adjacent spoilers deployed, the average air flow speed through the gap is less than 10% of the true air speed.The reduced size of the spoilers reduces the spanwise wing loading and the spoiler hinge moment, whilst providing a net aerodynamic effect (in terms of destroying lift over the wing) similar to that of a conventional spoiler array with no gaps.

The invention discloses a multi-point loading and side-pulling testing apparatus for static tests on blades of large wind turbines, which is characterized in that a to-be-tested blade is fixed by a permanent seat parallel to the ground, a plurality of side-pulling supports are arranged on one side of the blade and perpendicular to the ground, and the distribution number of the side-pulling supports is corresponding to the number of blade loading points; the testing apparatus is provided with at least a power plant, and the power plant loads static forces on sectionalization test parts of the blade by the plurality of side-pulling supports; the height of a fixed pulley on each side-pulling support can be adjusted with the height of the blade loading point, and the position of each side-pulling support can be flexibly moved according to different blade loading positions. The testing apparatus disclosed by the invention can adapt to tests on different-sized blades, and the blade loading points and the fixed pulleys are always in horizontal positions, therefore, a situation that forces transferred to the blade loading points through pulling a rope are always in the horizontal direction is ensured, and real and reasonable test data are obtained, thereby achieving a test effect on multi-point loading in static tests.

The invention discloses an oil-electricity hybrid power vertical lifting fixed wing long-endurance unmanned aerial vehicle which is of three-body parallel arrangement, so that a vehicle body has a relatively large loading space, and with the combination of an inclination mechanism and an oil-pneumatic variable-distance mechanism, relatively high pneumatic efficiency and relatively large carrying capability are achieved. In the takeoff, cruising and landing process of the unmanned aerial vehicle, main vertical lifting force in a vertical lifting period is provided by a first fuel power inclination variable-distance system and a second fuel power inclination variable-distance system, auxiliary vertical lifting force in the vertical lifting period is provided by a first lifting force electromotor and a second lifting force electromotor, and with the combination of the four power systems, posture adjusting moments for pitching and transverse rolling are provided. Due to adoption of the fuel power inclination variable-distance systems, relatively high thrust force and very high pneumatic efficiency are achieved, and different pneumatic effects expected by propellers in the vertical lifting and horizontal cruising process can be completely met through variable distances. Relatively high pneumatic efficiency and relatively good capability can be finally achieved, and a relatively longendurance time is achieved.

A tandem wing aircraft having a fore wing, an aft wing, and a middle wing, attached relative to the aircraft and each other such that the middle wing provides a substantial portion of the total lift at landing speeds, and a minimal portion of the total lift at cruise speeds. At cruise speeds, induced drag is minimized, permitting higher speeds, greater fuel efficiency, and / or greater payload. Advantageously, the wing loading at cruise speeds is higher providing better passenger comfort while still providing controllability and safety at landing speeds.

A static test loading method for long straight wings of a small unmanned air vehicle is characterized in that: a loading device includes wing chordwise tie belts (2), wing spanwise tie belts (4) which can constraint spanwise movement of the wing chordwise tie belts (2), wing loading point hanging rings (8) which are located on the wing chordwise tie belts (2), a locking device (3) which is located between a left wing and a right wing and under the wings and connects the spanwise tie belts (4) of the left wing and the right wing, and loading sandbags (7). According to the method, a tie belt frame design can be adopted, and a plurality of chordwise high-strength tie belts and spanwise high-strength tie belts constrained on a surface of the wings can form an outer load transmission frame, so that the weight of the loading sandbags can be converted into the load of the wings of the air vehicle, and the method can be used for static test loading of a structure. The loading method and device are easy to use, are reliable in loading, are low in cost, are good in adaptability, and can be used for static tests of various medium-sized unmanned air vehicles and various small unmanned air vehicles.

The invention provides a double-ridged horn antenna based on specially-shaped ridge loading. While the matching characteristics in the working frequency band of the double-ridged horn antenna are ensured, the gain radiation characteristics of the antenna are enhanced. The antenna comprises two oppositely-arranged specially-shaped ridge plates, a horn shell, a back cavity and two feed coaxial lines, wherein each specially-shaped ridge plate comprises a back cavity matching section and a specially-shaped transition section, and the ridge line of the specially-shaped transition section is formedby two exponential curve sections and three arc sections in smooth connection; the horn shell adopts a rectangular horn structure formed by a pair of curved surface metal walls and a pair of plane metal walls in a mutual splicing mode; the two specially-shaped ridge plates are loaded to different curved surface metal walls; the back cavity adopts a cuboid thin wall structure; and the shielding layer of the feed coaxial line is connected with the back cavity, and the inner core passes through the sealing end of the back cavity to be connected with the back cavity matching section. The double-ridged horn antenna based on specially-shaped ridge loading has an ultra wide working frequency band, and can be applied to fields such as communication, remote sensing and antenna measurement.

The invention discloses a wing load applying device, belongs to the technical field of airplane structure tests, and is applicable to application of a load to the surface of a wing under a condition of large deformation. The wing load applying device comprises a framework, a connection bolt, an actuator cylinder, a telescopic device, a load sensor and pulling plate bolts, wherein a double-lug joint is arranged at the bottom of the framework; a bottom end single lug joint and a top end single lug joint are arranged at two ends of the actuator cylinder; the framework and the actuator cylinder penetrate through the bottom end single lug joint and the top end single lug joint so as to be movably connected through connection bolts; the telescopic device and the actuator cylinder penetrate through the top end single lug joint through the pulling plate bolts so as to be movably connected; the telescopic device penetrates through the framework and is movably connected with the load sensor. According to the load applying device, the actuator cylinder can be retracted and shortened to apply a downward stretching load to the lower wing surface of the wing and also extend to meet the upward large deformation of the wing; meanwhile, the wing load applying device is easy and convenient to manufacture and mount, low in manufacturing cost and convenient for load application control; the load application control precision is improved, and generation of an impact load is effectively avoided.

An aircraft is disclosed, the aircraft having a fuselage having a centerline, and a wing extending from the fuselage and having a leading edge and a trailing edge. Additionally, the aircraft includes an engine mounted to the wing and having a rotating output shaft, and a propeller operably coupled to the output shaft and generating a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft. The propeller is located forward of the leading edge of the wing, so the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having corresponding localized areas of reduced chord length to neutralize the otherwise increased wing loading. A method of countering the aerodynamic effects of propeller wake acting on a wing is also disclosed.

The invention provides a loading device suitable for static test of composite wings. The loading device suitable for static test of composite wings comprises a main bearing crossbeam, upper and lower beam connecting plates, loading centers, wing loading pads and test loading applying plates. The loading device suitable for static test of composite wings is characterized in that an integral frame is formed by the main bearing crossbeam, the upper and the lower beam connecting plates, and the loading centers; the concentrated load from the test load applied to the plate is changed into several small concentrated loads and a load block is loaded from the wing contacting the load thimble, and a plurality of small concentrated loads are distributed into a uniformly distributed load to the wing skin. The loading device suitable for static test of composite wings adopted is capable of changing the normal tensile load applied to the wing into a localized load on the skin, and the delamination problem caused by too large local tension of composite materials is avoided, meanwhile, because of the flexibility of each component connection, the loading device suitable for static test of composite wings can be loading applying in the static test load for a plurality of airfoils and a plurality of loading points.

The invention discloses a light loading and unloading method for a cold chain transport vehicle. The method comprises the steps that a hydraulic cylinder is started to push a movable door to be overturned until a movable upper door makes contact with the ground; split charging boxes are unloaded from a loading carriage and pushed to the position beside products to be subjected to cold chain transportation; the products are placed in the split charging boxes and then the split charging boxes are pushed to the movable upper door; a horizontal bar is fed to the deepest position of the loading carriage along a guide rail first; then the split charging boxes are sequentially fed to the upper surface of the movable upper door one by one; steering pulleys of the split charging boxes are aligned with digging grooves; then the split charging boxes are pushed; the split charging boxes sequentially pass through a slope and the digging grooves to enter the movable upper door; the multiple split charging boxes are arrayed into a row on the movable upper door; a hand protecting sponge on the horizontal bar is pushed manually until buffer springs on the cross bar make contact with the split charging boxes; and the hydraulic cylinder is started to push the movable door to be overturned until a movable lower door is in a horizontal state. According to the light loading and unloading method for the cold chain transport vehicle, quick loading and unloading and light loading and unloading of cold chain transportation are achieved.

The invention discloses a device capable of performing a self-positioning multi-angle loading aging test on multiple torsional springs. The problem that an existing device cannot meet the requirementfor a small batch of testing is solved. Eccentric through holes (7) are formed in a hinge pin head (6), eccentric pin insertion holes (19) are arranged in the same circumference on the end face of theouter side of a left support baffle (1) at equal interval radian, eccentric pins (8) run through the eccentric through holes to be inserted into the eccentric pin insertion holes, a pin shaft rod (5)between the outer side face of a right support baffle (2) and a check ring (10) is sleeved with a compressed spring (9), an F-shaped switching plate (13) is clamped to an F-shaped switching plate clamping positioning table (12) through an end clamping opening in the F-shaped switching plate, a pin shaft rod between the left support baffle (1) and the F-shaped switching plate is sleeved with a torsional spring, the left end of the torsional spring is inserted into a torsional spring left end insertion hole (15), and the right end of the torsional spring is clamped to the F-shaped switching plate. The loading aging testing efficiency is improved, and the test cost is saved.