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.

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 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.

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 invention relates to an architectural structural system, in particular to the structural system used for an ocean platform. A swing wall structural system comprises a main body piece, a connecting piece and a swing wall body. The bottom end of the main body piece is fixedly arranged on a ground base, the connecting piece is connected with a lateral surface of the main body piece and a lateral surface of the swing wall body respectively in a hinged mode, and the bottom end of the swing wall body is connected with the ground base in a hinged mode. The swing wall structure is capable of increasing the ability of a tube and frame type ocean platform structure to entirely resist an external load, greatly increasing abilities to resist the ice loading, the wave loading, the wind loading and the earthquake load, even the tsunami (lessons of the tsunami caused by a big earthquake in Japan in 2011 are painful and the ocean platform structure cannot be destroyed because of the destruction of a regional rod piece.

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.

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 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 self-positioning multi-angle loading aging test device for multiple torsion springs, which solves the problem that the existing devices cannot meet the requirements of small batch testing. An eccentric through hole (7) is arranged on the pin shaft head (6), and an eccentric pin insertion hole (19) is arranged at equal intervals on the same circumference on the outer end face of the left bracket baffle (1), and the eccentric pin ( 8) Insert it into the eccentric pin insertion hole after passing through the eccentric through hole, and a compression spring ( 9), the F-shaped shift plate (13) is clamped on the F-shaped shift plate clamping positioning platform (12) through the terminal bayonet on it, and the gap between the F-shaped shift plate and the left bracket baffle (1) A torsion spring is sleeved on the pin shaft bar, and the left end of the torsion spring is plugged in the insertion hole (15) of the left end of the torsion spring, and the right end of the torsion spring is clamped on the F-shaped dial. The efficiency of loading aging test is improved, and the test cost is saved.