6 results about "Wing loading" patented technology

This invention discloses a loading device for simulating a telescopic wing transmission mechanism, comprising a telescopic wing motion simulation mechanism and a telescopic wing loading mechanism. The telescopic wing motion simulation mechanism includes a fixed base, a motor, a movable wing, and a linear bearing. The fixed base and the linear bearing are fixedly installed on a base platform. The motor is installed on the fixed base and drives the movable wing through a transmission mechanism. The movable wing is slidably installed on the linear bearing. The motor drives the movable wing to perform reciprocating linear motion along the linear bearing to simulate the extension and retraction process of the wing. The telescopic wing loading mechanism includes two sets of loading units respectively arranged on the extension side and the retraction side of the movable wing's movement stroke. Each set of loading units includes a fixed frame, a tray-pulley system, a hoist, and a load. The fixed frame is installed on the base platform, and the load is placed on the tray of the tray-pulley system. The tray-pulley system is connected to the movable wing through a steel cable.

A High Altitude Pseudo Satellite (HAPS) aircraft is disclosed for maintaining the span-wise shape of the wing and maintaining total bending and torsion loads. The aircraft including at least one aeroelastic span loaded fixed wing having an aspect ratio greater than 15 and wing loading less than 6 kg / m2, the wing having a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the center of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, and sensors which determine the amount of lift at points or regions along the wing span, the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the absolute speed and roll and pitch angle of the wing.

A high-altitude pseudo satellite (HAPS) aircraft having aeroelastic span loaded fixed wing(s) 1, aspect ratio greater than 15, wing loading less than 6 kg / m², and spoilers 6’ distributed across the wi

The utility model discloses a fixed-wing unmanned aerial vehicle capable of quickly dismounting and replacing wings, and relates to the technical field of fixed-wing unmanned aerial vehicles, the two wings are arranged on the left side and the right side of a vehicle body in a bilateral symmetry manner, mounting seats are fixedly arranged at the roots of the wings and cover the side wall of the vehicle body, and a connecting sleeve is fixed on a side plate of the vehicle body in a penetrating manner; the connecting plate is fixedly arranged on the mounting base, the connecting plate movably penetrates through the connecting sleeve, the positioning sleeve is fixedly arranged on the lower surface of the interior of the machine body, and the positioning rod movably penetrates through the connecting plate and is movably inserted into the positioning sleeve; the supporting and guiding mechanisms and the single-point positioning and locking structures are arranged on the wings and the aircraft body, and the corresponding energy storage structures are arranged, so that the assembly and disassembly operation of the wings can be quickly completed.

The invention relates to a folding wing dynamic loading device, and belongs to the field of folding wing loading tests. Comprising two wings, a mechanism bracket, a bottom plate, a supporting wheel assembly and two groups of loading mechanisms, wherein the bottom plate is of a flat plate-shaped structure which is horizontally arranged; the supporting wheel assembly is arranged at the bottom of the bottom plate to support and move the bottom plate; the mechanism support is vertically installed on the side edge of the upper surface of the bottom plate. The two wings are horizontally and symmetrically mounted below the mechanism bracket; the upper surfaces of the roots of the two wings are installed on the top of the mechanism support through a U-shaped frame. The two groups of loading mechanisms are symmetrically mounted on the upper surface of the bottom plate; each group of loading mechanism corresponds to one wing; each group of loading mechanism is connected with the corresponding wing to realize triaxial dynamic loading of the corresponding wing; loads are applied to the missile wing through the loading device according to the sequence that the loads change along with the unfolding position, and the dynamic load borne by the missile wing in the unfolding process is simulated.

The invention discloses a wing folding mechanism of a wing upper anticonfiguration aircraft, and belongs to the field of aircraft design. The unmanned aerial vehicle comprises folding wings, folding wings, inter-wing torsion springs, locking pin springs, locking pins, a wing loading platform, fixing bolts, upper counter locking pin springs, upper counter locking pins, supporting rods, side plates, upper counter tension springs and sliding supporting rods. Interference during folding of the wings of the large-wingspan aircraft is avoided through upper and lower layering of the wings, the wings with dihedral angles are rotated to be placed horizontally through the sliding platform, the storage space is reduced, the wings are rapidly unfolded after leaving a launch canister through the torsional springs arranged in the wings, locking is conducted through the locking pins, and the aircraft can be rapidly put into use. According to the invention, the wing is quickly unfolded and locked by adopting an upward-reversing and unfolding step-by-step limiting structure mode; by adopting the mode of combining the upper back locking and the tension spring, the folding process is simplified, the complexity of the folding mechanism is reduced, and the storage space after folding can be reduced.