37results about How to "Improved aerodynamic stability" patented technology

A finless projectile provides improved ease of use, aerodynamics, muzzle velocity, drag, target, and excursion accuracy, structural integrity, terminal effectiveness and safety, at lower cost. The finless projectile includes a slug, a forward projectile body, an aft projectile body, an obturator, and a pad. The finless projectile is a full bore projectile that defines a hollow core, but does not include a sabot nor does it carry explosives. The finless projectile functions by kinetic energy transfer from the projectile to the target by deforming the target. The center of gravity of the finless projectile is forward of the center of pressure to provide static stability to the finless projectile.

A vane placement of compressor for improving its pneumatic stability and avoiding the rotational stall features that the front ends of the vanes in same row are alternatively and axially arranged in back-and-forth direction. The staggered size is the 5-15% of the axial chord of each vane. The variation range of axial installation angle of the vane moved backward is 0 - -3 deg.C.

A ballistically launched foldable multirotor vehicle has a central body frame. A battery is located in an upper vertical location of the vehicle and positions a center of mass of the vehicle to provide aerodynamic stability during a launch. Fins are attached to the central body frame such that aerodynamic forces on the fins shift an aerodynamic center (AC) of the vehicle downward below the center of mass of the vehicle. Three or more foldable arms are attached to the central body frame via a hinge and exist in two states—a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis. Rotors mounted to each foldable arm are controlled by a motor to enable flight.

A solid projectile for a firearm having a central cylindrical section defining a bearing surface and an integral, coaxial leading section tapered into a uniform conical surface, the apex at the distal end thereof projecting to a point or apex. The apex angle of the conical surface of the leading section of the projectile is within the range of 20°-40° of arc.

The present disclosure relates to a method for improving aerdynamic stability of a working fluid flow through a compressor of a turbomachine, in particular through a compressor of gas turbine used for power production, particularly against rapidly changing aero speed of the compressor. The method comprises to introduce a first water mass flow to the working fluid flow of the compressor. Furthermore, the disclosure relates to a turbomachine, in particular a gas turbine, which can be driven according to the above method.

The invention relates to a ground-anchored-self-anchored suspension combined system bridge which belongs to the technical field of constructional engineering and particularly relates to a design of a long-span bridge under a complex geologic condition in bridge engineering. The ground-anchored-self-anchored suspension combined system bridge is characterized in that after a tower and a lateral hole pier are constructed, a concrete main girder of a cable-stayed bridge begins to be assembled through a cantilever; after the cantilever is assembled to a lateral hole, a main cable is suspended, one end thereof is anchored on a permanent anchor block, the other end thereof is anchored on a concrete girder external anchor block, and the anchor blocks are pulled on a temporary anchor through temporary anchor cables; the end of a main girder provided with the permanent anchor block is horizontally supported on a bridge abutment; each segment of a main steel girder in a span is hoisted through a cable crane; after folding, the temporary anchor cables are dismantled in batches, and the main cable is completely anchored at the end part of the main girder to finish the system switching from the temporary anchor to a self-anchor. The invention has the effects and advantages that material performance is fully exerted, and by aiming at the complex geologic condition, the huge anchor is saved, the construction cost is lowered, the construction period is shortened, and the risk in the construction process is reduced.

A system for improving the performance of a powered boat that includes both methods and apparatuses that provide a powered boat means to stabilize, control, and optimize the powered boat's performance when the powered boat is in powered motion. The system provides capabilities of enhancing the powered boat's performance by responding to both aerodynamic and hydrodynamic effects upon the powered boat when the powered boat is in motion. Some embodiments of the system are capable of altering its means of response to aerodynamic effects while the powered boat is in powered motion, other embodiments are capable of altering the powered boat's response to hydrodynamic effects while the powered boat is in powered motion, and still other embodiments are capable of altering the powered boat's response to both aerodynamic and hydrodynamic effects while the powered boat is in powered motion. Certain embodiments of the system are capable of utilizing aerodynamic elements that operate on the air stream flowing within a tunnel formed within a multihull of a powered boat, while other embodiments are capable of mitigating the effects of water impacts upon the roof of a tunnel formed within a multihull powered boat. Still other embodiments are capable of responding to aerodynamic effects by interacting with portions of the air stream that passes above the boat while mitigating the potential for negative effects due to cross-winds impacting the structure which rises above a deck of the powered boat.

The invention aims to provide a control method of a titanium alloy compressor tip clearance. The control method is characterized in that an abradable sealing coating is sprayed on the inner wall of acasing; tips of rotor blades are compositely electroplated with a Ni/c-BN coating; and the abradable sealing coating and the Ni/c-BN coating are used as a pair of abradable sealing friction pair, thereby forming a novel gas circuit sealing coating structure. In the operation process of an engine, the tips of the rotor blades can cut into the abradable sealing coating on the inner wall of the casing, thus grooves capable of improving the sealing effect are reserved, ideal radial airflow gaps are formed, and the maximum pressure difference is obtained, so that the power of the engine is remarkably improved, the consumption of aviation kerosene is reduced, and the one-time test run percent of pass of the whole engine is improved.

The invention discloses a composite wing unmanned aerial vehicle and an aerodynamic balance method. The composite wing unmanned aerial vehicle comprises a fuselage, wings located on the two sides of the fuselage, a main rotor located at the front end of the fuselage and auxiliary rotors installed on the wings. The unmanned aerial vehicle further comprises a pneumatic balance mechanism, the pneumatic balance mechanism comprises an air chamber installed on the vehicle body and drainage pipes connected to the air chamber, every two drainage pipes form a group, and each group of drainage pipes comprises a left drainage pipe and a right drainage pipe which are located on wings on the two sides of the vehicle body correspondingly. The controllability of the unmanned aerial vehicle is improved, and the use safety of the unmanned aerial vehicle is improved.

The invention discloses a miniature fixed-wing unmanned aerial vehicle with a belly adsorbed on a wall surface, which comprises a main wing, a vector power system, a pneumatic control surface, a vertical fin, an adsorption-separation system and a belly equipment bin, wherein the adsorption-separation system is mounted on the middle upper side of the belly; the adsorption-separation system comprises bionic adsorption dry glue and a separation servo mechanism; the bionic adsorption dry glue is laid on the outer side of the belly in the front-back direction of the main wing and is used for adsorbing a wall surface; two sets of separation servo mechanisms are symmetrically mounted on two sides of the belly and are used for realizing separation of the bionic adsorption dry glue from the wall surface; and the separation servo mechanism comprises a wall separation servo steering engine, a wall separation cam and a wall separation rocker arm. After the unmanned aerial vehicle flies to a preset site for a long distance, low-power-consumption long-time adsorption on a vertical wall surface can be realized, a reconnaissance task can be executed in the adsorption process, and the unmanned aerial vehicle is separated from the wall surface and returns after being completed.

The invention discloses an airship comprising an airship body; The airship body comprises opposite upper ball crown part and a lower ball crown part, wherein the bottoms of the upper ball crown part and the lower ball crown part are sealingly connected so that the profiles of the airship is dish-like. The camber of the upper ball crown is larger than that of the lower ball crown so that the airship body has a positive curved dish profile. According to the airship of the invention, the dish-like design is adopted so as to reduce wind resistance in all directions during flight and increase the profile lift of the airship, therefore saving power consumption.