7 results about "Aeroshell" patented technology

The invention belongs to the technical field of aerospace equipment, and particularly relates to a mechanical gripper used in a weightless environment. The mechanical gripper comprises a machine shell (1), a plurality of finger assemblies (2) and at least one power assembly (3). The power assembly (3) drives the pull rope (22) to be tightened and the finger assemblies (2) to overcome the elastic force of the torsional spring, so that the space occupied by storage of the mechanical gripper after compression is saved, and the mechanical gripper can complete the gripping action. And when the pull rope (22) is driven by the power assembly (3) to be in the relaxed state, the finger assemblies (2) are in the stretching state under the elastic reset action of the torsional springs so as to prepare to execute the grabbing action. Therefore, the size of the mechanical gripper is reduced, the use convenience is improved, and the mechanical gripper is easier to use when a spaceflight task is executed.

A kind of hydraulic pump shell based on electrical discharge machining includes cylinder wall, flange, mounting convex column, mounting screw hole, transmission shaft hole, shaft hole boss, cylinder bottom, flange hole, hydraulic control cylinder body, control liquid channel, bottom arc slot A, bottom arc slot B, bottom arc slot C, bottom arc slot D, milling port, cylinder inner wall strip groove, control return spring seat hole, control piston hole;Its characterized in that: the cylinder wall inner wall is equipped with cylinder inner wall strip groove;The cylinder bottom inner wall is equipped with bottom arc slot A, bottom arc slot B, bottom arc slot C, bottom arc slot D;Beneficial effect is: can promote the stability of aviation hydraulic system;Improve the quality and service life of aviation hydraulic pump;Beneficial to the energy saving of aviation aircraft, reduce failure rate, improve the production efficiency of aviation hydraulic system, promote flight endurance, improve the flight efficiency of aircraft;Promote the development of China's aviation industry.

An aircraft includes a fuselage and a wing, at least one hydrogen fuel tank and a fuel line configured to delivery fuel from the fuel tank to the engine. The fuel tank is installed externally of the fuselage and wing, and comprises an external aeroshell containing a plurality of pressure vessels configured to contain pressurised fuel therein.

The utility model provides an aero-engine EMU airborne monitoring device. The aero-engine EMU airborne monitoring device comprises a casing, an EMU electronic component board card, a heat conduction block and a first electric connector. The machine shell comprises a box body and an upper cover, and the upper cover is assembled on the box body; the EMU electronic component board card is arranged in the box body; the heat conduction block is arranged in the machine shell and located between the EMU electronic component board card and the inner wall of the machine shell, the upper surface and the lower surface of the heat conduction block are attached to a heating component on the EMU electronic component board card and the inner wall of the machine shell respectively, and the heat conduction block is used for conducting heat generated by the EMU electronic component board card to the machine shell. And the first electric connector is arranged on the side wall of the box body and is electrically connected with the EMU electronic component board card. Compared with the prior art, the airborne monitoring device for the EMU of the aero-engine provided by the utility model has the advantages that the overall weight can be reduced, the weight index can be better met, and the airborne monitoring device has good heat dissipation capability.

This invention discloses an aircraft with a folding and locking mechanism, belonging to the field of unmanned aerial vehicle (UAV) technology. The device includes a mounting housing and a self-locking mechanism and a locking mechanism located inside it. The self-locking mechanism has a supporting rotating shaft connected to the arms via a driven gear. The locking mechanism includes a corrugated expansion tube connected by a fairing and a flexible hose. The corrugated expansion tube drives a wedge-shaped pusher with a toothed lower end; the wedge-shaped pusher engages with a sliding rack, which is connected to the driven gear. Rotating a knob on the top of the housing drives a rotating disk, whose inclined top column simultaneously lifts all the wedge-shaped pushers. This invention, through a purely mechanical structure, utilizes the airflow pressure during flight to drive the corrugated expansion tube, causing the wedge-shaped pushers to press down and push the rack to slide, thereby automatically folding and locking the gears and arms to adaptively adjust the wind-receiving area and enhance wind resistance stability; all arms can be simultaneously unlocked by rotating a single knob, enabling rapid manual folding.

The invention relates to a spaceflight extravehicular screw mounting state detection tool, and belongs to the field of extravehicular operation and maintenance of spacecrafts and astronauts. Comprising a handle, a positioning detection assembly, an in-place indication assembly, a locking and unlocking assembly, a machine shell and an installation screw assembly. During use, an astronaut grabs the handle to make the positioning detection assembly go deep into the mounting screw assembly, and the in-place indication assembly can have three states of not stretching out completely, rebounding after stretching out and not rebounding after stretching out through the elastic force effect of a spring in the mounting screw assembly, and the three states correspond to the three states of completely tightening a screw, not completely tightening / unscrewing the screw and completely unscrewing the screw respectively. When the tool detects that the screw is completely unscrewed and locked, locking can be unlocked by operating the locking and unlocking assembly, and the next screw continues to be detected. The tool can greatly improve the operation efficiency and safety of astronauts.

The present invention relates to a casing intended to be externally applied, connected or fixed to the fuselage or to a wing of an aircraft or to a central or wing station / hardpoint of an aircraft, the casing entirely or partly delimiting a housing zone (HZ) of a super-orbital, orbital or sub-orbital launch vehicle.