30results about How to "Little impact on structural strength" patented technology

The invention relates to a sealing and riveting tool and a sealing and riveting method applicable to a composite vertical tail wing box of an airplane. According to a technical scheme in the invention, the sealing and riveting tool is such structured that a handle is connected with an extension tube; the extension tube is connected with a magnetic chuck; one end of a wind pipe is connected with awind-controlled switch, and the other end of the wind pipe passes through the handle and the extension tube and then communicates with the magnetic chuck; and an endoscope lens is mounted on the magnetic chuck and is connected with a display screen through a wire. As the sealing and riveting tool is employed for sealing and riveting of the composite vertical tail wing box of the airplane, a fastener can be inserted into a pre-drilled fastener hole in the enclosed wing box under the guidance of the endoscope lens, and then the wind-controlled switch on the wind pipe is turned on so as to fix stringers and / or angular pieces in an enclosed box section via the fastener. According to the invention, the assembling sequence of the wing box is rationally formulated, an endoscope is cooperatively used for observation and is manually hand-held, and the installation of fasteners between stringers and angular pieces is realized through an inherent lightening hole in the wing box, so engineering requirements are met.

The invention relates to a front cover structure for a railway vehicle head. The front cover structure comprises a front cover mounted at the head part of a vehicle body, and the front cover is divided into a plurality of pieces which are fixedly connected together through connecting structures. The front cover structure is simple and practical in integral structure, the front cover is divided into a plurality of pieces and then is sewn, and the strength of the connecting structures among the pieces is controlled, so that the local tearing strength of the front cover made of glass fiber reinforced plastics and the structural failure deformation process under the crashing condition are effectively controlled, the tearing failure is achieved according to the design requirements in the crashing process, the tearing part is bent by the crushing force according to the design requirements, the structure doesn't damage distribution and stretching of fiber in a glass fiber reinforced plastic body, the performance of the glass fiber reinforced plastics is reserved, small influence is produced on the integral structure of the glass fiber reinforced plastic body, the design only affects the strength of local glass fiber reinforced plastics according to the working condition requirements, tearing is performed step by step according to the design requirements after crashing, and the safety design and car coupler hanging requirements are met.

The present invention provides a vertical axis magnetic levitation tidal current energy generating device and method combined with offshore horizontal axis wind turbine towers, including a central unit, a magnetic levitation rotor unit and a support unit, wherein the central unit includes a horizontal axis wind turbine unit Pile tower and stator winding, the single pile tower is fixed on the seabed, the stator winding is sleeved on the outer wall of the single pile tower; the magnetic levitation rotor unit is suspended around the annular stator winding under the action of the support unit The supporting unit is a closed-loop track with a T-shaped cross section, which is correspondingly arranged under the magnetic levitation rotor unit, and is fixed on the seabed around the monopile tower. When the sea tide rises and falls, the sea current pushes the blades to rotate, which makes the poles of the permanent magnets in the rotor unit rotate. At this time, the stator winding installed on the outer wall of the single pile tower of the wind turbine converts the kinetic energy of the tidal current into electrical energy by cutting the rotating magnetic induction lines. This invention increases the tidal current energy under the sea to generate electricity on the basis of the existing offshore wind power generation system. The method effectively improves the comprehensive utilization rate of offshore energy.

The invention discloses a motor-driven aircraft hardpoint sealing mechanism, which comprises a casing (1), on which hanger holes (12) are opened, and outer bottom surfaces of the casing (1) are respectively installed with A sealing plate (9) that can rotate with it, the sealing plate (9) is located on both sides of the hanger hole (12), and a stepping motor that drives the sealing plate (9) to rotate is installed on the inner surface of the housing (1) (2) and the through-beam infrared sensors (4) positioned on both sides of the hanger hole (12). The invention is simple in structure and easy to use. When the hanger is installed, the ground personnel will open the sealing plate through a switch, and then the sealing plate will remain in the open state. It is necessary to reserve space for the sealing plate inside the shell. The plane size of the sealing mechanism and the corresponding skin opening are small, only slightly larger than the size of the pylon, which has little impact on the structural strength of the aircraft.

The invention discloses a large-span cross aisle building method applied to segmental lining tunnels. A plurality of rings of tunnel linings are sequentially dismounted at the joint portions of a built large-span cross aisle in the designing direction, expanded excavation is conducted outwards every time the tunnel linings are dismounted, then primary lining structures in a closed loop in the cross section direction at the crevasses are constructed in time after expanded excavation, secondary tunnel linings of a main tunnel and the large-span cross aisle are constructed under protection of primary lining, and building safety of the joints of the large-span cross aisle is ensured.

The invention discloses a near-space propeller with a propeller tip actively blowing air, and belongs to the field of propeller design. The propeller includes an air pump, an airflow duct, an air blowing port, an air intake port, an acceleration sensor and a control circuit. The air pump is located in the propeller hubs on both sides of the propeller shaft, the acceleration sensor and the control circuit are located inside the propeller hub, and the airflow duct is located in the propeller. Inside the blades on both sides of the propeller hub, air blowing ports are respectively provided on the lower surfaces of the propeller tips at both ends of the propeller, and air inlets are respectively provided on the windward surfaces of the propeller hub on both sides of the propeller shaft. The air outlet end of the air pump is communicated with the air inlet end of the air flow conduit, the air outlet end of the air flow conduit is communicated with the air blowing port, and the control circuit is electrically connected with the two air pumps and the acceleration sensor respectively. The propeller provided by the present invention effectively weakens the strength of the propeller tip vortex by setting the blowing power coefficient of the blowing port when blowing air, so as to achieve the purpose of increasing the pulling force and improving the efficiency.

The invention discloses an aircraft hardpoint sealing mechanism driven by springs. The aircraft hardpoint sealing mechanism comprises a casing (1), wherein a positioning ring (11) vertically extends upwards from the upper top surface of the casing (1), two sealing plates (5) which can be mutually connected in an abutting manner, springs (6) for driving the sealing plates (5) to close and handles (8) through which the sealing plates (5) can be opened are arranged in the positioning ring (11), and a lower hole (10) corresponding to the sealing plates (5) is formed in the middle part of the casing (1); a cover plate (4) is fixed on the positioning ring (11), and an upper hole (12) corresponding to the lower hole (10) is formed in the cover plate (4). The aircraft hardpoint sealing mechanism disclosed by the invention is simple in structure andconvenient to use, after the aircraft hardpoint sealing mechanism is closed, the casing and the sealing plates are completely flush with the outer surface of an aircraft and not protruded out of the surface of the aircraft completely, and aerodynamic performances of the aircraft are not influenced.

The invention provides an arm support device for engineering machinery, comprising a first joint arm and a second joint arm, and a first joint shaft and a second joint shaft, the first joint shaft and the second joint shaft are cross-fixed and The axes of the two are perpendicular, the two ends of the first coupling shaft are respectively rotatably mounted on the first joint arm, and the two ends of the second coupling shaft are respectively rotatably mounted on the second joint arm; The first driving mechanism, the first driving mechanism can drive the first joint arm and the first coupling shaft to rotate relatively; the second joint arm is equipped with a second driving mechanism, and the second driving mechanism can drive the second joint arm and the second coupling shaft relative rotation. The invention also provides a construction machine. The technical solution provided by the invention adopts the imitation universal joint transmission mode, and has a simple structure. The boom can swing in the vertical direction and / or horizontal direction, and the flexibility of fabric distribution is greatly improved. When rotating in a small range, there is no need to start the turntable, which saves energy. consumption.