30results about How to "Lower centroid height" patented technology

The invention discloses an embedded type cabin section axial horizontal butt joint device which comprises a bottom support frame, a horizontal guide rail, an angle brace, a first cabin section mounting frame, a first embedded cabin section support module, a second embedded cabin section support module, a ball screw mechanism and a second cabin section support module, wherein the first cabin section mounting frame is used for installing a first cabin section; the first embedded cabin section support module and the second embedded cabin section support module are used for supporting an embedded type cabin section in a way of cooperation and adjusting the height of the embedded type cabin section so as to guarantee an interface of the embedded type cabin section to be aligned with an interface of the first cabin section; the ball screw mechanism is used for driving the two support modules to support the embedded type cabin section together to enable the embedded type cabin section to move closely to the first cabin section so as to complete axial horizontal butt joint, and is used for driving a second cabin section arranged on the second cabin section support module to move closely to the first cabin section so as to complete the axial horizontal butt joint of the three cabin sections. The invention also provides an embedded type cabin section axial horizontal butt joint method. After the device and the method are adopted, radial small-gap embedded type cabin section butt joint can be realized; the device and the method are convenient to operate and high in work reliability.

The invention belongs to the technical field of specific vehicle chassis, and particularly relates to a low independent suspension of a specific vehicle chassis. The suspension is formed by connecting two or more sets of independent suspension subunits in series through pipelines. Each independent suspension subunit comprises an upper cross arm, a lower cross arm, a hydro-pneumatic spring A, a limiting block and a steering knuckle, wherein one end of an upper supporting lug of the hydro-pneumatic spring A is connected with a frame, one end of a lower supporting lug of the hydro-pneumatic spring A is connected with the lower cross arm, the upper cross arm is connected with the frame and the steering knuckle, the lower cross arm is connected with the frame and the steering knuckle, and the limiting block is connected with the frame and located above the upper cross arm. By the adoption of the low independent suspension of the special vehicle chassis, the requirements of a new generation cross-country military vehicle for high maneuverability and high cross-country ability can be met, and handling stability and driving safety of the vehicle are improved.

The invention provides an electric vehicle as well as forecabin arrangement structure and method. In the invention, the forecabin arrangement structure of the electric vehicle comprises a power assembly system which comprises a driving system and a range extender system, wherein the driving system is fixed through adopting three-point suspension in a forecabin; and the suspension points pass through the gravity centers of a motor and a speed reducer. According to the invention, the left-side space of the forecabin can be effectively utilized in a maximum range to ensure that enough right-sidespace can be left for the design of the distance-increasing equipment.

The invention provides a satellite casing and a satellite using the same. The satellite comprises the satellite casing and an optical load, wherein the satellite casing comprises a casing main body; the casing main body comprises a first end surface, a bottom end surface opposite to the first end surface, and a second end surface; the bottom end surface is used for being connected with an external component, the second end surface and the first end surface are both positioned on the same side of the bottom end surface, and a distance from the second end surface to the bottom end surface is smaller than that from the first end surface to the bottom end surface; and the optical load is arranged on the second end surface. The satellite casing and the satellite, disclosed by the invention, have the advantages that the vibratory response of the satellite can be reduced when a powered phase is launched, and the large visual field requirement of the optical load can also be satisfied.

The invention relates to a double-chamber hydragass spring which comprises an upper lug, a lower lug, a main cylinder, an elastic component, a back pressure cylinder, a piston, a guide pipe and the like, wherein the upper lug is positioned at the upper part of the main cylinder; the lower lug is positioned at the lower part of the back pressure cylinder, the upper lug and the main cylinder are connected through a thread structure, and the lower lug and the back pressure cylinder are connected through a thread structure; the upper lug and the lower lug are both provided with a bearing internally; the side part of the upper lug is connected with the elastic component; and the piston and the guide pipe are installed in the back pressure cylinder. The double-chamber hydragass spring is characterized in that the back pressure cylinder, the piston and the guide pipe are connected into a whole and installed in the cylinder body of the main cylinder; a main cavity is formed by a space among the upper surface of the piston, the main cylinder and the space below the upper lug; a main air chamber is formed by the main cavity, an elastic component oil liquid chamber of the elastic component and an air chamber; a back pressure air chamber is formed by a back pressure chamber in the back pressure cylinder and a ring chamber positioned between the main cylinder and the back pressure cylinder; the back pressure chamber and the ring chamber are connected through a connecting pipe. The double-chamber hydragass spring has the beneficial effects of simple structure, small size, light weight, good tightness and large bearing tonnage and is convenient to arrange and install.

The invention provides a soft landing mechanism buffer for a landing probe, which is used for buffering the impact of the spacecraft. The invention is mainly composed of an outer cylinder, a metal tie rod, an inner cylinder, a cutter, a support plate, a support rod, etc., adopts a piston structure, and tightens the metal pull rod between the support rod and the support plate, and the metal pull rod can be located inside The center of the barrel or around the outer wall of the inner barrel. Another structure of the present invention is a buffer structure with bidirectional buffer function. The invention absorbs the impact energy through the yield deformation of the metal tie rod, is less affected by the space environment, has stable performance, reliable operation and compact volume.

The invention discloses a caterpillar track chassis of a sandbeach cleaning trolley. The caterpillar track chassis of the sandbeach cleaning trolley comprises a left caterpillar track rack, a right caterpillar track rack, a fuel tank, a trolley frame, a balancing beam and dampers, wherein the rear portion of the left caterpillar track rack and the rear portion of the right caterpillar track rack are hinged to the two ends of the fuel tank respectively, the front portion of the left caterpillar track rack and the front portion of the right caterpillar track rack are respectively provided with one damper, and the two ends of the balancing beam are arranged on the dampers on the two sides respectively; the middle of the front of the trolley frame is connected to the middle of the balancing beam, the two sides of the rear of the trolley frame are connected to the two sides of the fuel tank, and therefore the trolley frame are respectively connected with the fuel tank and the balancing beam in a three-point connecting mode. Due to the fact that the rear portion of the left caterpillar track rack and the rear portion of the right caterpillar track rack can swing up and down along shafts on the two side of the fuel tank, the left caterpillar track rack and the right caterpillar track rack can achieve terrain-simulating driving, vibration of the trolley is reduced, and the driving speed is greatly improved; besides, due to the fact that the fuel tank is arranged below the trolley frame, the mass center height of the whole trolley is lowered, and loads of the trolley frame can be reduced.

The invention provides a satellite-rocket unlocking device for separating stacked satellites from carrying in the technical field of spaceflight satellites, and the satellite-rocket unlocking device comprises a satellite-rocket connecting ring, a swing rod and multiple satellite layers, and the multiple satellite layers are stacked on the satellite-rocket connecting ring; the satellite-rocket connecting ring is provided with a pin structure through a reserved pin hole, one end of the swing rod is hinged to the pin structure, and the other end of the swing rod is provided with an unlocking assembly. When the satellite layers are stacked in a pressed state, the swing rod is tightly attached to the side walls of the satellite layers, the multiple satellite layers are connected with the adapters through unlocking pieces to keep the compressed state, and a pressing base and the uppermost satellite layer are arranged in a pressed mode. And when the satellite layers are converted to be in a loose state for stacking, the unlocking pieces are disconnected with the adapters, the pressing base releases the pressing arrangement with the satellite layers, and the swing rod rotates around the axis of the pin structure in the direction away from the satellite stack. The overall centroid height of the satellite group is reduced, the circumferential utilization rate of the carrying fairing is increased, the unlocking risk of the stacked satellite layer is reduced, and the unlocking efficiency and the design reliability are improved.

A rear suspension fork device for a motile multifunctional vehicle (SUV) is achieved by the following proposal: the upper side of the lower swing-arm of the present vehicle five-link suspension fork and the lower side of the vehicle frame longitudinal beam are respectively provided with a spring seat; the upper and the lower ends of the spring are respectively connected to the spring seat. The rear suspension fork device has simple and reasonable structure as well as easy processing, and can effectively lower the centroid height, increase the spring distance, and improve the operation stability and the drive security; the rear suspension fork device can be used by matching with various SUV vehicles so that the industrialized production can be achieved, and the rear suspension fork device can be used as the renewal product of rear suspension fork of existing SUV vehicles.

The invention discloses a high-stability supporting frame. The high-stability supporting frame comprises a main supporting body and an adjusting supporting frame, wherein the adjusting supporting frame is mounted at the top of the main supporting body. According to the high-stability supporting frame, starting from the two aspects of thermal stability and vibration stability, the supporting frame is made of a super-invar alloy with a low linear expansion coefficient to improve the thermal stability; and a plurality of groups of rectangular steel and rib plate structures with the wall thicknesses which are gradually reduced from bottom to top in the vertical direction are adopted to reduce the height of the mass center of the supporting frame and improve the rigidity of the supporting frame, so that the vibration stability is improved. According to the high-stability supporting frame, ANSYS software is adopted to carry out modal analysis and topological optimization on the supporting frame to obtain an optimal pure-rigidity supporting frame structure, and a prototype is manufactured; and the eigen frequency and the amplitude amplification ratio of the supporting frame are measured and verified through a hammering method, a piezoelectric accelerometer and a vibration sensor.

The invention discloses a pitching synchronous driving mechanism of a dual-frequency communication-in-motion antenna. The mechanism comprises an azimuth rotation platform and a motor. A support arm isarranged on the azimuth rotation platform. A first shaft and a second shaft are rotationally arranged on the support arm, and the first shaft is parallel to the second shaft. A Ku planar antenna is rotationally arranged on the first shaft, a Ka planar antenna is rotationally arranged on the second shaft, and the opening surface of the Ku planar antenna is perpendicular to the opening surface of the Ka planar antenna. A motor and encoder combination is directly or indirectly assembled on the support arm. A main shaft of the motor is in transmission connection with the Ku planar antenna and theKa planar antenna simultaneously, and the transmission ratios are equal. According to the pitching synchronous driving mechanism of the dual-frequency communication-in-motion antenna, the adjusting time is shortened, the adjusting precision is improved, the adjusting mechanism is simplified, the size of the mechanism is reduced, and the weight of the mechanism is reduced.