30results about How to "High structural space utilization" patented technology

The invention relates to an axial main lens support mechanism for a vehicle-mounted self-adapting optical imaging telescope and belongs to the field of large-diameter self-adapting optical imaging detection. The mechanism solves the technical problems of low inherent frequency and low overall rigidity. The axial main lens support mechanism comprises balance mechanisms, main lenses and a main lens chamber, wherein the balance mechanisms comprise balance components and balance levers; each of the two ends of each balance lever is fixedly connected with one balance component respectively; the balance mechanisms are uniformly distributed and fixedly connected into the main lens chamber circumferentially via column articulation components and the balance levers; and the main lenses are located on the balance mechanisms. The mechanism is compact in structure, good in system rigidity, high in structural space utilization rate, small in assembly stress and high in locating accuracy, and surface shapes of the main lenses have small influence.

The invention discloses a PSD feedback-based two dimensional rapid control reflector and a control system thereof. The reflector comprises a pedestal, a PSD feedback optical path structure fixed on the pedestal, a movable support structure with piezoelectric ceramics, a fixed support structure without piezoelectric ceramics, a support connected with the movable support structure and the fixed support structure, and a reflector body fixed on the support. According to the invention, the feedback optical path structure based on a position sensing detector PSD is integrated, so deflection precision of angles of the reflector is improved; via the triangular support structure, it is ensured that while reflector can deflect in two dimensions, space utilization rate of the structure is greatly increased; and the structure of the reflector is quite compact and proper.

The invention discloses a miniaturized high-gain circularly polarized antenna based on a metamaterial. The antenna comprises a feeding connection port, a metal floor, a feeding coaxial line arranged on the metal floor, and a butterfly dipole structure connected with the feeding coaxial line. The butterfly dipole structure comprises a pair of dipole arms symmetrically arranged with respect to the feeding coaxial line, and each dipole arm is vertically connected with a thin plate, and the thin plate is connected to the metal floor. An open resonant cavity structure is formed among the pluralityof thin plates and the metal floor. The antenna can achieve high gain while achieving miniaturization, and is advantageous for scene applications with small size and high gain.

The invention provides a large commercial remote sensing satellite platform configuration and an assembly method. The platform configuration comprises a satellite platform main structure, a docking ring and a solar cell array, wherein the satellite platform main structure comprises a butt joint plate, storage box plates, partition plates, a camera plate, outer plates and truss rod assemblies. Thestorage box plates and the partition plates are arranged on the butt joint plate. A plurality of storage box plates and a plurality of partition plates are arranged and are transversely and longitudinally arranged to form a well-shaped structure; the camera plate is arranged above the well-shaped structure; the four outer plates are supported by the truss rod assemblies and arranged around the well-shaped structure; every two adjacent outer plates are connected through the corresponding outer skin; the solar cell array is arranged on the outer surfaces of the outer plates; the docking ring isfixed below the butt joint plate; subsystem single-machine devices are installed on the storage box plates and the partition plates; a propelling subsystem assembly is installed on the butt joint plate; and the two storage tanks are symmetrically installed relative to the mass center of the platform. The configuration is small in structural weight proportion, small in inertia, good in mechanical property, good in solar cell array area expansibility and convenient to assemble and operate.

The invention discloses an internal and external view field mixing splicing method for a large-width camera, and relates to the technical field of aerial remote sensing photogrammetry. The method comprises the following steps: 1, selecting four lenses to establish a lens group, and performing the dividing of the same grid at the focal plane position of each lens; 2, placing the focal plane modulesin parallel on the grids of the four lenses, wherein each focal plane module is provided with a detector, and the detectors on different focal plane modules are placed at different positions according to the dividing of the grids, and all the detectors are the same; 3, simultaneously performing the exposing and imaging of the same object through the four focal plane modules, wherein the first focal plane module generates a first image, the second focal plane module generates a second image, the third focal plane module generates a third image, and the fourth focal plane module generates a fourth image; 4, creating a 5*4 blank grid square matrix, and embedding four images into the new grid square matrix to obtain a final full-frame image. The method gives consideration to the realization of large-width imaging and the constraint of small-structure volume space.

The invention relates to the field of construction, and specifically discloses a building reinforcement structure, which comprises: a building base; an interface agent layer, which is covered on the surface of the building base; and a first polymer mortar layer, which is covered on the interface agent layer; A composite grid, partially embedded in the first polymer mortar layer; and a second polymer mortar layer, overlying the first polymer mortar layer and the composite grid; the composite grid includes a fiber grid skeleton and attached to it glue layer. The reinforcement structure of the building adopts the method of sandwiching fiber grids between two layers of polymer mortar, and the thickness of the repair layer is small, which improves the utilization rate of structural space; and can also significantly enhance the reinforcement strength. In addition, the composite grille is used to make the fiber grille and the polymer mortar layer have greater adhesion, forming a good synergistic effect; improving the binding force of the fiber grille and the main material, further improving the building reinforcement structure. Reinforced performance. The invention also discloses a building reinforcement method.

The invention relates to a sunken prefabricated cabin base. The sunken prefabricated cabin base comprises a frame defined by cross beams and longitudinal beams, wherein the frame is internally provided with a wiring support used for wiring, and the wiring support is arranged between the top surface and the bottom surface of the frame. The wiring support is arranged in the frame defined by the cross beams and the longitudinal beams of the sunken prefabricated cabin base and located between the top surface and the bottom surface of the frame. The cavity space of a sectional material is fully utilized to accommodate a cable connected with a cabinet in a prefabricated cabin, and the space utilization rate of the structure is high. The height of a cabinet mounting frame of the prefabricated cabin can be reduced as much as possible, the structure of the prefabricated cabin is simplified, the manufacturing is easy, the overall height of the prefabricated cabin is reduced, the arrangement of steps can be avoided when the prefabricated cabin is applied on site, and the workload of on-site construction operation is reduced.

The invention discloses a high-rigidity and high-damping satellite platform configuration, which belongs to the field of overall design of spacecrafts and comprises a satellite-rocket butt joint ring used for being in butt joint with a rocket adapter; a mounting plate, wherein one side of the mounting plate is fixedly connected with the satellite-rocket butt joint ring, the other side of the mounting plate is fixedly connected with an optical load plate, and the optical load plate bears an optical load; damping layers which are laid on the outer surface of the optical loading plate and the outer wall of the satellite-rocket butt joint ring; a restraint layer which is laid on the outer surface of the damping layer; the mounting plate comprises a butt joint plate, a partition plate, an outer plate and an optical load plate; the partition plate is of a #-shaped structure, the outer plate is arranged on the periphery of the partition plate, the butt joint plate, the partition plate, the outer plate and the optical load plate are all aluminum honeycomb sandwich plates, and embedded parts are embedded in the single-machine equipment installation position and the rigidity reinforcing position of the aluminum honeycomb sandwich plates. The high-rigidity and high-damping satellite platform configuration has advantages of convenient single equipment configuration and installation, and high space utilization ratio. On the premise that the system is high in rigidity and small in additional mass, structural damping is effectively increased so as to attenuate vibration response of all components of the system.

The invention relates to the technical field of space optical remote sensors, in particular to a frame structure of a small off-axis three-mirror ionospheric imager, and solves the problems of low rigidity and insufficient stray light suppression of the frame structure due to large length-width ratio of the structure caused by long focal length and wide field of view of an optical system. The frame structure mainly comprises a front cover plate, a rear cover plate, an off-axis three-mirror assembly, a main frame, a detector assembly, a T-shaped slit structure, a truss rod, a stray light elimination trap, a shading cylinder I, a shading cylinder II and a detector diaphragm. The off-axis three-mirror assembly comprises a primary mirror assembly, a secondary mirror assembly and a three-mirrorassembly. The main frame comprises a light inlet plate, a main mirror substrate, a secondary mirror substrate, a third mirror substrate, a detector substrate, a top plate, a bottom plate, a support plate I, a support plate II, a light barrier I, a light barrier II and a light barrier III. The frame structure is high in structural space utilization rate and high in specific stiffness, stray lightof an off-axis three-mirror system can be suppressed in a full-path mode, and the imaging quality of an optical system is effectively improved.

The invention discloses a large-format surveying and mapping camera system, which comprises a lens unit, a digital back focal plane unit, an electronics management and control unit and a data storageunit, wherein the lens unit comprises a first multispectral lens, a second multispectral lens, a third multispectral lens, a fourth multispectral lens, a first panchromatic lens, a second panchromaticlens, a third panchromatic lens and a fourth panchromatic lens; the digital back focal plane unit comprises a first multispectral digital back, a second multispectral digital back, a third multispectral digital back, a fourth multispectral digital back, a first panchromatic digital back group, a second panchromatic digital back group, a third panchromatic digital back group and a fourth panchromatic digital back group; and the electronics management and control unit comprises a signal conversion unit and a main control computer. According to the invention, the aerial survey camera can have alarge breadth, and the operation efficiency and precision of the aerial survey camera are improved.

The invention relates to a four-connecting-rod elastic switching mechanism, and belongs to the technical field of optical-mechanical structures. The technical problems that in the prior art, the transmission efficiency is low and the switching speed is low are solved. The four-connecting-rod elastic switching mechanism comprises a crank, a connecting rod, a rocking rod, a rack and an elastic hinge pin. The crank is hinged to the connecting rod. The connecting rod is connected to the rocking rod through the elastic hinge pin. The rocking rod is hinged to the rack. The rack is hinged to the crank. An object to be switched is precisely positioned and safely locked through precise limiting of the rocking rod, micro-overshoot of the crank and the elastic hinge pin, the four-connecting-rod elastic switching mechanism has the advantages that the structure is simple, the principle is reliable and the mechanical shock is small, the four-connecting-rod elastic switching mechanism is compact in structure, and the structural space utilization rate is high through the reasonable layout and ingenious integration of the object to be switched and the four-connecting-rod elastic switching mechanism.

The invention discloses a double-barrel ice cream machine, which comprises: a barrel body, a motor top cover and a motor lower cover are disposed on the upper edge of the barrel body, a motor assembly is disposed in the inner cavity formed by the motor top cover and the motor lower cover, a fixed mount is disposed in the middle of the barrel body, a first ice barrel body disposed between the fixed mount and the motor lower cover, a first rotating leaf disposed in the first ice barrel body, a second ice barrel body disposed between the fixed mount and the barrel body bottom with a second rotating leaf disposed therein, where, the second rotating leaf is connected with the first rotating leaf for driving, and the first rotating leaf is connected with the motor assembly for driving. The invention adopts the double ice barrel design and adds another driving rotating leaf in the first ice barrel disposed longitudinally to achieve a structure with higher space utilization rate; and can make ice creams of two different taste at one time by adopting the ice barrel body with double-barrel structure; The machine has a barrel body equipped on the two ice barrels, the gap between the two ice barrels can be used for containing ice cubes, which provides more convenience to use.

The invention discloses a bending and shaping die structure, and belongs to the field of shaping dies. The bending and shaping die structure comprises a shaping convex die, a shaping lower die movable block and a shaping lower die fixed block. The shaping lower die movable block is mounted on the shaping lower die fixed block through a rotating shaft, the shaping convex die is positioned at the position above one side of the shaping lower die movable block, and a contact face used for making contact with the lower surface of the shaping convex die is formed in the position, located under the shaping convex die, of the shaping lower die movable block. The bending and shaping die structure has the beneficial effects that, in the bending and shaping die structure, the shaping lower die movable block is mounted on the shaping lower die fixed block through the rotating shaft, compared with a conventional sliding structure, when the same effect is achieved, the friction effect is smaller, under the conditions that clean production is needed and oiling is not needed, friction force can be well reduced, the conditions of blocking and jamming and the condition that sliding blocks cannot reset in time are reduced, the service life of the die is prolonged, the product quality is ensured, and customer requirements are met.

The invention belongs to the technical field of air conditioning, and particularly discloses an air conditioner which comprises a hollow cabinet body and a plate type indoor heat exchanger arranged in the hollow cabinet body, and a heat exchange main body of the plate type indoor heat exchanger comprises a plurality of heat exchange pipes arranged in parallel; the plurality of heat exchange tubes are arranged between the left cabinet plate and the right cabinet plate, and two ends of each heat exchange tube are respectively connected to the front cabinet plate and the rear cabinet plate; each heat exchange tube is provided with a bent part, and a first heat exchange part and a second heat exchange part which extend reversely from the two ends of the bent part and are connected to the front cabinet plate and the rear cabinet plate respectively; the first heat exchange part, the bent part and the second heat exchange part enable the heat exchange main body to form a windward heat exchange surface protruding towards the lower part of the hollow cabinet body; and the length of the first heat exchange part is smaller than that of the second heat exchange part, and the position, connected to the front cabinet plate, of the first heat exchange part is lower than the position, connected to the rear cabinet plate, of the second heat exchange part. The air conditioner has the advantages that the heat exchange efficiency is high, the refrigeration efficiency is high, the overall size can be reduced, and the condensation phenomenon is reduced or even eradicated.

The invention relates to the field of power module case structure, in particular to a standard chassis structure of a DC-DC power module which is characterized in that the case comprises a left side cover, a right side cover, a main box body and a cover plate, and the case is compact in structure and convenient in disassembly. The connection port on the left cover is provided with a locking buckle, which can achieve the effects of anti-touch and quick insertion and extraction; A support frame is arranged in the main box body, a PCB mounting board is arranged on the support frame, and the insulating partition board and the PCB mounting board are connected to divide the main box body into upper and low chambers, so that the heat dissipation effect is good; The circuit board is installed on the upper surface of the PCB mounting board, the PCB mounting board is connected with the circuit board by screws, and the screw ends are all installed in the screw cap, so that the insulation effect is good; The secondary line between the circuit boards and the power line of the connection port are connected at the upper cavity part of the main box body and fixed with a tie strap, so that the interference prevention effect is good.

The invention discloses a piezoelectric multiband vibration energy harvesting device based on a folded beam structure, which generates power by using deformation of a piezoelectric material, and belongs to the field of energy saving technology and energy recovery. The piezoelectric multiband vibration energy harvesting device based on the folded beam structure comprises a folded beam, a square mass frame, a columnar fixing pin, a square block and a base. Under the condition that the environment vibration frequency is low in engineering, vibration energy can be collected in multiple frequency ranges through resonance of the units, so that the problems that an existing cantilever beam type energy harvester is narrow in working frequency band and limited in resonance working interval under natural conditions are solved, and the working efficiency of the cantilever beam type energy harvester is improved. The method is of great significance in improving the energy harvesting efficiency and playing a role in the practical application of the related energy harvesting device.

The invention discloses a combined conical section composite shell structure which comprises a conical composite shell, a front cabin and a cabin section connecting structure. The front cabin is installed on the head of the composite shell with the cone through a cabin section connecting structure. The space utilization rate of the composite shell is greatly improved through the design of the composite shell conical section structure, effective utilization of the charging space of the boosting engine with the conical section is achieved in combination with the forecabin structure, meanwhile, the negative mass of the shell is greatly reduced, the impact mass ratio of the engine is increased, and the problems that a traditional non-conical-section composite shell structure is low in space utilization rate and low in cost are solved. The problems that the docking space of the cabin sections cannot be utilized, and the overall passive mass of the structure is large are solved, meanwhile, the cabin section connecting structure is used for achieving sharing of the gravity of the forecabin in the vertical state of the rocket and releasing of axial stress in the internal pressure working state, and side deformation discordance between the forecabin and the composite shell is avoided.