42results about How to "Reduce envelope size" patented technology

The invention discloses a non-cooperative target satellite acquisition device and an acquisition method, and belongs to the technical field of aerospace. The non-cooperative target satellite acquisition device includes an outer shell, two four-link capturing pawl mechanisms, four horizontal locking mechanisms, a screw rod and a controller; the two four-link capturing pawl mechanisms are arranged in the outer shell face to face, and the lower parts thereof are fixedly connected with an installing bottom plate; the lower end of the screw rod crosses through the installing bottom plate, and the lower end thereof is connected with a driving mechanism; four horizontal locking mechanisms are respectively located at outside of the two four-link capturing pawl mechanisms, and every two horizontal locking mechanisms are installed on the upper part of the outer shell; both sides of the upper part of the four-link capturing pawl mechanisms are respectively equipped with pressure lever mechanisms; when the four-link capturing pawl mechanisms are descended, the pressure lever mechanisms compress the horizontal locking mechanism to horizontally glide towards inside; the top part of the outer shell is equipped with a photoelectric sensor, and the photoelectric sensor and the driving mechanism are electrically connected with the controller. The non-cooperative target satellite acquisition device is widely applied to the acquisition of various space crafts, and the non-cooperative target satellite acquisition device is wide in application range, big in tolerance, quick in response speed, high in reliability, and others.

A microstrip antenna using parasitical feed metal columns. The microstrip antenna includes four layers of dielectric plates, a radiating patch, metal floors, an SMP RF connector, a one-to-two power divider of a strip line form, a first feed metal column, a second feed metal column, a first parasitical feed metal column, and a second parasitical feed metal column. The antenna is additionally provided with the parasitical feed metal columns on the basis of a double-feed point circular polarization microstrip antenna, through electromagnetic coupling induction, the parasitical feed metal columns have electromagnetic field energy of a certain amplitude and phase, thereby changing surface current distribution of the microstrip antenna and electromagnetic field distribution between the microstrip antenna and the floors, so as to obtain a radiation pattern in rotational symmetry approximate to a ''four-feed point'' microstrip antenna, and at the same time, low elevation gain is improved, a feed network is simplified, feed loss is reduced, and the envelope size is diminished. The microstrip antenna using the parasitical feed metal columns in the invention is particularly suitable for occasions which have high requirements for miniaturization, rotational symmetry of a pattern and low elevation gain, and has popularization and application value.

The invention discloses a driving device for a solar cell array, which comprises: an A-axis mechanism driving rolling rotation and a B-axis mechanism driving pitching motion. The A-axis mechanism includes: an A-axis motor, a reducer, and a drive shaft, and a power and signal transmission device is arranged on one side of the drive shaft. The transmission of the A-axis motor through the drive shaft enables the solar array to achieve directional tracking of the rolling direction to the sun within the range of ±360°. The B-axis mechanism includes: a B-axis motor, a reducer, and a flexible spline of the reducer is connected in rotation with a support shaft. In the B-axis mechanism, the motor is decelerated by the reducer and the torque is amplified, so that the solar array can realize the sun orientation in the pitch direction within the range of ±90°. The invention solves the problem that the solar battery array cannot always be aligned with the sun's rays, and achieves beneficial effects of improving electric energy transmission and tracking precision.

The invention discloses a solar wing / antenna unfoldable supporting truss. The solar wing / antenna unfoldable supporting truss includes a first supporting rod, a second supporting rod, a third supporting rod and a fourth supporting rod. According to the solar wing / antenna unfoldable supporting truss of the invention, a truss rod system is optimized; the unfolding structure of an existing mechanism is simplified; the number of rod components can be decreased; a V-shaped oblique supporting type structure is adopted, so that the support stiffness of the solar wing / antenna unfoldable supporting truss in various spatial directions can be increased; inter-rod hinges are obliquely folded crossing type hinges, and therefore, the enveloping size of the folded truss rod system can be decreased, and the folding ratio of the supporting truss can be improved. The invention also provides an assembly adjustment method of the solar wing / antenna unfoldable supporting truss. With the method adopted, the rod components are not required to be dissembled and assembled in an installation and adjustment process. The method has the advantages of simplicity, convenience, easiness in implementation and high installation and adjustment efficiency.

The invention discloses a space-borne complex radar antenna high-rigidity biased-type fixed direction pointing mechanism, comprising: an active unfolding locking mechanism, an extension arm, a two-dimensional servo mechanism, a pressing releasing mechanism, and a floating bracket. The pressing releasing mechanism comprises a pressing cup, a supporting component, a pressing rod, a pressing head cover and a vibration damping head cover. The invention provides an effective solution for the installing and fixing of a space-borne complex radar antenna and the tracking and positioning of an in-orbit target. The mechanism has the advantages of small size in envelope, high rigidity in structure and convenience in installation.

The invention belongs to the technical field of robots, and particularly relates to a nucleus-related-complex-environment-oriented high-adaptability robotic versatile movement platform. The movement platform aims at improving the capacity of a robot to pass through the environments such as narrow space, flat channels, steps, obstacles and gullies. The platform is composed of four three-degree-of-freedom robotic leg systems based on synchronous belt driving; each three-degree-of-freedom robotic leg system comprises a foot-type robotic body, a hip-joint-'outward-stretching / inward-retracting' driving motor, an integral reduction gearbox of the driving motor, a gear A, a knee-joint-'stretching / bending' driving motor, a gear B, a hip-joint-'outward-stretching / inward-retracting' movement base, athigh connecting rod, a foot-end hexagonal rubber block, a hip-joint-'stretching / bending' driving motor, a bearing, a ball-screw installation rod base, a ball-screw nut connecting shaft, hip-joint pushing rods, a shank connecting rod and a ball screw.

A lighthead for a dual-mode searchlight including a generally concave housing with an attached infrared (IR) light source assembly, an insulating barrier and air gap between the visible and IR portions of the assembly, and a reflector integral to the housing.

The present disclosure relates to purification cassettes that have reinforcing features. One embodiment relates to a purification cassette with tensions members. A purification system may include a removable cassette defining a media cavity. A set of tension members may span between a first sidewall and second sidewall. The set of tension members can divide the media cavity into a plurality of lanes.

The invention discloses a miniature antenna servo apparatus. The miniature antenna servo apparatus comprises a pedestal, an orientation channel motor which is arranged on the pedestal, an orientation channel motor gear which is driven by the orientation channel motor, a pair of sector gears, an orientation channel and a pitching channel, wherein the pair of sector gears are arranged on the upper part of the pedestal and are meshed with the orientation channel motor gear; the orientation channel includes an orientation channel principal axis; the pitching channel includes a pitching channel principal axis which is perpendicular to the orientation channel principal axis; the pitching channel principal axis, the orientation channel principal axis and the pair of sector gears are connected as one body; and the orientation channel motor gear drives the sector gears to rotate so that the orientation channel principal axis and the pitching channel principal axis can also rotate around the hole axis at the upper part of the pedestal synchronously. The miniature antenna servo apparatus is simple in structure and is miniaturized, and has the advantages of being large in the installable detection assembly, being high in the bearable load moment of inertia, being able to realize the maximum compound angle limiting function, and being low in cost.

The invention relates to a satellite inflatable antenna. The inflatable antenna at least comprises a flexible antenna folding surface and an unfolding assembly. The unfolding assembly at least comprises a first-stage unfolding assembly and a second-stage unfolding assembly; the first-stage unfolding assembly can expand outwards under the driving action of inflation pressure applied to the first-stage unfolding assembly as driving force so as to drive at least part of the flexible antenna folding surface to be unfolded. When the first-stage unfolding assembly is expanded to a first-stage complete unfolding position, the second-stage unfolding assembly is expanded in a graded manner in a manner of releasing the shape memory effect of the shape memory material plate on the flexible antenna folding surface due to the driving force applied to the second-stage unfolding assembly, so that the flexible antenna folding surface can be unfolded in an incomplete or complete space in a graded and controllable manner from bottom to top in a manner of increasing the effective unfolding area and reducing the unfolding impact overload.

The invention discloses a flexible solar wing unfolding mechanism with a high unfolding-folding ratio. The flexible solar wing unfolding mechanism comprises a bottom plate, a shear fork rod assembly, a top plate and a solar blanket assembly; the unfolding mechanism further comprises a driving assembly integrated on the bottom plate; the driving assembly is provided with a driving motor and a transmission gear, and the transmission gear extends to the upper part of the bottom plate; and the driving assembly is in transmission connection with the shear fork rod assembly through the transmission gear and drives the shear fork rod assembly to be unfolded so as to drive the solar blanket assembly to be unfolded. The unfolding mechanism is simple in structure, high in reliability and small in mass; most structural parts in the mechanism are made of spaceflight-grade hard aluminum alloy and carbon fiber composite materials, the mechanical structure is simple and not numerous and jumbled, and the structural parts are subjected to lightweight design improvement on the premise that the strength and vibration requirements are guaranteed; and the unfolding mechanism is low in manufacturing cost and material price, structural parts are simple in structure and convenient to manufacture, the shear fork rod assembly drives the solar blanket assembly to move, and the unfolding mechanism has the advantages of being light in weight, small in folding size, large in unfolding span and high in unfolding and folding ratio.

The invention discloses a three-degree-of-freedom high-precision driving device, which is applicable to various payloads (antennas, cameras, receivers, etc.) on a space vehicle to perform movements such as deployment, driving, scanning, and precise pointing. The three-degree-of-freedom high-precision driving device includes: an A-axis mechanism for driving pitching motion, a B-axis mechanism for driving steering motion, and a C-axis mechanism for driving unfolding motion. The A-axis machine can make the payload realize pitching and directional movement within the range of ±95°; the B-axis mechanism can make the payload realize the steering and directional movement within the range of ±185°; the C-axis mechanism can make the payload move within the range of 0°~90° It realizes deployment movement and directional tracking with directional antenna. The present invention adopts the integrated design technology, cleverly integrates the planetary gear reducer and the encoder inside the motor assembly, and designs a harmonic reducer and a motion limit device in each axis mechanism, so that the mechanism design is compact, light in weight, Movement is reliable. The invention solves the problem that the payload cannot be accurately aimed at the target, and achieves the beneficial effects of widening the viewing angle and improving the tracking precision.

The invention provides a small satellite structure suitable for medium and high orbits. The small satellite structure comprises a top panel, a front panel, a right panel, a left panel, a rear panel, abottom panel, a laser communication load, a solar wing driving mechanism, a solar wing driving mounting bracket, a nano star sensor and a GNSS antenna mounting bracket. The top panel, the front panel, the right panel, the left panel, the rear panel and the bottom panel define a parallelepiped; the outer side of the front panel is connected with the laser communication load, the inner side of thefront panel is provided with the solar wing driving mounting bracket, and the solar wing driving mechanism is installed on the solar wing driving mounting bracket and penetrates through the right panel and the left panel; The nano star sensor and the GNSS antenna mounting bracket are mounted on the outer side of the top panel; and the rear panel is provided with a propulsion system mounting interface. The laser communication load is installed on the outer side of the satellite body defined by the six panels, heat dissipation of the load can be effectively improved, and a problem that heat dissipation in the satellite body is not facilitated when the load is placed in the satellite is solved.

The invention discloses a large-angle and high-efficiency ball-cage type constant-velocity universal joint with eight steel balls. Each inner race of a bell-shaped shell and each outer race of a star-shaped sleeve are conjugate and composed of two sections of tangential and reverse arcs separately; the central line of the first pair of inner races is located at the outer side of the central line of an inner spherical surface, an angle between the connection line of the tangential point A of the central track A of a steel ball I and the center of an inner-side arc I, and the central line of theinner races is 2-4 degrees, the central lines of the second pair of inner races and the fourth pair of inner races are superposed with the central line of the inner spherical surface, and an angle between the connection line of the tangential point A of the central track A of each of a steel ball II and a steel ball IV and the center of the inner-side arc I, and the central line of the inner races is 4-6 degrees; and the central line of the third pair of inner races is located at the inner side of the central line of the inner spherical surface, an angle between the connection line of the tangential point A of the central track A of a steel ball III and the center of the inner-side arc I, and the central line of the inner races is 9-11 degrees. The large-angle and high-efficiency ball-cage type constant-velocity universal joint with the eight steel balls is capable of achieving an angle of 52 degrees, high in strength and transmission efficiency, more compact in structure, lighter inmass, and adaptive to use in a vehicle with a lower requirement on a vehicle turning radius.

The invention relates to a searching and tracking integrated infrared zoom lens and an imaging method, and aims to solve the problems that the existing searching and tracking integrated infrared zoom lens adopts a diffractive optical element to correct chromatic aberration, so that the system structure is relatively complicated, a diffraction ring is generated on an image surface, and the signal-to-noise ratio and the imaging contrast ratio are reduced. The lens comprises a front-end telescope group, a sweep reflector and a rear-end imaging lens group which are sequentially arranged along a light path, wherein the sweep reflector is used for compensating image motion and expanding a field angle. The front-end telescope group comprises a first lens, a second lens, a third lens and a fourth lens which are sequentially arranged along a light path, the first lens is a silicon positive lens, the second lens is a germanium negative lens, the third lens is a silicon positive lens, and the fourth lens is a germanium negative lens; and the rear-end imaging lens group comprises a fifth lens, a sixth lens, a seventh lens and an eighth lens which are sequentially arranged along the light path, the fifth lens is a sulfur positive lens, the sixth lens is a silicon positive lens, the seventh lens is a germanium negative lens, and the eighth lens is a silicon positive lens.

The invention relates to a main bearing member used for optical minimal satellite and a common structure of an optical camera. The main bearing member comprises an optical camera, an on-satellite standalone device, a carbon fiber common structure, a diaphragm and a main reflector; the diaphragm can eliminate the stray light of a main reflector of the optical camera; and the on-satellite standalone device is installed on the fiber common structure. The invention provides a common structure for the main bearing structure of the optical small satellite and provides a common structure of the optical camera, both the main bearing structure and the common structure have functions of the camera light shielding housing and the satellite main bearing, improves the function utilization rate of the on-satellite structure member, and thus improves the space utilization rate in order to reduce the enveloping size and reduce the weight of the integral satellite.

The invention provides an attitude control engine module comprising a module support and engines. A first cavity is formed in the module support. A fluid supply flow channel is formed by the first cavity. A second cavity is formed in each engine. A fluid receiving flow channel is formed by each second cavity. The module support is connected with a transmitter in a fastened manner so that the fluidsupply flow channel and each fluid receiving flow channel can communicate with each other and form a fluid passageway together. Sealing structures are arranged at connection positions of the fluid supply flow channel and the fluid receiving flow channels. According to the attitude control engine module, in practical application, four oxidizing agent flow channels and four fuel flow channels can be formed by the module support through internal punching, the process technology is mature, the mechanical property is good, pipelines are reduced by eight and weld joints are reduced by sixteen compared with traditional design, and the system complexity is lowered.

The invention belongs to the technical field of aerospace thermal control and relates to a heat dissipation structure of a phased-array antenna, a phased-array antenna and a satellite platform. The heat dissipation structure of the phased-array antenna is used for conducting heat dissipation on the phased-array antenna of a satellite platform, wherein the satellite platform comprises a satellite cabin plate. The heat dissipation structure of the phased-array antenna comprises a first heat pipe, a flat heat pipe and a second heat pipe; the first heat pipe is buried in the satellite cabin plate; the flat heat pipe is arranged on the inner surface of the satellite cabin plate and used for supporting an antenna assembly of the phased-array antenna; a first protrusion is arranged on the flat heat pipe; the first protrusion is located in the satellite cabin plate, and the outer side face of the first protrusion and a part of the flat heat pipe located on the outer side of the first protrusion are attached to the first heat pipe; and the second heat pipe is arranged on the inner surface of the satellite cabin plate. The heat dissipation structure of the phased-array antenna is small in occupied space; the heat dissipation problem of the antenna assembly is solved; the heat dissipation path is shortened; the heat dissipation efficiency is improved; and normal work of the phased-array antenna on the satellite platform is guaranteed.

The invention provides a large-scale deployable high-rigidity high-storage-ratio light shield. The light shield comprises an unfolding cover, a supporting cylinder, an unfolding mechanism, a large-bearing pressing and releasing device, a locking mechanism and backlight face heat dissipation holes, the unfolding cover is connected with the supporting cylinder, the unfolding mechanism is arranged at the connecting rotating position of the unfolding cover and the supporting cylinder, the locking mechanism is arranged at the connecting position of the unfolding cover and the supporting cylinder and on the sunshine irradiation side, and the backlight face heat dissipation holes are formed in the side, back to the sunshine, of the supporting cylinder; and when the unfolding cover is folded and tightly attached to the supporting cylinder, the large-bearing pressing and releasing device is connected with the unfolding cover and the supporting cylinder. For the mechanically unfolded light shield, the integral design of the light shield and the supporting cylinder in the folded state enables the whole light shield to have higher rigidity and smaller envelope size, the design fully considers the structural light weight, and the light shield has better rigidity, smaller envelope size and higher material utilization rate.

The present disclosure relates to purification cassettes that have reinforcing features. One embodiment relates to a purification cassette with tensions members. A purification system may include a removable cassette defining a media cavity. A set of tension members may span between a first sidewall and second sidewall. The set of tension members can divide the media cavity into a plurality of lanes.

The invention discloses a solar wing / antenna unfoldable supporting truss. The solar wing / antenna unfoldable supporting truss includes a first supporting rod, a second supporting rod, a third supporting rod and a fourth supporting rod. According to the solar wing / antenna unfoldable supporting truss of the invention, a truss rod system is optimized; the unfolding structure of an existing mechanism is simplified; the number of rod components can be decreased; a V-shaped oblique supporting type structure is adopted, so that the support stiffness of the solar wing / antenna unfoldable supporting truss in various spatial directions can be increased; inter-rod hinges are obliquely folded crossing type hinges, and therefore, the enveloping size of the folded truss rod system can be decreased, and the folding ratio of the supporting truss can be improved. The invention also provides an assembly adjustment method of the solar wing / antenna unfoldable supporting truss. With the method adopted, the rod components are not required to be dissembled and assembled in an installation and adjustment process. The method has the advantages of simplicity, convenience, easiness in implementation and high installation and adjustment efficiency.

The invention discloses a light weight flexible robot, which comprises a control box, a flexible mechanical arm and a plurality of driving ropes, wherein each driving rope is uniformly distributed inthe circumference direction, and is fixedly connected with the flexible mechanical arm after the extending in the axial direction of the circumference; through the driving by the control box, the flexible mechanical arm is dragged to move; the control box comprises a control panel; the control panel is provided with a plurality of steps with different heights in the axial direction in a way of corresponding to each driving rope; an installing structure is arranged on each step; the height of each step is in direct proportion to the height of each driving rope; in the direction of the diameterparallel to the step on the circumference, the displacement of each installing structure relative to the located step is in direct proportion to the projection distance of the connecting line betweenthe circle center of each driving rope to the circle center of the circumference on the located step. The light weight flexible robot can realize the compact arrangement of each component in the control box; the enveloping dimension of the whole machine of the control box can be favorably reduced; the applicable scene of the robot is improved.

The invention relates to the technical field of satellites, in particular to a satellite platform structure which comprises a trapezoid box capable of being closed and at least four connecting assemblies. The trapezoidal box body comprises a first side cabin plate, a second side cabin plate, a third side cabin plate, a fourth side cabin plate, a first bottom cabin plate and a second bottom cabin plate; connecting assemblies are pre-buried in parts or all of the first side cabin plate, the second side cabin plate, the third side cabin plate, the fourth side cabin plate, the first bottom cabin plate and the second bottom cabin plate, and adjacent cabin plates in the first side cabin plate, the second side cabin plate, the third side cabin plate, the fourth side cabin plate, the first bottom cabin plate and the second bottom cabin plate are detachably connected; the satellite platform structure is simple in structure, so that the manufacturing and assembling time is greatly shortened; the space in the carrying fairing is fully utilized, and the launching space is saved; and meanwhile, only the solar panel assemblies are arranged on the third side cabin plate and the fourth side cabin plate, so that cabin opening or cabin sealing operation of the satellite platform structure is greatly simplified, the test time is further shortened, and the production efficiency is improved.

The invention relates to the technical field of spacecraft propulsion systems, in particular to a structural layout of a light and small rocket engine, which can realize a compact engine structure and is beneficial to product modularization and integration. According to the engine structure layout of the present invention, it includes a head shell module, a throttle ring, a propellant control valve, an injector core, a nozzle pipe, a combustion chamber pressure nozzle, valve fasteners, an internal leakage prevention sealing ring, and an anti-inner leakage sealing ring. Leaky sealing ring. The invention has the following advantages: 1) The engine product has a compact structure, which is conducive to reducing the envelope size of the engine; 2) The number of engine parts is small, which is conducive to improving the inherent reliability of the engine; 3) The throttle ring is easy to disassemble and assemble, which is convenient for engine flow resistance Adjustment; 4) The structure is properly hollowed out, which is conducive to weight reduction and heat protection of engine products.

The invention provides an attitude control engine module comprising a module support and engines. A first cavity is formed in the module support. A fluid supply flow channel is formed by the first cavity. A second cavity is formed in each engine. A fluid receiving flow channel is formed by each second cavity. The module support is connected with a transmitter in a fastened manner so that the fluidsupply flow channel and each fluid receiving flow channel can communicate with each other and form a fluid passageway together. Sealing structures are arranged at connection positions of the fluid supply flow channel and the fluid receiving flow channels. According to the attitude control engine module, in practical application, four oxidizing agent flow channels and four fuel flow channels can be formed by the module support through internal punching, the process technology is mature, the mechanical property is good, pipelines are reduced by eight and weld joints are reduced by sixteen compared with traditional design, and the system complexity is lowered.

The invention discloses a non-cooperative target satellite acquisition device and an acquisition method, and belongs to the technical field of aerospace. The non-cooperative target satellite acquisition device includes an outer shell, two four-link capturing pawl mechanisms, four horizontal locking mechanisms, a screw rod and a controller; the two four-link capturing pawl mechanisms are arranged in the outer shell face to face, and the lower parts thereof are fixedly connected with an installing bottom plate; the lower end of the screw rod crosses through the installing bottom plate, and the lower end thereof is connected with a driving mechanism; four horizontal locking mechanisms are respectively located at outside of the two four-link capturing pawl mechanisms, and every two horizontal locking mechanisms are installed on the upper part of the outer shell; both sides of the upper part of the four-link capturing pawl mechanisms are respectively equipped with pressure lever mechanisms; when the four-link capturing pawl mechanisms are descended, the pressure lever mechanisms compress the horizontal locking mechanism to horizontally glide towards inside; the top part of the outer shell is equipped with a photoelectric sensor, and the photoelectric sensor and the driving mechanism are electrically connected with the controller. The non-cooperative target satellite acquisition device is widely applied to the acquisition of various space crafts, and the non-cooperative target satellite acquisition device is wide in application range, big in tolerance, quick in response speed, high in reliability, and others.

A microstrip antenna using parasitical feed metal columns. The microstrip antenna includes four layers of dielectric plates, a radiating patch, metal floors, an SMP RF connector, a one-to-two power divider of a strip line form, a first feed metal column, a second feed metal column, a first parasitical feed metal column, and a second parasitical feed metal column. The antenna is additionally provided with the parasitical feed metal columns on the basis of a double-feed point circular polarization microstrip antenna, through electromagnetic coupling induction, the parasitical feed metal columns have electromagnetic field energy of a certain amplitude and phase, thereby changing surface current distribution of the microstrip antenna and electromagnetic field distribution between the microstrip antenna and the floors, so as to obtain a radiation pattern in rotational symmetry approximate to a ''four-feed point'' microstrip antenna, and at the same time, low elevation gain is improved, a feed network is simplified, feed loss is reduced, and the envelope size is diminished. The microstrip antenna using the parasitical feed metal columns in the invention is particularly suitable for occasions which have high requirements for miniaturization, rotational symmetry of a pattern and low elevation gain, and has popularization and application value.