43results about How to "Improve the mechanical environment" patented technology

An alternator for vehicles, the alternator being provided with a rotary shaft, comprising slip rings fixed to a rotary shaft to be rotated with the rotary shaft, brushes being placed to be in slide contact with the slip rings a brush holder that accommodates the brushes to be held therein; connection terminals fixed to the brush holder, brush leads electrically connecting the brushes to the connection terminals respectively, and a slip ring cover that covers the slip rings in cooperation with the brush holder, wherein the brush holder comprises first chambers in which the bushes are fixedly accommodated second chambers in which the brush leads are accommodated, the second combers communicating with the first chambers, and first air holes formed to open outside of the housing and formed as inlet / exhaust passages communicating with the second chambers.

The invention provides a carrier rocket booster tank structure for biased concentrated force. The structure comprises a front short shell, a front tank bottom, a cylinder segment, a rear tank bottom and a rear short shell, wherein the five parts form the whole tank structure through circumferential welded seams and form a sealed container which can store a propellant and bear various loads; the front short shell is welded into a whole by a radial outer reinforced wall plate and two positive outer reinforced wall plates, and the cylinder segment is composed of a mixed inner reinforced wall plate with a concentrated force diffusion function and an oblique inner reinforced wall plate. The carrier rocket booster tank structure solves the bearing and diffusion problem of the biased concentrated force, the biased concentrated force is diffused through the tank structure to become uniformly distributed force, and a good mechanical environment is provided for a cabin behind a tank. The tank structure has the characteristics of high bearing capacity, high structure efficiency, good concentrated force diffusion effect, etc.

The invention discloses a satellite-launcher connecting device which can effectively restrain structure vibration and improve the satellite mechanical environment at a launcher active flight section and particularly relates to a damping pipe support type damping adapter. The damping pipe support type damping adapter mainly comprises an upper end frame, eight upper end frame connectors, 16 shearing type damping pipes and eight lower end connectors. The eight upper end frame connectors and the eight lower end connectors are distributed in the periphery direction symmetrically. Each connector is connected with two damping pipes. Each damping pipe is connected with an upper connector and a lower connector in a crossing mode. A whole adapter structure with damping performance between a satellite and a launcher is formed, good damping and vibration isolation performance is achieved, the rigid index requirement which is needed for the adapter structure is met, and the requirement that structure weight is not increased is met.

The invention relates to the field of a medical treatment device, and is used for the design of an operation replacement piece of an artificial knee; the invention particularly discloses a design method of customized artificial knee joint prosthesis. The design method solves the technical problems of discontinuous curve curvature of thighbone vertical plane condyle, weak rolling ability and poor stability in the knee joint prosthesis at present. A design method of customized artificial knee joint prosthesis, wherein the design method includes steps of (1), fitting first vertical plane fitting ellipses of two condyles of the thighbone through a CT image of the thighbone tail end of a patient; (2), acquiring coronal plane fitting ellipses of two condyles of the thighbone through the CT image of the thighbone tail end of the patient; (3), according to the dimension of minor semi-axes of the coronal plane fitting ellipses of two condyles of the thighbone, acquiring second vertical plane fitting ellipses of two condyles of the thighbone, wherein L is equal to the length of minor semi-axes of the coronal plane fitting ellipses; (4), scanning the coronal plane fitting ellipses of two condyles of the thighbone along the corresponding second vertical plane fitting ellipses and forming a smooth curve face of the femoral condyle, and further forming a two-condyle structure at the tail end of the thighbone.

The invention provides an integrated satellite compact in layout. The integrated satellite comprises a bottom plate, and a mounting flange is arranged on the surface of the bottom plate; the mounting flange is used for arranging of an inner-satellite load device, and therefore a first force transmission path for the inner-satellite load device is formed. The four opposite angles of the surface of the bottom plate are each provided with a partition plate, and a top plate is supported by the four partition plates; and an outer-satellite load device is arranged on the top plate, and therefore a second force transmission path for the outer-satellite load device is formed. The integration satellite compact in layout has the beneficial effects that the integrated satellite configuration with the load as the center is provided, and the scheme of carrying out layout around the load is achieved; and meanwhile, the structural scheme with two main force transmission paths and one secondary force transmission path for the combined action is designed, the mechanic environment of the loads is optimized, the design complexity and the design pressure of a satellite structure and a load structure are reduced, and the bearing ratio of the satellite structure is improved.

The invention discloses an intelligent knee joint training instrument. The intelligent knee joint training instrument comprises a base, a leg bracket mechanism, a shank bracket mechanism, an adjustable grasping body, a horizontal adjusting support, a push frame, a reciprocating traction driving device and a traction controller; the horizontal adjusting support is arranged at the tail portion of the base, the side wall of the base is provided with a sliding groove, the leg bracket mechanism is connected with the push frame through the shank bracket mechanism, and the traction controller which extends into the base through the sliding groove and is connected with the reciprocating traction driving device is arranged at the lower end of the push frame. The intelligent knee joint training instrument is exquisite and reasonable in structural design, the leg is straightened by simulating natural motion of a human body, the knee patella is grasped through the grasping body to conduct up-and-down and right-and-left reciprocating motion to achieve massage recovery treatment on the knee patella, therefore, natural resilience of the human body is stimulated, patella extroversion is corrected, the mechanical environment of the patellofemoral joint is improved, quadriceps are strengthened, and the recovery effect is good.

The invention relates to a rubber buffering and vibration isolating elastomer structure which comprises an upper metal part, a rubber part and a lower metal part. An internal cavity structure is adopted by the rubber body of the invention to increase the buffering stroke of the rubber body, and the buffering deformation of the rubber body can reach 100%; and if the space along the axial direction of the elastomer structure is large enough, the buffering deformation can reach about 150%. The design of the cavity structure greatly increases the buffering deformation stroke of the rubber part by 2-4 times of the traditional rubber isolator, thereby greatly improving the buffering effect. The structure of the invention adopts the design of a gas channel; on the one hand, by the design of the gas channel, when the elastomer bears the impact load, because the action time of the load is short, the gas in the cavity is quickly discharged outwards through the gas channel, and the friction action of the gas and the channel increases the damping of the elastomer structure, thereby increasing the buffering effect of the elastomer structure; and on the other hand, by the design of the gas channel, the gas in the cavity can be smoothly discharged under the action of the load to avoid the uneven deformation of the rubber part caused by sealing of the cavity, thereby ensuring the rigidity stability of the elastomer structure in the deformation process.

The invention discloses a bionic knee-guarding support. The bionic knee-protecting supporting tool comprises two support clamping boards fixed at the two sides of the lower limb of a human body by a band; all the support clamping boards comprise thigh supporting boards connected with the thighs and crus supporting boards connected with the cruses; the thigh supporting boards and the crus supporting boards are rotatably connected at the positions of knee joints of the human body; the knee-guarding support also comprises a meniscus like structure capable of generating a function of a meniscus board, one end of the meniscus like structure is connected with each thigh supporting board, and the other end of the meniscus like structure is connected with the crus supporting board. By adoption ofthe technical scheme, the meniscus like structure can simulate the function of the meniscus so as to simulate the movement of the knee joints of the human body, the gravity from the thighbones is uniformly transmitted to the cruses in a decreasing manner, the concentrated load is avoided, and the pressure stress on the tibiofemoral joints is reduced; and in treatment of acute and chronic injuriesof the knee joints, enables the knee joints to carry out early-stage functional exercises and activities, and the load of the knee joints can be fully eliminated.

The invention relates to the technical field of momentum wheel micro-vibration isolation, and provides a remote sensing satellite momentum wheel vibration isolation bracket and a manufacturing methodthereof. The vibration isolation bracket is provided with a momentum wheel connecting piece corresponding to a momentum wheel mounting hole in the momentum wheel bracket, a first limiting groove is formed in the inner side wall of the momentum wheel mounting hole, a second limiting groove is correspondingly formed in the outer side wall of the momentum wheel connecting piece, the first limiting groove is connected with the corresponding second limiting groove through a vibration isolation pad, due to the fact that the vibration isolation pad has good stiffness and damping characteristics, during the satellite launch phase, vibration transferred from a satellite capsule plate to the momentum wheel bracket is transferred to the momentum wheel after attenuation of the vibration isolation pad,the mechanical environment of a momentum wheel can be improved, and it is ensured that the momentum wheel is not damaged by overload; and micro-vibration generated by the momentum wheel is finally transferred to the remote sensing load after vibration attenuation of the vibration isolation pad during in-orbit imaging of a satellite, the influence of disturbing force of micro-vibration on the camera visual axis can be controlled within the technical requirements of a camera, and the imaging quality of the remote sensing camera is ensured.

The invention provides main architecture of a small-type high-orbit satellite common platform. The main architecture of the small-type high-orbit satellite common platform comprises a shell, an intermediate baffle, a platform cabin main bearing truss set and a load cabin bearing truss, wherein the shell forms a holding space, and the intermediate baffle divides the holding space into a platform cabin and a load cabin; the platform cabin main bearing truss set applies supporting force on the partial outer shell and the intermediate baffle which form the platform cabin; and the load cabin bearing truss applies supporting force on the partial shell and the intermediate partition which form the load cabin. According to the main architecture of the small-type high-orbit satellite common platform, a bearing structure is composed of the platform cabin main bearing truss set, the load cabin bearing truss, a bottom plate inner embedded frame, and a baffle inner embedded frame.

The invention provides a shear type damping tube having a vibration damping performance and a vibration damping adapter. The shear type damping tube comprises an aluminum alloy joint, a carbon fiber tube, a damping glue layer, an aluminum alloy bushing and a steel spring tube, wherein the upper section of the carbon fiber tube is in bonding connection with the aluminum alloy joint; the outer side of the lower section of the carbon fiber tube is connected with the inner side of the aluminum alloy bushing through the damping glue layer; the inner side of the lower section of the carbon fiber tube is in bonding connection with the outer side of the steel spring tube; and the aluminum alloy bushing is connected with the steel spring tube. Compared with the prior art, the vibration damping adapter, produced by the shear type damping tube having the vibration damping performance, has excellent vibration damping performance to restrain low-frequency vibration of satellite effective load of an active flight section of a carrying rocket, and has better rigidity to improve the mechanical environment of the satellite effective load at the active flight section of the rocket when being used for connecting the carrier rocket with a satellite.

The invention discloses a novel three-dimensional shearing type shock absorber and relates to the technical field of shock absorbing. The shock absorber comprises a metal inner cylinder, a metal outercylinder and a lower metal part. The metal outer cylinder comprises a cylinder portion and a turnup portion. The cylinder portion is arranged outside the metal inner cylinder in a sleeving manner. The cylinder portion and the metal inner cylinder are connected through a first buffering part. The lower metal part is connected with the turnup portion through a second buffering part. According to the shock absorber, the first buffering part can deform in a shearing manner in the axial direction of the shock absorber, the second buffering part can deform in a shearing manner in the radial direction of the shock absorber, and thus the shock absorber focuses on shearing energy consumption in three directions on the severe vibration and impact mechanics conditions. Compared with a traditional shock absorber, the magnification times of resonance points is reduced greatly, and thus the mechanic environment of shock absorbed equipment is improved powerfully. In addition, according to the novelthree-directional shearing type shock absorber, the first buffering part and the second buffering part can be designed flexibly according to the actual conditions, and thus equivalent frequency in three directions can be met when the shock absorber is used.

The invention provides a main framework of a small high-orbit satellite public platform, the main framework of the small high-orbit satellite public platform comprises a shell, a middle partition plate, a platform cabin main bearing truss group and a load cabin bearing truss, the shell forms an accommodating space, and the middle partition plate divides the accommodating space into a platform cabin and a load cabin; the platform cabin main bearing truss group is arranged between a part of the shell and the middle partition plate which form the platform cabin and applies supporting force to thepart of the shell and the middle partition plate which form the platform cabin; the load cabin bearing truss is arranged between part of the shell and the middle partition plate which form the load cabin, and applies supporting force to the part of the shell and the middle partition plate which form the load cabin; the load cabin bearing truss is cylindrical, satellites are connected to the upperportion of the load cabin bearing truss in series for inter-satellite series structure design and mechanical transmission while the load cabin bearing truss bears satellite loads, and the inter-satellite series structure is used for a launching task of one rocket and two satellites of a small high-orbit satellite.

The invention discloses a method and a device for adjusting a knee joint prosthesis. The method comprises the following steps of: acquiring contact data of a contact area of a condyle surface of a current knee prosthesis, wherein the contact data comprises at least a contact stress and a contact area; acquiring physiological demand data of the target object; based on the contact data and the physiological demand data, determining whether to adjust the curvature of the current knee prosthesis. The method and the device solve the technical problem that the prior art is unable to improve and adjust the knee joint prosthesis for different patients, which leads to the inability to provide the knee joint prosthesis meeting the personalized needs of users.

The invention provides a gas cylinder support for a spacecraft. According to the gas cylinder support, gas cylinders can be arranged in a concentrated mode, the layout space is saved, the space utilization rate is improved, the force transferring route is direct, environment conditions are excellent, the bearing ratio is high, and the dynamic characteristic is good. The gas cylinder support comprises a gas cylinder installation plate and supporting plates, the gas cylinder installation plate and the supporting plates are carbon fiber skin aluminum honeycomb sandwich plates, the gas cylinder installation plate is installed on a center force bearing barrel, gas cylinder installation connectors with the same number as gas cylinders are evenly distributed on the upper surface of the gas cylinder installation plate in the circumferential direction, and each gas cylinder installation position on the lower surface of the gas cylinder installation plate is provided with one supporting plate. Each supporting plate is connected with the gas cylinder installation plate through a lateral embedded part; meanwhile, the supporting plates are connected with the center force bearing barrel through connection corner strips, and at least one supporting plate is connected with a middle plate through a connection corner strip.

The invention relates to a novel circuit board locking device with a damping vibration attenuation function, which comprises two parts, namely a damping locking strip and a damping mounting plate, which are both of a rubber-metal integrated structure and are mainly used for mounting a plugboard type printed circuit board (PCB). In a severe mechanical environment, the high-damping rubber material can convert dynamic energy into elastic potential energy and heat energy of rubber, so that the dynamic response of the PCB is reduced; and on the other hand, the device has a locking function due to the arc-shaped bulge locking structures on the damping locking strip and the damping mounting plate, so that the use reliability of the PCB is ensured. Besides, the novel circuit board locking device can be used in cooperation with a traditional three-section type or five-section type locking strip to form the adjustable damping locking device, and the mechanical environment of the PCB is powerfully improved.

An artificial intervertebral disc includes an upper joint (3) and a lower joint (7) configured according to the corresponding upper and lower positions, and which includes a removable fixing structure which makes a permanent connection between the upper joint (3) and the lower joint (7).

The invention relates to a rubber buffering and vibration isolating elastomer structure which comprises an upper metal part, a rubber part and a lower metal part. An internal cavity structure is adopted by the rubber body of the invention to increase the buffering stroke of the rubber body, and the buffering deformation of the rubber body can reach 100%; and if the space along the axial directionof the elastomer structure is large enough, the buffering deformation can reach about 150%. The design of the cavity structure greatly increases the buffering deformation stroke of the rubber part by2-4 times of the traditional rubber isolator, thereby greatly improving the buffering effect. The structure of the invention adopts the design of a gas channel; on the one hand, by the design of the gas channel, when the elastomer bears the impact load, because the action time of the load is short, the gas in the cavity is quickly discharged outwards through the gas channel, and the friction action of the gas and the channel increases the damping of the elastomer structure, thereby increasing the buffering effect of the elastomer structure; and on the other hand, by the design of the gas channel, the gas in the cavity can be smoothly discharged under the action of the load to avoid the uneven deformation of the rubber part caused by sealing of the cavity, thereby ensuring the rigidity stability of the elastomer structure in the deformation process.

The invention belongs to the field of structure design of a spacecraft assembly, and particularly relates to adjusting measurement of pointing accuracy of a spacecraft sensor as well as auxiliary supporting and vibration reduction of end parts. An embraced type sensor vibration reducing bracket with adjustable installing and pointing accuracy comprises an embraced hoop and adjusting supports, wherein each adjusting support comprises an adjusting screw rod, a supporting seat and a falling-preventing screw, the adjusting screw rod is provided with a locking nut, a wrench is arranged at one end of the adjusting screw rod, the other end is installed in a ring groove in the inner end surface of the supporting seat through the falling-preventing screw, a silica gel shock pad B is arranged on the outer end surface of the supporting seat, and the adjusting support is mounted at a threaded hole in the embraced hoop through the adjusting screw rod. According to the invention, the end parts of the sensor are subjected to auxiliary support, the installing form of the sensor is changed from a cantilever form to a simple support form, so that the mechanical environment of the sensor is improved, and the installation stability is improved; the precision adjusting measurement of a pointing shaft of the sensor can be realized at the accurate measurement stage of the spacecraft assembly.

The present invention provides an integrated satellite with a compact layout, which includes a bottom plate, and a mounting flange is arranged on the surface of the bottom plate, and the mounting flange is used to set up the on-satellite load equipment, thereby forming a first line for the on-satellite load equipment. Force transmission path; the surface of the bottom plate is further provided with a baffle on each of the four diagonal corners, and the four baffles support a top plate, and the top plate is used to set the extraterrestrial load equipment, thereby forming a pair of extraterrestrial load equipment the second force transmission path. The advantage of the present invention is that it proposes a load-centered integrated satellite configuration, realizes a layout around the load, and designs a structural scheme in which two main force transmission paths and one secondary force transmission path work together , realize the optimization of the mechanical environment of the load, reduce the complexity and pressure of the design of the satellite structure and load structure, and improve the bearing ratio of the satellite structure.

The invention provides a prosthesis connecting piece and a prosthesis assembly, and the prosthesis connecting piece comprises a telescopic rod which comprises a first rod body and a second rod body which can move relatively; a transmission structure which is arranged in the telescopic rod, wherein the transmission structure rotates to drive the second rod body to move relative to the first rod body, a through hole opposite to the transmission structure is formed in the telescopic rod, and an external tool can drive the transmission structure to rotate through the through hole; and a magnetic driving structure which can drive the transmission structure to rotate under the action of an external magnetic field. By applying the technical scheme of the invention, the problems of poor implantation effect and universality of the prosthesis in the prior art can be effectively solved.

The invention provides a satellite-rocket integrated satellite bottom frame which comprises a framework body (10). The framework body (10) is provided with a bearing plate (20) and a connecting ring (30), wherein the bearing plate (20) is of a square framework structure and is provided with a first mounting joint (21) so that connection with a satellite bottom plate (40) and a single machine can be achieved; the connecting ring (30) is of a skirt structure and is located below the bearing plate (20), and the connecting ring (30) is provided with a second mounting joint (31) so that connectionwith a rocket adapter (50) can be achieved; and the connecting ring (30) and the bearing plate (20) are formed integrally. According to the satellite-rocket integrated satellite bottom frame, the lightweight design of a satellite can be well achieved, and meanwhile the mechanical environment of the single machine on the satellite is improved so that the launching adaptability of the satellite canbe enhanced.

The invention belongs to the field of structure design of a spacecraft assembly, and particularly relates to adjusting measurement of pointing accuracy of a spacecraft sensor as well as auxiliary supporting and vibration reduction of end parts. An embraced type sensor vibration reducing bracket with adjustable installing and pointing accuracy comprises an embraced hoop and adjusting supports, wherein each adjusting support comprises an adjusting screw rod, a supporting seat and a falling-preventing screw, the adjusting screw rod is provided with a locking nut, a wrench is arranged at one end of the adjusting screw rod, the other end is installed in a ring groove in the inner end surface of the supporting seat through the falling-preventing screw, a silica gel shock pad B is arranged on the outer end surface of the supporting seat, and the adjusting support is mounted at a threaded hole in the embraced hoop through the adjusting screw rod. According to the invention, the end parts of the sensor are subjected to auxiliary support, the installing form of the sensor is changed from a cantilever form to a simple support form, so that the mechanical environment of the sensor is improved, and the installation stability is improved; the precision adjusting measurement of a pointing shaft of the sensor can be realized at the accurate measurement stage of the spacecraft assembly.

The invention relates to a method for improving the safety of a Doppler radar, belongs to the technical field of speed measurement radars, and solves the problems that the appearance of an existing Doppler radar is not conformal with a carrier, the required installation space is large, and the safety of the Doppler radar is guaranteed. The method for improving the safety of the Doppler radar comprises the following steps of: S1, performing protection treatment on the surface of each extension; S2, arranging each extension set of the radar in a shielding box body structure of each extension set, so as to realize the modular design of each extension set of the radar; S3, setting connectors of all the extensions to be in a differential structural form, and setting identification marks; S4, installing the shielding box bodies of all the extension sets in a main body frame of a conformal structure through using vibration reduction structures; and S5, installing an upper cover plate of the conformal structure, and sealing each extension of the radar in a cavity of the conformal structure. According to the method, the Doppler radar and the mounting surface can be conformal, the mounting space is small, and the safety is high.

The invention provides a satellite layout based on joint detection of multiple types of remote sensing instruments, which comprises a satellite platform, a laser / millimeter wave radar and a terahertz radar are respectively mounted at the top of the satellite platform through a first mounting rack and a second mounting rack, and a thruster unit is mounted at the bottom of the satellite platform. A first side face, a second side face, a third side face and a fourth side face are sequentially arranged on the peripheral side of the satellite platform, an optical imaging detection instrument, an earth data transmission antenna, an earth measurement and control antenna and a sun sensor are arranged on the first side face, and an antenna measurement and control antenna and a navigation receiving antenna are arranged on the third side face. According to the invention, three active radar loads, namely the laser radar, the millimeter wave radar and the terahertz radar, and an optical imaging instrument are arranged on the same platform, so that the application requirement of joint detection of multiple types of remote sensing instruments is met.

The invention relates to a circuit board locking device with the function of damping and vibration reduction, which includes two parts, a damping locking strip and a damping mounting plate, both of which are rubber-metal integrated structures, and is mainly used for plug-in printed circuit boards (PCBs). Install. In the present invention, the high-damping rubber material can convert dynamic energy into elastic potential energy and heat energy of the rubber under harsh mechanical environments, so that the dynamic response of the PCB is reduced; The locking structure enables the device to have a locking function, thereby ensuring the reliability of the PCB. In addition, the device can also be used in conjunction with the traditional three-section or five-section locking strip to form a so-called adjustable damping locking device, which can effectively improve the mechanical environment of the PCB.

The invention relates to the technical field of vibration reduction and locking of electronic equipment, aims to solve the problems that a vibration reduction device in the prior art is non-adjustable in vibration reduction frequency and poor in universality for different equipment, and provides a vibration reduction and heat dissipation locking device with adjustable vibration reduction frequency, which comprises a locking device body, and an elastic heat conduction pad is arranged at the bottom of the locking device body; a plurality of elastic vibration reduction blocks are arranged on the locking device body, and a vibration reduction elastic component is arranged in each elastic vibration reduction block; an adjusting part is arranged on the locking device body, and different elastic vibration reduction block combinations can be in contact with a case guide rail by adjusting the adjusting part, so that the vibration reduction frequency of the locking device is adjusted; and the device has the beneficial effects that according to the vibration reduction frequency requirements of different modules, the elastic vibration reduction blocks of different combinations make contact with the case guide rail, the vibration reduction frequency is adjusted, the mechanical environment of the module is improved, the environmental adaptability of the module under the vibration condition is improved, reliability is high, universality is good, and meanwhile, the elastic heat conduction pad is used for conducting heat.

The invention relates to a high-stability supporting structure applied to a long-strip-shaped space reflector. The high-stability supporting structure comprises a mirror frame, a center support, sidesupports, an upper support and a lower support. A reflector is installed in the mirror frame, and the center support is located in the center of the reflector. The side supports are inserted into thereflector from the sides of the mirror frame; the upper support and the lower support are respectively inserted into the reflector from the side surfaces of the mirror frame and are positioned on theother sides of the surface supports, and axes of the upper support and the lower support are overlapped; the upper support and the lower support are symmetrically arranged with the long axis of the reflector as the symmetry axis. By the adoption of the supporting structure, the long-strip-shaped reflector can achieve second-level stability; meanwhile, the good mechanical environment resistance isachieved, high reflector surface shape precision can be kept in a severe mechanical environment, and the problem that a reflector supporting structure is unstable is solved.

The invention relates to a spatial pointing mechanism capable of improving the environmental adaptability of a feeder, comprising a supporting part, the supporting part includes an X-direction mount, a cross bracket and a Y-direction mount, and the X-direction mount and the Y-direction mount are respectively Rotationally connected to the upper and lower sides of the cross bracket, the X-direction seat frame is rotationally connected to the cross bracket on the X axis, and the Y-direction seat frame is rotationally connected to the cross bracket on the Y axis; The X-direction seat frame is provided with an X-direction rotary joint bracket for installing the X-direction rotary joint, and the Y-direction seat frame is provided with a Y-direction rotary joint bracket for installing the Y-direction rotary joint; the upper and lower sides of the cross bracket An X-direction beam along the X-direction and a Y-direction beam along the Y-direction are respectively provided. The invention solves the technical problem in the prior art that the feeder has a bad working thermal environment due to the feeder generating heat during operation, produces relatively large thermal deformation and thermal stress, and adversely affects the performance of the feeder.

The invention discloses a bionic knee-guarding support. The bionic knee-protecting supporting tool comprises two support clamping boards fixed at the two sides of the lower limb of a human body by a band; all the support clamping boards comprise thigh supporting boards connected with the thighs and crus supporting boards connected with the cruses; the thigh supporting boards and the crus supporting boards are rotatably connected at the positions of knee joints of the human body; the knee-guarding support also comprises a meniscus like structure capable of generating a function of a meniscus board, one end of the meniscus like structure is connected with each thigh supporting board, and the other end of the meniscus like structure is connected with the crus supporting board. By adoption ofthe technical scheme, the meniscus like structure can simulate the function of the meniscus so as to simulate the movement of the knee joints of the human body, the gravity from the thighbones is uniformly transmitted to the cruses in a decreasing manner, the concentrated load is avoided, and the pressure stress on the tibiofemoral joints is reduced; and in treatment of acute and chronic injuriesof the knee joints, enables the knee joints to carry out early-stage functional exercises and activities, and the load of the knee joints can be fully eliminated.