34 results about "Orbital ring" patented technology

A non-contact magnetic drive assembly with mechanical stop elements for a vacuum deposition system employing a lift-off process having a HULA configuration featuring a plurality of magnets coupled in an annular orientation to a central ring and an orbital ring, each magnet of the orbital ring becomes superposed with a magnet of the central ring as the orbital ring rotates, and a central drive component driving either the central ring, the orbital ring around the central ring or both simultaneously, the central drive component provides a rotational speed allowing non-contact, magnetic drive rotation of the orbital ring around the central ring until a difference between a magnetic drive torque of the superposed magnets and the rotational speed of the central drive component causes the superposed magnets to decouple enabling mechanical drive rotation by interactive contact between a plurality of central ring teeth and a plurality of orbital ring.

Hybrid orbital fluid dynamic bearing motors are disclosed. The motors achieve improved efficiency advantages observed in fluid dynamic bearing motors containing an orbital ring. In addition, the hybrid orbital FDB motor has serial thrust bearings and traditional style journal bearings, which provide typically higher radial and angular stiffness not observed in previous orbital fluid dynamic bearing motor designs. Designs for centering orbital rings are also disclosed.

Hybrid orbital fluid dynamic bearing motors are disclosed. The motors achieve improved efficiency advantages observed in fluid dynamic bearing motors containing an orbital ring. In addition, the hybrid orbital FDB motor has serial thrust bearings and traditional style journal bearings, which provide typically higher radial and angular stiffness not observed in previous orbital fluid dynamic bearing motor designs. Designs for centering orbital rings are also disclosed.

The invention discloses a method of determining space environment synergistic effect relevancy. The method comprises the steps that a high and low temperature alternating environment is determined according to an in-orbit environment; a composite material is selected and is subject to several space environment states in groups; an environment effect test is completed according to a test scheme; according to the effect equivalent principle, an atomic oxygen test dose and test machine hours are determined; thermal circulation test parameters are made; a two-factor environment matrix test is completed, and a test sample performance parameter test after the two-factor environment matrix test is performed; and crossing comparison is performed on test data in a matrix table, and a simple adductratio, namely an additive coefficient, to a single-factor test result is obtained. According to the method, through understanding, processing, extrapolation and exploration of a ground single factor and the sequential action test data, the simultaneous acting effect of in-orbit space environment factors can be estimated and prejudged, and the effectiveness of space environment test research is effectively improved.

The invention relates to a rotary automatic lifting handrail. The rotary automatic lifting handrail comprises a hand support and a rotary lifting device, wherein the hand support is provided with a connecting block and a transmission block; a steel ball is arranged on the outer side wall of the connecting block; the rotary lifting device comprises a track ring, an inner gear ring, a transmission mechanism and a fixed seat; the track ring is installed on the inner gear ring; the transmission mechanism is in transmission connection with the inner gear ring; the fixed seat is installed on the inner gear ring; the track ring is provided with a sliding guide rail with two ends distributed on the inner side wall of the track ring and having uneven heights; the hand support is installed in the track ring through the connecting block; the steel ball is slidably embedded in the sliding guide rail; and the transmission block is in transmission connection with the transmission mechanism. The rotary automatic lifting handrail has the beneficial effects that a miniature planetary transmission system is arranged on a traditional handrail, so that automatic rotation and lifting functions are achieved; the rotating structure adopts guide rail type motion, the friction of the steel balls is small, the contact area is increased, the stability and the accuracy are improved; and the lifting structure adopts an inner gear meshing principle, the transmission block and the inner gear ring are meshed with each other to drive the hand support to rotate, so that the stable performance is improved.

A multiple-access transceiver handles communications with mobile stations in environments that exceed mobile station design assumptions without necessarily requiring modifications to the mobile stations. One such environment is in Earth orbit. The multiple-access transceiver is adapted to close communications with mobile stations while exceeding mobile station design assumptions, such as greater distance, greater relative motion and / or other conditions commonly found where functionality of a terrestrial transceiver is to be performed by an orbital transceiver. The orbital transceiver might include a data parser that parses a frame data structure, a signal timing module that adjusts timing based on orbit to terrestrial propagation delays, frequency shifters and a programmable radio capableof communicating from the Earth orbit that uses a multiple-access protocol such that the communication is compatible with, or appears to the terrestrial mobile station to be, communication between a terrestrial cellular base station and the terrestrial mobile station.

A non-contact magnetic drive assembly with mechanical stop elements for a vacuum deposition system employing a lift-off process having a HULA configuration featuring a plurality of magnets coupled in an annular orientation to a central ring and an orbital ring, each magnet of the orbital ring becomes superposed with a magnet of the central ring as the orbital ring rotates, and a central drive component driving either the central ring, the orbital ring around the central ring or both simultaneously, the central drive component provides a rotational speed allowing non-contact, magnetic drive rotation of the orbital ring around the central ring until a difference between a magnetic drive torque of the superposed magnets and the rotational speed of the central drive component causes the superposed magnets to decouple enabling mechanical drive rotation by interactive contact between a plurality of central ring teeth and a plurality of orbital ring.

The invention belongs to the technical field of space docking, and discloses an omnibearing docking system and method based on flight array. The outer end of a docking shell is fixedly provided with a driving steering engine through screws, the docking shell is cylindrical, the interior of the docking shell is hollow and serves as a steering engine rotating space, and a bearing ring is installed in the middle of the docking shell; a locking track ring is mounted on the inner ring of the bearing ring, and the inner side of the locking track ring is fixedly connected with a steering engine arm through a plurality of screws; a buffer block is mounted in a recess in the middle of the locking track ring, and is connected with the steering engine arm and the locking track ring through screws; and the side face of the buffer block is connected with the locking track ring through a fixing assembly. The system has obvious non-front-face butt joint capability, can realize structural locking between non-front faces of a flight array, and has the advantages of reliable connection, small occupied space and the like; and docking mechanisms are not active and passive, the two docking mechanisms are identical in structure and control principle except for the opposite rotation directions of the steering engines, and the uniformity of topological structures is achieved.

The invention relates to chemical fertilizer production equipment, in particular to a drum-type granulating machine for biological organic fertilizers. The machine comprises a support, an upper drum which can be rotatably mounted at the upper end of the support and a driving motor, wherein an orbital ring and a geared ring are fixedly mounted on the outer wall of the upper drum; the geared ring is in transmission connection with the driving motor by a driving gear; the orbital ring is mounted on a carrier roller in a rolling manner; an inner chamber of the upper drum is of a conical structure of which the diameter of the front end is small and the diameter of the rear end is large; a transfer hopper is arranged at the rear end of the upper drum; a ventilation hole is formed in the upper end of the transfer hopper; a discharging pipe is arranged at the lower end of the transfer hopper; the side wall of the transfer hopper is in butt joint with the upper drum; a lower drum can be rotatably mounted under the support; an inner chamber of the lower drum is of a conical structure of which the diameter of the front end is large and the diameter of the rear end is small; and the rear end of the lower drum is in butt joint with the discharging pipe. The reciprocating drum-type granulating machine for the biological organic fertilizers has reasonable structure, is high in production efficiency, can complete processes such as membrane coating, sieving and drying can be completed once, and meanwhile, wall attachment materials can be removed without needing shutdown of the machine.

The invention provides a burnup minimization control method for launching a low-orbit circumlunar aircraft in a lunar surface base, and belongs to the technical field of deep space exploration aircraft optimal control. The control method adopts a mixed method combining an indirect method based on the Pontryagin minimum principle and a direct method of one-dimensional numerical value search to achieve accurate orbit injection, save fuel consumption to the maximum extent, so the structural weight of the aircraft is reduced, the loaded load is increased, and the benefits of spaceflight launchingand space activities are improved. According to the method, the advantages of the indirect method and the direct method are combined; a problem is converted into a single-degree-of-freedom single-parameter searching problem through the indirect method, and is specifically solved through the direct method; and the global optimality of minimum burnup control in the process of launching the low-orbitcircumlunar aircraft in the lunar surface base, the rapidity of the solving process and the simplicity and feasibility of the control method in engineering implementation can be ensured.

The invention discloses a multi-degree-of-freedom intelligent mechanical arm and a testing method thereof. At the free end of the mechanism, the rotating mechanism is a multi-stage structure connected by a rotating shaft. The rotating mechanism can realize the movement of the cutter head towards or away from the stone through the rotating shaft; Image acquisition equipment, and the motor assembly that controls the circumferential rotation of the cutter head; the image acquisition equipment transmits the notch depth and the notch width position to the external processing unit, thereby obtaining the material data of the ring line on the stone surface. The step-by-step ring cloth test can obtain the material characteristic data of all positions on the stone surface, so that it is convenient for the operator to carry out stone carving design and stone carving process planning, and finely control stone carving materials and labor costs.

The invention discloses a guide rail support of an electric power maintenance robot, which comprises a mobile support and a displacement adjustment device arranged on the top of the mobile support. The displacement adjustment device is used for installing a maintenance mechanical arm and for adjusting The position is adjusted. The displacement adjustment device includes an orbital ring and a driving device installed on both sides of the mobile support. The orbital ring is driven by a first servo motor and rotates on the top of the mobile support. The orbital ring It includes a fixed section and a support section that is rotatably connected with the fixed section. When in use, the position of the mounting support can be controlled by controlling the cooperation of the screw and the track ring, and the track ring can be stored in the mobile when not in use. The two sides of the support further ensure that the mechanical arm can move freely in a large space, and at the same time avoid the problem that its large volume makes it difficult to pass through mountains or narrow roads in the wild.

The present invention relates to the technical field of bearing transposition devices, in particular to a super-large bearing pose transformation mechanism, which includes a bottom plate, a hollow rectangular fixing frame is arranged on the bottom plate, and a ring-shaped moving track is arranged inside the fixing frame. There is a through hole in the moving track that communicates with the outside world, and the wall of the through hole is provided with a number of gear teeth that are arranged at equal intervals in a ring shape. There are two moving devices facing each other on the circular moving track. There is a clamping and rotating device on the top, a jacking device on the bottom plate, and multiple rolling mechanisms between the arc plate and the gear. The operation of the present invention is simple and quick, and it is convenient to change the overturning posture and the tilting posture of the bearing, which brings convenience to the staff.

The invention provides a heat power machine device of a spherical gyro wheel, and the structure of a spherical external combination heat power machine is simplified, so that the whole device is integrated; tedious transmission devices and pats are removed; the spherical external combination heat power machine comprises primary parts such as a rotor, a power output shaft and a grating. The sizes of air chambers a and b on two sides of the grating are changed by means of the rotor, acting air chambers can be continuously and alternately generated and act continuously, so that the revolution can be greatly improved, and continuous power output is avoided. As the whole mechanical structure and part are symmetrical, the machine is steady and does not shake in mechanical rotation, and the output power is increased. The external combination heat power machine is more favorably actually produced and is applied and popularized in life, and development and utilization of a natural environmental-friendly energy source are facilitated.

A rolling bearing (1) is provided with an outer ring (1A), an inner ring (1B), a plurality of rolling bodies (1C), and a seal member (1D). The outer ring (1A) includes a first outer ring (10) and a second outer ring (20). The inner ring (1B) includes a first inner ring (30) and a second inner ring (40). The seal member (1D) is provided with: annular base sections (61, 71) that are affixed to a raceway ring of either an outer ring (1A) or an inner ring (1B); and annular protrusions (62, 72) that protrude from the base parts (61, 71) and extend toward a first region, which is a region of the other orbital ring of the outer ring (1A) and the inner ring (1B) that faces the orbital ring of the outer ring (1A) and the inner ring (1B).

A method for controlling the fuel consumption of a low-orbit orbiting spacecraft launched from a lunar base, which belongs to the field of optimal control technology for deep space exploration vehicles, adopts the indirect method based on the principle of Pontryagin's minimum value and the direct method of one-dimensional numerical search. The hybrid method combined with the above method can achieve accurate orbiting while saving fuel consumption to the greatest extent, so as to reduce the weight of the aircraft structure, increase the payload, and improve the benefits of space launch and space activities. The method provided by the present invention combines the advantages of the indirect method and the direct method: the problem is converted into a single-degree-of-freedom single-parameter search problem through the indirect method, and the direct method is specifically solved, which can ensure that the lunar surface base launches the low-orbit orbiter around the moon. The global optimality of fuel-saving control, the rapidity of the solution process, and the simplicity and feasibility of the control method in engineering implementation.

The invention discloses a multi-angle adjustable processing platform, comprising a bottom support mechanism, the bottom support mechanism includes a bottom support center plate, a bottom support connecting rod and a bottom fixing frame of a limit track ring, the bottom support center plate is set Below the center of the circle of the bottom fixed frame of the limiting track ring, and the bottom support center plate and the bottom fixed frame of the limit track ring are connected by a number of bottom support connecting rods, the bottom support center plate and the bottom support connecting rod The included angle between them is 15°, the bottom support center plate and the bottom fixed frame of the limit track ring are parallel to each other, the side panel of the limit track ring bottom fixed frame away from the bottom support center plate is fixedly connected with a rotating The limit track ring, the side of the rotation limit track ring near the center of the circle is provided with a table rotation limit track groove. The invention has a novel structure and is easy to use. It is a new and practical multi-angle adjustable processing platform.

Rollers, in particular track rollers or load bearing rollers for aerial cableway systems, are formed with a cylindrical tube located radially on the inside, two ring bearings located radially outside the tube and at an axial distance from each other , the rollers located radially outside the ring bearing. The roller body is formed as a raceway ring with two flanged disks flanking it. The rollers contain a ring generator located in a cavity surrounded by the roller body and two ring bearings.

An orbital ring rotary flapping wing power device is composed of a support, an engine, a coupler, a main shaft, an orbital ring supporting frame, an orbital ring connecting body, an orbital ring connecting bearing, a core orbital ring, a sliding sleeve, a sliding sleeve support, a sliding block, a sliding block shaft, a sliding block shaft bearing, a small pulley, a driving rocker arm, a driving rocker arm bearing, a middle shaft connecting block, a driven rocker arm, a driven shaft connecting block, a blade distribution wheel, blades, a blade support, a blade far-end bearing and a sectional type self-combination fan blade. The orbital ring rotary flapping wing power device can effectively provide vertical take-off and landing power for an aircraft, has the advantages of being high in power generation efficiency, good in control effect, low in cost, wide in application scene and the like, and has very positive effects.

Provided is a hub bearing capable of reducing the response delay of the hub bearing itself and improving the steering stability of a vehicle. A hub bearing (1) is provided with: an outer ring (2) that is a stationary-side raceway ring; a hub ring (3) and an inner ring (5) as rotation-side orbital rings; and a plurality of balls (4) as rolling elements provided between the raceway surface of the stationary-side raceway ring and the raceway surface of the rotating-side raceway ring, in which the rolling contact portions between the raceway surfaces and the rolling elements are lubricated by grease. The surface roughness of at least one orbital plane selected from the orbital plane of the stationary-side orbital ring and the orbital plane of the rotating-side orbital ring is 0.03 [mu] mRa or less. The grease is such that the traction coefficient of the rolling contact portion is 0.04 or less at 40 DEG C and the vehicle speed is 20 km / h or more.

The invention relates to a magnetic levitation rotor system and a helicopter having the same, and relates to the field of aviation, in particular to the field of rotor technology. The magnetic levitation rotor system includes a rotor ring (2) connected to the rotor tip and an orbital ring (1) that provides a magnetic levitation force for the rotor ring (2). The magnetic levitation force provided by the orbital ring (1) includes: A driving device that drives the blade to rotate and a suspension device that can levitate the blade tip. A first deflection drive mechanism is provided at the blade root of the rotor to provide a first deflection angle of the blade root. The rotor ring (2) A second deflection driving mechanism is provided to provide a second deflection angle of the blade tip. The rotor ring of the present invention only needs to be driven by the outer track ring, and the blades are connected through a central connector, which not only ensures the independent pitch change requirements of the rotor, but also offsets part of the blade load through the central connector, increasing the overall stability of the rotor ring. performance, improving work reliability.

According to one embodiment, a system includes a dual track loop including a first track loop and a second track loop; a single track loop spaced apart from the dual track loop; and a cross track extending between the dual track loop and the single track loop. The system also includes platforms disposed on the intersecting tracks. The platform is configured to translate between a position aligned with the first and second track rings of the dual track ring and a position aligned with the first and second portions of the single track ring. The system also includes a turntable coupled to the platform and configured to rotate the ride vehicle on the turntable and change the orientation of the ride vehicle relative to the fixed portion of the platform.

The invention discloses a method for determining the correlation degree of the synergy effect of the space environment. The method includes determining the high and low temperature alternating environment according to the orbital environment; selecting composite materials and subjecting them to several space environment states in groups; completing the environment according to the test plan. Effect test; according to the effect equivalent principle, determine the atomic oxygen test dose and test machine time; formulate thermal cycle test parameters; complete the two-factor environmental matrix test, and test the performance parameters of the test samples after the test; test the test data in the matrix table Carry out cross-comparison, respectively and the simple sum ratio of the single factor test results, namely the additivity coefficient. Through the understanding, processing, extrapolation and exploration of ground single factor and sequential action test data, the present invention can predict and predict the simultaneous action effect of on-orbit space environment factors, and effectively improve the effectiveness of space environment test research.