33 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.

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.

The invention relates to the technical field of bearing posture changing devices, in particular to an ultra-large bearing posture changing mechanism. The ultra-large bearing posture changing mechanismcomprises a base plate. A hollow rectangular fixing frame is arranged on the base plate. An annular moving track is arranged in the fixing frame. A through hole communicating with the outside is formed in the annular moving track. A plurality of teeth are annularly arranged on the wall of the through hole at equal intervals. Two opposite moving devices are arranged on the annular moving track. Clamping and rotating devices are arranged on the moving devices. A jacking device is also arranged on the base plate. A plurality of rolling mechanisms are arranged between an arc plate and a gear. According to the ultra-large bearing posture changing mechanism, operation is easy and fast, a bearing can be changed to be at a turning posture or an oblique posture, and convenience is brought to workers.

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 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 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).

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.