5 results about "Planetary system" patented technology

A continuous variable planetary (CVP) system comprises a C2 carrier having a pattern of slots, the slots having one or more slot walls; a C1 carrier, at least one of the C2 carrier or C1 carrier being rotatable relative to the other; at least three planetary assemblies coupled between the C2 carrier and the C1 carrier, each planetary assembly including a planet, a planet axle, and an end cap on at least one end of the planet axle, the end cap disposed within the slot, rotation of C2 carrier relative to the C1 carrier inducing a skew condition in the planet axle and thereby inducing a tilt condition on the planet axle; and a protective layer affixed against at least one of the one or more slot walls, the protective layer including one or more protective layer attachment features configured to attach to one or more slot wall attachment features.

The invention relates to a planetary reducer for a joint, belongs to the technical field of transmission machinery, and solves the problems that a planetary reducer in the prior art is large in overall weight and low in torque density. The planetary gear train comprises two stages of planetary gear trains, the first-stage planetary gear train comprises four first-stage planetary gears, and the second-stage planetary gear train comprises five second-stage planetary gears; the first-stage sun gear serves as a power input part, the output end of the first-stage planet carrier is coaxially and fixedly connected with the second-stage sun gear, and the second-stage planet carrier serves as a final output component of the speed reducer. The multi-planet differential design of the first-stage four planet gears and the second-stage five planet gears is adopted, the weight of the whole machine is reduced, and the torque density can be increased by about 15%.

A planetary system component support device comprises: - a solar support (1) rotatably mounted about a solar axis (S) relative to a reference system; at least one planetary support (2) rotatably mounted on the solar support (1) about a planetary axis (P) parallel to the solar axis (S); - first drive means (5) for driving the planetary support (2) when the solar support (1) rotates about the reference system; - at least one satellite support (3) rotatably mounted on the planetary support (2) about a satellite axis (R) inclined about the solar axis (S); - tilting means (4) for changing the inclination or orientation of the satellite axis (R) relative to the planetary support (2) when the planetary (2) or solar support rotates. Figure for the abbreviation: Fig. 1

The invention relates to a support device for parts of a planetary system, the support device comprising: - a sun support (1) rotatably mounted so as to rotate about a sun axis (S) relative to a reference system, at least one planet support (2) rotatably mounted on the sun support (1) so as to rotate about a planet axis (P) parallel to the sun axis (S); - first drive means (5) for driving the planet support (2) as the sun support (1) rotates relative to the reference system: - at least one satellite support (3) rotatably mounted on the planet support (2) so as to rotate about a satellite axis (R) which is tilted relative to the sun axis (S); - tilting means (4) for modifying the tilt or orientation of the satellite axis (R) relative to the planet support (2) as the planet support (2) or the sun support (1) rotates.

A planetary system component support device comprises: - a solar support (1) rotatably mounted about a solar axis (S) relative to a reference system; at least one planetary support (2) rotatably mounted on the solar support (1) about a planetary axis (P) parallel to the solar axis (S); - first drive means (5) for driving the planetary support (2) when the solar support (1) rotates about the reference system; - at least one satellite support (3) rotatably mounted on the planetary support (2) about a satellite axis (R) inclined about the solar axis (S); - tilting means (4) for changing the inclination or orientation of the satellite axis (R) relative to the planetary support (2) when the planetary (2) or solar support rotates. Figure for the abbreviation: Fig. 1