10 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%.

The utility model belongs to the technical field of gear boxes, and discloses a step-up gear box which comprises a box body, a multi-stage planetary system and an output planetary system. The multi-stage planetary system is arranged in the box body and comprises a middle sun gear rotationally connected to the box body, the output planetary system comprises an output rotating frame, an output gear ring, an output rotating wheel, an output sun gear and an output shaft, the output rotating frame is connected to the middle sun gear and the output gear ring, and the output rotating wheel is rotationally connected to the box body; the middle sun gear is connected to the output rotating stand and meshed with the output gear ring and the output sun gear, the output sun gear is connected to the output shaft, and the rotating axes of the middle sun gear, the output rotating stand, the output gear ring, the output sun gear and the output shaft are coaxially arranged. By means of the arrangement, the speed-increasing gearbox can achieve coaxial power output with the high rotating speed and the high speed ratio.

A kind of revolution and rotation planetary system electron beam evaporation coating method includes the following steps: S1, provides vacuum evaporation device: vacuum evaporation device includes shell, revolution and rotation planetary system, support platform, electron beam evaporation source and backing plate, the cavity and vacuum hole in the shell interior, revolution and rotation planetary system is located in cavity and includes multiple planetary pot, the rotation axis of each planetary pot is inclined relative to revolution axis, backing plate is used to shield vacuum hole but does not hinder vacuumizing;S2, place single crucible: the crucible is placed in the cavity to be located directly below revolution axis;S3, place the wafer to be coated;S4, vacuumizing;S5, start revolution and rotation planetary system;S6, execute first evaporation: the film thickness reached on the surface of each wafer is half of the expected total film thickness in first evaporation;S7, each wafer posture adjustment 180 degrees: S8, start revolution and rotation planetary system again;S9, execute second evaporation: the film thickness reached in second evaporation is half of the expected total film thickness.

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

The application discloses a kind of interplanetary transfer orbit optimization method using three-body system low-energy crossing, belong to aerospace technical field.The application implementation method is: in rotating system, the plane circular restricted three-body model describing the movement of spacecraft is established, based on plane circular restricted three-body model, three-body orbit dynamics is fully utilized to change the flight energy of spacecraft, and the fuel consumption required for interplanetary transfer is reduced.In the heliocentric inertial system, a high-fidelity ephemeris model is established.The perihelion Poincare mapping is used to represent the initial perihelion state of the spacecraft, and the feasible subset corresponding to the low-energy crossing motion in the phase space is determined by parameter scanning.The feasible subset corresponds to the initial perihelion state that can be weakly captured by the planetary system.Based on the feasible subset and the perihelion maneuvering strategy, a low-precision transfer orbit between planets is obtained in the plane circular restricted three-body model, and the high-precision transfer orbit is obtained by correcting the low-precision transfer orbit in the high-fidelity ephemeris model.

The invention refers to a device for increasing the efficiency of any rotary power generating system with progressive variation, whose planetary system may have two or more pairs of pinions, or / and satellites with any multiplication / demultiplication ratio with respect to the central pinion, characterized in that it consists of an assembled inner box, A, which is assembled axially in an assembled outer box, B, to which an assembled side box is axially fixed, C; assembled inner box, A, made of a primary drive shaft, (1), having a flange, by means of which the shaft is oriented and fixed on a cover, (2), in which, axially, is assembled a bearing, (3), and radially, in some bosses, a, processed cylindrically, are fixedly assembled some bearings, (4), in which, with a shoulder, conventionally right, son satellites, (15), are assembled, each of which, on a median shoulder, has assembled a bearing, (4′); axially, in the bearing, (3), is assembled an intermediate pinion, (6), which, to the left of its toothed crown, has assembled a second bearing, (18); in some bearings, (19), (FIG. 4) which are fixed in the cover, (2), are assembled some pinions, (14), which mesh both with the pinions, (15), and with the toothed crown of the intermediate pinion, (6); on the cover, (2), and oriented on the bearings, (4′), (18) and (19), is centered an intermediate cover, (5), which is firmly fixed to the cover, (2), by some screws, (13); on the cover, (5), being oriented and fixed a cylindrical wall, (20); on the conventional left side of each pinion, (15), one eccentric, (16), is fixed rigidly (FIG. 1, FIG. 4, FIG. 5, FIG. 6); after each eccentric, (16), on each pinion, (15), a bearing, (4″), is assembled; on each bearing, (4″), it is oriented, and on the cylindrical wall, (20), is oriented and fixed another cover, (21), in the center of which is assembled a bearing, (22), through which the intermediate pinion, (6), slides; assembled box, B, consisting of a cover, (23), oriented by means of a bearing, (24), on the primary motor shaft, (1), from the assembled inner box, A, cover, (23), on which it is oriented and fixed by means of screws, (25), with the conventionally right surface, an external cylindrical wall, (26), from which, on its conventionally left surface, a cover, (27), is oriented and fixed, by means of screws, (28); cover, (27), which is oriented by means of a bearing, (29), on the primary motor shaft, (1), and which, radially, has some bearings, (35), assembled; a spacer, (30), is interposed between the bearing, (22), and the bearing, (29), on the primary drive shaft, (1); after the bearing, (29), another spacer is assembled, (31), after which a unidirectional bearing, (7), then another spacer, (32), is assembled; assembled side box, C, consisting of a side cover, (36), provided with an axial hole, e, in which is mounted a bearing, (34), in which is assembled the output shaft, c, of a pinion, (11), in which a one-way bearing, (12), which works in the opposite direction to the one-way bearing, (7), is fixedly assembled; radially, on the same diameter on which the bearings are arranged, (35), but in the mirror, inside the side cover, (36), in some bosses, d, are mounted some bearings, (35′), in which are assembled some intermediate pinions, (9), which engages with third pinions, (10), also assembled in some bearings, (37), not shown in the figure, fixed radially in the side cover, (36); this assembled side box, C, is oriented, by means of the bearing, (12), assembled in the pinion, (11), on the primary motor shaft, (1), and, by means of the intermediate pinions, (9), in the bearings, (35), and, by means of the third pinions, (10), in some bearings, (37′), assembled in the cover, (27), and fixed to the cover, (27), by means of screws, (38).

The invention discloses a star-planet system starlight simulator based on a micropore target. The star-planet system starlight simulator comprises a light source, a converging mirror, a displacement table, the micropore target, a collimator and a diaphragm, a light source outputs a collimated light beam through a photonic crystal fiber, and the collimated light beam is focused to a micropore target through a converging mirror; the micropore target is manufactured through a laser direct writing technology and is arranged at the focus of the collimator to form an incoherent point light source, and after the incoherent point light source is collimated by the collimator, simulated star-planet system starlight is output; the displacement table is used for moving a light source module comprising a light source and a converging mirror to adjust the starlight brightness; the diaphragm is arranged at the emergent end of the collimator to simulate a receiving aperture. According to the invention, the single light source and the micropore target of the light-transmitting micropores with micron-sized diameter and spacing are utilized to realize the high-resolution simulation of the star-planet system with the arc-second angular distance, and the technical limitation that the traditional simulator can only simulate the star is overcome.