CN-119705865-B - Electromechanical thermal fusion type micro-driving mechanism for space

CN119705865BCN 119705865 BCN119705865 BCN 119705865BCN-119705865-B

Abstract

The invention discloses an electromechanical thermal fusion type micro-driving mechanism for a space, which comprises an outer structure and a driving and controlling integrated shafting, wherein the outer structure comprises a left outer assembly, a right outer assembly, a load support, a rear cover plate, a precision measuring mirror assembly, a locking assembly and a front cover plate, the left outer assembly comprises a left shafting support, a left connector panel, a left switching support and a left support locking nut, the right outer assembly comprises a right shafting support, a right connector panel, a right switching support and a right support locking nut, the driving and controlling integrated shafting comprises a mandrel assembly, a control assembly, a bottom cover plate, a connector assembly and a micro-stress detection device, and the mandrel assembly sequentially comprises a mandrel, a left bearing locking nut, a left bearing seat, a left bearing spacer, a left bearing, a permanent magnet synchronous motor, a right bearing spacer, a right bearing seat and a right bearing locking nut from left to right. The invention has long service life, high precision and programming and information processing capability.

Inventors

CHEN ZENGHAO
ZHOU HENGJIE
WU PENGFEI
YAN DAN
TAO CHENG
CAI SHUWEN

Assignees

上海航天控制技术研究所

Dates

Publication Date: 20260508
Application Date: 20241219

Claims (6)

1. An electromechanical thermal fusion type micro-driving mechanism for space is characterized by comprising an external structure and a driving and controlling integrated shafting; The external structure comprises a left external component, a right external component, a load support (5), a rear cover plate (6), a precision measuring mirror component (7), a locking component (9) and a front cover plate (8), wherein the left external component comprises a left shafting support (1), a left connector panel (2), a left switching support (3) and a left support locking nut (4), and the right external component comprises a right shafting support (10), a right connector panel (11), a right switching support (12) and a right support locking nut (13); The left shafting bracket (1) and the right shafting bracket (10) form a cube, and a front cover plate (8), a rear cover plate (6), a left connector panel (2) and a right connector panel (11) are respectively arranged on the front, the rear, the left and the right of the cube; the locking component (9) is fixed on the front cover plate (8); the load bracket (5) is positioned above the front cover plate (8); The precise measuring mirror assembly (7) is fixed on the right side of the rear cover plate (6) and is used for installation and calibration or used as an assembly precision reference; The driving and controlling integrated shafting comprises a mandrel assembly, a control assembly (22), a bottom cover plate (23), a connector assembly (24) and a micro-stress detection device (29); the mandrel assembly sequentially comprises a mandrel (21), a left bearing lock nut (14), a left bearing seat (15), a left bearing spacer ring (16), a left bearing (17), an angle measuring assembly (18), a permanent magnet synchronous motor, a right bearing spacer ring (25), a right bearing (26), a right bearing seat (27) and a right bearing lock nut (28) from left to right; The permanent magnet synchronous motor comprises a motor rotor (19) and a motor stator (20); the left switching support (3) is connected with the left end of the mandrel (21) through a left support locking nut (4), and the right switching support (12) is connected with the right end of the mandrel (21) through a right support locking nut (13); The mandrel assembly is fixed on a left shafting bracket (1) and a right shafting bracket (10) through a pair of angle contact ball bearings at two ends, the control assembly is embedded at the bottom of the micro-driving mechanism, two ends of the control assembly are respectively fixed on the left shafting bracket (1) and the right shafting bracket (10), and communication and power supply are realized through connector assemblies on a left connector panel (2) and a right connector panel (11); the left shafting bracket (1) and the right shafting bracket (10) are spliced to form a cavity, a micro-stress detection device (29) is embedded in four micro-thin walls of the cavity, the micro-stress detection device (29) detects micro-strain change reaction temperature change by utilizing a differential principle, and temperature slow-change and stability are realized by utilizing a stable micro-space formed by the cavity.
2. An electro-mechanical and thermal fusion micro-drive mechanism for a space according to claim 1, wherein the angular component (18) is driven by magneto-electric technology and has a unique 20-bit split magnetic encoder with interference shielding technology.
3. An electromechanical thermal fusion type micro-driving mechanism for space according to claim 1, wherein the mandrel assembly is connected with the left switching support (3) and the right switching support (12) through two ends of the mandrel (21) to realize the rotation of the load support (5), and the algorithm adaptation of the control assembly (22) is adopted to realize the high-precision pointing motion and the position maintenance of the load.
4. An electro-mechanical and thermal fusion type micro-driving mechanism for a space according to claim 1, wherein the bottom cover plate (23) is made of an aluminum alloy material, so that the control component (22) is prevented from being excessive and the irradiation resistance is improved.
5. The electromechanical thermal fusion type micro-driving mechanism for space according to claim 1, wherein the main control chip of the bottom cover plate (23) adopts an FPGA as a processor.
6. An electromechanical thermal fusion type micro-driving mechanism for space according to claim 1, wherein the locking component (9) is used for locking the front cover plate (8) and the load support (5) in the rocket driving section, limiting the free rotation of the front cover plate and the load support, and unlocking the front cover plate and the load support after entering the track to release the free degree of freedom of the front cover plate and the load support.

Description

Electromechanical thermal fusion type micro-driving mechanism for space Technical Field The invention relates to the technical field of space aircrafts and satellite driving mechanisms, in particular to an electromechanical heat fusion type micro-driving mechanism for space. Background With the increasing application demands of micro-nano satellites, the electromechanical thermal fusion type micro-driving mechanism for space is suitable for space aircrafts, satellite high-precision loads and other mechanisms with high-precision long-life pointing motion and position maintenance requirements, such as stable pointing of an optical axis of a space imaging camera and tracking of targets, and has the performance requirements of high-precision pointing and position maintenance, long-life rotation, on-orbit programming capability and information processing capability and resistance to meeting dynamic environment and space environment. The existing driving mechanisms of space aircrafts and satellites are mostly provided with one-stage or multi-stage speed reduction modes or direct drive brake modes, the requirements on long service life and full-period reliability are not met, and most of the space driving mechanisms are separated from the mechanisms by controllers and cannot meet the requirements on mechanical, electric, thermal fusion and light weight. Because the driving mechanism of the spacecraft and the satellite is directly exposed in a vacuum severe environment for a long time, is in a state of variable speed, stable operation and the like and has long service life, high-precision pointing, high-precision stability and programming and information processing capability are required, and the control component is embedded in the bottom of the mechanism, so that the tight integration of the mechanical mechanism and an electrical system is realized. With the development of miniaturization and light weight of spacecraft mechanisms, the driving mechanism in the prior art cannot meet the requirements. At present, no similar electromechanical thermal fusion type micro-driving mechanism is used in China, and no description or report of related technology is found in similar data at home and abroad. Disclosure of Invention In order to solve the problems, the invention provides an electromechanical thermal fusion type micro-driving mechanism for a space. The technical scheme of the invention is as follows: The electromechanical heat fusion type micro-driving mechanism for the space comprises an external structure and a driving and controlling integrated shafting, wherein the external structure comprises a left external component, a right external component, a load support, a rear cover plate, a precision measuring mirror component, a locking component and a front cover plate, the left external component comprises a left shafting support, a left connector panel, a left switching support and a left support locking nut, and the right external component comprises a right shafting support, a right connector panel, a right switching support and a right support locking nut; The front, the back, the left and the right of the cube are respectively provided with a front cover plate, a back cover plate, a left connector panel and a right connector panel; The locking component is fixed on the front cover plate; the load support is positioned above the front cover plate; the precision measuring mirror assembly is fixed on the right side of the rear cover plate and is used for installation and calibration or used as an assembly precision reference. And the electromechanical thermal fusion type micro-driving mechanism for the definition space comprises a mechanical coordinate system, a calibration coordinate system and a zero position coordinate system. The mechanical coordinate system of the electromechanical thermal fusion type micro-driving mechanism for the space is characterized in that the origin of coordinates is defined as the intersection point of the bottom surface of the base and the axis of the mounting hole, the axis is defined as the normal direction of the bottom surface of the base, the axis is defined as the rotation direction of the mandrel of the electromechanical thermal fusion type micro-driving mechanism for the space, and the mechanical coordinate system is determined according to the right-hand rule. The space is calibrated with an electro-mechanical-thermal fusion micro-drive mechanism, which is defined based on calibrating the precision mirror assembly. The three-axis direction is coincident with the orthogonal three normal of the precision measuring mirror assembly, the three-axis direction is coincident with the mechanical coordinate system, and the origin of coordinates is at the intersection point of the orthogonal three normal of the precision measuring mirror assembly. The space is defined on a mandrel of the mechanism by an electromechanical fusion type micro-driving mechanism zero position coordinate