Miniature hysteresis synchronous motor for inertial platform of aircraft
An inertial platform and synchronous motor technology, applied in the field of inertia, can solve the problems of unstable air supply, unstable asynchronous motor speed, and the temperature of the inertial platform cannot reach a balanced state, so as to improve the system accuracy and ensure stable operation.
Inactive Publication Date: 2019-03-12
TIANJIN NAVIGATION INSTR RES INST
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Problems solved by technology
The working principle of the asynchronous motor determines that its working speed changes with the change of the load. When the platform is working, due to the unstable speed of the asynchronous motor and the unstable air supply, the temperature in the inertial platform cannot reach an ideal equilibrium state.
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[0017] The embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that the embodiments are illustrative, not restrictive, and cannot limit the protection scope of the present invention.
[0018] A miniature hysteresis synchronous motor for an aircraft inertial platform, the motor adopts an outer rotor, an inner stator, and a hidden pole structure, see figure 1 . The motor mainly includes impeller (1), nut (2), motor shaft (3), end cover (4), screw (5), inertia rotor (6), stator armature (7), bearing (8), shell body (9) and terminal (10).
[0019] Terminal post (10) is installed on the outside of housing (9). A motor shaft (3) is coaxially installed in the housing, and the motor shaft is coaxially connected with an inertial rotor (6), and the inertial rotor is located between the housing and the motor shaft. The inertial rotor is composed of a rotor bracket (11) and a hysteresis ring (12). The ...
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The invention relates to a miniature hysteresis synchronous motor for an inertial platform of an aircraft. The miniature hysteresis synchronous motor for the inertial platform of the aircraft comprises an impeller, a nut, a motor shaft, an end cover, an inertial rotor, a stator armature, a shell and a wiring column; the wiring column is installed outside the shell; the motor shaft is coaxially installed in the shell; the motor shaft is coaxially connected to the inertial rotor; the inertial rotor is positioned between the shell and the motor shaft; the stator armature is arranged between the inertial rotor and the motor shaft; the stator armature is installed on the end cover; the end cover is fixedly installed at the upper end of the shell; and the upper end of the motor shaft passes through the end cover, and is coaxially installed with the impeller. By means of the miniature hysteresis synchronous motor for the inertial platform of the aircraft in the invention, the temperature inequality in the aircraft inertial platform is solved; the system precision is increased; the steady operation of the aircraft is effectively ensured; and the gap of the domestic field is filled.
Description
technical field [0001] The invention relates to the technical field of inertia, in particular to a miniature hysteresis synchronous motor for an aircraft inertial platform. Background technique [0002] Generally, the inertial platform of an aircraft is small in size, light in weight, and has limited internal space. There are various electromechanical instruments installed inside. These instruments heat unevenly during operation, which will lead to uneven internal temperature of the inertial platform. There are temperature gradients at different positions, which seriously affect the inertia. The accuracy of the instruments in the platform will increase the system output error, reduce the accuracy, and the attitude of the aircraft will deviate, which is not conducive to the stable operation of the aircraft. At present, micro asynchronous motors are used for ventilation circulation to balance the temperature in the inertial platform. The working principle of the asynchronous ...
Claims
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Patent Timeline
Login to View More IPC IPC(8): H02K9/06H02K7/00H02K7/08H02K5/22H02K5/24
CPCH02K5/225H02K5/24H02K7/003H02K7/083H02K9/06
Inventor 陈金来江建华乔娟张宝兴宋中建
Owner TIANJIN NAVIGATION INSTR RES INST