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Simultaneous base variable speed control and angle measurement method of dual-circuit stepping motor of rocket engine

A rocket engine and angle measurement technology, applied in the direction of motor generator control, control system, electrical components, etc., can solve limited problems, achieve the effect of avoiding interruption conflicts, realizing motor frequency conversion control, and ensuring the safety of test run control

Active Publication Date: 2020-03-24
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0004] At present, the processor resources of the motor measurement and control instrument are limited. How to realize the real-time variable speed control and angle measurement of the flow regulator and the fuel throttle valve dual-channel stepping motor at the same time under the limited processor resources, while avoiding conflicts. , it is a problem to ensure the safety of test run control

Method used

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  • Simultaneous base variable speed control and angle measurement method of dual-circuit stepping motor of rocket engine
  • Simultaneous base variable speed control and angle measurement method of dual-circuit stepping motor of rocket engine

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Embodiment Construction

[0051] The present invention will be described in detail below.

[0052] Such as Figure 1-2 As shown, the dual-path stepping motor simultaneous base speed control and angle measurement method of the rocket engine of the present invention includes the following steps:

[0053] 1) Power-on initialization

[0054] Define the priority of angle acquisition interrupt higher than motor speed control interrupt;

[0055] Define the pulse array of the acceleration section, the total value of pulse beats and the number of pulse units in the pulse array of the acceleration section. The pulse array of the acceleration section includes multiple pulse groups arranged in sequence, and each pulse group corresponds to a frequency of motor operation Point; each pulse group includes multiple repetitive pulse units arranged in sequence; each pulse unit corresponds to a step of the motor operation, each pulse unit includes multiple pulse beats arranged in sequence, one of which is low level, The rest ar...

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Abstract

The invention relates to a same time base variable speed control and angle measurement method for a rocket engine two-way stepping motor. The variable speed control is triggered based on a timing signal and adopts multi-level interrupt nesting technology. On the basis of setting an interrupt priority level, an angle acquisition interrupt program is nested in a two-way motor speed control interruptprogram. Stepping pulse transmission of a two-way motor is completed in an interrupt service program. The operation control of speed-up, speed-down and smooth sections of a flow regulator or a fuel throttle valve are executed in sequence. Therefore, the real-time speed control and angel measurement problems under the same time base of the two-way stepping motor of the flow regulator and the fuelthrottle valve are resolved under the condition of minimum occupancy of processor system resources, interrupt conflict is avoided, and the safety of test run control is ensured.

Description

Technical field [0001] The invention belongs to the technical field of liquid rocket engine flow regulation, and relates to a variable speed control and measurement method of a liquid rocket engine two-way stepper motor. Background technique [0002] With the advancement of the liquid oxygen / kerosene engine development process and the continuous improvement of engine performance and boundary condition assessment requirements, the research and development of flow regulator and fuel throttle flow adjustment technology and stepping motor control technology have been carried out, and according to This has developed a liquid oxygen kerosene engine motor measurement and control instrument, which controls the flow regulator and fuel throttle motor during the test run to achieve dual asynchronous, large-scale, real-time and high-precision adjustments of engine thrust and mixing ratio. [0003] The variable thrust and variable mixing ratio adjustment of the liquid oxygen kerosene engine is ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02P8/14
CPCH02P8/14
Inventor 刘军魏京芳徐中节孙海智董国创胡向龙李鹏
Owner XIAN AEROSPACE PROPULSION INST
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