A Software Trigger Method for Monostable Pulse
A monostable, pulsed technology, applied in the direction of electrical pulse generator circuits, etc., can solve the problems of energy system impact, increase system complexity, large instantaneous power of spacecraft, etc., to reduce complexity and avoid triggering multiple single channels at the same time. Effects of steady state pulses
Active Publication Date: 2014-10-08
BEIJING INST OF CONTROL ENG
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[0002] A spacecraft (satellite or spacecraft) usually includes a variety of components such as sensors and actuators. The power-on or switching of these components often requires monostable pulse triggering. Traditional spacecraft designs generally use hardware to trigger monostable pulses. This method has two limitations: 1) If the spacecraft contains many components, the implementation of the hardware circuit is relatively complicated. Taking the dedicated digital chip CC44538 as an example, each piece of CC44538 can output two pulses. When the spacecraft includes hundreds of 50 to 60 pieces of CC44538 are needed, which greatly increases the hardware cost and correspondingly increases the complexity of the system
2) When the spacecraft needs to output multiple pulses, the hardware will trigger the monostable pulses concurrently, causing the instantaneous power of the spacecraft to be too large, which will affect the energy system of the satellite or spacecraft
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[0019] In order to realize the software trigger control of the monostable pulse, the present invention designs a component switch register and a monostable pulse trigger register in a specific embodiment.
[0020] like figure 1 As shown, when the application software needs to generate a component switch or a key signal output function, first access the component switch register, set the corresponding position of the switch word to 1, and write 0 to the monostable pulse trigger register to generate a monostable pulse, and determine the switch according to the timing length The sustaining time of word writing 1. Only when the switch word is 1 and the monostable pulse is triggered, can the component switch pulse be output, otherwise the component switch pulse cannot be output. After the switching action ends, that is, after the monostable pulse width ΔT is triggered, the application software sends 0 to the corresponding position of the component switch register.
[0021] In ord...
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The invention discloses a software triggering method for monostable pulses, which includes the steps of determining triggering types and triggering time of components; generating component switching signals according to the triggering time; triggering monostable pulse signals; establishing the component switching signals and determining valid time; and detecting the valid time and invalid component switching signals. By the aid of the method, hardware circuit design complexity is reduced, the control problem that multipath monostable pulses need to be triggered and outputted simultaneously is solved, and multiple components are sequentially triggered.
Description
technical field [0001] The invention relates to a software trigger method for a monostable pulse, which belongs to the field of embedded software. Background technique [0002] A spacecraft (satellite or spacecraft) usually includes a variety of components such as sensors and actuators. The power-on or switching of these components often requires monostable pulse triggering. Traditional spacecraft designs generally use hardware to trigger monostable pulses. This method has two limitations: 1) If the spacecraft contains many components, the implementation of the hardware circuit is relatively complicated. Taking the dedicated digital chip CC44538 as an example, each piece of CC44538 can output two pulses. When the spacecraft includes hundreds of 50-60 pieces of CC44538 are needed, which greatly increases the hardware cost and correspondingly increases the complexity of the system. 2) When the spacecraft needs to output multiple pulses, the hardware will trigger the monostabl...
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IPC IPC(8): H03K3/02
Inventor 杨春河董晓刚张辉陈朝晖索旭华刘忠汉尹泉
Owner BEIJING INST OF CONTROL ENG