Modular satellite electric propulsion device with adjustable discharge pulses

A discharge pulse and propulsion device technology, applied in the direction of aerospace vehicle propulsion system devices, etc., can solve the problems of low energy utilization rate, poor modularity, low efficiency, etc., achieve adjustable on-off time, simplified fuel supply mechanism, and high efficiency Effect

Active Publication Date: 2020-02-07
遨天科技(北京)有限公司
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Problems solved by technology

[0009] The purpose of the present invention is to propose a modularized satellite electric propulsion device with adjustable discharge pulses in view o

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  • Modular satellite electric propulsion device with adjustable discharge pulses

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Embodiment 1

[0048] Such as figure 1 As shown, a modular satellite electric propulsion device with adjustable discharge pulse includes a power conversion module 1 , an energy storage and discharge module 2 , a pulse control module 3 , a switch drive module 4 , a thruster module 5 and a power module 6 .

[0049] Wherein, the power conversion module 1 includes a power converter 11 of an energy storage module, a power converter 12 of a switch driving module, and a power converter 13 of a pulse control module. The power conversion module 11 has functions of current limiting protection and surge suppression.

[0050] The energy storage and discharge module 2 includes a capacitor 21, an inductor 22, a controllable switch 23, a resistor 24, and the like. Using the principle that the current of the inductor 23 cannot change abruptly, an instantaneous increase in voltage is obtained. The power supply module 6 will charge the capacitor 21 when the power supply module 6 is powered on. When the cont...

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Abstract

The invention relates to a modular satellite electric propulsion device with adjustable discharge pulses, and belongs to the field of electric propulsion of micro-nano satellites. By combination withrapid on-off of a controllable switch and on the basis of incapacity of abrupt changes of inductive current, inductive energy storage and voltage boosting are realized, discharge between an anode anda cathode of a thrustor is realized, plasma is ionized and ejected to produce thrust, and the duty ratio of output PWM (pulse width modulation) rectangular waves and the frequency adjustment thrust are adjusted by a pulse control circuit. The modular satellite electric propulsion device has a small size, and a feed mechanism is simple; on the basis of a mode of the inductive energy storage, 3-27 Vof low voltage can be boosted to plasma breakdown voltage of hundreds to thousands volts instantaneously, and the voltage demand of satellite power supply and distribution is reduced; the cost is effectively reduced; with the adoption of modular design, functions can be freely combined according to the demands, an interface is compatible, and different series of thrustors can be formed by combination with power supply units with different discharge powers and frequencies; and the digital adjustable pulse control circuit is easy to debug, and accurate control over the thrust can be realized.

Description

technical field [0001] The invention relates to a modularized satellite electric propulsion device with adjustable discharge pulses, in particular to a modularized electric propulsion device with inductive energy storage and digitally adjustable pulse discharge frequency, belonging to the technical field of microsatellite electric propulsion. Background technique [0002] With the development of micro-electronic machinery and micro-nano technology, pico-satellites within 1 kg, nano-satellites within 10 kg, cube satellites and micro-satellites within 100 kg are showing a rapid development trend to meet the needs of commercial aerospace medium and low-orbit Internet of Things communication satellites, Large-scale deployment and low-cost application requirements of Internet communication satellites, remote sensing satellites, navigation enhancement satellites, and scientific experiment satellites. The quality and orbital characteristics of these satellites put forward new requi...

Claims

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Application Information

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IPC IPC(8): B64G1/40
CPCB64G1/40
Inventor 王红霞戴阳
Owner 遨天科技(北京)有限公司
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