Controlling and remote metering circuit applied to cubic satellite separation device

Abstract

The invention provides a controlling and remote metering circuit applied to a cubic satellite separation device. The circuit comprises a working circuit, a backup circuit and an interface circuit. Thefront end of the interface circuit is connected with a rocket controlling and remote metering cable, and the rear end of the interface circuit is connected with the working circuit and the backup circuit. The interface circuit comprises a first connector COM1, a first reed pipe K1 and a second reed pipe K2, wherein the first reed pipe K1 and the second reed pipe K2 are connected with the first connector COM1. The first connector COM1 comprises a first pin, a second pin, a third pin, a fourth pin, a fifth pin, a sixth pin, a seventh pin, an eighth pin and a ninth pin, wherein the second pin and the seventh pin are connected with the two ends of the first reed pipe K1 separately, the first pin and the sixth pin are connected with the two ends of the second reed pipe K2 separately, the fourth pin and the fifth pin are connected with the working circuit, and the eighth pin and the ninth pin are connected with the backup circuit. Dual-backup design is adopted for a control circuit and a remote metering circuit, any path of work can guarantee that a satellite normally pops up and a correct remote metering signal is transmitted to a rocket, and compared with other satellite separation schemes, high reliability is achieved.

Description

technical field [0001] The invention relates to the technical field of satellite launch, in particular to a control and telemetry circuit applied to a cubesat separation device. Background technique [0002] In recent years, with the rapid development of communication, optoelectronic components, materials, sensors, and other technologies, cube satellites with low cost and high functional density have gradually emerged, which greatly reduces the development cost and development cycle of satellites. Remote measurement and testing become possible. [0003] As an important subsystem of the CubeSat, the separation device's task is to ensure that the satellite can be separated from the rocket smoothly. Most of the existing satellite separation methods at home and abroad use explosive bolts or carbon knife burning wires. Explosive bolts use the impact force generated by the gunpowder stored in the explosive bolts to separate satellites, with complex structures and low safety; carb...

AI Technical Summary

Problems solved by technology

Most of the existing satellite separation methods at home and abroad use explosive bolts or carbon knife burning wires. Explosive bolts use the impact force generated by the gunpowder stored in the explosive bolts to separate satellites, with complex structures and low safety; carbon knife burning wires use The electric energy stored in the built-in supercapacitor module makes the carbon knife heat up, burns the fixed rope, and makes the satellite pop up, which is bulky and low in safety

Explosive bolts often require multiple bolts to work together. It is difficult to ensure that all bolts are disconnected at the same time. In addition, when the bolts are disconnected, the wreckage is easy to damage the satellite and the rocket. Therefore, it is necessary to set up a protective structure accordingly, which is complicated. , larger volume, not suitable for cubic star

The carbon knife burning method needs to provide a lot of power in an instant to make the carbon knife heat up and burn the protection rope. Generally, multiple sets of super capacitors are used to store electric energy and release energy after receiving the rocket control signal. However, the energy density of super capacitors is low and the volume Larger, and the super capacitor has inherent defects of self-discharge, it is not suitable for long-term storage, it needs to be charged regularly, and maintenance is troublesome

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