A Spacecraft Switch Matrix Fault Detection and Locating Device

Abstract

The invention discloses a device for detecting and positioning faults of switch matrixes of spacecrafts. The device comprises a self-test vector generation unit, more than one self-test isolation unit and more than one self-test state generation unit. Test vectors which are in one-to-one correspondence with various switches in the switch matrixes can be generated by the self-test vector generation unit and can be transmitted to the switch matrixes by the self-test vector generation unit, so that the corresponding switches can be turned on or off; each self-test isolation unit is arranged between the two corresponding adjacent stages of switches of the corresponding switch matrix, various channels of signals between every two adjacent stages of switches can be isolated by the corresponding self-test isolation unit, and the isolated signals can be combined with one another and then can be transmitted to the corresponding self-test state generation units; the combined signals can be received by the self-test state generation units, self-test state signals can be obtained after level states of the combined signals are converted, and the faults of the switch matrixes can be detected and positioned according to the self-test state signals under the conditions of the various test vectors. The device has the advantage that the faults of the switches can be detected and positioned without influence on operation of switch circuits.

Description

technical field [0001] The invention belongs to the technical field of spacecraft comprehensive electronics, and in particular relates to a spacecraft switch matrix fault detection and positioning device. Background technique [0002] The switch control is an important circuit component of the spacecraft. Usually, the spacecraft switch control is realized by relays or MOS tubes, but both relays and MOS tubes have certain failure modes. Therefore, in order to enhance the reliability of the design, generally The switch control circuit implemented by relays or MOS tubes adopts a series or parallel design method to form a switch matrix, thereby enhancing the reliability of the switch control circuit design. In addition, in order to understand the working state of the switch control circuit, it is necessary to detect the state of each switch in the switch control circuit. In the traditional detection method of switch working state, Hall devices are usually used in the switch circ...

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Problems solved by technology

In addition, in order to understand the working state of the switch control circuit, it is necessary to detect the state of each switch in the switch control circuit. In the traditional detection method of switch working state, Hall devices are usually used in the switch circuit or in the switch control circuit. Set the state quantity and remote measurement to judge whether the switch circuit is working normally. However, the Hall device occupies a large volume and area, and the weight is also large. It is acceptable for a small number of electric switch circuits, but for a large number of switch matrices The switch circuit in the circuit requires the use of a large number of Hall devices, which will lead to an increase in the weight and volume of the designed product, which is not conducive to the optimization of the design. The way to set the state quantity and remote measurement in the switch control circuit requires each switch to be set. Independent state or telemetry, thus occupying a large number of telemetry acquisition channels, which is unacceptable for the limited design resources on the spacecraft, and at the same time, no matter whether the Hall device is used or the way of setting the state quantity in the switch control circuit is only It can reflect the working state of the switch control circuit to a certain extent, but cannot locate the switch fault occurrence point in the switch control circuit, which brings difficulties to the isolation and recovery of spacecraft faults

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