Triaxial accelerometer and impact detecting switch

A technology for detecting switch and axis acceleration, which is applied in the field of avionics, can solve problems such as inability to adapt analog signals and poor maintainability, and achieve the effect of improving testability and maintainability

Active Publication Date: 2019-04-02
SHAANXI QIANSHAN AVIONICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a three-axis acceleration and shock detection switch that can adapt to the aircraft, so as to solve the

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  • Triaxial accelerometer and impact detecting switch
  • Triaxial accelerometer and impact detecting switch
  • Triaxial accelerometer and impact detecting switch

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Embodiment Construction

[0029] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0030] Such as figure 1 As shown, the three-axis accelerometer and the impact detection switch of the present invention include a power module 1, an acceleration acquisition board 2 and a data acquisition board 3, and the power module 1 is connected with a 28VDC power supply and an external button reset switch, and outputs a 28VDC power supply externally , simultaneously connected with the acceleration acquisition board 2 and the data acquisition board 3; the acceleration acquisition board 2 is connected to the data acquisition board through a parallel bus to output an acceleration signal; the data acquisition board 3 is connected to the ARINC-429 bus interface and the AFDX bus interface , The Ethernet bus interface is connected with other data acquisition devices on the aircraft, such as the central processing unit, flight data collector, etc., and can outpu...

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PUM

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Abstract

The invention belongs to the technical field of avionics, and particularly relates to a triaxial accelerometer and an impact detecting switch. The triaxial accelerometer and the impact detecting switch comprise a power module, an acceleration collecting board, and a data collecting board. The power module is connected with an external power source and an external button reset switch, and externally outputs power, and is connected to the acceleration collecting board and the data collecting board. The acceleration collecting board is connected to the data collecting board through a parallel busand outputs an acceleration signal to the data collecting board. The data collecting board comprises a microprocessor circuit and an A/D conversion circuit. According to the triaxial accelerometer and the impact detecting switch, the collected aircraft lateral, bus and normal acceleration can be output through an analog quantity, and can also be converted into a digital signal and output throughthe ARINC-429 bus and the AFDX bus which can adapt to multiple aircraft requirements, so that the maintainability of the equipment is improved; and two airborne devices are integrated, so that the total weight of the products is reduced.

Description

technical field [0001] The invention belongs to the technical field of avionics, and in particular relates to a three-axis accelerometer and an impact detection switch. Background technique [0002] The three-axis accelerometer can collect the lateral, longitudinal and normal accelerations of the aircraft, and output them to the on-board acquisition equipment in the form of analog quantities, which can be used to monitor the flight attitude of the aircraft. The impact detection switch can detect the overload signal of the aircraft. When the overload signal is detected, it can output a status signal to the cockpit audio recorder to ensure that the cockpit audio recorder stops data recording within 10 minutes. However, in the past, these two devices were two devices. Because both devices need to collect the three axial accelerations of the aircraft, the functions are redundant. It is no longer suitable for new aircraft, and the maintenance and detection of the previous three-...

Claims

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Application Information

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IPC IPC(8): G01P15/18G01P15/08
CPCG01P15/08G01P15/18
Inventor 屠晓涛
Owner SHAANXI QIANSHAN AVIONICS
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