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Ground velocity measurement method based on instrument landing system

A technology of instrument landing system and measurement method, which is applied in the directions of linear/angular velocity measurement, velocity/acceleration/shock measurement, measurement device, etc., which can solve the problem that signal integrity cannot support high-security applications of head-up flight guidance, and GPS signals are susceptible to interference , unable to output ground speed and other problems, to achieve the effect of high integrity, noise suppression, and smooth ground speed

Inactive Publication Date: 2018-02-23
LUOYANG INST OF ELECTRO OPTICAL EQUIP OF AVIC
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AI Technical Summary

Problems solved by technology

The existing attitude and heading reference system cannot output the ground speed. Although the GPS ground speed meets the requirements of the head-up flight guidance function in terms of accuracy, the GPS signal is easily interfered, and the integrity of the signal cannot support the high-safety application of the head-up flight guidance. , it is necessary to monitor the integrity of the GPS ground speed signal

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  • Ground velocity measurement method based on instrument landing system
  • Ground velocity measurement method based on instrument landing system
  • Ground velocity measurement method based on instrument landing system

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Embodiment Construction

[0030] Embodiments of the present invention are described in detail below, and the embodiments are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0031] The principle of the ground speed measurement method based on the instrument landing system of the present invention is as follows: figure 1 As shown, firstly, the vertical acceleration output by the attitude and heading reference system, the aircraft altitude output by the air data computer / radio altimeter, and the airport altitude output by the flight management system are used to calculate the vertical velocity of the aircraft through complementary filtering; and then based on the aircraft precision approach process Based on the assumption of accurately tracking the glide path, the ground speed based on the instrument landing system is calculated by using the geometric relationship; finally, the acceleration along the runway is used to filter the grou...

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Abstract

The invention, which belongs to the technical field of avionics display controlling, relates to a ground velocity measurement method based on an instrument landing system. According to vertical acceleration outputted by an attitude heading reference system, an aircraft height outputted by an air data computer / radio altimeter, and an airport altitude outputted by an aircraft management system, a vertical speed of the aircraft is calculated by complementary filtering; on the basis of a geometrical relationship, a ground velocity based on an instrument landing system is calculated; and then the ground velocity is filtered by using the acceleration along a runway direction to obtain a smooth available ground velocity. According to the ground velocity measurement method based on an instrument landing system, while the ground velocity that can not be outputted by the attitude heading reference system is calculated by using the vertical acceleration, the aircraft height, the airport height, the glide slope offset, and the reference glide slope angle comprehensively, noises caused by the glide slope offset are suppressed by acceleration complementary filtering, so that the obtained groundvelocity is smooth and has high integrity; and high-safety application like head-up flight guidance is supported.

Description

technical field [0001] The invention relates to a ground speed measurement method based on an instrument landing system, belonging to the technical field of avionics display control. Background technique [0002] The ground speed of the aircraft is an important input parameter of the approach guidance, run guidance and take-off guidance in the head-up flight guidance function. The accuracy and integrity of this parameter directly affect the performance and availability of the head-up flight guidance. The existing attitude and heading reference system cannot output the ground speed. Although the GPS ground speed meets the requirements of the head-up flight guidance function in terms of accuracy, the GPS signal is easily interfered, and the signal integrity cannot support the high-safety application of the head-up flight guidance. , it is necessary to monitor the integrity of the GPS ground speed signal. Contents of the invention [0003] The purpose of the present inventio...

Claims

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Application Information

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IPC IPC(8): G01P3/00
CPCG01P3/00
Inventor 杨世保丁浩高成志
Owner LUOYANG INST OF ELECTRO OPTICAL EQUIP OF AVIC
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