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A mixed altitude measurement method based on error feedback for aircraft inertia and GPS

A technology of error feedback and height measurement, which is applied in height/horizontal measurement, navigation through speed/acceleration measurement, and measurement devices, etc. It can solve the problem of low accuracy of single height measurement, achieve the best mixed measurement effect, and eliminate time accumulation error Effect

Active Publication Date: 2022-03-08
NAVAL AVIATION UNIV
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0004] The object of the present invention is to provide a kind of aircraft inertial plus GPS hybrid altitude measurement method based on error feedback, and then at least to a certain extent overcome the problem that the single altitude measurement accuracy is not high due to the limitations and defects of related technologies

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  • A mixed altitude measurement method based on error feedback for aircraft inertia and GPS
  • A mixed altitude measurement method based on error feedback for aircraft inertia and GPS
  • A mixed altitude measurement method based on error feedback for aircraft inertia and GPS

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Embodiment Construction

[0062] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided in order to give a thorough understanding of embodiments of the invention. However, those skilled in the art will appreciate that the technical solution of the present invention may be practiced without one or more of the specific details, or other methods, components, devices, steps, etc. may be adopted. In other instances, well-known technical solutions have not been shown or descr...

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Abstract

The invention relates to an aircraft inertial GPS hybrid altitude measurement method based on error feedback. It first installs the SiA200MEMS acceleration sensor, measures the carrier acceleration and performs two integrations to obtain the carrier inertial velocity signal and inertial height signal respectively; then installs the GPS position receiver to receive the GPS height information of the carrier. Then compare the inertial height with the GPS height to obtain the height error signal, and perform nonlinear transformation and correction to obtain the error correction signal. Then the acceleration measurement signal is introduced, integrated to obtain the compensation speed signal, and compared with the inertial speed to obtain the speed error signal, and filtered according to the height error signal, and superimposed and integrated with the inertial speed to obtain the compensation height signal. Finally, the composite speed signal is generated by compensating the error of the altitude nonlinear filter and the GPS filter signal, and the final composite altitude signal is generated through integral and altitude feedback self-compensation.

Description

technical field [0001] The invention relates to the field of high-precision height measurement of vehicles, moving bodies and unmanned aerial vehicles, in particular to a design method of an aircraft inertial and GPS hybrid height measurement method based on error feedback. Background technique [0002] Accurate altitude information measurement is very important for unmanned aerial vehicles, airships, automobiles, etc. in the fields of navigation and motion control. At present, in altitude measurement, the measurement range of atmospheric pressure measurement is limited and cannot be used at high altitudes. However, when inertial technology is used for height measurement, due to the two integrals from acceleration to height, the cumulative error will become larger and larger as time increases. The error of GPS measurement height information does not have the problem of time accumulation, but its terminal accuracy often has large random errors. Therefore, how to integrate th...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01S19/39G01S19/23G01C21/16G01C5/00G01C25/00
CPCG01S19/39G01S19/23G01C21/165G01C5/005G01C25/005
Inventor 纪军马培蓓丛林虎孙国磊隋江波寇昆湖
Owner NAVAL AVIATION UNIV