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Method and device for determining operating parameter correction threshold based on navigation system

A technology of operating parameters and navigation systems, which is applied in navigation calculation tools, offensive equipment, launch objects, etc., can solve the problems of low accuracy of rocket trajectory, and achieve the effect of improving accuracy.

Active Publication Date: 2020-09-29
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Abstract
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Problems solved by technology

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that the navigation correction threshold in the prior art is determined solely by rocket flight time, and the selection of correction parameters is blind, resulting in low accuracy of correcting the rocket trajectory, thereby providing a Method and device for determining operating parameter correction threshold based on navigation system

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  • Method and device for determining operating parameter correction threshold based on navigation system
  • Method and device for determining operating parameter correction threshold based on navigation system
  • Method and device for determining operating parameter correction threshold based on navigation system

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Embodiment Construction

[0024] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0025] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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Abstract

The invention provides a method and device for determining the operation parameter correction threshold based on a navigation system. The method comprises the following steps that when the updating period of the correction threshold reaches, the operation parameter value of an operation target at the current time is determined and comprises the apparent speed and the apparent position, and based on the operation parameter value of the operation target at the current time, the correction threshold of the operation parameter within a next cycle is determined. By means of the method, by calculating the operation parameter value of the operation target within the updating period of the correction threshold, the correction threshold of the operation parameter of the next cycle is determined, the fact that the correction threshold is determined by depending on setting of the operation parameter of the actual operation target is achieved, a more accurate standard is provided for the selectionof the correction parameter of the operation target, and the accuracy rate of the correction operation track of the operation target is increased.

Description

technical field [0001] The invention relates to the field of launch vehicle control, in particular to a method and device for determining an operating parameter correction threshold based on a navigation system. Background technique [0002] Integrated navigation usually uses two or more dissimilar navigation systems to measure and calculate the same navigation information, calculate and correct the errors of each navigation system, and provide accurate navigation information. The navigation correction threshold enables the rocket to correct the trajectory of the rocket according to the normal correction range during flight to ensure the normal flight of the rocket. [0003] In related technologies, the integrated navigation correction threshold is determined solely by the flight time of the rocket. For different rocket running times, different navigation correction thresholds are set. The correlation between the correction threshold and time is subject to human experience. ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/01G01C21/20
CPCF42B15/01G01C21/20
Inventor 彭小波徐国光亓朝玉
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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