Missile-borne platform navigation method and system
A navigation method and technology of a navigation system, which are applied in the field of missile-borne platform navigation methods and systems, can solve problems such as affecting navigation accuracy and unrecognizable map landmarks, and achieve the effect of improving navigation accuracy
Pending Publication Date: 2021-06-04
NAT UNIV OF DEFENSE TECH
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[0007] The embodiment of the present invention provides a missile-borne platform navigation method, which is used to solve the problem that some map landmarks in the existing MLs-based assisted inertial system may not be recognized and affect the navigation accuracy
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[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. 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.
[0030] Such as figure 1 As shown, the embodiment of the present invention provides a missile-borne platform navigation method, including:
[0031] S101. Obtain an output status value at the current moment through an inertial navigation device, the output status value including the attitude and position of the missile-borne platform;
[0032] S102. Query the map landmarks at the current moment, and calculate an output deviation estimate based on the map landma...
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The invention provides a missile-borne platform navigation method and system. The missile-borne platform navigation method comprises the following steps: acquiring an output state value at the current moment through an inertial navigation device; inquiring a map landmark at the current moment, and calculating an output deviation estimation value based on the map landmark at the current moment according to the inquired map landmark at the current moment; inquiring the opportunity landmark at the current moment, and calculating an output deviation estimation value based on the opportunity landmark at the current moment according to the inquired opportunity landmark at the current moment; carrying out fusion calculation on the output deviation estimation value based on the map landmark and the output deviation estimation value based on the opportunity landmark to obtain an output deviation compensation item at the current moment; and substituting the output deviation compensation item into the output state value at the current moment for compensation to obtain the corrected attitude and position of the missile-borne platform. According to the technical scheme, the state estimation precision of the missile-borne platform during guided missile navigation can be effectively improved.
Description
technical field [0001] The invention relates to the technical field of missile measurement and control, in particular to a missile-borne platform navigation method and system. Background technique [0002] As an important weapon, the navigation system provides navigation information such as the position, speed, and attitude of the missile-borne platform relative to a certain reference coordinate system, and is one of the core equipment for missile operations. [0003] As the most commonly used navigation method, the Global Navigation Satellite System (GNSS) can provide information such as the position, speed, and attitude of the carrier in real time. However, GNSS signals are susceptible to jamming or spoofing, have difficulty penetrating solid matter, and are easily lost if the vehicle is highly maneuvered. For this reason, autonomous navigation methods for missile-borne platforms have been developed to replace or assist GNSS. The most important and most commonly used is t...
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Login to View More IPC IPC(8): G01C21/18
CPCG01C21/18
Inventor 王炯琦吕东辉周萱影陈彧赟何章鸣侯博文魏居辉
Owner NAT UNIV OF DEFENSE TECH