Rapid Generation Method of Missile-borne Star Library for Starlight/Inertial Compound Guidance
A compound guidance and stellar technology, which is applied in navigation, navigation, surveying and navigation through speed/acceleration measurement, can solve the problems of inertial guidance precision reduction, etc., and achieve the goal of reducing the amount of calculation, reducing the amount of calculation, and fast calculation speed Effect
Active Publication Date: 2020-04-17
NAT UNIV OF DEFENSE TECH
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Problems solved by technology
In the process of inertial guidance, there are unavoidably the influence of error factors such as initial positioning and orientation errors, initial alignment errors, and inertial device drift errors, which reduce the accuracy of inertial guidance. Therefore, a starlight / inertial composite guidance method is proposed
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Embodiment Construction
[0048] Such as figure 2 Shown, the present invention realizes steps as follows:
[0049] 1) Get the original star database. The database should include star number ID, apparent magnitude M V , right ascension α 0 , declination δ 0 , right ascension proper dα / dt, declination proper dδ / dt and other information, the technical documentation of the database should include the reference epoch MJD adopted by the stellar database 0 , reference inertial coordinate system ICRS, and the conversion relationship between ICRS and J2000.0 geocentric agreement inertial coordinate system (hereinafter referred to as J2000.0 coordinate system)
[0050] 2) According to the magnitude M of the navigation star in the starlight / inertial composite guidance VN Requirements, remove the magnitude M from the original database V greater than M VN stars, let the number of remaining stars be N 0 .
[0051] 3) Stellar information preprocessing. According to the star's right ascension α 0 , decli...
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The invention discloses a rapid generation method for a starlight / inertial composite guidance missile-borne fixed star database, the rapid generation method fully considers storage and calculation speed conditions of a missile-borne computer, the missile-borne fixed star database is generated according to an order of nebula / star cluster, inertial platform limitation, ground level avoidance and strong light source avoidance, a celestial pole transformation method is used to achieve the ground level avoidance, less memory is occupied, and the calculation speed is faster. The avoidance calculation of the nebula / star cluster is completed before loading of a fixed star database onto a missile, the amount of calculation on the missile is reduced; when the missile-borne fixed star database is generated on the missile, the missile-borne fixed star database is generated according to the order of inertial platform limitation, ground level avoidance and strong light source avoidance, the amount of calculation of the missile-borne computer is minimized, and the storage limit of the computer is reduced; and the celestial pole transformation method is used to achieve the ground level avoidance,reduces the computational complexity of the existing algorithm and improves the calculation accuracy.
Description
technical field [0001] The invention relates to the technical field of guidance and control, and can be applied to long-range ballistic missiles and active-stage starlight / inertia composite guidance of launch vehicles, especially to the generation of missile-borne star libraries for starlight guidance in composite guidance. Background technique [0002] The active section of existing long-range ballistic missiles and launch vehicles generally adopts inertial guidance technology, that is, the information such as the apparent acceleration and angular velocity of the carrier is measured by inertial devices such as accelerometers and gyroscopes, and the real-time operating status of the carrier is obtained through navigation integration, and passed to guidance system. The guidance system calculates the guidance command and controls the motion state of the carrier to reach the expected value. In the process of inertial guidance, there are unavoidably the influence of error facto...
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IPC IPC(8): G01C21/16G01C21/20
CPCG01C21/165G01C21/20
Inventor 张洪波李鹏飞汤国建马宝林
Owner NAT UNIV OF DEFENSE TECH