A method for online compensation of system error of horizon system based on star-sensing

Abstract

The invention discloses an online compensation method of system error of a horizon sensor based on a star sensor. The online compensation method comprises the steps of: 1. judging whether the star sensor and the horizon sensor are available or not; 2. calculating the ratio K of a track clock to the interval time of a corrected point of the track clock, as well as K_integer and K_fractional part; 3. judging whether the K_integer is greater than or equal to 0 and less than or equal to N or not, and the K_fractional part is equal to 0 or not; 4. subtracting rolling and pitch attitudes of the horizon sensor from corresponding attitudes of the star sensor to obtain the amount of correction; 5. calculating new compensation table data; 6. limiting amplitude of the new compensation table data; 7. judging whether the K_integer is equal to N or not, and the K_fractional part is equal to 0 or not; 8. if the step 7 is met, assigning the Nth rolling and pitch compensation value data to (N+1)th and (N+2)th table elements; 9. calculating the amount of compensation of the horizon sensor at the current tempo by utilizing an interpolation method; and 10. calculating the calculating rolling and pitch attitudes of the horizon sensor at the current tempo. The online compensation method can be used for realizing the automatic updating of a correction interpolation table, calculating the compensated attitudes of the horizon sensor by utilizing the updated compensation table, and alleviating the pressure of updating the compensation table on the ground, and has strong timeliness and high correction accuracy.

Description

technical field

[0001] The invention relates to a method for determining the attitude of a satellite, in particular to a method for on-line compensation of an horizon system error based on star sensitivity. Background technique

[0002] Both the horizon and the star sensor (satellite sensor) are attitude-sensitive devices commonly used in satellites. The attitude calculation accuracy of the horizon is low, but the principle is simple, the flight experience is long, and the use is reliable; Orbital information is required, the ability to resist stray light interference is not strong, and there are certain requirements for satellite angular velocity, but its measurement accuracy is high, and it can also produce three-axis attitude information, so it has generally become the attitude reference of satellites in steady state in recent years.

[0003] The attitude of the horizon is based on the shape of the earth's atmospheric radiation layer, so two major model errors are introdu...

Examples

Embodiment Construction

[0046] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0047] The invention discloses a method for on-line compensation of an horizon system error based on star sensitivity. In the method, when deciding whether to update the compensation table, it is judged whether the orbital argument is in a certain range. Since the orbital argument is a decimal, it cannot It is beneficial to the realization of the algorithm on the satellite. For this reason, the concept of the orbit clock (OrbitT) is introduced, that is, the orbital angle is replaced by the method of counting on the satellite. The system accumulates and integrates in the unit of a takt time t length. When the integration reaches exactly one orbit period, the integral is cleared and the accumulation is restarted to ensure the consistency between the orbital clock and the orbital argument.

[0048] The following two examples are used to describe in...

technical field

[0001] The invention relates to a method for determining the attitude of a satellite, in particular to a method for on-line compensation of an horizon system error based on star sensitivity. Background technique

[0002] Both the horizon and the star sensor (satellite sensor) are attitude-sensitive devices commonly used in satellites. The attitude calculation accuracy of the horizon is low, but the principle is simple, the flight experience is long, and the use is reliable; Orbital information is required, the ability to resist stray light interference is not strong, and there are certain requirements for satellite angular velocity, but its measurement accuracy is high, and it can also produce three-axis attitude information, so it has generally become the attitude reference of satellites in steady state in recent years.

[0003] The attitude of the horizon is based on the shape of the earth's atmospheric radiation layer, so two major model errors are introdu...

Examples

Embodiment Construction

[0046] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0047] The invention discloses a method for on-line compensation of an horizon system error based on star sensitivity. In the method, when deciding whether to update the compensation table, it is judged whether the orbital argument is in a certain range. Since the orbital argument is a decimal, it cannot It is beneficial to the realization of the algorithm on the satellite. For this reason, the concept of the orbit clock (OrbitT) is introduced, that is, the orbital angle is replaced by the method of counting on the satellite. The system accumulates and integrates in the unit of a takt time t length. When the integration reaches exactly one orbit period, the integral is cleared and the accumulation is restarted to ensure the consistency between the orbital clock and the orbital argument.

[0048] The following two examples are used to describe in...

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