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A dual-bias passive control method for sun-synchronous orbit descending node local time

A technology of sun-synchronous orbit and descending node, which is applied in the direction of motor vehicles, space navigation vehicle guidance devices, space navigation equipment, etc., to achieve the effect of passive control principle and calculation process optimization, fuel saving, and less calculation.

Active Publication Date: 2020-08-14
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

[0004] The technical problem solved by the present invention is: in view of the situation that the local time of the descending node has a large drift range when the sun-synchronous orbit only has a single bias method of inclination, a double-bias passive control method for the local time of the descending node and the inclination is proposed to solve the problem of longer design life And the requirement of drift control constraints at lower node local time with higher precision, saving fuel and on-orbit maintenance costs

Method used

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  • A dual-bias passive control method for sun-synchronous orbit descending node local time
  • A dual-bias passive control method for sun-synchronous orbit descending node local time
  • A dual-bias passive control method for sun-synchronous orbit descending node local time

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Embodiment Construction

[0027] A dual-bias passive control method at the descending node of the sun-synchronous orbit, such as figure 1 As shown, the specific steps are as follows:

[0028] (1) When obtaining the sun-synchronous orbital position, adjust the mission's preset sun-synchronous orbital altitude H, and when the nominal descending node position is LTDN 0 And the satellite design life T;

[0029] According to the patent: "Sun-synchronous Orbital Inclination Offset Method Considering Multi-task Altitude", ZL201310108729.6, formula (1) calculates the nominal inclination i corresponding to the working height H 0 , The relationship between the two meets the following conditions:

[0030]

[0031] Where p=a(1-e 2 ), a=R e +H, R e Is the semi-major axis of the earth, e is the orbital eccentricity, μ is the earth's gravitational constant, J 2 Is the second-order harmonic coefficient of the earth's gravity, J 4 Is the fourth-order harmonic coefficient of the earth's gravity, n s Is the angular velocity of ...

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Abstract

A sun synchronous orbit drop point local time dual-offset passive control method features that that convergence direction of descent point local time and inclination angle are selected according to the height of descent point of sun synchronous orbit, nominal descent point local time and design life of descent point. Depending on where the initial point of descent is at a given bias, the drift atthe point of descent of several orbital inclination offsets during the lifetime is calculated, the drift accuracy under the given optimal orbital inclination offset is equal to the absolute value of the maximum value and the minimum value when judging the initial descent point, and the drift control constraint at the descent point with longer design life and higher accuracy is solved, so that thecontrol accuracy is higher.

Description

Technical field [0001] The invention relates to a dual-bias passive control method at the time of descending node of a sun-synchronous orbit, belonging to the field of orbital local time bias control. Background technique [0002] The descending node of the sun-synchronous orbit is an important indicator of the orbital change characteristics. The smaller the drift amount at the descending node during the lifetime of the orbit, the more stable the ground illumination conditions during satellite imaging. At the same time, for various optical sensors on the satellite , The whole star cooling and other working conditions are also more favorable. Generally speaking, the control of changing the orbital surface requires huge fuel consumption. Taking a low-orbit satellite weighing 1000kg as an example, using conventional chemical propellants, changing the orbit to change the ascending node right ascension of 0.1° or the inclination of 0.1° requires at least 10kg of fuel, and the 0.1° as...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 李志武白照广谭田朱兴鸿吕秋杰朱政帆
Owner AEROSPACE DONGFANGHONG SATELLITE
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