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A Tether-Coulomb Force Hybrid Satellite Formation Method in Geostationary Orbit

A technology of geostationary orbit and satellite formation, applied in the field of satellite formation, can solve the problems of complex control strategies, large fuel consumption, and fuel consumption, and achieve the effect of reducing mission fuel consumption and increasing the upper limit of the number

Active Publication Date: 2019-01-01
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The co-location control of geostationary orbit satellites requires fuel consumption, which has a certain impact on the satellite's on-orbit life
In addition, the currently known co-location control strategies are mainly aimed at co-location formations with less than four satellites. When there are many co-location satellites, the control strategy is very complicated, the fuel consumption is huge, and it is difficult to design and implement.

Method used

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  • A Tether-Coulomb Force Hybrid Satellite Formation Method in Geostationary Orbit
  • A Tether-Coulomb Force Hybrid Satellite Formation Method in Geostationary Orbit
  • A Tether-Coulomb Force Hybrid Satellite Formation Method in Geostationary Orbit

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Embodiment 1

[0044]In order to verify the feasibility of the method, a mixed formation system composed of five main stars and two auxiliary stars is selected, that is, N=5. The geometric and physical parameters of the formation are listed in Table 1.

[0045] Table 1 Geometric and physical parameters of the formation

[0046] The distance between the main star and the center l d

50m

The distance l between the auxiliary star and the center A

10000m

orbital angular velocity Ω

7.2915×10 -5 rad / s

Coulomb's electrostatic constant k c

8.988×10 9 N m 2 / C 2

secondary star mass m A

1000kg

Rope Stiffness Coefficient

22.1N / m

rope damping coefficient

0.245kg / s

[0047] A tether-coulomb force hybrid satellite formation method on a geostationary orbit disclosed in this embodiment includes the following steps:

[0048] For the tether-Coulomb force hybrid satellite formation on the geostationary orbit of N=...

Embodiment 2

[0058] In order to verify the feasibility of the method, a mixed formation system composed of eight main stars and two auxiliary stars is selected, that is, N=8. See Table 1 above for the geometric and physical parameters of the formation.

[0059] For the tether-Coulomb force hybrid satellite formation on the geostationary orbit of N=8, it can be deployed according to the following steps:

[0060] Step 1: Launch N main stars and two auxiliary stars together into geostationary orbit;

[0061] Step 2: Use the rope retractable device to gradually release the rope, and under the pull of the gravity gradient force, control the two auxiliary stars to move synchronously upward and downward in the vertical direction respectively. When the rope length reaches meters, stop releasing the rope;

[0062] Step 3: Use the electron gun to make the main stars carry the same kind of electric charge and the electric quantity is equal. From the formula (3), it can be calculated that the elect...

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Abstract

The invention discloses a rope-Coulombian force mixed satellite formation method in an earth stationary orbit, relating to a mixed satellite formation method, belonging to the field of satellite formation. Through launching N primary satellites and two auxiliary satellites into an orbit, a rope is gradually released by using a folding and unfolding device, under the effect of gravity gradient force, and finally the two auxiliary satellites are just above and under the plumb of a primary satellite plane. When the rope is released to a predetermined length, through an electron gun, the primary satellites carry a same type of charge with the equal electric quantity, under the repulsion effect of Coulombian force, the primary satellites are separated to N primary satellites near the earth stationary orbit, and a polygonoun formation configuration facing the earth is formed. When the formation configuration needs to be changed, a formation balance configuration is controlled and changed through adjusting the electric quantity of each primary satellite. According to the method, the multiple-satellites common position formation can be realized, an earth stationary track satellite capacity is developed, and the fuel consumption of formation maintenance and reconstruction control can be reduced. The method has a potential application value in the aspect of interference measurement to ground.

Description

technical field [0001] The invention discloses a tether-coulomb force hybrid satellite formation method on a geostationary orbit, relates to a hybrid satellite formation method, in particular to a hybrid satellite formation method used on a geostationary orbit, and belongs to the technical field of satellite formation . Background technique [0002] The geostationary orbit is a circular orbit with a height of about 35,800 km above the equator and geosynchronous rotation. Satellites operating in this orbit remain geostationary and can cover almost half of the earth. Therefore, in communication, remote sensing, navigation, early warning, data relay It is widely used in civil and military fields such as meteorology and meteorology (Liang Bin, Xu Wenfu, Li Cheng, Liu Yu. Research status and development trend of geostationary orbit service technology[J]. Acta Astronautics Sinica. 2010,31(1):1-13 ). [0003] The fixed-point accuracy of a typical geostationary orbit satellite is ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
CPCG05D1/10
Inventor 祁瑞张景瑞赵书阁
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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