Research on the Strategy of Orbital Avoidance for Optical Remote Sensing Satellite
This paper focuses on the orbit avoidance strategy of
the optical remote sensing satellite. The optical remote sensing
satellite, moving along the Sun-synchronous orbit, is equipped with
laser warning equipment to alert CCD camera from laser attacks. This
paper explores the strategy of satellite avoidance to protect the CCD
camera and also the satellite. The satellite could evasive to several
target points in the orbital coordinates of virtual satellite. The so-called
virtual satellite is a passive vehicle which superposes the satellite at the
initial stage of avoidance. The target points share the consistent cycle
time and the same semi-major axis with the virtual satellite, which
ensures the properties of the satellite’s Sun-synchronous orbit remain
unchanged. Moreover, to further strengthen the avoidance capability
of satellite, it can perform multi-target-points avoid maneuvers. On
occasions of fulfilling the satellite orbit tasks, the orbit can be restored
back to virtual satellite through orbit maneuvers. There into, the avoid
maneuvers adopts pulse guidance. In addition, the fuel consumption is
optimized. The avoidance strategy discussed in this article is
applicable to optical remote sensing satellite when it is encountered
with hostile attack of space-based laser anti-satellite.
[1] Jing Wuxing. Fuel-optimal Precise Rendezvous Guidance Law in
Elliptical Reference Orbit with J_2 Perturbation. Chinese Space Science
and Technology. 2011.4(2):16~26.
[2] Roger C, Widhalm. Minimum impulse orbital evasive maneuvers. Journal
of Guidance, Control, and Dynamics.1989.12(1):121~123.
[3] John E, Prussing Ronalds, Clifton. Optimal multiple-impulse satellite
evasive maneuver. Journal of Guidance, Control, and Dynamics.
1994.17(3):3 99~506.
[4] Wangmin, Zhoujun. Nonlinear programming of optimal escape trajectory
for satellite pulse thrust. Journal of Astronautics. 2006.7(4): 776~780.
[5] Lawden, D. F. Optimal Escape from a Circular Orbit. Astronautica Acta.
1958(4): 218-233.
[6] Whifen, G. J. Application of the SDC Optimal Control lgorithm to
Low-Thrust Escape and Capture Trajectory Optimization. AAS/AIAA
Space Flight Mechanics Meeting. 2002(1): 27-30.
[7] Anastassios E, Jon A. Simsz. Simple control laws for continuous-thrust
escape or capture and their use in optimisation. AIAA/AAS
Astrodynamics Specialist Conference and Exhibit. 2002,5(8): 1~10.
[1] Jing Wuxing. Fuel-optimal Precise Rendezvous Guidance Law in
Elliptical Reference Orbit with J_2 Perturbation. Chinese Space Science
and Technology. 2011.4(2):16~26.
[2] Roger C, Widhalm. Minimum impulse orbital evasive maneuvers. Journal
of Guidance, Control, and Dynamics.1989.12(1):121~123.
[3] John E, Prussing Ronalds, Clifton. Optimal multiple-impulse satellite
evasive maneuver. Journal of Guidance, Control, and Dynamics.
1994.17(3):3 99~506.
[4] Wangmin, Zhoujun. Nonlinear programming of optimal escape trajectory
for satellite pulse thrust. Journal of Astronautics. 2006.7(4): 776~780.
[5] Lawden, D. F. Optimal Escape from a Circular Orbit. Astronautica Acta.
1958(4): 218-233.
[6] Whifen, G. J. Application of the SDC Optimal Control lgorithm to
Low-Thrust Escape and Capture Trajectory Optimization. AAS/AIAA
Space Flight Mechanics Meeting. 2002(1): 27-30.
[7] Anastassios E, Jon A. Simsz. Simple control laws for continuous-thrust
escape or capture and their use in optimisation. AIAA/AAS
Astrodynamics Specialist Conference and Exhibit. 2002,5(8): 1~10.
@article{"International Journal of Electrical, Electronic and Communication Sciences:71342", author = "Zheng Dian Xun and Cheng Bo and Lin Hetong", title = "Research on the Strategy of Orbital Avoidance for Optical Remote Sensing Satellite", abstract = "This paper focuses on the orbit avoidance strategy of
the optical remote sensing satellite. The optical remote sensing
satellite, moving along the Sun-synchronous orbit, is equipped with
laser warning equipment to alert CCD camera from laser attacks. This
paper explores the strategy of satellite avoidance to protect the CCD
camera and also the satellite. The satellite could evasive to several
target points in the orbital coordinates of virtual satellite. The so-called
virtual satellite is a passive vehicle which superposes the satellite at the
initial stage of avoidance. The target points share the consistent cycle
time and the same semi-major axis with the virtual satellite, which
ensures the properties of the satellite’s Sun-synchronous orbit remain
unchanged. Moreover, to further strengthen the avoidance capability
of satellite, it can perform multi-target-points avoid maneuvers. On
occasions of fulfilling the satellite orbit tasks, the orbit can be restored
back to virtual satellite through orbit maneuvers. There into, the avoid
maneuvers adopts pulse guidance. In addition, the fuel consumption is
optimized. The avoidance strategy discussed in this article is
applicable to optical remote sensing satellite when it is encountered
with hostile attack of space-based laser anti-satellite.", keywords = "Optical remote sensing satellite, satellite avoidance,
virtual satellite, avoid target-point, avoid maneuver.", volume = "9", number = "10", pages = "1220-4", }