Constant-thrust glideslope guidance algorithm for time-fixed rendezvous in real halo orbit

Lian, Yijun; Ye, Meng; Tang, Guojian; Liu, Luhua

doi:10.1016/j.actaastro.2012.04.049

Cited by 18 publications

(10 citation statements)

References 12 publications

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“…15 Lian et al. 16 proposed a fixed-time glideslope guidance algorithm, which was capable of guiding the spacecraft approaching a target vehicle on a quasi-periodic Halo orbit in real Earth–Moon system. The constant-thrust glideslope algorithm provides an effective approach to guide the spacecraft to rendezvous with a target in multi-body realm.…”

Section: Introductionmentioning

confidence: 99%

Finite-time velocity-free prescribed performance control for Halo orbit autonomous rendezvous

Zheng

Luo

Zhao

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper studies the problem of autonomous rendezvous in the libration point orbit without relative velocity measurement information. The proposed rendezvous algorithm consists of the finite-time-convergent differentiator and the finite-time prescribed performance controller. Wherein, the differentiator is used to compute the unknown relative velocity between the target and the chaser spacecraft. The novel differentiator-based finite-time prescribed performance controller ensures that the rendezvous error converges to an arbitrarily small prescribed region in finite time in spite of the presence of additive bounded disturbances. Furthermore, the prescribed convergence rate can be also achieved simultaneously. The associated stability proof is constructive and accomplished by the development of a Lyapunov function candidate. Numerical simulations on a final rendezvous approach example are provided to demonstrate the effectiveness and robustness of the proposed control algorithm.

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Section: Introductionmentioning

confidence: 99%

Finite-time velocity-free prescribed performance control for Halo orbit autonomous rendezvous

Zheng

Luo

Zhao

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…For the convenience of making comparisons with the method proposed in [8], we use the identical initial conditions therein for the following simulation. The initial epoch is 56279.32388311 MJD (18 Dec 2012 07:46:23.500 UTCG), and initial target's position is located on a quasi-periodic halo orbit (8000 km of z-amplitude).…”

Section: Simulationsmentioning

confidence: 99%

“…This large difference may be resulted from two possible reasons. First, full nonlinear dynamics are adopted instead of linearized dynamics; second, the terminal SMC is a continuous control, being able to vary the magnitude as required at any instant, while the glideslope control in [8] is merely several discrete impulses. …”

Section: A Rendezvous With a Stationary Targetmentioning

confidence: 99%

“…The computation of the two angles uses the following equations [8], 159.5 m/s of delta-v has been saved using terminal SMC. This large difference may be resulted from two possible reasons.…”

Section: A Rendezvous With a Stationary Targetmentioning

confidence: 99%

“…Moreover, these orbits are inherently unstable [7], posing great challenge to the guidance and control system design for spacecraft moving in the vicinity of these orbits. Lian, Meng, Tang, and Liu [8] proposed an algorithm based on impulsive glideslope guidance for a spacecraft approaching a target on a real halo orbit within a given flight time. For a range of 500 km, the suitable rendezvous time was 5 hours.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Libration point orbit rendezvous in real earth-moon system using terminal sliding mode control

Lian

Tang

2013

2013 6th International Conference on Recent Advances in Space Technologies (RAST)

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This paper studies the problem of libration point orbit rendezvous using terminal sliding mode control. The underlying dynamics are the full nonlinear equations of motion in a complete Solar System model, taking into account all the gravitational forces from the Sun, the Moon, and the planets, whose positions are computed using the JPL DE405 ephemeris. The prominent advantage of terminal sliding mode control, owing to the specific design of the sliding surface, is that the time of convergence can be prescribed a priori, which means the rendezvous time is fully under control. Besides the sliding surface design, a controller suited to the dynamical model is also derived to insure the global stabilization of the approach. Preliminary results validate the availability of the approach, and comparisons are made with the results obtained using glideslope guidance in previous work.

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Optimal impulsive time-fixed transfers around the libration points of the restricted three-body problem

Zhou¹,

Hu²,

Bai³

et al. 2020

Astrophys Space Sci

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Constant-thrust glideslope guidance algorithm for time-fixed rendezvous in real halo orbit

Cited by 18 publications

References 12 publications

Finite-time velocity-free prescribed performance control for Halo orbit autonomous rendezvous

Finite-time velocity-free prescribed performance control for Halo orbit autonomous rendezvous

Libration point orbit rendezvous in real earth-moon system using terminal sliding mode control

Optimal impulsive time-fixed transfers around the libration points of the restricted three-body problem

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