The periodic dynamics of the irregular heterogeneous celestial bodies

Lan, Lei; Yang, Ming–Hsuan; Baoyin, Hexi; Li, Junfeng

doi:10.1007/s10509-017-3016-0

Cited by 8 publications

(18 citation statements)

References 29 publications

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“…Similar to this idea, there are some literature suggests adopting the atmospheric air as the propellant [8,9,10]. In addition, Lei Lan et al [11] has proposed a kind of debris engine that using the space debris as the propellant transferred from the space robotic cleaner, disintegrated into the power and charged by the gamma-ray photoelectric effect or the behavior of tangent rub of tungsten needles, which would be accelerated by a electrostatic particle accelerator ejected in the form of high-temperature and high-pressure charged powder providing the thrust. That is a good idea suggesting the utilization of space debris, but it has some drawbacks such as the low thrust density and the serious erosion of the gridding electrodes that determines the efficiency of the thruster, which can be overcome by the hall thruster through founding the matching performance between the space debris powder and corresponding thruster to find the optimal operational environment and conditions.…”

Section: Introductionmentioning

confidence: 93%

A novel hall thruster utilizing space debris as the propellant

Peng¹,

Ling²

2016

Proceedings of the 2016 International Conference on Advanced Electronic Science and Technology (AEST 2016)

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Abstract. The paper proposed a new conception of using space debris as the working medium of the hall thruster. At first, we described differences of the physical properties between the space debris powder and gaseous propellants and estimated the charge quantity of the charged space debris powder. Then, we dealt with the operating principles and design process of the novel hall thruster with a modified cusped configuration of magnetic field along the discharge channel to make the ionization process more uniform and efficient. Given a design case, we demonstrated the validity of the novel idea through the simulation by the ANSYS Maxwell of the magnetic field distribution. The results are that the cusped configuration is 230~310 Gauss (increasing from the central line of discharge channel to the wall) in magnetic field and its gradient is 107 Gauss/cm, the maximum radial magnetic field is located in the exit plane of the thruster and has a 230 Gauss/cm gradient and a trend of inwards concave. This novel hall thruster with space debris as the propellant will not only augment the effective payload of the spacecraft and decrease the economic burden of the xenon propellant, but also it can resolve the space debris problem substantially.

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Section: Introductionmentioning

confidence: 93%

A novel hall thruster utilizing space debris as the propellant

Peng¹,

Ling²

2016

Proceedings of the 2016 International Conference on Advanced Electronic Science and Technology (AEST 2016)

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“…So k can be computed after obtaining the length of the segment l * 1 . (Zeng et al 2018;Lan et al 2017;.…”

Section: Equations Of Motionmentioning

confidence: 99%

“…The optimized parameters of the bodies under analysis in this article are shown in Table 3, where Φ is determined by setting Φ = arctan (2σ) in which σ is given by l 2 /l 1 and was determined in Lan et al (2017) and Yang et al (2018).…”

Section: Applicationmentioning

confidence: 99%

“…On the other hand, when the body does not resemble a sphere, this expansion is no longer convenient and, in some cases, convergence cannot be guaranteed (Elipe & Riaguas 2003). Generally, when the field point is located within the circumscribing sphere, the series diverge (Lan et al 2017;Elipe & Riaguas 2003). Furthermore, the expansion of low-order Legendre coefficients often does not provide a good approximation for the motion of a spacecraft due to the fact that higher order terms can generate divergence after several iterations (Riaguas et al 1999;Jiang & Baoyin 2018).…”

Section: Introductionmentioning

confidence: 99%

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Dynamics Around an Asteroid Modeled as a Mass Tripole

Santos

Marchi

Sousa-Silva

et al. 2020

RMxAA

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The orbital dynamics of a spacecraft orbiting around irregular small celestial bodies is a challenging problem. Diffculties to model the gravity field of these bodies arise from the poor knowledge of the exact shape as observed from the Earth. In order to understand the complex dynamical environment in the vicinity of irregular asteroids, several studies have been conducted using simplified models. In this work, we investigate the qualitative dynamics in the vicinity of an asteroid with an arched shape using a tripole model based on the existence of three mass points linked to each other by rods with given lengths and negligible masses. We applied our results to some real systems, namely, asteroids 8567, 243 Ida and 433 Eros and also Phobos, one of the natural satellites of Mars.

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“…The two moonlets, Alexhelios and Cleoselene, of this large-size-ratio triple asteroid 216 Kleopatra move near the primary's equatorial plane(Descamps et al 2011;Jiang et al 2016). The result can help us to understand the orbit stability of the moonlets Alexhelios and Cleoselene Lan et al (2017). investigate the periodic orbit families to analyze the stable and unstable regions in the gravitational potential of 4 Vesta, 216 Kleopatra, 243 Ida, and 433 Eros.…”

mentioning

confidence: 98%

Orbital stability close to asteroid 624 Hektor using the polyhedral model

Jiang

Baoyin

2018

Advances in Space Research

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We investigate the orbital stability close to the unique L4-point Jupiter binary Trojan asteroid 624 Hektor. The gravitational potential of 624 Hektor is calculated using the polyhedron model with observational data of 2038 faces and 1021 vertexes. Previous studies have presented three different density values for 624 Hektor. The equilibrium points in the gravitational potential of 624 Hektor with different density values have been studied in detail. There are five equilibrium points in the gravitational potential of 624 Hektor no matter the density value. The positions, Jacobian, eigenvalues, topological cases, stability, as well as the Hessian matrix of the equilibrium points are investigated. For the three different density values the number, topological cases, and the stability of the equilibrium points with different density values are the same. However, the positions of the equilibrium points vary with the density value of the asteroid 624 Hektor. The outer equilibrium points move away from the asteroid's mass center when the density increases, and the inner equilibrium point moves close to the asteroid's mass center when the density increases. There exist unstable periodic orbits near the surface of 624 Hektor. We calculated an orbit near the primary's equatorial plane of this binary Trojan asteroid; the results indicate that the orbit remains stable after 28.8375 d.

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The periodic dynamics of the irregular heterogeneous celestial bodies

Cited by 8 publications

References 29 publications

A novel hall thruster utilizing space debris as the propellant

A novel hall thruster utilizing space debris as the propellant

Dynamics Around an Asteroid Modeled as a Mass Tripole

Orbital stability close to asteroid 624 Hektor using the polyhedral model

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