Simeng Huang

Simeng Huang
Politecnico di Milano | Polimi · Department of Aerospace Engineering

Doctor of Philosophy

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14
Publications
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72
Citations

Publications

Publications (14)
Article
Full-text available
This paper investigates two strategies that exploit low-thrust propulsion and natural effects for the complete de-orbiting of spacecraft from a Low Earth Orbit (LEO). The first strategy aims to actively lower the perigee altitude by low-thrust propulsion to achieve passive drag-induced re-entry. The second strategy aims to actively move the spacecr...
Article
Full-text available
No general rules exist for constellation design; instead, constellation designers have to consider various cost drivers in a trade-off way. This paper presents a systematic method for the design of continuous global coverage Walker and Street-of-Coverage constellations, by taking seven critical constellation properties (coverage, robustness, self-i...
Thesis
Full-text available
As the demand for services from Space is more and more important to life on the Earth, the international interest in satellite constellations is increasingly growing. For example, in the recent years, many large constellations, which are composed of hundreds to thousands of satellites, are being or to be deployed in Low Earth Orbit (LEO), to provid...
Conference Paper
Full-text available
In the recent years, many large constellations have been announced to be deployed in Low Earth Orbit. Together with the existing space debris, the failed satellites from large constellations will pose a severe safety threat to the space environment. Driven by the strong demand to remove the failed satellites, D-Orbit and Politecnico di Milano, part...
Article
Full-text available
This paper deals with the planar transfer problems (orbit raising and de-orbiting) for co-planar satellites with low-thrust propulsion, taking the self-induced collision avoidance into consideration at the mission design stage. A Blended Error-Correction steering law, with which the thrust direction changes in a self-adaptive way, is developed by b...
Conference Paper
Full-text available
This paper conducts a trade-off study on large constellation de-orbiting by using low-thrust and de-orbiting balloons. A novel de-orbiting strategy is proposed: the low-thrust propulsion is firstly used to actively de-orbit the satellites to de-orbiting corridors, and the de-orbiting balloons are then de-ployed to enhance the passive de-orbiting, d...
Conference Paper
Full-text available
This paper deals with the propulsive phase of de-orbiting phase for coplanar satellites in large constellations. The design is conducted via two layers: the first layer is to design a time-optimal deorbiting trajectory for a single satellite; the second layer is to find the optimal de-orbit timing for each satellite to start the de-orbiting in orde...
Article
Full-text available
A trajectory planning method for angular velocity of spacecraft is developed to avoid the impassable singular states for singular gimbal control moment gyroscope (SGCMG) systems in this paper. A new set of attitude parameters, named σ-parameters, is first developed. Based on the properties of σ-parameters, two approximate decoupled rotations are pr...
Conference Paper
Full-text available
This paper deals with the planar transfer problem (i.e. orbit raising and de-orbiting phases) for low Earth orbit coplanar satellites constellation. The objectives are to minimize the total time of transfer and to maximize the miss distance during these phases so as to minimize the collision hazard. A Blended Error-Correction (BEC) steering law, co...
Article
The resonant frequencies will be excited if satellites perform a rapidly maneuver, which will increase the vibration settling time. In order to reduce the maneuver time and the residual vibration after maneuver, a set of shaped angular acceleration profiles are presented, and their analytical solutions are derived by minimizing the time integral of...
Conference Paper
Full-text available
This paper conducts a general study of the constellation geometries for two classical constellation patterns with circular orbits in the region of continuous global coverage. The significant properties for constellation design are identified and assessed with a parametrical approach. The comparison of two constellation patterns in terms of the seve...
Article
Full-text available
To enable the quickest possible escape from an impassable singular surface, a rapid singularity-escape steering strategy is proposed. This steering strategy works when encountering an impassable singular surface. This strategy consists of three main steps. The first step is to determine the nearest escapable point, which is always on the edge of th...

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Projects

Projects (2)
Project
Space benefits mankind through the services it provides to Earth. Future space activities progress thanks to space transfer and are safeguarded by space situation awareness. Natural orbit perturbations are responsible for the trajectory divergence from the nominal two-body problem, increasing the requirements for orbit control; whereas, in space situation awareness, they influence the orbit evolution of space debris that could cause hazard to operational spacecraft and near Earth objects that may intersect the Earth. However, this project proposes to leverage the dynamics of natural orbit perturbations to significantly reduce current extreme high mission cost and create new opportunities for space exploration and exploitation. The COMPASS project will bridge over the disciplines of orbital dynamics, dynamical systems theory, optimisation and space mission design by developing novel techniques for orbit manoeuvring by “surfing” through orbit perturbations. The use of semi-analytical techniques and tools of dynamical systems theory will lay the foundation for a new understanding of the dynamics of orbit perturbations. We will develop an optimiser that progressively explores the phase space and, though spacecraft parameters and propulsion manoeuvres, governs the effect of perturbations to reach the desired orbit. It is the ambition of COMPASS to radically change the current space mission design philosophy: from counteracting disturbances, to exploiting natural and artificial perturbations. COMPASS will benefit extensive international, including the ESA, NASA, JAXA, CNES, and ASI. Indeed, the proposed idea of optimal navigation through orbit perturbations will address various major engineering challenges in space situation awareness, for application to space debris evolution and mitigation, missions to asteroids for their detection, exploration and deflection, and in space transfers, for perturbation-enhanced trajectory design.