Tao Nie

Tao Nie
Beijing Institute of Technology | BIT · School of Aerospace Engineering

PhD

About

18
Publications
5,496
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76
Citations
Additional affiliations
July 2019 - present
Technion - Israel Institute of Technology
Position
  • PostDoc Position
Education
August 2016 - August 2018
Technion - Israel Institute of Technology
Field of study
  • Aerospace Engineering
September 2014 - July 2019
Harbin Institute of Technology
Field of study
  • Aerospace Engineering
September 2010 - June 2014
Harbin Institute of Technology
Field of study
  • Aerospace Engineering

Publications

Publications (18)
Preprint
Full-text available
Low-thrust orbit control has been widely studied, mostly by using direct or indirect optimization to detect time-optimal and fuel-optimal orbit transfers. In this paper, we propose an alternative approach for designing efficient low-thrust orbit transfers. The main idea is to create an artificial resonance between the period of the control accelera...
Article
Full-text available
Constellation design theory has been studied extensively. However, analysis of longitude-dependent perturbation effects on inter-satellite distance drift has not received much attention. In addition to oblateness-related perturbations, sectoral and tesseral perturbations are non-negligible for low Earth orbits, due to their effect on inter-satellit...
Preprint
Full-text available
Constellation design theory has been studied extensively. However, analysis of longitude-dependent perturbation effects on inter-satellite distance drift has not received much attention. In addition to oblateness-related perturbations, sectoral and tesseral perturbations are non-negligible for low Earth orbits, due to their effect on inter-satellit...
Article
Full-text available
The effects of third-body perturbations on natural and artificial satellite orbits have been studied extensively. However, much less attention has been given to the case considering the orbital inclination of the third body. In this paper, it is shown that a perturbed orbit, even with a small initial inclination—much less than the critical Kozai in...
Article
Full-text available
Initializing the satellite orbit to be coplanar with a third-body's orbit renders the mean inclination and mean right ascension of the ascending node (RAAN) fixed. Applying this observation to formation flying missions, when the chief satellite orbit and the third-body orbit are coplanar, the relative dynamics have analytical solutions. In this sce...
Article
Full-text available
Using differential solar radiation pressure (DSRP) for satellite formation keeping is not a new idea. However, there is no exiting design methodology of DSRP-based controllers for lunar satellite formation keeping. Lunar orbits are different from low Earth orbits, because the third-body effects are dominant. This paper develops a DSRP-based formati...
Article
Full-text available
Finding boundedness conditions of relative orbits is an important topic in designing satellite formation flying missions. Most works studied relative orbits under the $J_2$ perturbation. Little attention has been given to the third-body perturbation. Other than the nodal precession and perigee rotation, as in the $J_2$ problem, the third-body pertu...
Article
Full-text available
A general third-body perturbation problem, considering the perturbing body in an elliptic and inclined orbit, is investigated by using a semi-analytical theory. Previous works have contributed to deriving the averaged third-body-perturbed dynamics, but did not provide a transformation between osculating and mean elements in the general case. In thi...
Article
Full-text available
Finding relative orbits for satellite formations flying around the Earth, which are long-term bounded under various perturbations, has been a vibrant field of study. However, much less attention has been given to detecting such orbits for circumlunar formation flying missions. As opposed to low-Earth orbits, in circumlunar missions the third-body e...
Article
Full-text available
Lunar frozen orbits, characterized by constant orbital elements on average, have been previously found using various dynamical models, incorporating the gravitational field of the Moon and the third-body perturbation exerted by the Earth. The resulting mean orbital elements must be converted to osculating elements to initialize the orbiter position...
Article
Full-text available
Finding satellite relative orbits that are resilient to differential gravitational perturbations has received much attention in the literature. In particular, detecting “invariant” relative orbits under the J2 perturbation was considered a solved problem. These “invariance” conditions result in constraints on the differential mean semimajor axis, i...
Preprint
Finding satellite relative orbits that are resilient to differential gravitational perturbations has received much attention in the literature. In particular, detecting "invariant" relative orbits under the J2 perturbation, was considered a solved problem. These "invariance" conditions result in constraints on the differential mean semimajor axis,...
Preprint
Full-text available
Lunar frozen orbits, characterized by constant mean eccentricity, mean inclination, and mean argument of periapsis, have been previously found using various dynamical models, incorporating the unique gravitational field of the Moon and the third-body perturbation exerted by the Earth. The resulting mean orbital elements must be converted to osculat...
Article
Full-text available
The gain-switching PD control law for target tracking is proposed with the introduction of the image plane error, defined as the deviation between the target image centroid and the center of the image plane, into the close-loop of tracking control. The switching function is designed for switching of PD gain in order to compensate the effects of mea...
Article
Full-text available
A method based on analytical gradients for solving classical Lambert orbit transfer problem is presented for existing complex solution model and slow convergence rate. The Lambert problem is transformed into transcendental equation for solving the constrained problem with transfer time. The true anomaly is selected as the iterative variable. The an...

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Projects

Projects (2)
Project
We study how to design constellations so as to optimize various performance metrics (mainly variants of the GDOP). Some of the emerging applications include regional navigation satellite systems and regional geolocation.
Project
Enable operation of satellite formations around the moon, with guaranteed long-term stability of relative orbits and reduced fuel consumption under third-body effects and gravitational perturbations.