Low-thrust de-orbiting from Low Earth Orbit through natural perturbations

Huang, Shuheng; Colombo, Camilla; Alessi, Elisa Maria; Wang, Y.; Hou, Zujun

doi:10.1016/j.actaastro.2022.02.017

Cited by 3 publications

(8 citation statements)

References 32 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Numerical simulation is carried out in different scenarios, which comprise of transfers from LEO (Low Earth Orbit) to GEO (Geostationary Earth Orbit), from LEO to LEO, and from LEO to MEO (Medium Earth Orbit). The orbit states are presented in terms of classical orbital elements, as listed in Table 1: the subscript “ G ,” “ K ,” and “ H ” respectively represents that the parameters are taken from Guelman's method, 29 Kechichian's method, 30 and Huang's method 31 . Accordingly, the spacecraft parameters are listed in Table 2.…”

Section: Numerical Simulationmentioning

confidence: 99%

“…30 (mostly 3.5 × 10 −4 m/s 2 ), and Ref. 31 (mostly 1 × 10 −2 m/s 2 ). In PSO, we set 50 particles and 90 iterations.…”

Section: Numerical Simulationmentioning

confidence: 99%

“…Huang considered the effects of the Earth second zonal harmonics in the low‐thrust transfer problem, but his averaged equations of motion neglected the low‐thrust effect on the change rate of the eccentric anomaly; therefore, a small eccentricity ( e o = 0.001 as listed in Table 1) was used. In fact, the proposed method can also address Earth perturbations: the velocity impulse at r k can be compensated with the variations on orbital states between r k and r k +1 , which can be derived by the perturbed equations of motion 31 . In addition, our algorithm allows arbitrary orbital elements, for example, e o = 0.8.…”

Section: Numerical Simulationmentioning

confidence: 99%

“…The orbit states are presented in terms of classical orbital elements, as listed in Table 1: the subscript "G," "K," and "H" respectively represents that the parameters are taken from Guelman's method, 29 Kechichian's method, 30 and Huang's method. 31 Accordingly, the spacecraft parameters are listed in Table 2. The proposed method respectively shares the same magnitude of acceleration with Ref.…”

Section: The Mesh Refinement Algorithmmentioning

confidence: 99%

“…In fact, the proposed method can also address Earth perturbations: the velocity impulse at r k can be compensated with the variations on orbital states between r k and r k+1 , which can be derived by the perturbed equations of motion. 31 In addition, our algorithm allows arbitrary orbital elements, for example, e o = 0.8. Consequently, the proposed method performs better in LEO H -LEO H case, for Huang's method obtained a 37 m/s larger total velocity impulse and an error in orbital semi-major axis of mostly 2 km under the acceleration of 1 × 10 −2 m/s 2 .…”

Section: Orbitmentioning

confidence: 99%

See 4 more Smart Citations

A mesh refinement method for low‐thrust orbit transfer problems

Hong-yu

Bai

Wang

et al. 2023

Optim Control Appl Methods

View full text Add to dashboard Cite

This paper researches the fuel-optimal geocentric orbit transfer problem using a low-thrust, electric propulsion. First, the transfer trajectory is divided into N burn-coast arcs via introducing (N−1) intermediate orbits between the initial and the target orbits. By restricting the time duration of each burn, the changes in orbital states caused by one time of ignition can be represented by a discrete velocity impulse; therefore, a considerable large N, a great many optimization variables, and a months and revolutions long trajectory will be calculated to solve the optimization problem. By proposing a new transfer coordinate system, the performance index is analytically calculated, and strict constraints derived from the continuous condition between adjacent orbits are removed from the mathematical optimization model. Meanwhile, an improved particle swarm optimization (PSO) method and a mesh refinement method are proposed to address the optimization problem. The mesh refinement algorithm begins with a simple bi-impulse transfer problem, automatically increases/decreases N, and finally converges to the optimal solution. Numerical simulation shows the efficiency of the method with some classical and representative scenarios.

show abstract

Section: Numerical Simulationmentioning

confidence: 99%

“…30 (mostly 3.5 × 10 −4 m/s 2 ), and Ref. 31 (mostly 1 × 10 −2 m/s 2 ). In PSO, we set 50 particles and 90 iterations.…”

Section: Numerical Simulationmentioning

confidence: 99%

Section: Numerical Simulationmentioning

confidence: 99%

Section: The Mesh Refinement Algorithmmentioning

confidence: 99%

Section: Orbitmentioning

confidence: 99%

See 3 more Smart Citations

A mesh refinement method for low‐thrust orbit transfer problems

Hong-yu

Bai

Wang

et al. 2023

Optim Control Appl Methods

View full text Add to dashboard Cite

show abstract

Estimation of the Possibility of Using Electric Propulsion Systems for Large-Sized Orbital Debris Post-Mission Disposal

Golubek¹,

Dron²,

PETRENKO³

2023

Kosm. nauka tehnol.

View full text Add to dashboard Cite

The steady increase in the amount of large-sized orbital debris represents a substantial threat to satellite missions. Currently, many methods of cleaning near-Earth space with the use of various means based on various physical principles are considered. Out of them all, the active method using a rocket propulsion system is the most commonly implemented. Considering the high specific impulse, small size, and mass of electric propulsion systems, they are a particularly attractive choice as means of post-mission disposal. Despite their advantages, such systems have certain peculiarities that need to be considered in the process of designing and implementing modern post-mission disposal means. These peculiarities include the maximum time of a single firing of the electric propulsion system, the maximum time of the battery charging, and the time of operation of the control system. The purpose of this work is the determination the capabilities of the modern Hall thrusters ST-25 and ST-40 developed by Space Electric Thruster Systems in solving the problem of post-mission disposal of large-sized orbital debris from low-Earth orbits taking into account the limitations on the power supply system. To achieve this goal, methods of analysis, synthesis, comparison, and computer simulation were used. In the course of the carried-out research, the following problems were solved. A scheme for post-mission disposal of large-sized orbital debris from low-Earth orbit was developed with consideration of the use of an electric propulsion system. The dependence was determined of the minimum delta-v increment required for post-mission disposal of an object within 25 years on the initial altitude of the orbit and the ballistic coefficient of the orbital debris. The upper boundary of the combinations of masses of orbital debris, the altitude of the initial orbit, and the ballistic coefficient were determined, for which post-mission disposal from near-Earth orbits is possible with the use of electric propulsion systems. The obtained results can be used in solving problems of the development of modern means of active post-mission disposal of orbital debris with the use of Hall thrusters developed by Space Electric Thruster Systems

show abstract

Research on the Reconfiguration Method of Space-Based Exploration Satellite Constellations for Moving Target Tracking at Sea

Wang,

Luo,

et al. 2023

Applied Sciences

View full text Add to dashboard Cite

In addressing the challenge of tracking moving targets at sea, our focus has been directed towards the development of a reconstruction methodology founded upon satellite orbital manoeuvres. This endeavour has led us to devise a predictive model for manoeuvres within a geographic coordinate system, alongside the creation of a three-phase orbital manoeuvre model. A Non-dominant Sorting Adaptive Memetic (NSAM) algorithm is proposed in this paper, which is a two-layer multi-objective optimization algorithm that retains the advantages of evolutionary algorithms based on the population’s evolution and has an excellent local optimization ability of local search algorithms. The proposed algorithm can be used to solve multi-objective optimization problems. By comparing the target observation results before and after the satellite reconstruction simulation, it can be concluded that the orbital manoeuvring can effectively improve the observation probability and observation duration of the target at a certain speed. The orbital manoeuvre model created in this paper provides a certain methodical support for the tracking problem of moving targets at sea.

show abstract

Low-thrust de-orbiting from Low Earth Orbit through natural perturbations

Cited by 3 publications

References 32 publications

A mesh refinement method for low‐thrust orbit transfer problems

A mesh refinement method for low‐thrust orbit transfer problems

Estimation of the Possibility of Using Electric Propulsion Systems for Large-Sized Orbital Debris Post-Mission Disposal

Research on the Reconfiguration Method of Space-Based Exploration Satellite Constellations for Moving Target Tracking at Sea

Contact Info

Product

Resources

About