scholarly journals Analysis of the advantages of an aerodynamic compensator in contactless space debris removal

2020 ◽  
Vol 2020 (4) ◽  
pp. 55-64
Author(s):  
A.A. Fokov ◽  
◽  
S.V. Khoroshylov ◽  
D.S. Svorobin ◽  
◽  
...  
Keyword(s):  
Control System ◽  
Space Debris ◽  
Position Control ◽  
Ion Beam ◽  
Orbital Plane ◽  
Cross Sectional ◽  
Debris Removal ◽  
Low Earth Orbits ◽  
The Cost ◽  
Propellant Consumption

A modified scheme of the known technology for contactless space debris removal, which is called Ion Beam Shepherd, is considered. This scheme uses an aerodynamic compensator in order to reduce the propellant consumption of the additional electrojet thruster of the shepherd spacecraft. The thruster serves to compensate the spacecraft motion caused by the action of the main electrojet thruster, whose ion plume “brakes” the space debris object. The aerodynamic compensator significantly increases the spacecraft cross-sectional area compared to the space debris object one. This fact, together with the aerodynamic perturbations acting in the direction perpendicular to the orbital plane, calls for estimating the propellant consumption of the control system thruster to maintain the required position of the spacecraft relative to the space debris object in that direction. The goal of this article is to identify the advantages of using the aerodynamic compensator in space debris removal from low Earth orbits using the Ion Beam Shepherd technology. The tasks of the study are to estimate the reduction in the cost of the momentum of the additional electrojet thruster during contactless space debris object de-orbiting due to the use of the aerodynamic compensator and the additional cost of the momentum of the thruster of the spacecraft – space debris object relative position control system to correct deviations perpendicular to the orbital plane. Using a number of simplifying assumptions, integral estimates of these costs are obtained. Using these cost estimates, it is shown that the use of an aerodynamic compensator is advantageous in terms of the cost of the saved electrojet thruster propellant (xenon) regardless of the type of the spacecraft control system thruster.

scholarly journals Out-of-plane relative motion of a spacecraft with an aerodynamic compensator during contactless space debris removal

2021 ◽  
Vol 27 (2) ◽  
pp. 15-27
Author(s):  
A.A. Fokov ◽  
◽  
S.V. Khoroshylov ◽  
D.S. Svorobin ◽  
◽  
...  
Keyword(s):  
Relative Motion ◽  
Space Debris ◽  
Ion Beam ◽  
Reaction Force ◽  
Orbital Plane ◽  
Cross Sectional ◽  
Out Of Plane ◽  
Simplifying Assumptions ◽  
Low Earth Orbits ◽  
Earth Orbits

The article investigates the feasibility of using an aerodynamic compensator for contactless removal of space debris from low Earth orbits, taking into account aerodynamic disturbances in the direction perpendicular to the orbital plane. The object of the research is a modified scheme of the “ion beam shepherd” de-orbiting concept. The modification consists in replacing an additional electric thruster with an aerodynamic compensator designed to compensate the shepherd spacecraft motion caused by the reaction force of the main electric thruster, the ion plume of which creates a “braking” effect on the space debris object. The shepherd spacecraft with the aerodynamic compensator has a relatively large cross-sectional area. In this case, it is necessary to control the relative motion caused by the aerodynamic disturbances in the direction perpendicular to the orbital plane. This control requires additional propellant for the thrusters of the relative motion control system of the shepherd spacecraft. The article presents the calculation of the propellant consumption using a number of simplifying assumptions. The validity of these assumptions is verified by numerical integration of the equations of relative motion. The feasibility of using the aerodynamic compensator for contactless removal of space debris, taking into account aerodynamic disturbances acting in the direction perpendicular to the orbital plane, is shown.

scholarly journals Ion Beam Shepherd for Contactless Space Debris Removal

2011 ◽  
Vol 34 (3) ◽  
pp. 916-920 ◽  
Author(s):  
Claudio Bombardelli ◽  
Jesus Pelaez
Keyword(s):  
Space Debris ◽  
Ion Beam ◽  
Debris Removal

scholarly journals Analyzing Costs of Space Debris Removal in Basis of Three Kinds of Methods

2017 ◽  
Vol 9 (8) ◽  
pp. 151
Author(s):  
Jialin Wen
Keyword(s):  
Monte Carlo ◽  
Unit Volume ◽  
Space Debris ◽  
Water Jet ◽  
The Earth ◽  
Water Jet Cutting ◽  
Debris Removal ◽  
Capture Method ◽  
Dangerous Place ◽  
The Cost

The number of different space debris on the orbits around the earth has gotten more and more attentions. These debris pieces put spacecraft in a dangerous place. We built a model based on the problems of the space debris’ removal, discussing the cost of the three common methods (ground-based laser removing, water jet cutting and net-capture) for removing the debris. First we used the Monte Carlo to simulate the space debris’ number and speed. Then we built models for the three common methods respectively, explored the removing efficiency of different size of debris and their cost for removing a unit volume of the debris. Finally we find that The laser removing method is suiTable for medium-sized debris with the diameter less than 10cm, the water jet method is suiTable for large-sized debris with the diameter within 10cm and 1400cm, the net-capture method is suiTable for super-large-sized debris with diameter bigger than 1400cm. Also, we analyzed the advantages and shortcoming of each method.

scholarly journals Ion beam shepherd satellite for space debris removal

2013 ◽  
Author(s):  
M. Merino ◽  
E. Ahedo ◽  
C. Bombardelli ◽  
H. Urrutxua ◽  
J. Peláez
Keyword(s):  
Space Debris ◽  
Ion Beam ◽  
Debris Removal

scholarly journals Design and simulation of an optimized small wind turbine

2021 ◽  
Author(s):  
◽  
Norberto Fernando Soares Sanjimba
Keyword(s):  
Control System ◽  
Wind Turbine ◽  
Wind Turbines ◽  
Cross Sectional Area ◽  
Sectional Area ◽  
Cross Sectional ◽  
Cost Of Energy ◽  
Small Wind Turbines ◽  
The Cost ◽  
Large Wind

The volatility of fossil fuel's price, pollution, and emission associated with converting fos- sil fuel into a useful type of energy led man to search for more sustainable energy sources that are pollution-free and renewable. Today, renewable energy technologies, such as solar and large wind turbines, are developed to a stage of maturity, having the cost of produc- ing electricity dropping signi􏰀cantly in the last decade, therefore making these technologies competitive with the traditional counterpart. The cost of producing electricity through small wind turbines is still high compared to large wind turbines or photovoltaic technology. For small wind turbines to successfully compete with other technologies and contribute to the diversi􏰀cation of o􏰈-grid technology, further research is needed to reduce the levelised cost of energy (LCOE). Therefore, this study aims to reduce the levelised cost of energy (LCOE) of small wind turbines. To achieve the ob- jective, a 10 kW wind turbine operating at a site of an average wind speed of 7.5 m/s was designed, optimized, and simulated. With low LCOE in mind, the turbine components were designed as simple as possible to reduce manufacturing costs. The blades are made of uniform cross-sectional area, which made possible to use aluminum as the blade material, and the blade cross-sectional area is made out of a high lift airfoil. The hub is made of aluminum and modelled and designed as a disc with holes to bolt the blades and attach the main shaft. The mainframe is treated as a thick plate with a proper arrangement to connect the generator, the main and yaw bearings, the tail support, and any other ancillaries needed. An octal tapered tower with a height of 20 m made of steel was designed and optimized for low weight. The electrical power is to be produced by a direct drive variable speed permanent magnet synchronous generator. The control system is designed in such a way that allows the turbine to operate in maximum power e􏰊ciency for any speed below the rated speed, and to increase reliability, a sensorless control system is suggested. The research started with a broad review of the relevant literature on wind turbines in general and small wind turbines. The turbine blades design began by analysing the aero- dynamic performance of the blade. To accomplish that, XFoil was used to generate the aerodynamic parameters of the airfoil, the Blade Element Momentum (BEM) method was used to estimate the blades' aerodynamic performance, and Qblade was employed to com- pare the results, and Computational Fluid Dynamics (CFD) was used to verify the results. The preliminary design was done using standard IEC 61400-2 to obtain the load cases, and general engineering formulas, CFD and Finite Element Analysis (FEA) was used to analyse the load in the components according to IEC 61400-2, FAST-V7 was used to simulate the turbine's overall performance, standard formulas were used to evaluate the economic perfor- mance of the design, MatLab was used to perform all needed calculations. In this study, it is evident that using standard IEC 61400-2 to estimate the load, gyroscopic load components dominate the design, and the control system must be used to limit those loads. The designed turbine has relatively high e􏰊ciency and low LCOE.

scholarly journals Geomagnetic Energy Approach to Space Debris Deorbiting in a Low Earth Orbit

2019 ◽  
Vol 2019 ◽  
pp. 1-18 ◽  
Author(s):  
Guanhua Feng ◽  
Wenhao Li ◽  
Heng Zhang
Keyword(s):  
Angular Momentum ◽  
Geomagnetic Field ◽  
Space Debris ◽  
High Efficiency ◽  
Low Earth Orbit ◽  
Future Application ◽  
Spin Angular Momentum ◽  
Momentum Exchange ◽  
Debris Removal ◽  
Low Earth Orbits

The space debris removal problem needs to be solved urgently. Over 70% of debris is distributed between the 500 km and 1000 km low Earth orbits (LEO), and existing methods may be theoretically feasible but are not the high-efficiency and low-consumption methods for LEO debris removal. Based on the torque effect of a static magnet interacting with the geomagnetic field, a new spin angular momentum exchange (SAME) method by geomagnetic excitation (without working medium consumption) for LEO active debris deorbiting is proposed. The LEO delivery capability of this method is researched. Two kinds of spin angular momentum accumulation (SAMA) strategies are proposed. Then through numerical simulation under the dipole model and International Geomagnetic Reference Field (IGRF11) model, the results confirm the physical feasibility and basic performance of the proposed method. The method can be applied to the regions of the LEO below 1000 km with different altitudes/inclinations and eccentricities, and with existent magnetorquer technology, only several days of preparation is required for about 104 m·kg mechanism-scale-debris-mass deorbiting, which can be used for deorbiting missions in debris-intensive areas (altitude≤1000 km); without consideration of external effects on the geomagnetic field distribution, it has the same deorbiting capability with that of the LEO below 1000 km when the altitude is over 1000 km. Besides, the method is characterized by explicit mechanism, flexible control strategy and application, and low dependence on the scale. Finally, the key technology requirements and future application of LEO active debris removal and on-orbit delivery by using SAME are prospected.

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