Aerospace

Research

23 pages, 14171 KiB

Open AccessArticle

Theoretical and Experimental Investigation of Geomagnetic Energy Effect for LEO Debris Deorbiting

by Guanhua Feng, Chen Zhang, Heng Zhang and Wenhao Li

Aerospace 2022, 9(9), 511; https://doi.org/10.3390/aerospace9090511 - 14 Sep 2022

Cited by 2 | Viewed by 2025

Space debris is increasingly problematic and needs active removal, especially in low Earth orbits (LEO). Paying for the vast cost of the disposal of debris from the situation is still inevitable even though pivotal technical hurdles have been overcome with the growing maturity [...] Read more.

Space debris is increasingly problematic and needs active removal, especially in low Earth orbits (LEO). Paying for the vast cost of the disposal of debris from the situation is still inevitable even though pivotal technical hurdles have been overcome with the growing maturity of capturing and deorbiting methods. To this end, a novel geomagnetic energy (GME) propellant approach is firstly proposed to propel a spinning tethered spacecraft for LEO debris deorbiting, without the use of expendable fuel and a large-length tether. In this method, the time-cumulative effect of the interacted torque of the spacecraft’s electromagnet and geomagnetic field is used to accelerate the rotating system for GME storage, and the space momentum exchange from the angular momentum of system to the linear momentum of debris is introduced to deorbit the debris for GME release. Next, an on-orbit directional GME storage mechanism is built, and the corresponding two optimal strategies are put forward. Both theoretical and simulation results demonstrate that GME can be stored in the expected direction on any inclined LEO below 1000 km. Deorbiting kg-level debris can be accomplished within several orbital periods with the existing magnetorquer technology. Finally, proof-of-principle experiments of the GME effect are performed and elementarily validate the LEO GME utilization in space. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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17 pages, 2019 KiB

Open AccessArticle

Impedance Control Using Selected Compliant Prismatic Joint in a Free-Floating Space Manipulator

by Piotr Palma, Karol Seweryn and Tomasz Rybus

Aerospace 2022, 9(8), 406; https://doi.org/10.3390/aerospace9080406 - 28 Jul 2022

Cited by 10 | Viewed by 1927

Abstract

The success of space missions like capture-and-deorbit or capture-and-service relies on the ability of the capturing satellite to establish a stable mechanical connection by its gripping tool with the object being intercepted. Most of the potential objects of capture missions are not equipped [...] Read more.

The success of space missions like capture-and-deorbit or capture-and-service relies on the ability of the capturing satellite to establish a stable mechanical connection by its gripping tool with the object being intercepted. Most of the potential objects of capture missions are not equipped with dedicated docking ports; hence, the satellite robot intercepting them will have to provide the mechanical compliance necessary for the safe establishment of contact between the two structures. Articulated robotic arms with controlled mechanical impedance are one set of promising solutions for this challenge. In this study, the authors discuss how the mechanical impedance realized only along a single axis can be useful for facilitating the contact between the manipulator arm’s end effector of a free-floating robot and an uncooperative object in microgravity. By distinguishing a dominant direction in the final approach and contact establishment maneuver, the need for impedance control of six degrees of freedom may be relaxed, and a single prismatic joint with controlled impedance can be used at the end effector. Such architecture is simulated and compared with the full model-based six-degree-of-freedom Cartesian impedance control of a free-floating manipulator. Authors then discuss the limitations and possibilities of such architecture in a potential practical setting. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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20 pages, 8266 KiB

Open AccessArticle

Spectral Light Curve Simulation for Parameter Estimation from Space Debris

by Max Nussbaum, Ewan Schafer, Zizung Yoon, Denise Keil and Enrico Stoll

Aerospace 2022, 9(8), 403; https://doi.org/10.3390/aerospace9080403 - 26 Jul 2022

Cited by 10 | Viewed by 3293

Abstract

Characterisation of space debris has become a fundamental task to facilitate sustainable space operations. Ground-based surveillance provides the means to extract key attributes from spacecraft. However, signal inversion attempts are generally under-constrained, which is why an increase in measurement channels through multispectral observations [...] Read more.

Characterisation of space debris has become a fundamental task to facilitate sustainable space operations. Ground-based surveillance provides the means to extract key attributes from spacecraft. However, signal inversion attempts are generally under-constrained, which is why an increase in measurement channels through multispectral observations is expected to benefit parameter estimation. The current approach to simulating space debris observation at the Institute of Technical Physics of the German Aerospace Centre (DLR) in Stuttgart relies on monochromatic images taken from the POV-Ray render engine to form light curve signals. Rendered scenes are generated based on the location of an observer by propagating a target’s orbit and rotation. This paper describes the simulation of spectral light curves through the extension of DLR’s Raxus Prime simulation environment. Light reflections are computed using the Mitsuba2 spectral render engine, while atmospheric attenuation is accounted for by the radiative transfer library libRadTran. A validation of the simulator was achieved using multispectral measurements, carried out at the Uhlandshöhe research observatory in Stuttgart. Measured and synthetic data were found to be in agreement based on an RMS error <1% of the total measured signal count. Further, simulated spectral products were used to determine a target’s surface material composition and rotation state and examine aspects of laser ranging to non-cooperative targets. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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8 pages, 3373 KiB

Open AccessArticle

Design of an Integrated Platform for Active Debris Removal

by Senwei Lv, Haojun Zhang, Yao Zhang, Bowen Ning and Rui Qi

Aerospace 2022, 9(7), 339; https://doi.org/10.3390/aerospace9070339 - 25 Jun 2022

Cited by 6 | Viewed by 2449

Abstract

In research concerning active debris removal, scholars have proposed dozens of schemes for removing debris. However, every scheme has both advantages and disadvantages, and no scheme possesses an overwhelming advantage. This paper proposes an integrated platform scheme which integrates multiple capture and deorbit [...] Read more.

In research concerning active debris removal, scholars have proposed dozens of schemes for removing debris. However, every scheme has both advantages and disadvantages, and no scheme possesses an overwhelming advantage. This paper proposes an integrated platform scheme which integrates multiple capture and deorbit technologies, such as a tethered net, harpoon, and robotic arm, to improve the success rate in terms of the active removal of debris of different shapes and different sizes. The design of the mechanisms of the integrated platform is presented in detail. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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16 pages, 2248 KiB

Open AccessArticle

Geostationary Orbital Debris Collision Hazard after a Collision

by Haitao Zhang, Zhi Li, Weilin Wang, Yasheng Zhang and Hao Wang

Aerospace 2022, 9(5), 258; https://doi.org/10.3390/aerospace9050258 - 10 May 2022

Cited by 6 | Viewed by 2750

Abstract

Many space objects are densely distributed in the geostationary (GEO) band, and the long-term impact of the collision of GEO spacecraft and space debris on the GEO environment has attracted more and more attention. After summarizing the advantages and disadvantages of the long-term [...] Read more.

Many space objects are densely distributed in the geostationary (GEO) band, and the long-term impact of the collision of GEO spacecraft and space debris on the GEO environment has attracted more and more attention. After summarizing the advantages and disadvantages of the long-term evolution model based on the “Cube” collision probability calculation model, the “Grid” model, a long-term evolution model especially suitable for GEO band, was established. For four types of collision and disintegration events, the “Grid” model was used to study the space environment in the GEO band after collisions between GEO spacecraft and space debris. Future collisions were simulated, and the number of space objects in the next 100 years was counted. Once space debris and massive spacecraft were completely disintegrated after collision, the number of space objects and the collision probability increased sharply, and this caused a collision cascading syndrome. Even if there was no initial disintegration event, collision and disintegration events occurred in the long-term evolution of the GEO band, which led to an increase in the number of space objects. However, the collision probability was much lower, and the number of space objects grew much more slowly without the initial collision. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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11 pages, 4059 KiB

Open AccessArticle

Impact Pressure Distribution Recognition for Large Non-Cooperative Target in Ground Detumbling Experiment

by Siqi Peng, Huibo Zhang, Chaoqun Qi, Jialiang Xu, Rui Ma and Shijie Dai

Aerospace 2022, 9(5), 226; https://doi.org/10.3390/aerospace9050226 - 20 Apr 2022

Cited by 1 | Viewed by 2201

Abstract

During the contact between the detumbling end-effector and large non-cooperative target, the recognition of impact pressure distribution is important for estimating the success rate of detumbling mission. To figure out the pressure trends, the ground experiments before the real space mission are necessary. [...] Read more.

During the contact between the detumbling end-effector and large non-cooperative target, the recognition of impact pressure distribution is important for estimating the success rate of detumbling mission. To figure out the pressure trends, the ground experiments before the real space mission are necessary. However, due to the drawbacks of the pressure array-like sensor, dynamic characteristics of impact, and unavoidable noise, the accurate dynamic pressure distribution is hard to obtain. In this letter, we propose a recognition method, Impact Pressure Distribution Recognition. The proposed method can quickly generate dynamic impact pressure distribution without limitation on sensor accuracy through pressure data supplement and area correction based on contact model. The analysis results show that our method can efficiently recognize multiple distributed pressure and rebuild the more accurate impact pressure distribution. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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16 pages, 4126 KiB

Open AccessFeature PaperArticle

TDE-Based Adaptive Integral Sliding Mode Control of Space Manipulator for Space-Debris Active Removal

by Zhibin Zhang, Xinhong Li, Xun Wang, Xin Zhou, Jiping An and Yanyan Li

Aerospace 2022, 9(2), 105; https://doi.org/10.3390/aerospace9020105 - 16 Feb 2022

Cited by 10 | Viewed by 3015

Abstract

The safe and dependable removal of large-scale space debris has been a long-standing challenge that is critical to the safety of spacecraft and astronauts. In the process of capturing and deorbiting space debris, the space manipulator must achieve extremely high control and precision. [...] Read more.

The safe and dependable removal of large-scale space debris has been a long-standing challenge that is critical to the safety of spacecraft and astronauts. In the process of capturing and deorbiting space debris, the space manipulator must achieve extremely high control and precision. However, strong couplings, model uncertainties, and various inevitable unknown disturbances cause many difficulties in coordinated control of the space manipulator. To solve this challenge, this study examines the stabilization control of a space manipulator after capturing non-cooperative large-scale space debris and presents an adaptive integral sliding mode control (AISMC) scheme with time-delay estimation (TDE). The coupling term and lumped uncertainty are estimated by TDE technology, which eliminates the requirement of prior knowledge. Adaptive sliding mode control (ASMC) is used as desired injecting dynamics to compensate TDE errors, and a PID-type integral sliding mode surface is designed to reduce steady-state errors. The Lyapunov criterion is used to prove the global stability of the controller. Simulation results show that the controller has high tracking accuracy and strong robustness. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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18 pages, 1553 KiB

Open AccessArticle

Comparison of Tethered Post-Capture System Models for Space Debris Removal

by Minghe Shan and Lingling Shi

Aerospace 2022, 9(1), 33; https://doi.org/10.3390/aerospace9010033 - 11 Jan 2022

Cited by 16 | Viewed by 4343

Abstract

The space debris problem poses a huge threat to operational satellites and has to be addressed. Multiple removal methods have been proposed to keep Earth’s orbit stable. Flexible connection capturing methods, such as the harpoon system, tether–gripper system and the net system, are [...] Read more.

The space debris problem poses a huge threat to operational satellites and has to be addressed. Multiple removal methods have been proposed to keep Earth’s orbit stable. Flexible connection capturing methods, such as the harpoon system, tether–gripper system and the net system, are potential candidate methods for space debris removal in the future. However, the tethered system is usually assumed as a dumbbell model where two end masses are connected by a rigid bar. This traditional model is not accurate enough to predict the motion of the target, neither the whole system. In this paper, three models, namely the modified dumbbell model, lumped-mass model and the ANCF model, to describe a tethered post-capture system for space debris removal are described and compared. Moreover, modal analysis of the tethered system is performed, and an analytical solution of the system’s natural frequency is derived. In addition, two configurations of the tethered system, namely the single tether configuration and the sub-tether configuration are simulated and compared based on three models, respectively. Finally, the influence on the chaser satellite by the initial angular velocity of the target is analyzed. Full article

(This article belongs to the Special Issue Space Debris Removal: Challenges and Opportunities)

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