RemoveDEBRIS: An in-orbit demonstration of technologies for the removal of space debris

Aglietti, Guglielmo S.; Taylor, B.C.; Fellowes, Simon; Ainley, Sean; Tye, Daniel; Cox, C. M.; Zarkesh, A.; Mafficini, A.; Vinkoff, N.; Bashford, K.; Salmon, Thierry; Retat, Ingo; Burgess, Chris; Hall, Alexander; Chabot, Thomas; Kanani, Keyvan; Pisseloup, Aurélien; Bernal, Cesar; Chaumette, François; Pollini, A.; Steyn, Willem J.

doi:10.1017/aer.2019.136

Cited by 47 publications

(12 citation statements)

References 13 publications

(13 reference statements)

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“…In this section, the feasibility of using space harpoons to fix IMUs to space debris is described. Space harpoons are an important method for Active Space Debris Removal (ADR) missions, and validation experiments have been conducted by the Surrey Space Centre of [22][23][24][25]. "The satellite was launched the 2 April 2018, to the International Space Station (ISS) and from there, on the 20 June 2018, was deployed via the NanoRacks Kaber system into an orbit of 405 km altitude" [24].…”

Section: Feasibility Analysis Of Space Harpoonsmentioning

confidence: 99%

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Dynamic Parameter Estimation of Large Space Debris Based on Inertial and Visual Data Fusion

et al. 2021

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Most large space debris has large residual angular momentum, and the de-tumbling and capturing operation can easily cause instability and failure of tracking satellites. Therefore, it is necessary to perform real-time dynamic parameter identification of space debris prior to the imminent de-tumbling and capture operation, thus improving the efficiency and success of active debris removal (ADR) missions. A method for identifying dynamic parameters based on the fusion of visual and inertial data is proposed. To obtain the inertial data, the inertial measurement units (IMU) with light markers were fixed on the debris surface by space harpoon, which has been experimentally proven in space, and the binocular vision was placed at the front of a tracking satellite to obtain coordinates of the light markers. A novel method for denoising inertial data is proposed, which will eliminate the interference from the space environment. Furthermore, based on the denoised data and coordinates of the light markers, the mass-center location is estimated. The normalized angular momentum is calculated using the Euler–Poinsot motion characteristics, and all active debris removal parameters are determined. Simulations with Gaussian noise and experiments in the controlled laboratory have been conducted, the results indicate that this method can provide accurate dynamic parameters for the ADR mission.

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Section: Feasibility Analysis Of Space Harpoonsmentioning

confidence: 99%

“…In this paper, we also use the above assumption: the inertial unit can be attached to the surface of space debris using the space harpoon [22], which has successfully done space experiments. Because the IMUs are generally light, it does not bring too much difficulty to the attachment.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Parameter Estimation of Large Space Debris Based on Inertial and Visual Data Fusion

et al. 2021

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“…8 Due to these advantages, many studies have been carried out on tether-net systems, for example, dynamics, 9 control, 10 and experiments. 11 Botta et al 12 developed a commercial software named Vortex Studio to study the deployment dynamics of the tether-net system. Golebiowski et al 13…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation and behavior prediction of a space net system throughout the capture process: Spread, contact, and close

Huang,

Zou,

Pan

et al. 2023

Int Journal of Mech Sys Dyn

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In this paper, we develop an exhaustive numerical simulator for the dynamic visualization and behavior prediction of the tether‐net system during the whole space debris capture phases, including spread, contact, and close. First of all, to perform its geometrically nonlinear deformation, discrete different geometry theory is applied to model the mechanical response of a flexible net. Based on the discretization of the whole structure into multiple vertexes and lines, the internal force and associated Hession are derived in a closed form to solve a series of nonlinear dynamic equations of motion. The spread and deployment of a packaged net can be realized using this well‐established net solver. Next, a multidimensional incremental potential formulation is selected to achieve the intersection‐free boundary nonlinear contact and collision between the deformable net and rigid debris. Finally, for the closing mechanism analysis, a log‐like barrier functional is derived to achieve the nondeviation condition between the ring–rod linkage system. The continuous log barrier functionals constructed for both the contact model and the linkage system are smooth and differentiable, and, therefore, the nonlinear net capture dynamic system can be efficiently solved through a fully implicit time integrator. Overall, as a demonstration, the whole capture process of a defunct satellite using a hexagon net is simulated through our well‐established numerical framework. We believe that our comprehensive numerical methods could provide new insight into the optimal design of active debris removal systems and promote further development of the online control of tether tugging systems.

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“…For the net capture method, it has in total three phases to deorbit a space debris object, that is the deployment, capture and post-capture phases. Numerous research studies focused on the first two phases, e.g., the sensitivity analysis [9], simulator design [9][10][11][12], parabolic flight experiments [12][13][14], and even on-orbit experiments [15]. Shan et al have analyzed the initial conditions, such as the bullet mass, shooting velocity and the shooting angle's influence on the output parameters, the net opening area, the deployment time and the travelling distance during the net deployment phase [9].…”

Section: Introductionmentioning

confidence: 99%

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

Shan

Shi

2022

Aerospace

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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.

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RemoveDEBRIS: An in-orbit demonstration of technologies for the removal of space debris

Cited by 47 publications

References 13 publications

Dynamic Parameter Estimation of Large Space Debris Based on Inertial and Visual Data Fusion

Dynamic Parameter Estimation of Large Space Debris Based on Inertial and Visual Data Fusion

Numerical simulation and behavior prediction of a space net system throughout the capture process: Spread, contact, and close

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

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