Spacecraft Deorbit Point Targeting Using Aerodynamic Drag

Omar, Sanny; Bevilacqua, Riccardo; Guglielmo, David; Fineberg, Laurence; Treptow, Justin; Clark, Scott; Johnson, Yusef

doi:10.2514/1.g002612

Cited by 17 publications

(4 citation statements)

References 17 publications

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“…Eqn. 22 is proven in this author's previous work for circular orbits where density is a function of semi major axis [22].…”

Section: Orbit Lifetime Analysismentioning

confidence: 62%

“…However, differential drag techniques, or modifying the relative drag-induced acceleration between two spacecraft, have been proposed previously by Leonard in 1986 [18] as means of thruster-free orbital maneuvering, and then built upon by many researchers since then, including some of the authors of this paper [19,20,21]. By modulating the drag area of a spacecraft appropriately, the spacecraft can be made to de-orbit away from populated areas without the use of any thrusters [22]. This technique could be used to save fuel for spacecraft containing thrusters and could be used to provide controlled re-entry for spacecraft whose thrusters have failed or that do not contain thrusters.…”

Section: Introductionmentioning

confidence: 99%

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Drag Deorbit Device: A New Standard Reentry Actuator for CubeSats

Guglielmo

Omar²,

Bevilacqua³

et al. 2019

Journal of Spacecraft and Rockets

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With the advent of CubeSats, research in Low Earth Orbit (LEO) becomes possible for universities and small research groups. Only a handful of launch sites can be used, due to geographical and political restrictions. As a result, common orbits in LEO are becoming crowded due to the additional launches made possible by low-cost access to space. CubeSat design principles require a maximum of a 25-year orbital lifetime in an effort to reduce the total number of spacecraft in orbit at any time. Additionally, since debris may survive re-entry, it is ideal to de-orbit spacecraft over unpopulated areas to prevent casualties.The Drag Deorbit Device (D3) is a self-contained targeted re-entry subsystem intended for CubeSats. By varying the cross-wind area, the atmospheric drag can be varied in such a way as to produce desired maneuvers. The D3 is intended to be used to remove spacecraft from orbit to reach a desired target interface point. Additionally, attitude stabilization is performed by the D3 prior to deployment and can replace a traditional ADACS on many missions.This paper presents the hardware used in the D3 and operation details. Four stepper-driven, repeatedly retractable booms are used to modify the cross-wind area of the D3 and attached spacecraft. Five magnetorquers (solenoids) over three axes are used to damp rotational velocity. This system is expected to be used to improve mission flexibility and allow additional launches by reducing the orbital lifetime of spacecraft.The D3 can be used to effect a re-entry to any target interface point, with the orbital inclination limiting the maximum latitude. In the chance that the main spacecraft fails, a timer will automatically deploy the booms fully, ensuring the spacecraft will

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“…Eqn. 22 is proven in this author's previous work for circular orbits where density is a function of semi major axis [22].…”

Section: Orbit Lifetime Analysismentioning

confidence: 62%

Section: Introductionmentioning

confidence: 99%

Drag Deorbit Device: A New Standard Reentry Actuator for CubeSats

Guglielmo

Omar²,

Bevilacqua³

et al. 2019

Journal of Spacecraft and Rockets

Self Cite

View full text Add to dashboard Cite

show abstract

“…However, more recently, methods exploiting differential lift have emerged [63,64] and methods using differential drag have been demonstrated in-orbit [65,66]. Use of drag augmentation has been proposed for targeting of atmospheric re-entry location [67][68][69] and also collision avoidance [70], whilst adjustment of orbital inclination using out-of-plane forces [27] have also been studied. Passive aerodynamic stabilisation or aerostability (the pointing of a spacecraft in the direction of the oncoming flow) has been demonstrated in orbit by several missions [6,71,72], whilst further aerodynamic attitude control concepts including use of external surfaces to perform detumbling [73], internal momentum management [74], and pointing manoeuvres [75][76][77][78] have also been considered.…”

Section: Aerodynamic Controlmentioning

confidence: 99%

The Benefits of Very Low Earth Orbit for Earth Observation Missions

Crisp,

Roberts,

Livadiotti

et al. 2020

Preprint

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Very low Earth orbits (VLEO), typically classified as orbits below approximately 450 km in altitude, have the potential to provide significant benefits to spacecraft over those that operate in higher altitude orbits. This paper provides a comprehensive review and analysis of these benefits to spacecraft operations in VLEO, with parametric investigation of those which apply specifically to Earth observation missions. The most significant benefit for optical imaging systems is that a reduction in orbital altitude improves spatial resolution for a similar payload specification. Alternatively mass and volume savings can be made whilst maintaining a given performance. Similarly, for radar and lidar systems, the signal-to-noise ratio can be improved. Additional benefits include improved geospatial position accuracy, improvements in communications link-budgets, and greater launch vehicle insertion capability. The collision risk with orbital debris and radiation environment can be shown to be improved in lower altitude orbits, whilst compliance with IADC guidelines for spacecraft post-mission lifetime and deorbit is also assisted. Finally, VLEO offers opportunities to exploit novel atmosphere-breathing electric propulsion systems and aerodynamic attitude and orbit control methods.However, key challenges associated with our understanding of the lower thermosphere, aerodynamic drag, the requirement to provide a meaningful orbital lifetime whilst minimising spacecraft mass and complexity, and atomic oxygen erosion still require further research. Given the scope for significant commercial, societal, and environmental impact which can be realised with higher performing Earth observation platforms, renewed research efforts to address the challenges associated with VLEO operations are required.

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“…Noticeably, this review focusses on the theoretic developments of the control theories and does not discuss project related publications. Also, using BC modifications for reentry point targeting [28][29][30][31][32], as it is frequently discussed, is not included since it does not belong in the classical field of differential lift and drag methods.…”

Section: Figmentioning

confidence: 99%

On the exploitation of differential aerodynamic lift and drag as a means to control satellite formation flight

et al. 2019

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In order for a satellite formation to maintain its intended design despite present perturbations (formation keeping), to change the formation design (reconfiguration) or to perform a rendezvous maneuver, control forces need to be generated. To do so, chemical and/or electric thrusters are currently the methods of choice. However, their utilization has detrimental effects on small satellites' limited mass, volume and power budgets. Since the mid-eighties, the potential of using differential drag as a means of propellant-less source of control for satellite formation flight is actively researched. This method consists of varying the aerodynamic drag experienced by different spacecraft, thus generating differential accelerations between them. Its main disadvantage, that its controllability is mainly limited to the in-plain relative motion, can be overcome by using differential lift as a means to control the out-of-plane motion. Due to its promising benefits, a variety of studies from researchers around the world have enhanced the state-of-the-art over the past decades which results in a multitude of available literature. In this paper, an extensive literature review of the efforts which led to the current state-of-the-art of different lift and drag based satellite formation control is presented. Based on the insights gained during the review process, key knowledge gaps that need to be addressed in the field of differential lift in order to enhance the current state-of-the-art are revealed and discussed. In closer detail, the interdependence between the feasibility domain / the maneuver time and increased differential lift forces achieved using advanced satellite surface materials promoting quasi-specular or specular reflection, as currently being developed in the course of the DISCOVERER project, is discussed. Keywords Satellite aerodynamics • differential lift • differential drag • formation flight control • propellant less control Acknowledgements This project has received funding from the European Union's Horizon 2020 research and innovation program under grant agreement No. 737183. This reflects only the author's view and the European Commission is not responsible for any use that may be made of the information it contains. The author would like to thank the reviewers, the DISCOVERER team as well as several colleagues from IRS for their valuable feedback and suggestions.

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Spacecraft Deorbit Point Targeting Using Aerodynamic Drag

Cited by 17 publications

References 17 publications

Drag Deorbit Device: A New Standard Reentry Actuator for CubeSats

Drag Deorbit Device: A New Standard Reentry Actuator for CubeSats

The Benefits of Very Low Earth Orbit for Earth Observation Missions

On the exploitation of differential aerodynamic lift and drag as a means to control satellite formation flight

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