End-of-Life de -Orbiting Strategies for Satellites

Janovsky, R.; Kassebom, Martin; Lübberstedt, Hendrik; Romberg, Oliver; Burkhardt, Holger; Sippel, Martin; Krülle, G.; Fritsche, B.

doi:10.2514/6.iac-03-iaa.5.4.05

Cited by 14 publications

(16 citation statements)

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“…We use that model in STK to generate the decay lifetime of a Cubesat starting from 180 km, which is the minimum height for a LEO satellite. The results will be verified with statistics acquired through open literature [14], [15]. A summary of the decay lifetime is shown in Table II.…”

Section: Performance Evaluationsupporting

confidence: 63%

Global communication coverage using Cubesats

Lin

2017

2017 IEEE 7th Annual Computing and Communication Workshop and Conference (CCWC)

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Abstract-Cubesat constellations may become the next generation of communication backbone architecture to provide future worldwide communication services. In this paper, we investigate the feasibility of deploying Cubesat constellations with inter-satellite links (ISL) for the delivery of global continuous communication. Cubesat constellation designs for various mission scenarios are proposed and verified using a simulation toolkit commonly used by space engineers.Index Terms-Cubesat, inter-satellite links, binary phase shift keying, code shift keying, low earth orbit, pilot symbol, sensor, Mary frequency shift keying, M-ary phase shift keying, quadrature phase shift keying, Systems Tool Kit, unmanned aerial vehicle.

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Section: Performance Evaluationsupporting

confidence: 63%

Global communication coverage using Cubesats

Lin

2017

2017 IEEE 7th Annual Computing and Communication Workshop and Conference (CCWC)

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“…A set of 2 x 4 reaction control thrusters (RCTs) for orbit maintenance and slew maneuvers after the perigee measurement phase is used as part of the chemical propulsion system (CPS) together with 1 x 6 Orbit Control thrusters (OCTs) for de-orbiting. The latter is becoming a stringent requirement for future mission designs to avoid uncontrolled growth of space debris and reduce the risk of potential collisions between debris and intact spacecraft [40,41]. The Micro-Propulsion System (MPS) is based on GAIA heritage [42] and primarily used for attitude control, employing a set of 2x8 micro-proportional thrusters to this purpose.…”

Section: Spacecraft Overviewmentioning

confidence: 99%

STE-QUEST mission and system design

Hechenblaikner¹,

Hess²,

Vitelli³

et al. 2014

Exp Astron

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STE-QUEST is a fundamental science mission which is considered for launch within the Cosmic Vision programme of the European Space Agency (ESA). Its main scientific objectives relate to probing various aspects of Einstein's theory of general relativity by measuring the gravitational red-shift of the earth, the moon and the sun as well as testing the weak equivalence principle to unprecedented accuracy. In order to perform the measurements, the system features a spacecraft equipped with two complex instruments, an atomic clock and an atom interferometer, a ground-segment encompassing several ground-terminals collocated with the best available ground atomic clocks, and clock comparison between space and ground via microwave and optical links. The baseline orbit is highly eccentric and exhibits strong variations of incident solar flux, which poses challenges for thermal and power subsystems in addition to the difficulties encountered by precise-orbit-determination at high altitudes. The mission assessment and definition phase (Phase-A) has recently been completed and this paper gives a concise overview over some system level results.

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“…This does not constitute a limitation for small spacecraft as the associated casualty area is small, and thus the location of the entry point is irrelevant. On the other hand, large spacecraft are characterized by large casualty area and the constraint on casualty risk can be met only if the re-entry occurs in low-density populated areas (Janovsky et al, 2004). As long as the action of drag does not completely circularise the orbit during the last phase of disposal, it is reasonable to assume that re-entry will occur in the proximity of the pericenter.…”

Section: Earth Re-entrymentioning

confidence: 99%