Fundamentals of the LISA stable flight formation

Dhurandhar, S.; Nayak, K. Rajesh; Koshti, Sucheta; Vinet, J.-Y.

doi:10.1088/0264-9381/22/3/002

Cited by 89 publications

(129 citation statements)

References 4 publications

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“…The movement of the LISA constellation has been discussed with a two-body model [2,5,[9][10][11][12]. Two-body motion implies that only the effect of the Sun's gravity is considered, and thus it differs from reality, but can give adequate starting orbits for optimization.…”

Section: The Results Of Orbit Optimizationmentioning

confidence: 99%

“…In 1985, Faller et al [3] presented the concept of detecting gravitational waves by using laser ranging in space, and Vincent et al [4] studied the orbital mechanics for the gravitational wave experiment in 1987, then after the LISA concept came into being, Folkner et al [5], Cutler [6], Hughes [7], Hechler et al [8], Dhurandhar et al [9], Sweetser [10] and Nayak et al [11] investigated the LISA constellation from the viewpoint of science and spaceflight mission, respectively. Because of the complexity of the space environment in which the LISA constellation moves, and the extremely high stability of the constellation required in the space project, further advanced research is expected.…”

Section: Co-orbital Restricted Problem Orbit Design Orbit Optimizatmentioning

confidence: 99%

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Orbit design for the Laser Interferometer Space Antenna (LISA)

Xia

Heinzel

et al. 2010

Sci. China Phys. Mech. Astron.

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The Laser Interferometer Space Antenna (LISA) is a joint ESA-NASA mission for detecting low-frequency gravitational waves in the frequency range from 0.1 mHz to 1 Hz, by using accurate laser interferometry between three spacecrafts, which will be launched around 2018 and one year later reach their operational orbits around the Sun. In order to operate successfully, it is crucial for the constellation of the three spacecrafts to have extremely high stability. Based on the study of operational orbits for a 2015 launch, we design the operational orbits of beginning epoch on 2019-03-01, and introduce the method of orbit design and optimization. We design the orbits of the transfer from Earth to the operational orbits, including launch phase and separation phase; furthermore, the relationship between energy requirement and flight time of these two orbit phases is investigated. Finally, an example of the whole orbit design is presented. co-orbital restricted problem, orbit design, orbit optimization, launch energyThe Laser Interferometer Space Antenna (LISA) is a joint ESA-NASA mission for detecting low-frequency gravitational waves in the frequency range from 0.1 mHz to 1 Hz. Three spacecrafts will be launched around 2018, and reach their operational orbits around the Sun after 14 months. Observation will last 5 to 10 years.As shown in Figure 1, the three spacecrafts form an equilateral triangle with an arm-length (side length) of around 5×10 6 km. The center of the constellation moves on an Earth-like orbit around the sun, trailing 20° behind the Earth. The angle between the direction from the constellation center to the Sun and the constellation plane is about 60°. Distance variations between the spacecraft will be measured by laser interferometry to detect gravitational waves. In order to avoid additional complications in the challenging interferometry, in order for LISA to operate successfully, it is crucial that the constellation of the three spacecrafts has extremely high stability. More stable constellation makes simplifications in the hardware realizationDue to the combined effect of the eccentricity of the spacecraft orbit and the gravity of the other bodies in the solar system including the Earth, all of the arm length, l, the internal angles of the constellation, β and the trailing angle behind the Earth, θ vary continuously, causing relative velocities between the spacecraft, v r , as an indicator of the Figure 1 LISA constellation moving around the Sun.

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Section: The Results Of Orbit Optimizationmentioning

confidence: 99%

Section: Co-orbital Restricted Problem Orbit Design Orbit Optimizatmentioning

confidence: 99%

Orbit design for the Laser Interferometer Space Antenna (LISA)

Xia

Heinzel

et al. 2010

Sci. China Phys. Mech. Astron.

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“…118 -123,137,138 For eLISA/NGO, we followed the analytical procedure of Dhurandhar et al 123 [see Sec. 7.1] in making our initial choice of the initial conditions in Ref.…”

Section: Numerical Orbit Design and Orbit Optimization For Elisa/ngomentioning

confidence: 99%

Gravitational wave detection in space

2017

One Hundred Years of General Relativity

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“…We shall later see, in section 4.2, how a different, more convenient initial condition can be chosen. Moreover, for a rigid, polygonal constellation, the distance of the S/C from the origin must be constant, say h, so that we obtain [8] …”

Section: Zeroth-order Approximationmentioning

confidence: 99%

Optimizing the Earth–LISA ‘rendezvous’

Marchi¹,

Pucacco²,

Bassan³

2012

Class. Quantum Grav.

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We present a general survey of heliocentric LISA orbits, hoping that it might help in the exercise of rescoping the mission. We try to semi-analytically optimize the orbital parameters in order to minimize the disturbances coming from the Earth-LISA interaction. In a set of numerical simulations, we include non-autonomous perturbations and provide an estimate of Doppler shift and breathing as a function of the trailing angle.

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Fundamentals of the LISA stable flight formation

Cited by 89 publications

References 4 publications

Orbit design for the Laser Interferometer Space Antenna (LISA)

Orbit design for the Laser Interferometer Space Antenna (LISA)

Gravitational wave detection in space

Optimizing the Earth–LISA ‘rendezvous’

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