Vaccum Deployment and Testing of a 20M Solar Sail System

Lichodziejewski, David; Derbes, Billy; Sleight, David W.; Mann, Troy

doi:10.2514/6.2006-1705

Cited by 20 publications

(16 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As mentioned, a recent sail design possesses a characteristic acceleration of 0.58 mm/s 2 [34]. JAXA's IKAROS is the first mission to have flown using a sail as its only propulsive device, and NASA recently deployed the NanoSail-D2.…”

Section: Resultsmentioning

confidence: 99%

See 1 more Smart Citation

Generating Solar Sail Trajectories in the Earth-Moon System Using Augmented Finite-Difference Methods

Wawrzyniak¹,

Howell²

2011

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Using a solar sail, a spacecraft orbit can be offset from a central body such that the orbital plane is displaced from the gravitational center. Such a trajectory might be desirable for a single-spacecraft relay to support communications with an outpost at the lunar south pole. Although trajectory design within the context of the Earth-Moon restricted problem is advantageous for this problem, it is difficult to envision the design space for offset orbits. Numerical techniques to solve boundary value problems can be employed to understand this challenging dynamical regime. Numerical finite-difference schemes are simple to understand and implement. Two augmented finite-difference methods (FDMs) are developed and compared to a Hermite-Simpson collocation scheme. With 101 evenly spaced nodes, solutions from the FDM are locally accurate to within 1740 km. Other methods, such as collocation, offer more accurate solutions, but these gains are mitigated when solutions resulting from simple models are migrated to higherfidelity models. The primary purpose of using a simple, lower-fidelity, augmented finite-difference method is to quickly and easily generate accurate trajectories.

show abstract

Section: Resultsmentioning

confidence: 99%

“…[34]. The sunlight direction is expressed relative to the rotating frame and is a function of time, that is,…”

Section: System Dynamical Modelmentioning

confidence: 99%

Generating Solar Sail Trajectories in the Earth-Moon System Using Augmented Finite-Difference Methods

Wawrzyniak¹,

Howell²

2011

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…However such a value is well below the current technological capabilities. For example proposals for NASA's Millennium Space Technology 9 mission include solar sails that produce thrust on the order of 0.58 mm/s 2 to values as high as 1.70 mm/s 2 (Lichodzeijewski and Derbes, 2006). Moreover it is widely accepted (Macdonald et al, 2006;Ozimek et al, 2009) that for a near term solar sail technology a reasonable performance is a c = 0.5 − 1 mm/s 2 (β is on the order of 0.05 − 0.2), especially when non-Keplerian orbits and AEPs are considered (West, 2008).…”

Section: Power Radial Thrustmentioning

confidence: 99%

Artificial equilibrium points for a generalized sail in the circular restricted three-body problem

Aliasi

Mengali

Quarta

2011

Celest Mech Dyn Astr

View full text Add to dashboard Cite

This paper introduces a new approach to the study of artificial equilibrium points in the circular restricted three-body problem for propulsion systems with continuous and purely radial thrust. The propulsion system is described by means of a general mathematical model that encompasses the behavior of different systems like a solar sail, a magnetic sail and an electric sail. The proposed model is based on the choice of a coefficient related to the propulsion type and a performance parameter that quantifies the system technological complexity. The propulsion system is therefore referred to as generalized sail. The existence of artificial equilibrium points for a generalized sail is investigated. It is shown that three different families of equilibrium points exist, and their characteristic locus is described geometrically by varying the value of the performance parameter. The linear stability of the artificial points is also discussed.

show abstract

“…14,15 The first test configuration was a sail membrane configuration with four sail/net membrane quadrants attached to the rings on the booms. The sail membrane configuration was used to measure the static sail membrane shape using photogrammetry and vibration frequencies and mode shapes using laser vibrometry under a combined simulated solar flux loading and gravity loading condition.…”

Section: -Meter Solar Sail Ground Test and Structural Analysismentioning

confidence: 99%

“…7,8,12,13,14,15 In phase 1 of the program, a test plan was created consisting of solar sail component, sub-system, and sub-scale system ground tests that simulated the vacuum and thermal environments of space with the limitation of being tested within Earth's gravitational field. In phase 2 of the program, boom component test articles of the solar sail were initially tested to determine material and section properties.…”

Section: Introductionmentioning

confidence: 99%

Structural Analysis and Test Comparison of a 20-Meter Inflation-Deployed Solar Sail

Sleight¹,

Mann²,

Lichodziejewski³

et al. 2006

47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials ConferenceSelf Cite

12
0
2
0

View full text Add to dashboard Cite

Vaccum Deployment and Testing of a 20M Solar Sail System

Cited by 20 publications

References 8 publications

Generating Solar Sail Trajectories in the Earth-Moon System Using Augmented Finite-Difference Methods

Generating Solar Sail Trajectories in the Earth-Moon System Using Augmented Finite-Difference Methods

Artificial equilibrium points for a generalized sail in the circular restricted three-body problem

Structural Analysis and Test Comparison of a 20-Meter Inflation-Deployed Solar Sail

Contact Info

Product

Resources

About