Equilibria near asteroids for solar sails with reflection control devices
- 234 Downloads
Solar sails are well-suited for long-term, multiple-asteroid missions. The dynamics of solar sails near an asteroid have not yet been studied in detail. In this paper, out-of-plane artificial equilibria in a Sun-asteroid rotating frame and hovering points in a body-fixed rotating frame are studied (using a solar sail equipped with reflection control devices). First, the dynamics and the stability of out-of-plane artificial equilibria are studied as an elliptical restricted three body problem. Next, the body-fixed hovering problem is discussed as a two-body problem. Hovering flight is only possible for certain values of the latitude of the asteroid’s orbit. In addition, the feasible range of latitudes is determined for each landmark on the asteroid’s surface. The influence of the sail lightness number on the feasible range is also illustrated. Several special families of hovering points are discussed. These points include points above the equator and poles and points with an altitude equal to the radius of the synchronous orbit. In both of these types of problems, the solar sail (equipped with reflection control devices) can equilibrate over a large range of locations.
KeywordsSolar sail Reflection Control Device Asteroid Artificial equilibrium Body-fixed hovering
This work has been supported by the National Natural Science Foundation of China (No. 11272004 and No. 41174025).
- Curtis, S., Mica, J., Nuth, J., Marr, G., Rilee, M., Bhat, M.: Autonomous nano-technology swarm. In: 51st International Astronautical Congress, Rio de Janeiro, Brazil (2000). Paper 00-Q.5.08Google Scholar
- Curtis, S.A., Rilee, M.L., Clark, P.E., Marr, G.C.: Use of swarm intelligence in spacecraft constellations for the resource exploration of the asteroid belt. In: Proceedings of the 3rd International Workshop on Satellite Constellations and Formation Flying, Pisa, Italy (2003)Google Scholar
- Dachwald, B., Boehnhardt, H., et al.: Gossamer roadmap technology reference study for a multiple NEO rendezvous mission. In: Macdonald, M. (ed.) Advances in Solar Sailing. Springer Praxis Books: Astronautical Engineering, Vol. 1, Germany, vol. 1, pp. 211–216 (2013). 3rd International Symposium on Solar Sailing, Glasgow, United KingdomGoogle Scholar
- Heiligers, J., Ceriotti, M., McInnes, C.R., Biggs, J.D.: Mission analysis and systems design of a near-term and far-term pole-sitter mission. In: 1st IAA Conference on Dynamics and Control of Space Systems, Porto (2012)Google Scholar
- Mu, J.S., Gong, S.P., Li, J.F.: Coupled control of reflectivity modulated solar sail for GeoSail formation flying. J. Guid. Control Dyn. (2014). doi: 10.2514/1.G000117
- Zhukov, A.N., Lebedev, V.N.: Variational problem of transfer between heliocentric circular orbits by means of a solar sail. Cosm. Res. 2, 41–44 (1964)Google Scholar