Heliogyro Orbital Control Authority

Jeannette Heiligers, D. Guerrant, D Lawrence

Research output: Chapter in Book/Conference proceedings/Edited volumeConference contributionScientificpeer-review

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Abstract

Solar sailing is an elegant form of space propulsion that reflects solar photons to produce thrust. Different sail configurations exist, including a traditional flat sail (either square- or disc-shaped) and a heliogyro, which divides the sail membrane into a number of long, slender blades, analogous to a helicopter rotor. The magnitude and direction of the induced thrust force depends on the sail’s attitude with respect to the Sun, i.e. on the cone angle. At each cone angle, a flat sail can only generate force of particular magnitude and direction, while this paper demonstrates that a heliogyro can arbitrarily reduce the magnitude of the thrust vector through the additional control of pitching the blades. This gives the heliogyro more force control authority, which is exploited in this paper for orbital control. A linear-quadratic regulator feedback controller is used to quantify the maximum error in the injection state vector of a solar sail Sun-Earth sub-L1 halo orbit from which the nominal orbit can still be recovered. The conclusion is that approximately an order of magnitude larger error in position and velocity can be accommodated, demonstrating superior capabilities of the heliogyro over a flat sail for orbital control.
Original languageEnglish
Title of host publicationProceedings of the 25th International Symposium on Space Flight Dynamics
Subtitle of host publicationMunich, Germany
Number of pages26
Publication statusPublished - 2015
Event25th international symposium on space flight dynamics - Munich, Germany
Duration: 19 Oct 201523 Oct 2015
Conference number: 25

Conference

Conference25th international symposium on space flight dynamics
Abbreviated title ISSFD 2015
CountryGermany
CityMunich
Period19/10/1523/10/15

Keywords

  • heliogyro
  • solar sail
  • sub-L1 halo orbit
  • orbital control

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