This paper reviews solar sail trajectory design and dynamics, attitude control, and structural dynamics. Within the area of orbital dynamics, methods relevant to transfer trajectory design and non-Keplerian orbit generation are discussed. Within the area of attitude control, different control strategies, including utilisation of solar radiation pressure and conventional actuators, are discussed. Finally, the methods of modelling structural dynamics during and after deployment are discussed, before considering possible future trends in developing of solar sailing missions.

Review on solar sail technology

Solar sailing technology challenges

Space debris is growing dramatically with the rapid pace of human exploration of space, which seriously threatens the safety of artificial spacecraft in orbit. Therefore, the active debris removal (ADR) is important. This review aims to review the ADR methods and to advance related research in the future. The current research and development status are clearly demonstrated by mapping knowledge domain and charts. In this paper, the latest research results are classified and summarized in detail from two aspects of space debris capture and removal. The scheme comparison and evaluation of all ADR methods are performed, and the applicable scopes of various methods are summarized. Each ADR method is scored using a cobweb evaluation model based on six indicators. Future development of ADR is discussed to promote further research interest.

Survey on research and development of on-orbit active debris removal methods

Summary The low power-conversion efficiency (PCE) and reproducibility reported to date for roll-to-roll (R2R)-fabricated perovskite solar cells (PSCs) results from difficulty in controlling perovskite film quality. Here, we present a systematic comparison of the hot-deposition method, which induces crystal-growth-driven (CGD) film formation, and the anti-solvent method, which induces nucleation-driven (ND) film formation, for one-step perovskite film formation. Perovskite films produced by the two methods show markedly different micro-structural and optoelectronic properties; however, PCEs of CGD-type PSCs are only marginally lower than those of ND-type PSCs. Importantly, the average performance of PSCs incorporating a CGD-type perovskite layer is independent of humidity during fabrication and displays improved stability and reproducibility, prompting further investigation of upscaling potential. R2R-produced PSCs on plastic substrate with four slot-die-coated functional layers show superior reproducibility and micro-structural, optoelectronic, and photovoltaic properties comparable with those of glass-based PSCs, indicating excellent promise for translation to a manufacturing process.

A Lab-to-Fab Study toward Roll-to-Roll Fabrication of Reproducible Perovskite Solar Cells under Ambient Room Conditions

An Advanced Composites-Based Solar Sail System for Interplanetary Small Satellite Missions

Gossamer-1: Mission concept and technology for a controlled deployment of gossamer spacecraft

Deorbitsail is a 3U Cubesat project that will launch, deploy, and support a large drag sail deorbiting payload. The flight payload sail system will deploy to 5 by 5 meters, increasing the frontal area of the spacecraft dramatically. A series of 4-by-4-meter sail deployments has been performed with a prototype of the proposed system. The prototype system tests included partial deployments in environmental chambers and full-scale deployment at ambient lab conditions. Design changes arising from testing of the sail system prototype are described in this paper. Engineering model construction is underway and the Deorbitsail launch will be in 2014. Deorbitsail is a European Commission 7th Framework Programme project with nine partner organizations. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Testing of the Deorbitsail drag sail subsystem

DE-ORBIT SAIL is a cubesat based drag sail for the de-orbiting of satellites in a low earth orbit It is scheduled for launch in late 2014 and will deploy a 25m² sail supported by deployable carbon fiber booms designed and manufactured by DLR This boom possesses a closed cross-section formed by two omega-shaped half-shells Due to this cross-sectional design the boom features a high torsional stiffness Thereby a high bending strength is achieved compared to other boom concepts for similar applications as the boom is less sensitive to flexural torsional buckling The boom concept selection is based on a detailed analysis of three types of deployable booms which differ in their cross-sectional design From this analysis the double-omega boom was determined as most suited for DE-ORBIT SAIL For the manufacturing of the booms a novel method is used where the booms are manufactured in an integral way in one piece

/pdf/the-boom-design-of-the-de-orbit-sail-satellite-4eonscq4iv.pdf

The Boom Design of the De-Orbit Sail Satellite

One of the key challenges for small satellites is packaging and reliable deployment of structural booms and arrays used for power, communication, and scientific instruments. The lack of reliable and efficient boom and membrane deployment concepts for small satellites is addressed in this work through a collaborative project 
between NASA and DLR. The paper provides a state of the art overview on existing spacecraft deployable appendages, the special requirements for small satellites, and initial concepts for deployable booms and arrays needed for various small satellite applications. The goal is to enhance deployable boom predictability and ground testability, develop designs that are tolerant of manufacturing imperfections, and incorporate simple and reliable deployment systems.

/pdf/advanced-deployable-structural-systems-for-small-satellites-4pg66bm6k9.pdf

Advanced Deployable Structural Systems for Small Satellites

Following the highly successful flight of the first interplanetary solar sail, JAXA's IKAROS, with missions to come such as NASA's NEAscout nanospacecraft solar sail and JAXA's Solar Power Sail (a solar-electric propelled mission to a Jupiter Trojan asteroid), and on the back-ground of the ever increasing power demand of GEO satellites now including all-electric spacecraft, there is renewed interest in large lightweight structures in space. Among these, deployable membrane or ‘gossamer’ structures can provide very large functional areas for innovative space applications which can be stowed into limited volumes of launch vehicle fairings as well as secondary payload launch slots, depending on the scale of the mission. Large area structures such as solar sails or high-power photovoltaic generators require a technology that allows their controlled and thereby safe deployment. Before using such technology for a dedicated science or commercial mission, it is necessary to demonstrate its reliability, i.e., TRL 6 or higher. A reliable technology that enables controlled deployment was developed in the Gossamer-1 solar sail project of the German Aerospace Center. It included the verification of its functionality with various laboratory tests to qualify the hardware for a first demonstration in low Earth orbit. We provide an overview of the Gossamer-1 hardware development and qualification campaign. The design is based on a crossed boom configuration with triangular sail segments. Using engineering models, all aspects of the deployment were tested under ambient environment. Several components were also subjected to environmental qualification testing. An innovative stowing and deployment strategy for a controlled deployment and the required mechanisms has been worked out. The tests conducted provide allow a mechanical characterization of this process, in particular the measurement of the deployment forces. The stowing and deployment strategy was verified by tests with an engineering qualification model of one (out of four) Gossamer-1 deployment units. According to a test-as-you-fly approach the tests included vibration testing, venting, thermal-vacuum testing and ambient deployment testing. In these tests the deployment strategy proved to be suitable as a controlled deployment for gossamer spacecraft. Deployments on system level were demonstrated to be robust and controllable. The Gossamer-1 solar sail membranes were also equipped with small thin-film photovoltaic arrays intended to supply the core spacecraft. In our follow-on project GoSolAr, the focus is now entirely on deployment systems for huge thin-film photovoltaic arrays. Based on the Gossamer-1 experience, deployment technology and qualification strategies, new technologies for the integration of thin-film photovoltaics are being developed and qualified for a first in-orbit technology demonstration within five years. Main objective is the further development of a deployment technology for a 25 m2gossamer solar power generator and a flexible photovoltaic membrane. GoSolAr enables a wider range of deployment concepts beyond solar sail optimized methods. It uses the S2TEP bus system developed at the Institute of Space Systems as part of the DLR satellite roadmap.

Martin Hillebrandt

Papers

Gossamer-1: Mission concept and technology for a controlled deployment of gossamer spacecraft

Testing of the Deorbitsail drag sail subsystem

The Boom Design of the De-Orbit Sail Satellite

Advanced Deployable Structural Systems for Small Satellites

Membrane Deployment Technology Development at DLR for Solar Sails and Large-Scale Photovoltaics