Ground-based Surveys and the AsteroidFinder Mission

An overview of the historical development of planet discoveries and minor planet surveys is presented, with a focus on presently active ground-based surveys, significant amateur contributions, and planned space-based surveys and NEO detection capabilities. A keystone in the near-future development of asteroid surveys is the DLR R&D AsteroidFinder mission planned to launch in late 2014, and intended to extend the area covered from the nighttime-accesible elongations >60° down towards 30° angular distance to the Sun, without north-south hemisphere bias. Abstract as given in the workshop programme: Surveys sol et mission AsteroidFinde

Verification Testing of the Gossamer-1 Deployment Demonstrator

Gossamer structures for innovative space applications, such as solar sails, require a technology that allows their controlled and thereby safe deployment. Before employing such technology for a dedicated science mission, it is necessary, to demonstrate its reliability with a Technology Readiness Level of six or higher. The aim of the presented work is to provide a reliable technology that enables the controlled deployment and verification of its functionality with various laboratory tests to qualify the hardware for a first demonstration in low Earth orbit. The development was made in the Gossamer-1 project of the German Aerospace Center. This presentation provides an overview of the Gossamer-1 hardware development. The design is based on a crossed boom configuration with triangular sail segments. Employing 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 are described. The tests conducted provide insight into the deployment process and allow a mechanical characterization of this process, in particular the measurement of the deployment forces. Deployment on system level could partially be demonstrated to be robust and controllable. The deployment technology is on Technology Readiness Level four approaching level five, with a qualification model for environmental testing currently being built

Apophis and the Waves - The need for Frequency Coordination and Radio Amateur and University Community Support Before, During, After Close Approach

On Earth most definitely and likely also around the Moon, in the few days centred on Friday, April 13th, 2029, 21:45 UT, every informed and curious naked eye, lens, mirror and dish within the horizon will be aimed at (99942) Apophis for an once-in-a-1000 years opportunity of scientific observations. Most will watch or listen. Many will transmit. Some will get in the way of others. And a few will blast it with all they can - for the best of science. We intend to start the discussion to include the public in the unique observation of Apophis, in particular focusing on the radio amateur community and the need for world-wide coordination to avoid mutual interference

Performance analysis and mission applications of a new solar sail concept based on crossed booms with tip-deployed membranes

For precursor solar sail activities a strategy for a controlled deployment of large membranes was developed based on a combination of zig-zag folding and coiling of triangular sail segments spanned between crossed booms. This strategy required four autonomous deployment units that were jettisoned after the deployment is completed. In order to reduce the complexity of the system an adaptation of that deployment strategy is investigated. A baseline design for the deployment mechanisms is established that allows the deployment actuation from a central bus system in order to reduce the complexity of the system. The mass of such a sail craft will be slightly increased but its performance is still be reasonable for first solar sail missions. The presented design will be demonstrated on breadboard level showing the feasibility of the deployment strategy. The characteristic acceleration will be evaluated and compared to the requirements of certain proposed solar sail missions

Soil to Sail - Asteroid Landers on Near-Term Sailcraft as an Evolution of the GOSSAMER Small Spacecraft Solar Sail Concept for In-Situ Characterization

Any effort which intends to physically interact with specific asteroids requires understanding at least of the composition and multi-scale structure of the surface layers, sometimes also of the interior. Therefore, it is necessary first to characterize each target object sufficiently by a precursor mission to design the mission which then interacts with the object. In small solar system body (SSSB) science missions, this trend towards landing and sample-return missions is most apparent. It also has led to much interest in MASCOT-like landing modules and instrument carriers. They integrate at the instrument level to their mothership and by their size are compatible even with small interplanetary missions. The DLR-ESTEC GOSSAMER Roadmap NEA Science Working Groups‘ studies identified Multiple NEA Rendezvous (MNR) as one of the space science missions only feasible with solar sail propulsion. The parallel Solar Polar Orbiter (SPO) study showed the ability to access any inclination and a wide range of heliocentric distances. It used a separable payload module conducting the SPO mission after delivery by sail to the proper orbit. The Displaced L1 (DL1), spaceweather early warning mission study, outlined a very lightweight sailcraft operating close to Earth, where all objects of interest to planetary defence must pass. These and many other studies outline the unique capability of solar sails to provide access to all SSSB, at least within the orbit of Jupiter. Since the original MNR study, significant progress has been made to explore the performance envelope of near-term solar sails for multiple NEA rendezvous. However, although it is comparatively easy for solar sails to reach and rendezvous with objects in any inclination and in the complete range of semi-major axis and eccentricity relevant to NEOs and PHOs, it remains notoriously difficult for sailcraft to interact physically with a SSSB target object as e.g. the HAYABUSA missions do. The German Aerospace Center, DLR, recently brought the GOSSAMER solar sail deployment technology to qualification status in the GOSSAMER-1 project and continues the development of closely related technologies for very large deployable membrane-based photovoltaic arrays in the GOSOLAR project, on which we report separately. We expand the philosophy of the GOSSAMER solar sail concept of efficient multiple sub-spacecraft integration to also include landers for one-way in-situ investigations and sample-return missions. These are equally useful for planetary defence scenarios, SSSB science and NEO utilization. We outline the technological concept used to complete such missions and the synergetic integration and operation of sail and lander. We similarly extend the philosophy of MASCOT and use its characteristic features as well as the concept of Constraints-Driven Engineering for a wider range of operations. For example, the MASCOT Mobility hopping mechanism has already been adapted to the specific needs of MASCOT2. Utilizing sensors as well as predictions, those actuators could in a further development be used to implement anti-bouncing control schemes, by counteracting with the lander‘s rotation. Furthermore by introducing sudden jerk into the lander by utilization of the mobility, layers of loose regolith can be swirled up for sampling

Probes to the Inferior Planets - a New Dawn for NEO and IEO Detection Technology Demonstration from Heliocentric Orbits Interior to the Earth’s?

With the launch of MESSENGER and Venus Express, a new wave of exploration of the inner solar system has begun. Noting the growing number of probes to the inner solar system, it is proposed to connect the expertise of the respective spacecraft teams and the NEO and IEO survey community to best utilize the extended cruise phases and to provide additional data return in support of pure science as well as planetary defence. Several missions to Venus and Mercury are planned to follow in this decade. Increased interest in the inferior planets is accompanied by several missions designed to study the Sun and the interplanetary medium (IPM) from a position near or in Earth orbit, such as the STEREO probes and SDO. These augment established solar observation capabilities at the Sun-Earth L1 Lagrangian point such as the SOHO spacecraft. Thus, three distinct classes of spacecraft operate or observe interior to Earth's orbit. All these spacecraft carry powerful multispectral cameras optimized for their respective primary targets. MESSENGER is scheduled to end its six-year interplanetary cruise in March 2011 to enter Mercury orbit, but a similarly extended cruise with several gravity-assists awaits the European Mercury mission BepiColombo. Unfortunately, the automatic abort of the orbit insertion manoeuvre has also left Akatsuki (a.k.a. Venus Climate Orbiter (VCO), Planet-C) stranded in heliocentric orbit. After an unintended fly-by, the probe will catch up with Venus in approximately six years. Meanwhile, it stays mostly interior to Venus in a planet-leading orbit. In addition to the study of comets and their interaction with the IPM, observations of small bodies akin to those carried out by outer solar system probes are occasionally attempted with the equipment available. The study of structures in the interplanetary dust (IPD) cloud has been a science objective during the cruise phase of the Japanese Venus probe Akatsuki from Earth to Venus. IPD observations in the astronomical H-band (1.65 µm) are supported by its IR2 camera down to 1.5 µW/m2sr in single 2 minute exposures. In the same setting, point sources of 13 mag can be detected. Obviously, a number of large asteroids exceed this threshold. The Earthguard-1 study, completed in 2003 by the DLR Institute of Planetary Research and Kayser-Threde under ESA contract, proposed a dedicated steerable Ø20...35 cm telescope and CCD camera payload on a probe to the inner solar system, to detect Near-Earth and Inner-Earth Objects (NEOs, IEOs) in favourable opposition geometry. A ride-share on a Mercury orbiter and a dedicated low-thrust propulsion spacecraft to a heliocentric 0.5 AU orbit were studied. A similar-sized telescope is presently being developed for the AsteroidFinder satellite of DLR. Therefore, the technical feasibility of a number of asteroid observation scenarios involving spacecraft and targets interior to Earth’s orbit is assessed based on the latest available spacecraft information and asteroid population models. A rough estimate of the required effort in terms of ground-based spacecraft operations and on-board resources is given for selected representative scenarios

This is what a MASCOT can do for you - at Apophis

In a similarly brief event some 10½ years before Apophis' fly-by on Friday, April 13th, 2029, the Mobile Asteroid Surface Scout, MASCOT, successfully completed its 17-hours mission on the ~km-sized C-type potentially hazardous asteroid (162173) Ryugu. Investigating the surface and its thermal properties, looking for a magnetic field, and imaging the stark landscapes of this dark rubble pile, it contributed valuable close-up information before the surface sampling by its mothership, HAYABUSA2. We outline the capabilities of the asteroid nanolanders MASCOT, MASCOT2, and the options for optimized MASCOT@Apophis designs in particular for small spacecraft rendezvous missions to Apophis

Sailing at the brink - The no-limits of near-/now-term-technology solar sails and SEP spacecraft in (multiple) NEO rendezvous

Near-Earth object (NEO) in-situ exploration can provide invaluable information for science, possible future deflection actions and resource utilisation. This is only possible with space missions which approach the asteroid from its vicinity, i.e. rendezvous. This paper explores the use of solar sailing as means of propulsion for NEO rendezvous missions. Given the current state of sail technology, we search for multiple rendezvous missions of up to ten years and characteristic acceleration of up to 0.10 mm/s2. Using a tree-search technique and subsequent trajectory optimisation, we find numerous options of up to three NEO encounters in the launch window 2019-2027. In addition, we explore steerable and throttleable low-thrust (e.g. solar-electric) rendezvous to a particular group of NEOs, the Taurid swarm. We show that an acceleration of 0.23 mm/s2 would suffice for a rendezvous in approximately 2000 days, while shorter transfers are available as the acceleration increases. Finally, we show low-thrust options (0.3 mm/s2) to the fictitious asteroid 2019 PDC, as part of an asteroid deflection exercise

Low-thrust: the fast & flexible path to Apophis

By the time of Apophis' fly-by on Friday, April 13th, 2029, more satellites than have ever been launched since the beginning of the space age to this day will reach low Earth orbit (LEO). Almost all of them will be microsatellites of less than ~250 kg equipped with solar-electric propulsion (SEP). We propose the use of already created low-thrust trajectories to Apophis to help advance design trades in the early study phases of missions to Apophis. It appears that small spacecraft missions could benefit from solar-electric or sail propulsion

Special Testing and Test Strategies for Unique Space Hardware Developments

Hardware developments for new and innovative space applications require extensive testing in order to demonstrate the functionality under the expected environmental conditions. Within several projects the German Aerospace Center (DLR), Institute of Space Systems used its test capabilities for unique tests campaigns that went beyond standard qualification testing