Cubesat Application for Planetary Entry (CAPE) Missions: Micro-Reentry Capsule (MIRCA)

The Cubesat Application for Planetary Entry Missions (CAPE) concept describes a high-performing Cubesat system which includes a propulsion module and miniaturized technologies capable of surviving atmospheric entry heating, while reliably transmitting scientific and engineering data. The Micro Return Capsule (MIRCA) is CAPEs first planetary entry probe flight prototype. Within this context, this paper briefly describes CAPEs configuration and typical operational scenario, and summarizes ongoing work on the design and basic aerodynamic characteristics of the prototype MIRCA vehicle. CAPE not only opens the door to new planetary mission capabilities, it also offers relatively low-cost opportunities especially suitable to university participation

The Use of NASA GSFC Modular, Reconfigurable, Rapid (MR^2) Small Satellite for the Measurement of Greenhouse Gases

The Small Rocket/Spacecraft Technology (SMART) is an existing microsatellite prototype bus that provides the ability to accommodate focused science (and technology validation) missions without the need to spend large resources typical of highperforming spacecraft. SMART represents the sum value of GSFCs long tradition of developing systems that find efficient application in a series of missions, exemplified by two successful major programs: the Multi-mission Modular Spacecraft (MMS), and the Small Explorer Program (SMEX). SMART is based on an evolutionary architecture based drawn from these two experiences: the Modular, Reconfigurable, Rapid (MR2) architecture. This paper shows a SMART-derivative spacecraft (with re-sized structure) used to accommodate the Abundance of Methane via Interferometric Glint Observation (AMIGO) instrument. The principal objective of AMIGO is to map and quantify the abundance of the major greenhouse gases (particularly methane) and to identify and quantify their sources and sinks on a global basis. In addition, a Laser retro-reflector instrument of opportunity is included, to add to the constellation of spacecraft relevant to the definition and regular update of the International Terrestrial Reference Frame (ITRF)

Resin-Impregnated Carbon Ablator: A New Ablative Material for Hyperbolic Entry Speeds

Ablative materials are required to protect a space vehicle from the extreme temperatures encountered during the most demanding (hyperbolic) atmospheric entry velocities, either for probes launched toward other celestial bodies, or coming back to Earth from deep space missions. To that effect, the resin-impregnated carbon ablator (RICA) is a high-temperature carbon/phenolic ablative thermal protection system (TPS) material designed to use modern and commercially viable components in its manufacture. Heritage carbon/phenolic ablators intended for this use rely on materials that are no longer in production (i.e., Galileo, Pioneer Venus); hence the development of alternatives such as RICA is necessary for future NASA planetary entry and Earth re-entry missions. RICA s capabilities were initially measured in air for Earth re-entry applications, where it was exposed to a heat flux of 14 MW/sq m for 22 seconds. Methane tests were also carried out for potential application in Saturn s moon Titan, with a nominal heat flux of 1.4 MW/sq m for up to 478 seconds. Three slightly different material formulations were manufactured and subsequently tested at the Plasma Wind Tunnel of the University of Stuttgart in Germany (PWK1) in the summer and fall of 2010. The TPS integrity was well preserved in most cases, and results show great promise

Linking and Combining Distributed Operations Facilities using NASA's "GMSEC" Systems Architectures

NASA's Goddard Mission Services Evolution Center (GMSEC) ground system architecture has been in development since late 2001, has successfully supported eight orbiting satellites and is being applied to many of NASA's future missions. GMSEC can be considered an event-driven service-oriented architecture built around a publish/subscribe message bus middleware. This paper briefly discusses the GMSEC technical approaches which have led to significant cost savings and risk reduction for NASA missions operated at the Goddard Space Flight Center (GSFC). The paper then focuses on the development and operational impacts of extending the architecture across multiple mission operations facilities

Mission Design und Technologie für ein Titan Aerobot Ballon-System (TABS)

An alternative implementation to a Titan aerobot mission is presented that uses tried (by similarity) and relatively low-risk methods for designing and deploying a Hydrogen-filled balloon in Titan’s atmosphere. This is a departure from the current consensus approach of using a Montgolfier (hot air) balloon for in-situ exploration. It was demonstrated that this mission implementation is not only feasible, but also presents a risk advantage in the deployment (the most critical part of operations) of this system, without the need for a complicated scheme of lines and ties that can snatch or rupture the material. With on-board Hydrogen, and an auxiliary tank for replenishment during a six-month mission, the Titan Aerobot Balloon System (TABS) is capable of gathering up to 892 Mbits of data per day, that includes optical, spectroscopy, and atmospheric remote and in-situ sensing. This data is transmitted directly to Earth with a steerable 1-meter parabolic dish antenna. During the course of formulating mission enablers, a new Thermal Protection System (TPS) material was also designed, manufactured, and tested at the Institut für Raumfahrtsysteme of the Universität Stuttgart. This new carbon/Phenolic ablator was successfully demonstrated at the IRS’ Plasma Wind tunnel. Two out of three sample types proved to be viable ablators, with no sign of delamination, and with thermal properties that enable high-speed entry not only in Titan’s atmosphere, but also for Earth re-entry and planetary sample return missions. TABS entry vehicle is 628 kg with a total floating mass including gondola and buoyant system of 242 kg (both numbers include a 30% contingency). TABS can be launched in a Space X Falcon 9 rocket, with a 30% performance margin (on top of the 30% contingency). There is enough mass and volume reserve left in the launch vehicle for co-manifested spacecraft, so international cooperation is not only built-into TABS, the flight can also accommodate the addition of separate contributions with the potential for individual partner cost-sharing and savings.Diese Arbeit präsentiert eine Variante einer robotischen Raumsonde zur Erkundung des Saturnmondes Titan unter Nutzung von Analogie- und Risikominderungsmethoden zum Entwurf eines wasserstoffgefüllten Ballons, der sich in Titans Atmospäre entfaltet. Dies ist ein Umdenken, weg vom gegenwärtig akzeptierten Vorgehen, wo ein Heißluftballon (Montgolfiere) zur In-Situ-Erforschung verwendet wird. Es hat sich gezeigt, dass die Umsetzung einer solchen Mission nicht nur durchführbar ist, sondern auch Vorteile durch Risikoverringerung während der Entfaltungsphase bietet – dem kritischsten Teil des Ablaufes. Das System kommt dabei ohne ein kompliziertes Geflecht aus Leinen und Verbindungen aus, die reißen und andere Komponenten oder Materialien beschädigen können. Mit an Bord gelagertem Wasserstoff sowie einem Hilfstank zum Nachfüllen während einer sechsmonatigen Mission ist TABS (Titan Aerobot Balloon System) in der Lage bis zu 892 MBits an Daten pro Tag zu sammeln (aus optischer, spektroskopischer und atmospärischer Fernerkundung sowie aus In-Situ-Messungen). Diese Daten werden mittels einer steuerbaren 1 m Parabolantenne direkt zur Erde gesendet. Im Verlauf der Arbeit wurde ein neues Karbon-Phenol-Hitzeschildmaterial am Institut für Raumfahrtsysteme (IRS) der Universität Stuttgart entwickelt, gefertigt und getestet und daraufhin erfolgreich im IRS-Plasmawindkanal validiert. Zwei der drei untersuchten Konzepte erwiesen sich als realisierbar – ohne Anzeichen von Ablösung und mit Thermaleigenschaften, die nicht nur einen atmosphärischen Hochgeschwindigkeitseintritt am Titan ermöglichen sondern auch einen Wiedereintritt an der Erde sowie zukünftige planetare Probenrückführungsmissionen. Das TABS-Eintrittsfahrzeug hat eine Masse von 628 kg mit einer Masse des Ballonfahrzeuges von 242 kg inklusive Gondel und Auftriebskörper (jeweils einschließlich 30% Sicherheitsreserve). Ein Start von TABS an der Spitze der SpaceX Falcon 9 Rakete bietet einen Leistungsspielraum von 30% zusätzlich zur bereits vorhandenen 30% Sicherheitsreserve. Die verfügbare Masse- und Volumenreserve eröffnet daher die Möglichkeit eines kombinierten Starts mit weiteren Raumsonden/Satelliten. Internationale Zusammenarbeit ist also nicht nur innerhalb des TABS-Projektes durchführbar, sondern auch im Rahmen der Kostenteilung eines gemeinsamen Starts

Cubesat Application for Planetary Entry (CAPE) Missions: Micro-Return Capsule (MIRCA)

The Cubesat Application for Planetary Entry Missions (CAPE) concept describes a high-performing Cubesat system which includes a propulsion module and miniaturized technologies capable of surviving atmospheric entry heating, while reliably transmitting scientific and engineering data. The Micro Return Capsule (MIRCA) is CAPE’s first planetary entry probe flight prototype. Within this context, this paper briefly describes CAPE’s configuration and typical operational scenario, and summarizes ongoing work on the design and basic aerodynamic characteristics of the prototype MIRCA vehicle. CAPE not only opens the door to new planetary mission capabilities, it also offers relatively low-cost opportunities especially suitable to university participation. In broad terms, CAPE consists of two main functional components: the “service module” (SM), and “CAPE’s entry probe” (CEP). The SM contains the subsystems necessary to support vehicle targeting (propulsion, ACS, computer, power) and the communications capability to relay data from the CEP probe to an orbiting “mother-ship”. The CEP itself carries the scientific instrumentation capable of measuring atmospheric properties (such as density, temperature, composition), and embedded engineering sensors for Entry, Descent, and Landing (EDL). The first flight of MIRCA was successfully completed on 10 October 2015 as a “piggy-back” payload onboard a NASA stratospheric balloon launched from Ft. Sumner, NM

The Voyage of Exploration and Discovery: Earth-Moon, Mars and Beyond

This viewgraph is a printout of a presentation which originally contained multimedia components. The presentation summarizes the accomplishments of the Cassini-Huygens mission, with numerous images and video clips of Saturn, its rings, and its moons. The presentation also summarizes a feasibility analysis of the Neptune-Triton Explorer (NExTEP)

Planetary Entry Vehicle Prototyping Using Cubesats (or How to Progress on a Shoe-String Budget and Hope to Play with the Big Guys): The Micro Return Capsule (MIRCA)

Imagine standing on the surface of an alien planet or satellite. High in the sky, a soft breeze is interrupted by the whistling sound of a tiny probe sent from Earth to study the atmosphere, or to land on some high-value target on the surface. Now imagine that this probe is followed by a dozen others, all entering in distributed locations throughout the geographic landscape. These probes are systematically and methodically being released from an orbiting spacecraft, perhaps having arrived months in advance. Or maybe the probes themselves are released systematically months in advance by and approaching mother-ship. Although probes have been sent to celestial neighbors before, what is unique is that these new vehicles had their genesis on the highly popular Cubesat specification My dream is to make spaceflight so mundane, we can actually routinely leave the bounds of our planet to explore en masse our solar system. For that, we must create systems that allow us to bring space exploration within the realm of our everyday lives. No longer exquisite systems but just good enough, where failure is an option and a new opportunity

Cubesat Application for Planetary Entry Missions (CAPE)

The Cubesat Application for Planetary Entry Missions (CAPE) concept describes a high-performing Cubesat system which includes a propulsion module and miniaturized technologies capable of surviving atmospheric entry heating, while reliably transmitting scientific and engineering data. The Micro Return Capsule 2 (MIRKA2) is CAPEs first planetary entry probe flight prototype. Within this context, this paper summarizes CAPEs configuration and typical operational scenario. It also summarizes MIRKA2s design and basic aerodynamic characteristics, and discusses potential challenges drawn from the experience of missions such as Stardust and MUSES-C. CAPE not only opens the door to new planetary mission capabilities, it also offers relatively low-cost opportunities especially suitable to university participation

Small Rocket/Spacecraft Technology (SMART) Platform

The NASA Goddard Space Flight Center (GSFC) and the Department of Defense Operationally Responsive Space (ORS) Office are exercising a multi-year collaborative agreement focused on a redefinition of the way space missions are designed and implemented. A much faster, leaner and effective approach to space flight requires the concerted effort of a multi-agency team tasked with developing the building blocks, both programmatically and technologically, to ultimately achieve flights within 7-days from mission call-up. For NASA, rapid mission implementations represent an opportunity to find creative ways for reducing mission life-cycle times with the resulting savings in cost. This in tum enables a class of missions catering to a broader audience of science participants, from universities to private and national laboratory researchers. To that end, the SMART (Small Rocket/Spacecraft Technology) micro-spacecraft prototype demonstrates an advanced avionics system with integrated GPS capability, high-speed plug-and-playable interfaces, legacy interfaces, inertial navigation, a modular reconfigurable structure, tunable thermal technology, and a number of instruments for environmental and optical sensing. Although SMART was first launched inside a sounding rocket, it is designed as a free-flyer