Communication Architecture and Technologies for Missions to Moon, Mars, and Beyond

Kulkarni, Tapan R.; Dharne, A.G.; Mortari, Daniele

doi:10.2514/6.2005-2778

Cited by 10 publications

(11 citation statements)

References 3 publications

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“…In the view of geometry, the constellation is a double-triangle: satellites at LL 3 , LL 4 and LL 5 can cover the Earth, and satellites at LL 2 , LL 4 and LL 5 can cover the Moon. Each two spacecrafts can link directly, and all of spacecrafts can communicate with the Earth (see Fig 3).…”

Section: Constellation Configuration Schemementioning

confidence: 99%

“…Bhasin et al, adopted libration point orbits in deep space communicating architecture developed for NASA's future exploration and science missions [4] . Klkarni at Earth-Moon, Sun-Earth and Sun-Mars libration points and a couple of relay satellites in a heliocentric earth orbit to support data and command communication for future space missions to moon, Mars and beyond [5] . Lee et al, proposed to place three satellites in LL 3 , LL 4 and LL 5 to substitute geostationary orbit [6,7] .…”

Section: Introductionmentioning

confidence: 99%

“…Klkarni at Earth-Moon, Sun-Earth and Sun-Mars libration points and a couple of relay satellites in a heliocentric earth orbit to support data and command communication for future space missions to moon, Mars and beyond [5] . Lee et al, proposed to place three satellites in LL 3 , LL 4 and LL 5 to substitute geostationary orbit [6,7] . The three satellites almost place in equilateral triangle and maintenance their relative position, which can cover all the Earth.…”

Section: Introductionmentioning

confidence: 99%

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A new constellation configuration scheme for communicating architecture in cislunar space

2006

57th International Astronautical Congress

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In this paper, a new constellation configuration scheme based on Non-Kepler orbits is proposed for the communicating architecture in the cislunar space. The constellation consists of four satellites which are respectively placed at the libration points L 3 , L 4 and L 5 , and the Halo orbit at the point L 2 of Earth-Moon system. The constellation is able to cover a majority of the Earth's and lunar surfaces, and to provide communication for any two points inside the cover region near real-timely (with time delay of 2-3s). The entire coverage rate by the constellation is calculated by the mesh method. Furthermore, the remainder coverage rate is also given when some of the satellites happen to fail. Then the cost of stationkeeping, launching and attitude control for the constellation is investigated. Finally, some aspects about communications, such as satellite links, delays, ground stations, and communication equipments, are surveyed preliminarily.

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Section: Constellation Configuration Schemementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A new constellation configuration scheme for communicating architecture in cislunar space

2006

57th International Astronautical Congress

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“…Many of these focused on the trade between space relay and direct-to-Earth station links 5,6,7 . Several others focused on top-level architecture based on relays at various destinations 8,9,10,11,12 . Much has changed in terms of microwave and optical technology since the publication of the referenced papers; Ka-band communication systems are being deployed, optical communication is being demonstrated, and spacecraft buses are becoming increasingly more functional and operational.…”

Section: Introductionmentioning

confidence: 99%

Design Concepts for a Small Space-Based GEO Satellite for Missions between Low Earth and Near Earth Orbits

Bhasin

Warner

Oleson

et al. 2014

SpaceOps 2014 Conference

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The main purpose of the Small Space-Based Geosynchronous Earth orbiting (GEO) satellite is to provide a space link to the user mission spacecraft for relaying data through ground networks to user Mission Control Centers. The Small Space Based Satellite (SSBS) will provide services comparable to those of a NASA Tracking Data Relay Satellite (TDRS) for the same type of links. The SSBS services will keep the user burden the same or lower than for TDRS and will support the same or higher data rates than those currently supported by TDRS. At present, TDRSS provides links and coverage below GEO; however, SSBS links and coverage capability to above GEO missions are being considered for the future, especially for Human Space Flight Missions (HSF). There is also a rising need for the capability to support high data rate links (exceeding 1 Gbps) for imaging applications. The communication payload on the SSBS will provide S/Ka-band single access links to the mission and a Ku-band link to the ground, with an optical communication payload as an option. To design the communication payload, various link budgets were analyzed and many possible operational scenarios examined. To reduce user burden, using a larger-sized antenna than is currently in use by TDRS was considered. Because of the SSBS design size, it was found that a SpaceX Falcon 9 rocket could deliver three SSBSs to GEO. This will greatly reduce the launch costs per satellite. Using electric propulsion was also evaluated versus using chemical propulsion; the power system size and time to orbit for various power systems were also considered. This paper will describe how the SSBS will meet future service requirements, concept of operations, and the design to meet NASA users' needs for below and above GEO missions. These users' needs not only address the observational mission requirements but also possible HSF missions to the year 2030. We will provide the trade-off analysis of the communication payload design in terms of the number of links looking above and below GEO; the detailed design of a GEO SSBS spacecraft bus and its accommodation of the communication payload, and a summary of the trade study that resulted in the selection of the Falcon 9 launch vehicle to deploy the SSBS and its impact on cost reductions per satellite. Nomenclature

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“…In 2008, NASA, JPL and the University of California jointly launched the ARTEMIS program, which was the first Earth-Moon libration point mission [2]. At present, the main applications of the libration point orbits focus on: 1) Using invariant manifolds to realize the low-energy interplanetary flight, namely interplanetary superhighway (IPS) [3]; 2) deployment of satellite constellation in orbits near libration points to achieve deep space communications [4]; 3) deployment of SFF in libration point periodic orbits to achieve long baseline interferometry, such as the Maxim, TPF and Datrwin; 4) research on rendezvous and docking between the satellites and the space stations in libration point orbits [5]. The theoretical basis of the latter two applications is the relative motion of the CR3BP.…”

Section: Introductionmentioning

confidence: 99%

Floquet-based design and control approach to spacecraft formation flying in libration point orbits

Zhang

Jin-hai

2011

Sci. China Technol. Sci.

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A method for spacecraft formation flying (SFF) design and control near libration point orbits was developed by making use of the Floquet theory for periodic orbits. Firstly, the Floquet theory used in libration point orbits was introduced and the coefficients of four Floquet periodic modes were proved to be nearly constant when the amplitude in z direction of earth-moon L1 halo orbits is less than 20000 km. On this basis, a configuration design approach to SFF in L1 halo orbits was proposed, and several types of special configurations were obtained with periodic mode 3 and mode 5 or mode 4 and mode 6. Then, in order to control the SFF configuration concisely, those coefficients of the 5 modes (except the stable one) must be kept constant. A stationkeeping method for SFF was developed, which controls 5 Floquet modes simultaneously. Finally, simulations showed that the Floquet-based approach of configuration design and control for SFF is effective, simple and convenient. The research may be of value for deep space explorations. circular restricted three body problem, spacecraft formation flying, Floquet modes, configuration design, formation control Citation: Meng Y H, Zhang Y D, Dai J H. Floquet-based design and control approach to spacecraft formation flying in libration point orbits. Sci China Tech Sci, 2011, 54: 758766,

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Communication Architecture and Technologies for Missions to Moon, Mars, and Beyond

Cited by 10 publications

References 3 publications

A new constellation configuration scheme for communicating architecture in cislunar space

A new constellation configuration scheme for communicating architecture in cislunar space

Design Concepts for a Small Space-Based GEO Satellite for Missions between Low Earth and Near Earth Orbits

Floquet-based design and control approach to spacecraft formation flying in libration point orbits

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