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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 19 records
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NASA NTRS1974

Orbit design concepts for Jupiter orbiter missions

Advanced mission and orbit planning efforts are currently in progress for a Mariner-class Jupiter orbiter. Baseline spacecraft and orbit design criteria are the goals of a NASA effort to define such a mission. Orbit design concepts that have been discovered during the early stages of mission planning are both challenging and exciting. A description is given of several such concepts that may greatly increase the flexibility and scientific return of orbiters designed for close study of the Galilean satellites and exploration of the Jovian system. Some new jargon is introduced in discussions to describe the exploitation of gravity-assist trajectories using the giant satellites for orbit control. Orbit 'pumping' and 'cranking' and 'resonance hopping' are defined and shown to be dynamically feasible means of controlling the orbit and, thus, the scientific return. A candidate encounter sequence is presented for an equatorial tour of the Galilean moons.

Uphoff, C.↗
NASA NTRS2009

An Overview of the Jupiter Europa Orbiter Concept's Europa Science Phase Orbit Design

Jupiter Europa Orbiter (JEO), the proposed NASA element of the proposed joint NASA-ESA Europa Jupiter System Mission (EJSM), could launch in February 2020 and conceivably arrive at Jupiter in December of 2025. The concept is to perform a multi-year study of Europa and the Jupiter system, including 30 months of Jupiter system science and a comprehensive Europa orbit phase of 9 months. This paper provides an overview of the JEO concept and describes the Europa Science phase orbit design and the related science priorities, model pay-load and operations scenarios needed to conduct the Europa Science phase. This overview is for planning and discussion purposes only.

Lock, Robert E.↗
NASA NTRS1991

Mars Observer trajectory and orbit design

The Mars Observer launch, interplanetary, Mars orbit insertion, and mapping orbit designs are described. The design objective is to enable a near-maximum spacecraft mass to be placed in orbit about Mars. This is accomplished by keeping spacecraft propellant requirements to a minimum, selecting a minimum acceptable launch period, equalizing the spacecraft velocity change requirement at the beginning and end of the launch period, and constraining the orbit insertion maneuvers to be coplanar. The mapping orbit design objective is to provide the opportunity for global observation of the planet by the science instruments while facilitating the spacecraft design. This is realized with a sun-synchronous near-polar orbit whose ground-track pattern covers the planet at progressively finer resolution.

Beerer, Joseph G.↗
NASA NTRS2004

Orbit Design for Phase I and II of the Magnetospheric Multiscale Mission

The Magnetospheric Multiscale Mission (MMS) is a NASA mission intended to make fundamental advancements in our understanding of the Earth s magnetosphere. There are three processes that MMS is intended to study including magnetic reconnection, charged particle acceleration, and turbulence. There are four phases of the MMS mission and each phase is designed to study a particular region of the Earth's magnetosphere. The mission is composed of a formation of four spacecraft that are nominally in a regular tetrahedron formation. In this work, we present optimal orbit designs for Phase I and II. This entails designing reference orbits such that the spacecraft dwell-time in the region of interest is a maximum. This is non-trivial because the Earth's magnetosphere is dynamic and its shape and position are not constant in inertial space. Optimal orbit design for MMS also entails designing the formation so that the relative motion of the four spacecraft yields the greatest science return. We develop performance metrics that are directly related to the science return, and use Sequential Quadratic Programming (SQP) to determine optimal relative motion solutions. While designing for optimal science return, we also consider practical constraints such as maximum eclipse time and minimum inter-spacecraft separation distances. Data are presented that illustrates how long we can ensure that the formation remains in the relevant region of the Earth's magnetosphere. We also draw general conclusions about where in the orbit acceptable tetrahedron configurations can be provided and for how long.

Hughes, Steve P.↗
NASA NTRSDate not supplied

HelioSwarm: Transfer Trajectory and P/2 Lunar Resonant Orbit Design for a Multi-Satellite Observatory

The HelioSwarm mission will fly a multi-satellite observatory in a P/2 lunar resonant orbit to study plasma turbulence in the solar wind. Lunar resonant orbits enable long-term access to high Earth altitudes. The relative dynamics of a multi-satellite observatory introduce novel considerations for lunar resonant orbit design. Additional maneuvers in the post lunar encounter transfer enable heightened control of the lunar resonant orbit initial state compared to previous missions. Adjusting the mission orbit’s initial conditions enables refinement of the orbit design based on requirements imposed by the relative dynamics of the observatory. refinement of the orbit design based on requirements imposed by the relative dynamics of the observatory.

cislunar↗
NASA NTRS2003

Orbit Design for Phase I and II of the Magnetospheric Multiscale Mission (MMS)

The Magnetospheric Multiscale Mission (MMS) is a NASA mission intended to make fundamental advancements in our understanding of the Earth's Magnetosphere. There are three processes that MMS is intended to study including magnetic recon- nection, charged particle acceleration, and turbulence. There are four phases of the MMS mission and each phase is designed to study a particular region of the Earth's magnetosphere. The mission is composed of a formation of four spacecraft that are nominally in a regular tetrahedron formation. In this work, we present optimal orbit designs for Phase I and II. This entails designing optimal reference orbits so that the spacecraft dwell-time in the region of interest is a maximum. This is non-trivial because the Earth's magnetosphere is dynamic and its shape and position are not constant in inertial space. Optimal orbit design for MMS also entails designing the formation so that the relative motion of the four spacecraft yields the greatest science return. We develop performance metrics that are related to the science return, and use Sequential Quadratic Programming (SQP) to determine optimal relative motion solutions. We also ensure that practical constraints such as maximum eclipse time and minimum inter-spacecraft separation distances are not violated.

Hughes, Steve P.↗
NASA NTRS2004

Orbit Design Based on the Global Maps of Telecom Metrics

In this paper we describe an orbit design aide tool, called Telecom Orbit Analysis and Simulation Tool(TOAST). Although it can be used for studying and selecting orbits for any planet, we solely concentrate on its use for Mars. By specifying the six orbital elements for an orbit, a time frame of interest, a horizon mask angle, and some telecom parameters such as the transmitting power, frequency, antenna gains, antenna losses, link margin, received threshold powers for the rates, etc. this tool enables the user to view the animation of the orbit in two and three-dimensional different telecom metrics at any point on the Mars, namely the global planetary map.

Mars orbiter↗
NASA NTRS1993

Mars Relays Satellite Orbit Design Considerations for Global Support of Robotic Surface Missions

This paper discusses orbit design considerations for Mars relay satellite (MRS)support of globally distributed robotic surface missions. The orbit results reported in this paper are derived from studies of MRS support for two types of Mars robotic surface missions: 1) the mars Environmental Survey (MESUR) mission, which in its current definition would deploy a global network of up to 16 small landers, and 2)a Small Mars Sample Return (SMSR) mission, which included four globally distributed landers, each with a return stage and one or two rovers, and up to four additional sets of lander/rover elements in an extended mission phase.

Robitics Mars↗
NASA NTRS1991

Spacecraft Orbit Design and Analysis (SODA). Version 2.0: User's guide

The Spacecraft Orbit Design and Analysis (SODA) computer program, Version 2.0, is discussed. SODA is a spaceflight mission planning system that consists of six program modules integrated around a common database and user interface. SODA runs on a VAX/VMS computer with an Evans and Sutherland PS300 graphics workstation. In the current version, three program modules produce an interactive three dimensional animation of one or more satellites in planetary orbit. Satellite visibility and sensor coverage capabilities are also provided. Circular and rectangular, off nadir, fixed and scanning sensors are supported. One module produces an interactive three dimensional animation of the solar system. Another module calculates cumulative satellite sensor coverage and revisit time for one or more satellites. Currently, Earth, Moon, and Mars systems are supported for all modules except the solar system module.

Stallcup, Scott S.↗
NASA NTRS1989

Spacecraft Orbit Design and Analysis (SODA), version 1.0 user's guide

The Spacecraft Orbit Design and Analysis (SODA) computer program, Version 1.0 is described. SODA is a spaceflight mission planning system which consists of five program modules integrated around a common database and user interface. SODA runs on a VAX/VMS computer with an EVANS & SUTHERLAND PS300 graphics workstation. BOEING RIM-Version 7 relational database management system performs transparent database services. In the current version three program modules produce an interactive three dimensional (3D) animation of one or more satellites in planetary orbit. Satellite visibility and sensor coverage capabilities are also provided. One module produces an interactive 3D animation of the solar system. Another module calculates cumulative satellite sensor coverage and revisit time for one or more satellites. Currently Earth, Moon, and Mars systems are supported for all modules except the solar system module.

Stallcup, Scott S.↗
NASA NTRS1989

Mars Rover Sample Return Orbiter design concepts

The observational orbiter of the Mars Rover Sample Return mission will observe the (10x10 km) landing sites and provide data that will be used in the decision to commit the landing vehicles to a landing at a chosen site. To provide observational data from orbit at a surface resolution consistent with the hazard tolerance of the landing vehicles, the orbiter imaging subsystem must be capable of 0.25 meters resolution per picture element (pixel). The design of the imaging, pointing, and data subsystems capable of providing this capability has been completed in this study. The rationale for these requirements and the more detailed derived requirements affecting the spacecraft design are discussed.

Randolph, J. E.↗
NASA NTRSDate not supplied

An Observational Approach to Low Lunar Frozen Orbit Design

Low lunar frozen orbits can be used to enable long-duration missions at the Moon while also minimizing the fuel usage necessary for orbit maintenance. There is no analytical expression for determining these frozen orbits, so a high-fidelity simulation approach is required. A differential correction targeting approach was used to find initial conditions that zeroed out argument of periapsis and eccentricity growth. This approach was used during the Lunar Reconnaissance Orbiter extended mission period for four different frozen orbit instances. Observations of the evolution of key orbit elements (e.g. periapsis altitude and the eccentricity vector) led to an understanding of the orbit dynamics and helped to formulate a simple observational approach to finding frozen or quasi-frozen low lunar orbits that looks at minimizing the spread in the periselene altitude evolution.

Moon Frozen Orbit LRO↗
NASA NTRSDate not supplied

An Observational Approach to Low Lunar Frozen Orbit Design

Low lunar frozen orbits can be used to enable long-duration missions at the Moon while also minimizing the fuel usage necessary for orbit maintenance. There is no analytical expression for determining these frozen orbits, so a high-fidelity simulation approach is required. A differential correction targeting approach was used to find initial conditions that zeroed out argument of periapsis and eccentricity growth. This approach was used during the Lunar Reconnaissance Orbiter extended mission period for four different frozen orbit instances. Observations of the evolution of key orbit elements (e.g. periapsis altitude and the eccentricity vector) led to an understanding of the orbit dynamics and helped to formulate a simple observational approach to finding frozen or quasi-frozen low lunar orbits that looks at minimizing the spread in the periselene altitude evolution.

Moon Frozen Orbit LRO↗
NASA NTRS2002

Preliminary Optimal Orbit Design for the Laser Interferometer Space Antenna (LISA)

In this paper we present a preliminary optimal orbit analysis for the Laser Interferometer Space Antenna (LISA). LISA is a NASA/ESA mission to study gravitational waves and test predictions of general relativity. The nominal formation consists of three spacecraft in heliocentric orbits at 1 AU and trailing the Earth by twenty degrees. This configuration was chosen as a trade off to reduce the noise sources that will affect the instrument and to reduce the fuel to achieve the final orbit. We present equations for the nominal orbit design and discuss several different measures of performance for the LISA formation. All of the measures directly relate the formation dynamics to science performance. Also, constraints on the formation dynamics due to spacecraft and instrument limitations are discussed. Using the nominal solution as an initial guess, the formation is optimized using Sequential Quadratic Programming to maximize the performance while satisfying a set of nonlinear constraints. Results are presented for each of the performance measures.

Hughes, Steven P.↗