Engineering topics

Satter, Celeste M.

Publications and source records attributed to Satter, Celeste M..

6 records

NASA NTRS2005

Deployable Mini-Payload Missions Enabled by Small Radioisotope Power Systems (RPSs)

Deployable mini-payloads are envisioned as small, simple, standalone instruments that could be deployed from a mother vehicle such as a rover or the proposed Jupiter Icy Moons Orbiter to key points of interest within the solar system. Used in conjunction with a small radioisotope power system (RPS), these payloads could potentially be used for long-duration science missions or as positional beacons for rovers or other spacecraft. The RPS power source would be suitable for deployable mini-payload missions that would take place anywhere there is limited, intermittent, or no solar insolation. This paper introduces two such concepts: (1) a seismic monitoring station deployed by a rover or aerobot, and (2) a passive fields and particles station delivered by a mother spacecraft to Jupiter.

deployables↗

NASA NTRS2005

JIMO follow-on mission studies

Team Prometheus is a geographically-distributed, collaborative engineering team composed of representatives from several NASA centers and the Department of Energy (DOE). During the months of April through September 2004, Team Prometheus performed studies of representative Saturn/Titan and Neptune/Triton science missions based on proposed Jupiter Icy Moons Orbiter (JIMO) technology. The principal objectives of these studies were: 1) to assess the feasibility of using direct copies of the baseline JIMO flight system designs to perform these follow-on missions, and 2) to identify and assess technologies or potential enhancements or alterations to the baseline JIMO designs which could reduce the cruise durations to meet NASA Headquarters-specified programmatic goals. A tertiary objective was to provide feedback to the JlMO Project on the suitability of the JIMO reference designs for potential follow-on applications

Satter, Celeste M.↗

NASA NTRS2005

JIMO follow on mission studies

UNKNOWN

Satter, Celeste M.↗

NASA NTRS2004

Enabling exploration with small radioisotope power systems

The purpose of this report is to provide an initial reference document to support further definition of science community needs for small-RPS flight systems. It describes the most recent results of the ongoing NASA/DOE studies, and provides information for review by potential users that might take advantage of these types of power systems. This is extremely important since any future decision to proceed with the development of such units will require a strong identified need from the space science community and a well-defined set of power and operational requirements. NASA and DOE intend to use this document as a basis for soliciting information on additional small-RPS-enabled mission concepts, along with their respective power and operational requirements. This report is a first step in fleshing out a roadmap for potential future development and acquisition.

Shirley, James H.↗

NASA NTRS1991

Structural design of the Large Deployable Reflector (LDR)

An integrated Large Deployable Reflector (LDR) analysis model was developed to enable studies of system responses to the mechanical and thermal disturbances anticipated during on-orbit operations. Functional requirements of the major subsystems of the LDR are investigated, design trades are conducted, and design options are proposed. System mass and inertia properties are computed in order to estimate environmental disturbances, and in the sizing of control system hardware. Scaled system characteristics are derived for use in evaluating launch capabilities and achievable orbits. It is concluded that a completely passive 20-m primary appears feasible for the LDR from the standpoint of both mechanical vibration and thermal distortions.

Satter, Celeste M.↗

NASA NTRS1988

A precision pointing system for space telescope class optical trackers

This paper reports on the results of a study effort whose main objective was to develop a conceptual design for a space based, large-payload (3000 kg) pointing system capable of both rapid slew maneuvers (0.35 rad/sec-squared) and very stable tracking (1 microrad, 1 sigma, each axis). The key features of the resulting solution are: (1) cross elevation over elevation gimbal system, (2) closed cross elevation gimbal ring, (3) graphite-epoxy structure, (4) two-motor reactionless joint torquers, (5) payload mounted vernier reaction wheel, and (6) gyrostabilized model following control system.

Sevaston, George E.↗