1 edition of Design considerations for the ORION satellite found in the catalog.
Design considerations for the ORION satellite
Austin Walker Boyd
A general purpose satellite (ORION) has been designed which will launch from the Space Shuttle using a NASA Get-Away-Special (GAS) canister. The design is based on the use of a new extended GAS canister and a low profile launch mechanism. The satellite is also configured to launch as a dedicated payload on SCOUT or commercial expendable launch vehicles. The satellite is cylindrical, measuring 19 inches in diameter and 35 inches long. The maximum spacecraft mass is 250 pounds, of which 32 pounds are nominally dedicated to user payloads. The remaining 218 pounds encompass the satellite structure and support elements, which include a hydrazine propulsion subsystem and a spin stabilized attitude control subsystem. The propulsion subsystem provides sufficient impulse to enable circular orbits as high as 835 nm or elliptic orbits with apogees at 2200 nm, leaving a nominal shuttle orbit of 135 nm. Four stabilizing booms or active nutation control techniques are employed for spin stabilization about the longitudinal axis of the spacecraft. Attitude control accuracies on the order of 1 deg are attainable for a total mission duration of 90 days to 3 years. Total satellite cost is $1.5 million. The thesis outlines the history of general purpose spacecraft, the ORION design criteria, and the design of the major subsystems.
|Other titles||Design considerations for the ORION satellite: structure, propulsion and attitude control subsystems for a small, general purpose satellite|
|Statement||Austin Walker Boyd Jr|
|Contributions||Naval Postgraduate School (U.S.)|
|The Physical Object|
|Pagination||626 p. ;|
|Number of Pages||626|
Spherical Satellite Max/Min Temperatures Where A=satellite surface area, AC is the satellite cross-sectional area, and F is the view factor = (1-cos ρ)/2 4 1 min 4 1 max ⎥⎦ ⎤ ⎢⎣ ⎡ + = ⎥⎦ ⎤ ⎢⎣ ⎡ + + + = σε ε σε α ε α A AFq Q T A A G AFq AFG a K Q T I W C s I s a W s s Similar analysis. satellite Relay satellite Relay satellite Sensor satellite Sensor satellite Crossover or Intersatellite links Mission data Launch phase TT&C TT&C Satellite Ground station TT&C Tracking, Telemetry and Control The communications architecture consists of satellites and ground stations interconnected with communications links. (Adapted from SMAD.).
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The Orion crew module uses a high-speed communications system employing four phased array antennas that will be used for video, data and voice communications with the spacecraft as well as command uplink and telemetry downlink to ground stations or NASA’s Tracking and Data Relay Satellite Systems. Design Considerations • Required satellite coverage determines the number and location of ground stations – LEOs are particularly demanding because of short and infrequent contact opportunities – Large quantities of mission data must be stored on board and downlinked in short periods – Infrequent TT&C contact demands more on-.
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Attitude control accuracies on the order of 1 deg are attainable for a total mission duration of 90 days to 3 years. Total satellite cost is $ million. The thesis outlines the history of general purpose spacecraft, the ORION design criteria, and the design of Pages: Design considerations for the ORION satellite: structure, propulsion and attitude control subsystems for a small, general purpose spacecraft by Boyd, Austin Walker.
It will become too aggresive to pre-design something really realistic based upon the satellite data available inside this book. Even as of today, natural satellite taylored design makes this approach quite dangerous, although it may work at the very beginning.
It seems authors decided to follow the "Orion" approach, focussing primary on /5(36). Full text of "Design considerations for the ORION satellite: structure, propulsion and attitude control subsystems for a small, general purpose spacecraft" See other formats.
Orion, also known as Mentor or Advanced Orion, is a class of United States spy satellites that collect signals intelligence (SIGINT) from space. Operated by the National Reconnaissance Office (NRO) and developed with input from the Central Intelligence Agency (CIA), five have been launched from Cape Canaveral on Titan IV and Delta IV rockets since These satellites collect radio.
Orion engineers developed unique ways to test Orion systems while continuing to design and build the flight spacecraft. This includes the Structural Test Article that is a structural twin of the crew module, system module and launch abort system.
These elements are going through a litany of physical structural tests to validate the spacecraft. Initial design criteria were developed by examination of the satellite itself, including launch vehicles, orbital profiles and ground interfaces. After consideration of these design constraints, a review of commercially available TT&C antennas was conducted to determine compatibility with Orion, cumulating in recommendation of the conical log.
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Spin stabilization of the ORION satellite using a thruster attitude control system with optimal control considerations Cunningham, Janet L. (Naval Postgraduate School, ) ; The controlled system is the ORION satellite spinning about its single axis of symmetry.
Design considerations for space flight hardware The environmental and design constraints are reviewed along with some insight into the established design and quality assurance practices that apply to low earth orbit (LEO) space flight hardware.
It is intended as an introduction for people unfamiliar with space flight considerations. Some basic data and a bibliography are included. NASA's crewed moon return is drawing ever closer. Aerospace company Lockheed Martin has finished building the Orion capsule that will fly on the uncrewed Artemis 1.
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Project Orion was a study of a spacecraft intended to be directly propelled by a series of explosions of atomic bombs behind the craft (nuclear pulse propulsion).Early versions of this vehicle were proposed to take off from the ground (with significant associated nuclear fallout); later versions were presented for use only in non-nuclear tests were conducted using models.
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Developed in both one- and two-stage designs, the missile was moderately successful in testing, and helped pave the way for development of the GAM Skybolt addition, the Bold Orion was used in early anti-satellite.
The Altair spacecraft, previously known as the Lunar Surface Access Module or LSAM, was the planned lander spacecraft component of NASA's cancelled Constellation program. Astronauts would have used the spacecraft for landings on the Moon, which was intended to begin around The Altair spacecraft was planned to be used both for lunar sortie and lunar outpost missions.
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All the areas of spacecraft systems engineering are covered at an intermediate level of theory and mathematical formulation.
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