The Experts below are selected from a list of 1809 Experts worldwide ranked by ideXlab platform
Nasa - One of the best experts on this subject based on the ideXlab platform.
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LANDSAT D to test thematic mapper, inaugurate operational system
2019Co-Authors: NasaAbstract:NASA will Launch the Landsat D spacecraft on July 9, 1982 aboard a new, up-rated Delta 3920 Expendable Launch Vehicle. LANDSAT D will incorporate two highly sophisticated sensors; the flight proven multispectral scanner; and a new instrument expected to advance considerably the remote sensing capabilities of Earth resources satellites. The new sensor, the thematic mapper, provides data in seven spectral (light) bands with greatly improved spectral, spatial and radiometric resolution.
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The 1981 Expendable Launch Vehicle schedule announced
2019Co-Authors: NasaAbstract:Fifteen satellite Launchings are summarized. Included in the 1981 schedule are two NASA scientific payloads, two weather satellites, and eight commercial geosynchronous communications satellites.
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Delta II Geotail Test D5040
2017Co-Authors: NasaAbstract:This video presents live footage of the Delta II Expendable Launch Vehicle Geotail test. The Geotail Satellite was Launched aboard Delta II to study the dynamics of the Earth's magnetotail over a wide range of distance. The mission lasted almost four years.
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Assessment of candidate-Expendable Launch Vehicles for large payloads
2017Co-Authors: NasaAbstract:In recent years the U.S. Air Force and NASA conducted design studies of 3 Expendable Launch Vehicle configurations that could serve as a backup to the space shuttle--the Titan 34D7/Centaur, the Atlas II/Centaur, and the shuttle-derived SRB-X--as well as studies of advanced shuttle-derived Launch Vehicles with much larger payload capabilities than the shuttle. The 3 candidate complementary Launch Vehicles are judged to be roughly equivalent in cost, development time, reliability, and payload-to-orbit performance. Advanced shuttle-derived Vehicles are considered viable candidates to meet future heavy lift Launch requirements; however, they do not appear likely to result in significant reduction in cost-per-pound to orbit.
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Turnaround Operations Analysis for OTV. Volume 3: Technology Development Plan
2016Co-Authors: NasaAbstract:An integrated technology development plan for the technologies required to process both GBOTVs and SBOTVs are described. The plan includes definition of the tests and experiments to be accomplished on the ground, in a Space Shuttle Sortie Mission, on an Expendable Launch Vehicle, or at the Space Station as a Technology Development Mission (TDM). The plan reflects and accommodates current and projected research and technology programs where appropriate.
Smith, David Alan - One of the best experts on this subject based on the ideXlab platform.
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Space Launch System (SLS) Mission Planner's Guide
2018Co-Authors: Smith, David AlanAbstract:The purpose of this Space Launch System (SLS) Mission Planner's Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessment. Like ELV Programs, once approved to fly on SLS, specific payload requirements will be defined in unique documentation
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Space Launch System (SLS) Mission Planners Guide
2018Co-Authors: Smith, David AlanAbstract:The purpose of this Space Launch System (SLS) Mission Planners Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessments. Like ELV programs, specific payload requirements will be defined in unique documentation once manifested to fly on SLS. SLS users requiring additional mission planning information or more detailed technical interchange concerning specific SLS accommodations should contact the SLS Spacecraft/Payload Integration and Evolution (SPIE) office
Hans Mark - One of the best experts on this subject based on the ideXlab platform.
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Encyclopedia of Space Science and Technology - Evolution of U.S. Expendable Launch Vehicles
Encyclopedia of Space Science and Technology, 2003Co-Authors: Michael I. Yarymovych, Hans MarkAbstract:Robert H. Goddard was a Professor of Physics at Clark University in Worcester, Massachusetts from 1919 to 1945. During this time he performed his classic experiments in liquid-fueled rocketry. This article gives the history of Goddard's discoveries and the rising interest at in rockets in Germany at that time. Details are given on the V-2 Rocket team that Wernher von Braun developed in Germany and what happened to this team after World War II. In 1946 the U.S. embarked on a vigorous program to develop large liquid-fuled rockets for military reasons. Von Braun joined the U.S. Army rocket development program in 1950. Later the U.S. Air Force became involved in rocket development. The Air Force established the Western Development Division, which was given the job of developing three missile systems: two intercontinental ballistic missiles (Atlas and Titan); and one intermediate range ballistic missile (Thor). Development of these missiles is discussed. The Evolved Expendable Launch Vehicle Program (EELV) concept is detailed. The EELV was developed to reduce the cost of access to space. The Delta IV Launch Vehicle was developed under EELV, as was the Atlas V. Keywords: United States; Expendable Launch Vehicles; history; world war II; development; rocket development; U.S. Army; U.S. Air Force; intercontinental ballistic missiles; evolved Expendable Launch Vehicle program
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Encyclopedia of Space Science and Technology - Evolution of U.S. Expendable Launch Vehicles
Encyclopedia of Space Science and Technology, 2003Co-Authors: Michael I. Yarymovych, Hans MarkAbstract:Robert H. Goddard was a Professor of Physics at Clark University in Worcester, Massachusetts from 1919 to 1945. During this time he performed his classic experiments in liquid-fueled rocketry. This article gives the history of Goddard's discoveries and the rising interest at in rockets in Germany at that time. Details are given on the V-2 Rocket team that Wernher von Braun developed in Germany and what happened to this team after World War II. In 1946 the U.S. embarked on a vigorous program to develop large liquid-fuled rockets for military reasons. Von Braun joined the U.S. Army rocket development program in 1950. Later the U.S. Air Force became involved in rocket development. The Air Force established the Western Development Division, which was given the job of developing three missile systems: two intercontinental ballistic missiles (Atlas and Titan); and one intermediate range ballistic missile (Thor). Development of these missiles is discussed. The Evolved Expendable Launch Vehicle Program (EELV) concept is detailed. The EELV was developed to reduce the cost of access to space. The Delta IV Launch Vehicle was developed under EELV, as was the Atlas V. Keywords: United States; Expendable Launch Vehicles; history; world war II; development; rocket development; U.S. Army; U.S. Air Force; intercontinental ballistic missiles; evolved Expendable Launch Vehicle program
Valerie C. Thomas - One of the best experts on this subject based on the ideXlab platform.
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A Vibroacoustic Database Management Center for Shuttle and Expendable Launch Vehicle Payloads
Journal of Environmental Sciences-china, 2006Co-Authors: Valerie C. ThomasAbstract:A Vibroacoustic Database Management Center has recently been established at the Jet Propulsion Laboratory (JPL). The center uses the Vibroacoustic Payload Environment Prediction System (VAPEPS) computer program to maintain a database of flight and ground-test data and structural parameters for both shuttle and Expendable Launch-Vehicle payloads. Given the Launch-Vehicle environment, the VAPEPS prediction software, which employs Statistical Energy Analysis (SEA) methods, can be used with or without the database to establish the vibroacoustic environment for new payload components. This paper summarizes the VAPEPS program and describes the functions of the Database Management Center at JPL.
James R Wertz - One of the best experts on this subject based on the ideXlab platform.
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responsive low cost access to space with elvis an Expendable Launch Vehicle with integrated spacecraft
2003Co-Authors: Richard E Van Allen, Thomas P Bauer, Shyama Chakroborty, Sonya Collier, Paul Graven, Jane Hansen, Hans F Meissinger, James R WertzAbstract:The ELVIS (Expendable Launch Vehicle with Integrated Spacecraft) concept involves: (1) dropping off the upper stage of the Launch Vehicle as low as possible, with integral low-thrust propulsion taking the spacecraft to its final orbital destination; (2) using the spacecraft bus to provide the avionics functions needed to fly a Launch Vehicle to orbit so as to avoid the duplication of avionics hardware and software between the satellite bus and the Launch Vehicle. The result is a reduction in the parts count, weight, and cost of the Launch Vehicle. There are major benefits associated with early staging — the upper stage can reenter safely without a retro burn, and the mass-to-orbit available from small Launch Vehicles is significantly increased. The mass gain will depend on the hardware configuration and the orbit destination, but can be as much as a factor of two or more for some low Earth orbits. In addition, the spacecraft bus operates from the time of Launch and can begin the mission essentially as soon as the spacecraft reaches its operational orbit or, in some cases, even before. The small spacecraft thus achieves a new level of responsiveness, allowing spacecraft to be Launched in response to rapidly changing circumstances. This paper describes a representative ELVIS configuration and performance gains for typical mission destinations, and sample applications that are enabled or made more efficient by the use of this approach. Technical issues and tradeoffs associated with this design will be discussed. * © 2003 Microcosm, Inc. Introduction The costs of getting to space and operating in space continue to be the barriers that constrict the small satellite market. There are several ways to reduce or remove these barriers that can be used separately or in combination. One is to utilize low-cost Launch Vehicles that are emerging in the industry, such as the Sprite , that will drop Launch costs by as much as an order of magnitude and add responsiveness at the same time. Another is to use the avionics in the spacecraft bus to control the Launch Vehicle and eliminate the need for duplication of hardware. The major benefit from the dual use of the avionics is to have a fully functioning spacecraft at orbit insertion, immediately ready to begin performing a mission. A third option, a technique termed the Modified Launch Mode (MLM), can be applied to maximize the system performance and significantly increase the payload mass that reaches the operational orbit. Finally, we can also reduce the systems cost by taking advantage of proven autonomous orbit transfer and control
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Responsive, Low-Cost Access to Space with ELVIS — An Expendable Launch Vehicle with Integrated Spacecraft
2003Co-Authors: Richard E Van Allen, Thomas P Bauer, Shyama Chakroborty, Sonya Collier, Paul Graven, Jane Hansen, Hans F Meissinger, James R WertzAbstract:The ELVIS (Expendable Launch Vehicle with Integrated Spacecraft) concept involves: (1) dropping off the upper stage of the Launch Vehicle as low as possible, with integral low-thrust propulsion taking the spacecraft to its final orbital destination; (2) using the spacecraft bus to provide the avionics functions needed to fly a Launch Vehicle to orbit so as to avoid the duplication of avionics hardware and software between the satellite bus and the Launch Vehicle. The result is a reduction in the parts count, weight, and cost of the Launch Vehicle. There are major benefits associated with early staging — the upper stage can reenter safely without a retro burn, and the mass-to-orbit available from small Launch Vehicles is significantly increased. The mass gain will depend on the hardware configuration and the orbit destination, but can be as much as a factor of two or more for some low Earth orbits. In addition, the spacecraft bus operates from the time of Launch and can begin the mission essentially as soon as the spacecraft reaches its operational orbit or, in some cases, even before. The small spacecraft thus achieves a new level of responsiveness, allowing spacecraft to be Launched in response to rapidly changing circumstances. This paper describes a representative ELVIS configuration and performance gains for typical mission destinations, and sample applications that are enabled or made more efficient by the use of this approach. Technical issues and tradeoffs associated with this design will be discussed. * © 2003 Microcosm, Inc. Introduction The costs of getting to space and operating in space continue to be the barriers that constrict the small satellite market. There are several ways to reduce or remove these barriers that can be used separately or in combination. One is to utilize low-cost Launch Vehicles that are emerging in the industry, such as the Sprite , that will drop Launch costs by as much as an order of magnitude and add responsiveness at the same time. Another is to use the avionics in the spacecraft bus to control the Launch Vehicle and eliminate the need for duplication of hardware. The major benefit from the dual use of the avionics is to have a fully functioning spacecraft at orbit insertion, immediately ready to begin performing a mission. A third option, a technique termed the Modified Launch Mode (MLM), can be applied to maximize the system performance and significantly increase the payload mass that reaches the operational orbit. Finally, we can also reduce the systems cost by taking advantage of proven autonomous orbit transfer and control
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the scorpius Expendable Launch Vehicle family and status of the sprite small Launch Vehicle
2003Co-Authors: Shyama Chakroborty, James R Wertz, Robert Conger, Jack KulpaAbstract:Microcosm and the Scorpius ® Space Launch Company are developing a family of Expendable Launch Vehicles that will provide low-cost, responsive access to space. The Scorpius ® family includes single and two-stage suborbital and orbital Vehicles with payloads ranging from 700 lbs to LEO for the Sprite Mini-lift Launch Vehicle to over 50,000 lbs to LEO (18,000 lbs to GTO) for the Heavy-lift Vehicle. Two suborbital Vehicles have been flown successfully from White Sands Missile Range, including the SR-XM-1 in March 2001, which was, effectively, a full-scale test of a Sprite pod, although not all of the Sprite components were flown. The first Sprite orbital Launch is scheduled for 2006. This paper describes the technology and development plan of the Sprite Small Launch Vehicle (SLV). Starting with a contract from the Air Force Research Laboratory in 1993, technology development has progressed with increasing maturity in design, manufacturing techniques, and component develop- ment and qualification. Low-cost and scalable ablative engines based on flight-proven technology, all- composite propellant tanks, and a Tridyne-based High Performance Pressurization System are all in the final stages of qualification. A low-cost baseline design has been developed for the Sprite upper stage. The Scorpius ® modular design approach, built around scalable critical components such as the engines and all-composite propellant tanks, will allow us to transition from the Sprite SLV to the medium-lift Exodus and then to heavier-lift Vehicles if the need justifies the economic investment.
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The Scorpius Expendable Launch Vehicle Family and Status of the Sprite Mini-Lift
20th AIAA International Communication Satellite Systems Conference and Exhibit, 2002Co-Authors: Robert E. Conger, Shyama Chakroborty, James R Wertz, Jack KulpaAbstract:Microcosm and the Scorpius Space Launch Company (SSLC) are well into the development of an all -new generation of Expendable Launch Vehicles to support commercial and government missions. The Scorpius � Vehicle family extends from one and two stage sub orbital Vehicles for target and science applications, to small -, medium - and heavy -lift orbital Vehicles. These new liquid fueled Vehicles have LEO and GTO capabilities.
