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  • 1
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    A phase one AR/C system design (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Phase One AR&C System Design integrates an evolutionary design based on the legacy of previous mission successes, flight tested components from manned Rendezvous and Proximity Operations (RPO) space programs, and additional AR&C components validated using proven methods. The Phase One system has a modular, open architecture with the standardized interfaces proposed for Space Station Freedom system architecture.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington, NASA Automated Rendezvous and Capture Review. Executive Summary; p 26-27
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Relative navigation requirements for automatic rendezvous and capture systems (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This paper will discuss in detail the relative navigation system requirements and sensor trade-offs for Automatic Rendezvous and Capture. Rendezvous navigation filter development will be discussed in the context of navigation performance requirements for a 'Phase One' AR&C system capability. Navigation system architectures and the resulting relative navigation performance for both cooperative and uncooperative target vehicles will be assessed. Relative navigation performance using rendezvous radar, star tracker, radiometric, laser and GPS navigation sensors during appropriate phases of the trajectory will be presented. The effect of relative navigation performance on the Integrated AR&C system performance will be addressed. Linear covariance and deterministic simulation results will be used. Evaluation of relative navigation and IGN&C system performance for several representative relative approach profiles will be presented in order to demonstrate the full range of system capabilities. A summary of the sensor requirements and recommendations for AR&C system capabilities for several programs requiring AR&C will be presented.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: NASA, Washington, NASA Automated Rendezvous and Capture Review. A Compilation of the Abstracts; 2 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Performance capabilities of a Phase One Automatic Rendezvous and Capture System (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This paper presents an analysis of the performance of the existing 'Phase One' AR&C system developed at the C.S. Draper Laboratory for both the rendezvous and proximity operations mission phases. This material has been developed as a result of Draper Laboratory involvement through NASA's Johnson Space Center in the development of the flight proven IGN&C rendezvous systems for Apollo, Skylab, and Shuttle. The development of these systems using Draper computer simulations has required automation of all crew inputs to the IGN&C system and thus provided the unique opportunity to develop and test those system capabilities required for AR&C. This paper expands upon the material in the papers presented by the authors at the NASA Autonomous Rendezvous and Docking Conference held at JSC on August 15-16, 1991.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington, NASA Automated Rendezvous and Capture Review. A Compilation of the Abstracts; 2 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Report on the loss of the Mars Climate Orbiter Mission : JPL special review board (1999)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: The Mars Climate Orbiter (MCO) was launched on December 11, 1998. The MCO was to arrive at Mars and begin orbit insertion on September 23, 1999. The Mars Orbit Insertion (MOI) burn, a 16-minute maneuver to slow the spacecraft and enable capture into an orbit around Mars, began on schedule. Five minutes into the maneuver, and approximately 49 seconds before the anticipated time for loss of communication, the MCO was occulted by Mars. Thereafter, no contact with the spacecraft could be established. On September 24, 1999, an internal JPL team (the MCO Peer Review Team) was appointed to help investigate the reason for the loss of spacecraft signal. The Peer Review Team's findings are presented in this report.
    Keywords: Lunar and Planetary Science and Exploration
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Cooperative control of two active spacecraft during proximity operations (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A cooperative autopilot is developed for the control of the relative attitude, relative position and absolute attitude of two maneuvering spacecraft during on orbit proximity operations. The autopilot consists of an open-loop trajectory solver which computes a nine dimensional linearized nominal state trajectory at the beginning of each maneuver and a phase space regulator which maintains the two spacecraft on the nominal trajectory during coast phases of the maneuver. A linear programming algorithm is used to perform jet selection. Simulation tests using a system of two space shuttle vehicles are performed to verify the performance of the cooperative controller and comparisons are made to a traditional passive target/active pursuit vehicle approach to proximity operations. The cooperative autopilot is shown to be able to control the two vehicle system when both the would be pursuit vehicle and the target vehicle are not completely controllable in six degrees of freedom. The cooperative controller is also shown to use as much as 37 percent less fuel and 57 percent fewer jet firings than a single pursuit vehicle during a simple docking approach maneuver.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-185596 , NAS 1.26:185596 , CSDL-T-1037
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Free-Flight Test Results of Scale Models Simulating Viking Parachute/Lander Staging (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results of Viking Aerothermodynamics Test D4-34.0. Motion picture coverage of a number of Scale model drop tests provides the data from which time-position characteristics as well as canopy shape and model system attitudes are measured. These data are processed to obtain the instantaneous drag during staging of a model simulating the Viking decelerator system during parachute staging at Mars. Through scaling laws derived prior to test (Appendix A and B) these results are used to predict such performance of the Viking decelerator parachute during staging at Mars. The tests were performed at the NASA/Kennedy Space Center (KSC) Vertical Assembly Building (VAB). Model assemblies were dropped 300 feet to a platform in High Bay No. 3. The data consist of an edited master film (negative) which is on permanent file in the NASA/LRC Library. Principal results of this investigation indicate that for Viking parachute staging at Mars: 1. Parachute staging separation distance is always positive and continuously increasing generally along the descent path. 2. At staging, the parachute drag coefficient is at least 55% of its prestage equilibrium value. One quarter minute later, it has recovered to its pre-stage value.
    Keywords: Spacecraft Design, Testing and Performance
    Type: TR-3720386
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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