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  • 1
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    Instrument Pointing Control System for the Stellar Interferometry Mission - Planet Quest (2006)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: This paper describes the high precision Instrument Pointing Control System (PCS) for the Stellar Interferometry Mission (SIM) - Planet Quest. The PCS system provides front-end pointing, compensation for spacecraft motion, and feedforward stabilization, which are needed for proper interference. Optical interferometric measurements require very precise pointing (0.03 as, 1-(sigma) radial) for maximizing the interference pattern visibility. This requirement is achieved by fine pointing control of articulating pointing mirrors with feedback from angle tracking cameras. The overall pointing system design concept is presentcd. Functional requirements and an acquisition concept are given. Guide and Science pointing control loops are discussed. Simulation analyses demonstrate the feasibility of the design.
    Keywords: Spacecraft Instrumentation and Astrionics
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  • 2
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    Spitzer Space Telescope: Focal Plane Survey Final Report (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: This final report summarizes the results and accuracies of the Spitzer Space Telescope focal plane survey. Accuracies achieved are compared to the focal plane survey calibration requirements put forth in the SIRTF IOC-SV Mission Plan [14] and pre-flight predictions made in [2]. The results of this focal plane survey are presently being used to support in-flight precision pointing, precision incremental offsets, IRS peakup array calibration, and ground pointing reconstruction...
    Keywords: Optics
    Type: JPL-D-27667-B
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  • 3
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    Attitude Controller for the Atmospheric Entry of the Mars Science Laboratory (2008)
    In:  Other Sources
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    Publication Date: 2019-08-24
    Description: This paper describes the attitude controller for the atmospheric entry of the Mars Science Laboratory (MSL). The controller will command 8 RCS thrusters to control the 3- axis attitude of the entry capsule. The Entry Controller is formulated as three independent channels in the control frame, which is nominally aligned with the stability frame. Each channel has a feedfoward and a feedback path. The feedforward path enables fast response to large bank commands. The feedback path stabilizes the vehicle angle of attack and sideslip around its trim position, and tracks bank commands. The feedback path has a PD/D control structure with deadbands that minimizes fuel usage. The performance of this design is demonstrated via computer simulations.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 2008 AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 4
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    An Integrated Optimal Estimation Approach to Spitzer Space Telescope Focal Plane Survey (2004)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper discusses an accurate and efficient method for focal plane survey that was used for the Spitzer Space Telescope. The approach is based on using a high-order 37-state Instrument Pointing Frame (IPF) Kalman filter that combines both engineering parameters and science parameters into a single filter formulation. In this approach, engineering parameters such as pointing alignments, thermomechanical drift and gyro drifts are estimated along with science parameters such as plate scales and optical distortions. This integrated approach has many advantages compared to estimating the engineering and science parameters separately. The resulting focal plane survey approach is applicable to a diverse range of science instruments such as imaging cameras, spectroscopy slits, and scanning-type arrays alike. The paper will summarize results from applying the IPF Kalman Filter to calibrating the Spitzer Space Telescope focal plane, containing the MIPS, IRAC, and the IRS science Instrument arrays.
    Keywords: Optics
    Type: SPIE Astronomical Telescopes and Instrumentation; Jun 21, 2004 - Jun 25, 2004; Glasgow; United Kingdom
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  • 5
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    Entry Attitude Controller for the Mars Science Laboratory (2007)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper describes the preliminary concept for the RCS 3-axis attitude controller for the exo-atmospheric and guided entry phases of the Mars Science Laboratory Entry, Descend and Landing. The entry controller is formulated as three independent channels in the control frame, which is nominally aligned with the stability frame. Each channel has a feedfoward and a feedback. The feedforward path enables fast response to large bank commands. The feedback path stabilizes the vehicle angle of attack and sideslip around its trim position, and tracks bank commands. The feedback path has a PD/D structure with deadbands that minimizes fuel usage. The performance of this design is demonstrated via simulation.
    Keywords: Spacecraft Design, Testing and Performance
    Type: IEEEAC 1500, Version 3 , IEEE Aerospace Conference; Mar 03, 2007 - Mar 10, 2007; Big Sky, MT; United States
    Format: text
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  • 6
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    Pointing Control System Architecture for the Eclipse Mission (2006)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper describes the high performance pointing control system used to point the Eclipse telescope. Eclipse is a new mission under study at Jet Propulsion Laboratory for a proposal as a discovery mission. Eclipse is a space telescope for high-contrast optical astronomy. It will be used to investigate the planetary bodies and environments. The main objective of the Eclipse mission is to study planets around nearby stars. Eclipse is designed to reveal planets or dust structures by reducing the scattered and diffracted light within a few arcseconds of a star to a level three orders of magnitude lower than any instrument on the Hubble Space Telescope (HST). Eclipse achieves this high contrast using a 1.8 meter diameter telescope, a coronagraphic system for control of diffracted light, and active wavefront correction using a Precision Deformable Mirror (DM) for the suppression of scattered light. The observatory will be launched into a Sun-synchronous 690 Km, 98.2(deg) Earth Orbit in 2012.
    Keywords: Astronomy
    Type: AAS 06-073 , 29th Annual American Astronautical Society Guidance and Control Conference; Feb 04, 2006 - Feb 08, 2006; Breckenridge, CO; United States
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  • 7
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    Exo-C: a Probe-Scale Space Mission to Directly Image and Spectroscopically Characterize Exoplanetary Systems Using an Internal Coronagraph (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: "Exo-C" is NASA's first community study of a modest aperture space telescope designed for high contrast observations of exoplanetary systems. The mission will be capable of taking optical spectra of nearby exoplanets in reflected light, discover previously undetected planets, and imaging structure in a large sample of circumstellar disks. It will obtain unique science results on planets down to super-Earth sizes and serve as a technology pathfinder toward an eventual flagship-class mission to find and characterize habitable exoplanets. We present the mission/payload design and highlight steps to reduce mission cost/risk relative to previous mission concepts. At the study conclusion in 2015, NASA will evaluate it for potential development at the end of this decade. Keywords: Exoplanets, high contrast imaging, optical astronomy, space mission concepts
    Keywords: Astrophysics
    Type: GSFC-E-DAA-TN16540
    Format: application/pdf
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  • 8
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    SIRTF Focal Plane Survey: A Pre-flight Error Analysis (2003)
    In:  Other Sources
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    Publication Date: 2019-07-12
    Description: This report contains a pre-flight error analysis of the calibration accuracies expected from implementing the currently planned SIRTF focal plane survey strategy. The main purpose of this study is to verify that the planned strategy will meet focal plane survey calibration requirements (as put forth in the SIRTF IOC-SV Mission Plan [4]), and to quantify the actual accuracies expected. The error analysis was performed by running the Instrument Pointing Frame (IPF) Kalman filter on a complete set of simulated IOC-SV survey data, and studying the resulting propagated covariances. The main conclusion of this study is that the all focal plane calibration requirements can be met with the currently planned survey strategy. The associated margins range from 3 to 95 percent, and tend to be smallest for frames having a 0.14" requirement, and largest for frames having a more generous 0.28" (or larger) requirement. The smallest margin of 3 percent is associated with the IRAC 3.6 and 5.8 micron array centers (frames 068 and 069), and the largest margin of 95 percent is associated with the MIPS 160 micron array center (frame 087). For pointing purposes, the most critical calibrations are for the IRS Peakup sweet spots and short wavelength slit centers (frames 019, 023, 052, 028, 034). Results show that these frames are meeting their 0.14" requirements with an expected accuracy of approximately 0.1", which corresponds to a 28 percent margin.
    Keywords: Space Transportation and Safety
    Type: JPL-D-26678
    Format: text
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  • 9
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    Mars Science Lander GN&C Design for Entry, Descent, and Landing (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: International ESA Conference on Guidance and Navigation Control Systems; Jun 05, 2011 - Jun 10, 2011; Carlsbad; Czechoslovakia
    Format: text
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