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Orbit design and control of technology validation mission for refractive space telescope in formation flying

Orbit design and control of technology validation mission fo...

引用

AIAA Guidance, Navigation, and control Conference 2014 - SciTech Forum and Exposition 2014

作者： Park, Sang-Young Calhoun, Philip C. Shah, Neerav Williams, Trevor W. Yonsei University Seoul 120-749 Korea Republic of NASA Goddard Space Flight Center Greenbelt MD 20771 United States Astrodynamics and Control Lab Department of Astronomy Korea Republic of Attitude Control System Engineering Branch MS 591 8800 Greenbelt Rd Greenbelt MD 20771 United States Navigation and Mission Design Branch MS 595 8800 Greenbelt Rd Greenbelt MD 20771 United States

ISBN: (数字)9781624103179

ISBN: (纸本)9781600869624

Many proposed formation flying missions seek to advance the state of the art in spacecraft science imaging by utilizing precision dual spacecraft formation flying to enable a "virtual" telescope (VT). Using precision alignment of two spacecraft very long focal lengths can be achieved by locating the optics on one spacecraft and the detector on the other. Furthermore, orders of magnitude improvement in science imaging over conventional single spacecraft instruments is possible with advances in precision formation flying. Precise astrometric alignment control is required for accurate inertial pointing of the VT. This work presents orbit design and control approaches for VT formation flying, with specific application to the recently proposed Virtual Telescope Demonstration Mission (VTDM) using cubesats. The characteristics of the mission orbit are derived from solutions to Hill's equations for the relevant mission orbit. A relative orbit control technique pertaining to the astrometric alignment problem is developed by utilizing the Constrained Model Predictive control (CMPC) approach. This method enables design of formation flying control laws for a thruster assembly with limited magnitude. Precision formation flying is achieved by use of separate control laws for formation maintenance and precision astrometric alignment. The proposed control scheme compensates for inertial astrometric alignment errors as well as differences in orbital perturbations between the VTDM satellites. Numerical simulations are shown to validate the performance of the proposed relative orbit and alignment control laws for the VTDM. The results satisfy mission requirements and indicate the general applicability of the control algorithm to the VT formation flying architecture. Consequently, the proposed methods of orbit design and control can be applied to inertial astrometric alignment and formation keeping for the many proposed dual spacecraft precision formation flying missions.

关键词： Spacecraft

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Covariance analysis of astrometric alignment estimation architectures for precision dual spacecraft formation flying

Covariance analysis of astrometric alignment estimation arch...

引用

AIAA Guidance, Navigation, and control Conference 2012

作者： Calhoun, Philip C. Shah, Neerav Attitude Control System Engineering Branch NASA Goddard Space Flight Center MS 591 8800 Greenbelt Rd Greenbelt MD 20771 United States

ISBN: (数字)9781600869389

ISBN: (纸本)9781600869389

Many proposed formation flying missions seek to advance the state of the art in spacecraft science imaging by utilizing precision dual spacecraft formation flying to enable a "virtual" telescope. Using precision dual spacecraft alignment, very long focal lengths can be achieved by locating the optics on one spacecraft and the detector on the other. Proposed science missions include astrophysics concepts with spacecraft separations from 1000 km to 25,000 km, such as the Milli-Arc-Second Structure Imager (MASSIM) X-ray telescope and the New Worlds Observer exoplanet mission as well as, heliophysics concepts for solar coronagraphs and X-ray imaging with smaller separations (50m - 500m). All of these proposed missions require advances in precision formation flying of two spacecraft. In particular, very precise astrometric alignment control and estimation is required for accurate inertial pointing of the virtual telescope, which is required to perform the orders of magnitude improvement in the science imaging. The work presented in this paper focuses on analysis of proposed navigation systems and architectures for achieving precise dual spacecraft astrometric alignment. First, the dynamics of dual spacecraft relative motion, within a restricted n-body problem framework, are shown to reduce to a simple linear form and are used in estimation filter design and error analysis for deep space mission applications, such as MASSIM. This model is augmented with simplified measurement process models of relevant measurement types. These include inertial sensors, such as accelerometers and rate gyros, as well as optical alignment sensors, such as star and laser beacon trackers. A consider-state covariance analysis tool is developed from these process models and used to study the performance of proposed estimation architectures for the MASSIM application, specifically focusing on the transverse alignment between the two spacecraft with the goal of achieving mm-scale transverse alignm

关键词： Spacecraft

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Solar dynamics observatory on-orbit jitter testing, analysis, and mitigation plans

Solar dynamics observatory on-orbit jitter testing, analysis...

引用

AIAA Guidance, Navigation and control Conference 2011

作者： Liu, Kuo-Chia Blaurock, Carl A. Bourkland, Kristin L. Morgenstern, Wendy M. Maghami, Peiman G. Attitude Control System Engineering Branch NASA Goddard Space Flight Center Greenbelt MD 20771 United States AIAA United States Nightsky Systems Inc 301 Fayetteville St Raleigh NC 27601 United States

ISBN: (纸本)9781600869525

The recently launched Solar Dynamics Observatory (SDO) has two science instruments onboard that required sub-arcsecond pointing stability. Significant effort has been spent pre-launch to characterize the disturbances sources and validating jitter level at the component, sub-assembly, and spacecraft levels. However, an end-to-end jitter test emulating the flight condition was not performed on the ground due to cost and risk concerns. As a result, the true jitter level experienced on orbit remained uncertain prior to launch. Based on the pre-launch analysis, several operational constraints were placed on the observatory aimed to minimize the instrument jitter levels. If the actual jitter is below the analysis predictions, these operational constraints can be relaxed to reduce the burden of the flight operations team. The SDO team designed a three-day jitter test, utilizing the instrument sensors to measure pointing jitter up to 256 Hz. The test results were compared to pre-launch analysis predictions, used to determine which operational constraints can be relaxed, and analyzed for setting the jitter mitigation strategies for future SDO operations.

关键词： Orbits

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Filtering methods for error reduction in spacecraft attitude estimation using quaternion star trackers

Filtering methods for error reduction in spacecraft attitude...

引用

AIAA Guidance, Navigation and control Conference 2011

作者： Calhoun, Philip C. Sedlak, Joseph E. Superfin, Emil NASA Goddard Space Flight Center Attitude Control System Engineering Branch MS 591 8800 Greenbelt Rd. Greenbelt MD 20771 United States A.i. solutions Inc. Mission Services Division 10001 Derekwood Lane Lanham MD 20706 United States

ISBN: (纸本)9781600869525

Precision attitude determination for recent and planned space missions typically includes quaternion star trackers (ST) and a three-axis inertial reference unit (IRU). Sensor selection is based on estimates of knowledge accuracy attainable from a Kalman filter (KF), which provides the optimal solution for the case of linear dynamics with measurement and process errors characterized by random Gaussian noise with white spectrum. Non-Gaussian systematic errors in quaternion STs are often quite large and have an unpredictable time-varying nature, particularly when used in non-inertial pointing applications. Two filtering methods are proposed to reduce the attitude estimation error resulting from ST systematic errors, 1) extended Kalman filter (EKF) augmented with Markov states, 2) Unscented Kalman filter (UKF) with a periodic measurement model. Realistic assessments of the attitude estimation performance gains are demonstrated with both simulation and flight telemetry data from the Lunar Reconnaissance Orbiter.

关键词： Star trackers

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