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Measurement of SPT-140 Hall Thruster Swirl Torque during the Psyche Mission

Measurement of SPT-140 Hall Thruster Swirl Torque during the...

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AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Snyder, John Steven Nicholas, Austin K. Collins, Steven M. Ortega, Alejandro Lopez Electric Propulsion Group Jet Propulsion Laboratory California Institute of Technology PasadenaCA United States Navigation and Control Systems Engineer Jet Propulsion Laboratory California Institute of Technology PasadenaCA United States Guidance and Control Systems Section Jet Propulsion Laboratory California Institute of Technology PasadenaCA United States

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

Hall-thruster swirl torque is small enough that it is difficult to measure in ground-based facilities, but large enough that its effects on interplanetary spacecraft can be significant and must be actively managed. NASA’s Psyche mission has provided the first opportunity to directly measure the swirl torque produced by a Hall thruster operating at powers greater than 1.5 kW. When the electric propulsion system is operating, the spacecraft attitude control methodology forces the net torque on the spacecraft to align with a pre-determined direction in the body frame, after which the thruster-induced swirl torque can be separated from the other torques acting on the spacecraft. The swirl torques produced by three of the four thrusters on the Psyche spacecraft were determined over the full operating discharge power range of 1.0 to 4.5 kW, and the maximum value of that torque was 0.86 mN-m at full power. It is shown that the SPT-140 swirl torque results can be scaled from full power to lower powers by the product of the discharge current and the magnet current, and evaluation of cruise thrusting data as the thruster is throttled down in power suggests that swirl torque is not changing significantly with time as a function of operating condition. Finally, calculations of swirl torque using updated numerical simulations are shown to agree reasonably well with the flight data, thus providing confidence in their use for other thrusters prior to flight. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： NASA

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Current Status and Analyses of the SPLICE Hazard Detection Software

Current Status and Analyses of the SPLICE Hazard Detection S...

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AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Liu, John Y. Chen, Po-Ting Aldrich, Jack D. Bocchino, Robert L. Vaughan, Geoffrey Jet Propulsion Laboratory California Institute of Technology Payload/Instrument Pointing Control Systems Engineering Guidance and Control Section 4800 Oak Grove Drive PasadenaCA91109 United States Jet Propulsion Laboratory California Institute of Technology Guidance and Control Section 4800 Oak Grove Drive PasadenaCA91109 United States Jet Propulsion Laboratory California Institute of Technology Flight Software and Avionics Systems Section 4800 Oak Grove Drive PasadenaCA91109 United States

This paper provides a status report of the current development and analysis efforts for the hazard detection (HD) software for the Safe and Precise Landing-Integrated Capabilities Evolution (SPLICE) project. © 20... 详细信息

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

关键词： Hazards

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ELSA: Europa Lander Lidar Sensor Assembly – Field Testing and Performance Analysis

ELSA: Europa Lander Lidar Sensor Assembly – Field Testing a...

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AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Katake, Anup B. Chen, Po-Ting Konefat, Edward Zapien, Xavier Clouse, Daniel Ryan, Daniel Bolduc, Andrew Gebara, Christine Berger, Lindsey Alexander, James Miguel San Martin, A. Bakalski, Ivelin Portier, Joel Machan, Roman Reed, Daniel Group Supervisor Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Field Test Planner Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Robotics Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Instruments Division Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Mechanical Engineering Division Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Environmental Requirements Engineering Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States 4600 Forbes Boulevard LanhamMD20706 United States

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

To enable safe landing on unknown terrain, such as Europa, JPL has been developing next- generation dual-mode lidars that can provide long range altimetry as well as dense 3D mapping in real-time during landing. In this paper, we discuss the design, integration, and performance of one of the lidars built in partnership with industry. A form, fit, function and performance equivalent lidar model was field-tested on a fully instrumented helicopter platform over natural terrains and man-made targets. We present some of the highlights from the various flight tests. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Flight testing

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Auxiliary Gyroscope Approach for Balanced Performance via Gyro Self-Calibration

Auxiliary Gyroscope Approach for Balanced Performance via Gy...

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International Symposium on Inertial Sensors and Systems INERTIAL

作者： John Y. Liu Guidance & Control Section Jet Propulsion Laboratory California Institute of Technology Pasadena CA USA

Gyro noise and bias are often performance limiting factors in space and terrestrial navigation systems, especially in cases where no aiding sensors are available. A gyro unit with good performance in both noise and bias may be very expensive and with undesirable SWaP. In this paper, we propose to make use of the self-calibrating capabilities of an inexpensive MEMS Coriolis Vibratory Gyros (CVG) gyro as an auxiliary sensor for a set of primary gyros of any type, including those not capable of self-calibrating, to greatly reduce the biases of the primary and auxiliary gyros, as the primary gyros' biases can all be made observable and calibratable using the auxiliary CVG's self-calibration capability in real-time without impacting the normal use of the primary gyros. The combined gyro system can therefore retain the good noise performance of the primary gyros while greatly improving on its bias stability performance.

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Cis-lunar navigation accuracy using optical observations of natural and artificial targets

Cis-lunar navigation accuracy using optical observations of ...

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AAS/AIAA Astrodynamics Specialist Conference, 2019

作者： Bradley, Nicholas Olikara, Zubin Bhaskaran, Shyam Young, Brian Outer Planet Navigation Group Mission Design and Navigation Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Inner Planet Mission Analysis Group Mission Design and Navigation Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Flight Path Control Group Mission Design and Navigation Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States

ISBN: (纸本)9780877036654

On-board optical-based autonomous navigation (AutoNav) has the potential to significantly reduce reliance on ground-based assets, and can provide a robust back-up system for unexpected ground outages. We continue an investigation of AutoNav across the solar system by assessing optical-only navigation performance in cis-lunar space using simulated observations of the center of the Moon, lunar landmarks, artificial satellites, and asteroids. We show that AutoNav in cis-lunar space is feasible and effective, and that artificial satellites, the Moon center, and lunar landmarks are effective targets for navigation. Optical AutoNav is feasible within current technological capabilities. © 2020, Univelt Inc. All rights reserved.

关键词： Moon

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High precision pointing control for WFIRST CGI instrument 42nd

High precision pointing control for WFIRST CGI instrument

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42nd AAS Rocky Mountain section Guidance and control Conference, 2019

作者： Fathpour, Nanaz Alvarez-Salazar, Oscar Arndt, David Mandić, Milan Shields, Joel Sirlin, Sam Valverde, Alfredo Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology MS 198-326 4800 Oak Grove Drive PasadenaCA91109-8099 United States Guidance and Control Section Jet Propulsion Laboratory United States

ISBN: (纸本)9780877036616

Coronagraph Instrument (CGI) is one of two instruments on the Wide Field Infrared Survey Telescope (WFIRST), a NASA observatory, currently planned to launch in 2025. CGI is a JPL instrument and includes an imaging mode and a spectroscopic mode to perform exoplanet direct imaging and spectroscopic characterization of planets and debris disks around nearby stars. In order to achieve a very tight contrast stability, it requires pointing stability of 0.7 milliarcsecond (mas) RMS over the duration of the observation. This paper discusses CGI pointing architecture and approach to achieve this level of pointing performance, and flight implementation of the pointing system. The architecture is based on nested loops to reject Line Of Sight (LOS) jitter due to one of the largest disturbances on board, the reaction wheel assembly (RWA), as well as other disturbance sources, and thermal drift. The control architecture includes spacecraft ACS, as a feedback control that uses the low-order wavefront sensing (LOWFS) camera and Fast Steering Mirror (FSM) to suppress the telescope pointing drift and jitter, and a feedforward control, that is used to reject sinusoidal tones of the RWA. The LOWFS camera uses high flux from the obscured science target to achieve high sampling rate measurements of the LOS. The FSM has a local control loop that is used to linearize the piezoelectric actuators (PZT) hysteresis. Local feedback of the PZT displacement is provided by strain gauge sensors. This paper will present various aspects of the controller design, some sensor modeling, performance simulation, and operational constraints during CGI observations to meet tight pointing requirements. Some results from our control Analysis Simulation Testbed (CAST) will be reported. © 2019. California Institute of Technology.

关键词： Cameras

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Adaptations of guidance, navigation, and control verification and validation philosophies for small spacecraft 42nd

Adaptations of guidance, navigation, and control verificatio...

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42nd AAS Rocky Mountain section Guidance and control Conference, 2019

作者： Pong, Christopher M. Sternberg, David C. Chen, George T. Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States

ISBN: (纸本)9780877036616

Decades of experience developing increasingly capable and more complex spacecraft have resulted in a set of accepted practices and philosophies to verify and validate (V&V) guidance, navigation, and control (GN&C) subsystems. Until recently, small, low-cost spacecraft have had very simple or non-existent GN&C subsystems requiring minimal or no subsystem testing. As the next generation of small spacecraft take on more challenging GN&C requirements, the GN&C community is struggling with how to scale the subsystem V&V effort to produce spacecraft approaching the reliability of flagship-class missions while staying within the reduced resources of a small satellite project. For this paper, we will examine five aspects of GN&C V&V (requirements definition, software testing and analysis, hardware component testing, integrated vehicle testing, and in-flight V&V) and compare the V&V campaign of a flagship-class mission (Mars 2020) to that of two recent, successful CubeSat missions: ASTERIA and MarCO. Experiences from the development of these CubeSats yield valuable lessons learned and guidelines for future small spacecraft designers. © 2019, Univelt Inc. All rights reserved.

关键词： C (programming language)

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Demonstration of stereo vision for Deorbit descent and landing 42nd

Demonstration of stereo vision for Deorbit descent and landi...

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42nd AAS Rocky Mountain section Guidance and control Conference, 2019

作者： Sternberg, David C. Setterfield, Timothy P. Bailey, Erik S. Ansar, Adnan I. Johnson, Andrew E. Payload/Instrument Pointing Control Systems Engineering Group Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States GN&C Hardware and Testbed Development Group Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States EDL Guidance and Control Systems Group Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Aerial and Orbital Image Analysis Group Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States Guidance and Control Section Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive PasadenaCA91109 United States

ISBN: (纸本)9780877036616

Planetary landers need to reduce velocity at low altitude for soft landing. Traditionally, estimating velocity and altitude has been performed with radar sensors whose performance meets the specific mission needs. There are not very many options for these sensors and they are difficult to include in a flight system either due to obsolescence, prohibitive cost or difficulty in accommodation. Recently, alternative sensing modalities are being pursued including Doppler LiDAR and vision. This paper describes results from a recent helicopter field test of a binocular stereo vision system for deorbit descent and landing applications. The system consisted of two 18.6˚ field of view cameras mounted 1.7m apart. Post processing of the images showed ranging accuracy better than 1% up to 500m and 17 cm/s velocimetry accuracy at 37m. For a flight system these images could be input into an FPGA-based processor which processes dense stereo and visual odometry in less than 1 second to achieve the stereo ranging frame rates required for soft landing. When coupled with vision based Terrain Relative Navigation this stereo system enables landing accuracies on the order of 10m. © 2019. California Institute of Technology.

关键词： Optical radar

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Lidar-generated digital elevation models for hazard detection - Requirements and analysis 42nd

Lidar-generated digital elevation models for hazard detectio...

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42nd AAS Rocky Mountain section Guidance and control Conference, 2019

作者： Chen, Po-Ting Kaki, Siddarth San Martin, A. Miguel Skulsky, David Katake, Anup Trawny, Nikolas Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Dr. PasadenaCA91109 United States Guidance and Control Section MS 198-326 United States Dept. of Aerospace Engineering and Engineering Mechanics The University of Texas AustinTX78712 United States Guidance and Control Section MS 198-326 United States Guidance and Control Section MS 321-560 United States Guidance and Control Section MS 198-235 United States

ISBN: (纸本)9780877036616

Hazard detection is an enabling technology for safe landing on planetary bodies with limited terrain knowledge, such as Jupiter’s icy moon Europa. Using a Light Detection and Ranging (LIDAR) sensor, a lander scans the landing site and constructs a Digital Elevation Model (DEM) in real-time during descent. This DEM is processed by hazard detection algorithms to construct a safety cost map and determine the safest landing location. The target location is then provided to the guidance and control system to execute a hazard avoidance divert maneuver. We derived requirements on the DEM quality and accuracy from the proposed Europa Lander Deorbit, Descent, and Landing (DDL) concept of operations and the lander hazard tolerance. A modular geometric LIDAR modeling tool and re-gridding algorithms were developed and integrated into a highfidelity 6-DOF dynamics simulation. The modular nature of the model allows us to simulate various detector aspect ratios, laser pulse repetition rates, scan mechanisms, optical designs, and basic error models. This tool was developed to support the parametric sensitivity analysis of the DEM quality with respect to the LIDAR design, site topography, scanning pattern, noise properties, and navigation state knowledge errors, and to evaluate the generated DEMs against the Europa Lander requirements. © 2019, Univelt Inc. All rights reserved.

关键词： Optical radar

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The cassini mission: Reconstructing thirteen years of the most complex gravity-assist trajectory flown to date 15th

The cassini mission: Reconstructing thirteen years of the mo...

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15th International Conference on Space Operations, SpaceOps 2018

作者： Bellerose, Julie Roth, Duane Wagner, Sean Outer Planet Navigation Group Mission Design and Navigation Section Jet Propulsion Laboratory / Caltech Pasadena91109 United States Mission Design and Navigation Section Jet Propulsion Laboratory / Caltech Pasadena91109 United States Flight Path Control Group Mission Design and Navigation Section Jet Propulsion Laboratory / Caltech Pasadena91109 United States

ISBN: (数字)9781624105623

ISBN: (纸本)9781624105623

Cassini launched in 1997 and completed its prime mission, its Equinox first extended mission, and its Solstice second extended mission. Since its arrival at Saturn in 2004, Cassini completed almost 300 orbits around the planet. Over the span of the mission, significant improvements were made to all the major satellites ephemeris, and to Saturn gravitational and pole models. These improvements have enabled better trajectory reconstructions throughout the timeframe of the mission, although using about one hundred different models of the Saturn system. Now that the mission is over, the paper reports on the uniform reconstruction of the entire Cassini orbital mission, which uses one consistent Saturn system model and satellite ephemerides throughout. We discuss the challenges of undertaking this task, and comparison strategies for choosing the best and greatest Cassini trajectory for its very final delivery. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Orbits

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