MiniCarb: A Passive, Occultation-Viewing, 6U CubeSat for Observations of CO2, CH4, and H2O

2021 ◽  
Author(s):  
Emily L Wilson ◽  
Vincent J. Riot ◽  
A. J. DiGregorio ◽  
guruthisvaran Ramu ◽  
Paul Cleveland ◽  
...  
Keyword(s):  
Attitude Control ◽  
Low Cost ◽  
Lawrence Livermore National Laboratory ◽  
National Laboratory ◽  
Space Station ◽  
Solar Panels ◽  
Attitude Control System ◽  
Environmental Testing ◽  
Nasa Goddard Space ◽  
Modular Platform

Abstract We present the final design, environmental testing, and launch history of MiniCarb, a 6U CubeSat developed through a partnership between NASA Goddard Space Flight Center and Lawrence Livermore National Laboratory. MiniCarb’s science payload, developed at Goddard, was an occultation-viewing, passive laser heterodyne radiometer for observing methane, carbon dioxide, and water vapor in Earth’s atmosphere at ~1.6 microns. MiniCarb’s satellite, developed at Livermore, implemented their CubeSat Next Generation Bus plug-and-play architecture to produce a modular platform that could be tailored to a range of science payloads. Following the launch on December 5, 2019, MiniCarb traveled to the International Space Station and was set into orbit on February 1, 2020 via Northrop Grumman’s (NG) Cygnus capsule which deployed MiniCarb with tipoff rotation of about 20 deg/sec (significantly higher than the typical rate of 3 deg/sec from prior CubeSats), from which the attitude control system was unable to recover resulting in a loss of power. In spite of this early failure, MiniCarb had many successes including rigorous environmental testing, successful deployment of its solar panels, and a successful test of the radio and communication through the Iridium network. This prior work and enticing cost (approximately $2M for the satellite and $250K for the payload) makes MiniCarb an ideal candidate for a low-cost and rapid rebuild as a single orbiter or constellation to globally observe key greenhouse gases.

Development of a Low-Cost, Open Hardware Attitude Control System for High Powered Rockets

2015 ◽  
Author(s):  
Erin S. Schmidt ◽  
Jeremy Louke ◽  
Kenneth Amell ◽  
Jeff Hickman ◽  
Brentley Wiles
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Low Cost ◽  
Attitude Control System ◽  
Open Hardware

ADDASAT Development Plan for the Attitude Control System

2013 ◽  
Vol 436 ◽  
pp. 47-53
Author(s):  
Radu D. Rugescu ◽  
Mihai Al. Barbelian ◽  
Efim Micu
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Low Cost ◽  
Environmental Policies ◽  
Laboratory Model ◽  
Land Resources ◽  
Attitude Control System ◽  
Low Friction ◽  
Orbital System ◽  
Real Scale

As a part of the ORVEAL project, a real scale laboratory model of the inertial platform for ADDASAT is developed by the joint ADDA and UPB teams, ensuring the capability of a three-axis attitude control demonstration in the ground laboratory that simulates weightlessness by low friction bearings. The study is part of the larger ADDA-UPB program for developing the low cost NERVA orbital system for applications in enhanced environmental policies and land resources surveillance. The ORVEAL research is granted by Romanian UEFISCDI financing authority.

Space Station RCS attitude control system

1991 ◽  
Author(s):  
STEVEN LEE ◽  
REINHOLD MATULENKO ◽  
J. CALDWELL
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Space Station ◽  
Attitude Control System

Multifunctional Structures for Attitude Control

2019 ◽  
Author(s):  
Vedant ◽  
James T. Allison
Keyword(s):  
Attitude Control ◽  
Mechanical Vibration ◽  
Systems Design ◽  
Small Strain ◽  
Small Displacement ◽  
Solar Panels ◽  
Attitude Control System ◽  
Deployable Structures ◽  
Solar Arrays ◽  
Satellite Attitude Control

Abstract The Engineering Systems Design Lab (ESDL) at the University of Illinois introduced Strain-Actuated Solar Arrays (SASAs) as a solution for precise satellite Attitude Control System (ACSs). SASA is designed to provide active mechanical vibration (jitter) cancellation, as well as small slew maneuver capabilities to hold a pose for short time periods. Current SASA implementations utilize piezoelectric distributed actuators to strain deployable structures, and the resulting momentum transfer rotates the spacecraft bus. A core disadvantage, however, is small strain and slew capability. Initial SASA systems could help improve pointing accuracy, but must be coupled with another ACS technology to produce large reorientations. A novel extension of the original SASA system is presented here that overcomes the small-displacement limitation, enabling use of SASA as a sole ACS for some missions, or in conjunction with other ACSs. This extension, known as Multifunctional Structures for Attitude Control (MSAC), can produce arbitrarily-large rotations, and has the potential to scale to large spacecraft. The system utilizes existing flexible deployable structures (such as solar arrays or radiators) as multifunctional devices. This multi-role use of solar panels extends their utility at a low mass penalty, while increasing reliability of the spacecraft ACS.

scholarly journals Satellite Attitude Control System Design considering the Fuel Slosh Dynamics

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Luiz Carlos Gadelha de Souza ◽  
Alain G. de Souza
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Rigid Motion ◽  
Linear Quadratic Regulator ◽  
Solar Panels ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Fuel Slosh

The design of the satellite attitude control system (ACS) becomes more complex when the satellite structure has different type of components like, flexible solar panels, antennas, mechanical manipulators, and tanks with fuel. A crucial interaction can occur between the fuel slosh motion and the satellite rigid motion during translational and/or rotational manoeuvre since these interactions can change the satellite centre of mass position damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances thus affecting the satellite attitude acquisition. As a result, the design of the satellite controller needs to explore the limits between the conflicting requirements of performance and robustness. This paper investigates the effects of the interaction between the liquid motion (slosh) and the satellite dynamics in order to predict what the damage to the controller performance and robustness is. The fuel slosh dynamics is modelled by a pendulum which parameters are identified using the Kalman filter technique. This information is used to design the satellite controller by the linear quadratic regulator (LQR) and linear quadratic Gaussian (LQG) methods to perform a planar manoeuvre assuming thrusters are actuators.

Adaptive control applied to Space Station attitude control system

1992 ◽  
Author(s):  
QUANG LAM ◽  
RICHARD CHIPMAN ◽  
TSAY-HSIN HU ◽  
ERIC HOLMES ◽  
JOHN SUNKEL
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Space Station ◽  
Attitude Control System

scholarly journals Sun-Pointing Attitude Control Scheme for Magnetic-based Satellite

2021 ◽  
Author(s):  
Xiwang Xia ◽  
Yonghe ZHANG ◽  
Jun Jiang
Keyword(s):  
Attitude Control ◽  
Attitude Determination ◽  
Direct Method ◽  
Low Cost ◽  
Solar Array ◽  
Solar Panels ◽  
Control Effort ◽  
Control Scheme ◽  
Control Schemes ◽  
Magnetic Attitude Control

Abstract For some low-orbit satellites, SADA (solar array drive assembly) is not necessary but steady sun-pointing is required. Magnetic-based attitude control schemes are adopted by more and more low-cost low-orbit satellites and magnetic-based sunpointing attitude control schemes have been proposed for various satellites. For magnetic Attitude Determination and Control System (ADCS), magnetometer and magnetic torquer are the core ADCS components while sun sensor and gyro, which would be employed to determine or estimate sun vector, are important ones. Due to the underactuated characteristics, magnetic attitude control torque could not stabilize the full attitude but the two components of the attitude, simultaneously, which means that magnetic attitude control effort could orientate the solar panels to the Sun. A Lyapunov function, combining the rotational energy and sun angle, is formulated and a PD-type sun-pointing attitude control scheme is proposed to meet the requirements corresponding to sun-pointing task. Further, the effectiveness of the PD-type sun angle-based magnetic attitude control scheme, composed of proportional term, damping term and spinning term, has been verified by use of Lyapunov direct method. Simulations show that, the proposed PD-type attitude control scheme is a suitable sun-pointing scheme for magnetic satellites.

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