scholarly journals The Eu:CROPIS Mass Property Campaign: Trimming a Spin-Stabilized Compact Satellite for a Long-Term Artificial Gravity Experiment

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Fabian Orlowski-Feldhusen ◽  
Sebastian Kottmeier ◽  
Ansgar Heidecker ◽  
Olaf Mierheim ◽  
Oliver Kolakowski ◽  
...  
Keyword(s):  
Attitude Control ◽  
Life Support ◽  
Moment Of Inertia ◽  
Attitude Control System ◽  
Satellite Mission ◽  
Spin Stabilization ◽  
Mass Property ◽  
Property Measurement ◽  
Flight Model

Eu:CROPIS (Euglena Combined Regenerative Organic Food Production in Space) is the first mission of DLR’s compact satellite program. The launch of Eu:CROPIS took place on December 3rd in 2018 on-board the Falcon 9 SSO-A mission. The satellite’s primary payload Eu:CROPIS features a biological experiment in the context of closed loop coupled life support systems. The Eu:CROPIS satellite mission uses spin stabilization along its Z -axis to provide defined acceleration levels for the primary and secondary payloads to simulate either a Moon or Mars gravity environment. For the payload performance, it is vital to achieve a minimum deviation between spacecraft Z -axis and the major moment of inertia (MoI) axis to minimize the offset of the envisaged acceleration levels. Specific moment of inertia ratios between the spin- and minor axes had to be maintained to allow the attitude control system to keep the satellite at a stable rotation despite environmental disturbances. This paper presents the adaptive and flexible trimming strategy applied during the flight model production, as well as the mass property measurement acceptance campaign and the respective results.

Development experience of the attitude control system using single-axis control moment gyros for long-term orbiting space stations

1988 ◽  
Vol 18 ◽  
pp. 91-98 ◽  
Author(s):  
V.N. Branets ◽  
D.M. Weinberg ◽  
V.P. Verestchagin ◽  
N.N. Danilov-Nitusov ◽  
V.P. Legostayev ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Control Moment ◽  
Development Experience

Fault Diagnosis and Fault-Tolerant Control of Micro-Satellite Propulsion Mode Attitude Control

2015 ◽  
Vol 764-765 ◽  
pp. 607-612
Author(s):  
Ho Nien Shou
Keyword(s):  
Attitude Control ◽  
Unscented Kalman Filter ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Fault Detection And Diagnosis ◽  
Attitude Control System ◽  
Orbit Control ◽  
Thrust Control ◽  
Detection And Diagnosis

Micro-satellite has long-term in-orbit work in the harsh environment of space, the components such as actuators and sensors in the attitude control system continue to perform in-orbit control operations, therefore are prone to faults. In practical mission, such as formation flying, orbital transfer, de-tumbing and attitude control need to use thruster to control. As the thrust control is fail, the entire mission fails. In the paper, the two-stage unscented kalman filter is used to obtain the effectiveness factor value and system estimated states are obtained. Meanwhile, a robust thruster controller is designed with the estimated results to accomplish the joint design of Fault Detection and Diagnosis and Fault-Tolerant Control.

scholarly journals Design of Attitude Control Systems for CubeSat-Class Nanosatellite

2013 ◽  
Vol 2013 ◽  
pp. 1-15 ◽  
Author(s):  
Junquan Li ◽  
Mark Post ◽  
Thomas Wright ◽  
Regina Lee
Keyword(s):  
Control System ◽  
System Design ◽  
Attitude Control ◽  
Low Cost ◽  
Control System Design ◽  
Nonlinear Controller ◽  
Attitude Control System ◽  
Satellite Mission ◽  
Design Work ◽  
Fine Control

We present a satellite attitude control system design using low-cost hardware and software for a 1U CubeSat. The attitude control system architecture is a crucial subsystem for any satellite mission since precise pointing is often required to meet mission objectives. The accuracy and precision requirements are even more challenging for small satellites where limited volume, mass, and power are available for the attitude control system hardware. In this proposed embedded attitude control system design for a 1U CubeSat, pointing is obtained through a two-stage approach involving coarse and fine control modes. Fine control is achieved through the use of three reaction wheels or three magnetorquers and one reaction wheel along the pitch axis. Significant design work has been conducted to realize the proposed architecture. In this paper, we present an overview of the embedded attitude control system design; the verification results from numerical simulation studies to demonstrate the performance of a CubeSat-class nanosatellite; and a series of air-bearing verification tests on nanosatellite attitude control system hardware that compares the performance of the proposed nonlinear controller with a proportional-integral-derivative controller.

scholarly journals Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite

2018 ◽  
Vol 2018 ◽  
pp. 1-13 ◽  
Author(s):  
Anwar Ali ◽  
Shoaib Ahmed Khan ◽  
M. Usman Khan ◽  
Haider Ali ◽  
M. Rizwan Mughal ◽  
...  
Keyword(s):  
Modular Forms ◽  
Power Distribution ◽  
Attitude Control ◽  
Power Efficiency ◽  
Electric Power System ◽  
Testing Time ◽  
Attitude Control System ◽  
Satellite Mission ◽  
Essential Components ◽  
Commercial Off The Shelf

The Electric Power System (EPS) and attitude control system (ACS) are the essential components of any satellite. EPS and ACS efficiency and compactness are substantial for the proper operation and performance of the satellite’s entire mission life. So, realizing the significance of EPS and ACS subsystems for any satellite, they have been assimilated and developed in modular forms focusing on efficiency and compactness. The EPS is comprised of three modules called the solar panel module (SPM), power conditioning module (PCM), and power distribution module (PDM) while the ACS has an embedded magnetorquer coil. For compactness and miniaturization purposes, the magnetorquer coil is embedded inside the SPM. The components used are commercial off-the-shelf (COTS) components emphasizing on their power efficiency, small dimensions, and weight. Latch-up protection systems have been designed and analyzed for CMOS-based COTS components, in order to make them suitable for space radioactive environment. The main design features are modularity, redundancy, power efficiency, and to avoid single component failure. The modular development of the EPS and ACS helps to reuse them for future missions, and as a result, the overall budget, development, and testing time and cost are reduced. A specific satellite mission can be achieved by reassembling the required subsystems.

Double Fail-Safe Attitude Control System for Artificial Meteor Microsatellite ALE-1

2021 ◽  
Vol 19 (1) ◽  
pp. 9-16
Author(s):  
Shinya FUJITA ◽  
Yuji SATO ◽  
Toshinori KUWAHARA ◽  
Yuji SAKAMOTO ◽  
Yoshihiko SHIBUYA ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Fail Safe

67. Loving your child to death: Considerations of the care of chronically-ill children and euthanasia in Emil Sher's Mourning Dove and implications for medical educations

2007 ◽  
Vol 30 (4) ◽  
pp. 65
Author(s):  
K. Mukhida
Keyword(s):  
Life Support ◽  
Terminally Ill ◽  
Chronically Ill ◽  
Legal Aspects ◽  
Mourning Dove ◽  
Medical Professionals ◽  
Constant Pain ◽  
Withdraw Life Support ◽  
Wheat Farmer

How do parents cope when their child is ill or dying, when he or she experiences constant pain or suffering? What do parents think of the contributions that medical professionals make to the care of their chronically or terminally ill child? Is it possible for a parent to love a child so much that the child is wished dead? The purpose of this paper is to explore those questions and aspects of the care of chronically or terminally ill children using Mourning Dove’s portrayal of one family’s attempt to care for their ill daughter. A play written by Canadian playwright Emil Sher, Mourning Dove is based on the case of Saskatchewan wheat farmer Robert Latimer who killed his 12 year old daughter Tracy who suffered with cerebral palsy and lived in tremendous pain. Rather than focusing on the medical or legal aspects of the care of a chronically ill child, the play offers a glimpse into how a family copes with the care of such a child and the effects the child’s illness has on a family. Reading and examination of non-medical literature, such as Mourning Dove, therefore serve as a useful means for medical professionals to better understand how illness affects and is responded to by patients and their families. This understanding is a prerequisite for them to be able to provide complete care of children with chronic or terminal illnesses and their families. Nuutila L, Salanterä S. Children with long-term illness: parents’ experiences of care. J Pediatr Nurs 2006; 21(2):153-160. Sharman M, Meert KL, Sarnaik AP. What influences parents’ decisions to limit or withdraw life support? Pediatr Crit Care Med 2005; 6(5):513-518. Steele R. Strategies used by families to navigate uncharted territory when a child is dying. J Palliat Care 2005; 21(2):103-110.

Flight performance of the LES-8/9 three-axis attitude control system

1980 ◽  
Author(s):  
F. FLOYD ◽  
C. MUCH ◽  
N. SMITH ◽  
J. VERNAU ◽  
J. WOODS
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Flight Performance ◽  
Attitude Control System
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