Design and fabrication of a full-scale actively controlled satellite appendage simulator unit

Jack H. Jacobs; Dan Quenon; Steve Hadden; Rick Self

doi:10.1117/12.351569

9 July 1999 Design and fabrication of a full-scale actively controlled satellite appendage simulator unit

Jack H. Jacobs, Dan Quenon, Steve Hadden, Rick Self

Proceedings Volume 3674, Smart Structures and Materials 1999: Industrial and Commercial Applications of Smart Structures Technologies; (1999) https://doi.org/10.1117/12.351569
Event: 1999 Symposium on Smart Structures and Materials, 1999, Newport Beach, CA, United States

Abstract

Modern satellites require the ability to slew and settle quickly in order to acquire or transmit data efficiently. Solar arrays and communication antennas cause low frequency disturbances to the satellite bus during these maneuvers causing undesirable induced vibration of the payload. The ability to develop and experimentally demonstrate attitude control laws which compensate for these flexible body disturbances is of prime importance to modern day satellite manufacturers. Honeywell has designed and fabricated an actively controlled Appendage Simulator Unit (ASU) which can physically induce the modal characteristics of satellite appendages on to a ground based satellite test bed installed on an air bearing. The ASU consists of two orthogonal fulcrum beams weighting over 800 pounds each utilizing two electrodynamic shakers to induce active torques onto the bus. The ASU is programmed with the state space characteristics of the desired appendage and responds in real time to the bus motion to generate realistic disturbances back onto the satellite. Two LVDT's are used on each fulcrum beam to close the loop and insure the system responds in real time the same way a real solar array would on-orbit. Each axis is independently programmable in order to simulate various orientations or modal contributions from an appendage. The design process for the ASU involved the optimization of sensors, actuators, control authority, weight, power and functionality. The smart structure system design process and experimental results are described in detail.

Citation Download Citation

Jack H. Jacobs, Dan Quenon, Steve Hadden, and Rick Self "Design and fabrication of a full-scale actively controlled satellite appendage simulator unit", Proc. SPIE 3674, Smart Structures and Materials 1999: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 1999); https://doi.org/10.1117/12.351569

ACCESS THE FULL ARTICLE

INSTITUTIONAL
Select your institution to access the SPIE Digital Library.

SELECT YOUR INSTITUTION

PERSONAL
Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.

PERSONAL SIGN IN

No SPIE Account? Create one

PURCHASE THIS CONTENT

SUBSCRIBE TO DIGITAL LIBRARY

50 downloads per 1-year subscription

Members: $195

Non-members: $335 ADD TO CART

25 downloads per 1 - year subscription

Members: $145

Non-members: $250 ADD TO CART

PURCHASE SINGLE ARTICLE

Includes PDF, HTML & Video, when available

Members: $17.00

Non-members: $21.00 ADD TO CART

PROCEEDINGS
12 PAGES

DOWNLOAD PAPER SAVE TO MY LIBRARY

GET CITATION

RIGHTS & PERMISSIONS

Get copyright permission Get copyright permission on Copyright Marketplace

KEYWORDS

Satellites

Control systems

Device simulation

Sensors

Antennas

Control systems design

Digital signal processing

Show All Keywords

Keywords/Phrases

Search In:

Publication Years