Dual-Spin Spacecraft Nutation Control Using Articulated Payloads
A technique is presented for achieving active control of nutation on a dual-spin spacecraft with an articulated payload through use of the payload's control system. Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic i...
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| Veröffentlicht in: | IEEE transactions on aerospace and electronic systems 1980-01, Vol.AES-16 (1), p.74-83 |
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| container_end_page | 83 |
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| container_title | IEEE transactions on aerospace and electronic systems |
| container_volume | AES-16 |
| creator | Slafer, Loren I. |
| description | A technique is presented for achieving active control of nutation on a dual-spin spacecraft with an articulated payload through use of the payload's control system. Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servodesign parameters. The design techniques presented are verified through a series of on-orbit tests recently conducted on the OSO-8 spacecraft. |
| doi_str_mv | 10.1109/TAES.1980.308878 |
| format | Article |
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Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servodesign parameters. 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Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servodesign parameters. The design techniques presented are verified through a series of on-orbit tests recently conducted on the OSO-8 spacecraft.</description><subject>Aerospace control</subject><subject>Aircraft</subject><subject>Asymptotic stability</subject><subject>Control systems</subject><subject>Damping</subject><subject>Energy dissipation</subject><subject>Energy states</subject><subject>Payloads</subject><subject>Space vehicles</subject><subject>Spinning</subject><issn>0018-9251</issn><issn>1557-9603</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>1980</creationdate><recordtype>article</recordtype><recordid>eNqNkD1PwzAQhi0EEuVjR2LJxJZyFzd2vFGV8iFVgNR2thzngoLSJNjO0H9PoiBmptPd-7w3PIzdIMwRQd3vluvtHFUGcw5ZJrMTNsM0lbESwE_ZDACzWCUpnrML77-GdZEt-Iw9PPamjrdd1UTbzliyzpQheuuDCVXbRKu2Ca6to72vms9o6UJl-9oEKqIPc6xbU_grdlaa2tP177xk-6f1bvUSb96fX1fLTWwTKUIsUyVQUAIScjJCWZGaEsZjzgEUypK4JV6QtJBIUKQ4RypyiZjZ3Kb8kt1NfzvXfvfkgz5U3lJdm4ba3uuECyUFyP-BgGIAYQKta713VOrOVQfjjhpBj0716FSPTvXkdKjcTpWKiP7wBUKSDOkPjWBxsw</recordid><startdate>198001</startdate><enddate>198001</enddate><creator>Slafer, Loren I.</creator><general>IEEE</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>198001</creationdate><title>Dual-Spin Spacecraft Nutation Control Using Articulated Payloads</title><author>Slafer, Loren I.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c276t-759616e2070bea69c65af05961b300917fe3ce3de7c02709e9331edb7118cbc53</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>1980</creationdate><topic>Aerospace control</topic><topic>Aircraft</topic><topic>Asymptotic stability</topic><topic>Control systems</topic><topic>Damping</topic><topic>Energy dissipation</topic><topic>Energy states</topic><topic>Payloads</topic><topic>Space vehicles</topic><topic>Spinning</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Slafer, Loren I.</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>IEEE transactions on aerospace and electronic systems</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Slafer, Loren I.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Dual-Spin Spacecraft Nutation Control Using Articulated Payloads</atitle><jtitle>IEEE transactions on aerospace and electronic systems</jtitle><stitle>T-AES</stitle><date>1980-01</date><risdate>1980</risdate><volume>AES-16</volume><issue>1</issue><spage>74</spage><epage>83</epage><pages>74-83</pages><issn>0018-9251</issn><eissn>1557-9603</eissn><coden>IEARAX</coden><abstract>A technique is presented for achieving active control of nutation on a dual-spin spacecraft with an articulated payload through use of the payload's control system. Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servodesign parameters. The design techniques presented are verified through a series of on-orbit tests recently conducted on the OSO-8 spacecraft.</abstract><pub>IEEE</pub><doi>10.1109/TAES.1980.308878</doi><tpages>10</tpages></addata></record> |
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| ispartof | IEEE transactions on aerospace and electronic systems, 1980-01, Vol.AES-16 (1), p.74-83 |
| issn | 0018-9251 1557-9603 |
| language | eng |
| recordid | cdi_proquest_miscellaneous_23697016 |
| source | IEEE Electronic Library (IEL) |
| subjects | Aerospace control Aircraft Asymptotic stability Control systems Damping Energy dissipation Energy states Payloads Space vehicles Spinning |
| title | Dual-Spin Spacecraft Nutation Control Using Articulated Payloads |
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