Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) AND ADDRESS(ES) PERFORMING ORGANIZATION REPORT NUMBERComposite Technology Development, Inc 2600 Campus Drive Suite D Lafayette, CO 80026 SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S) *Air Force Research LaboratorySpace Vehicles 3550 Aberdeen Ave SE SPONSOR/MONITOR'S REPORTKirtland AFB, NM 87117-5776 NUMBER(S) AFRL-VS-PS-TP-2006-1025 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. (Clearance #VS06-0130) SUPPLEMENTARY NOTESPublished in the 47 th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference Proceedings, 1 -4 May 2006, Newport, RI Government Purpose Rights ABSTRACTFuture small spacecraft will have a need for lightweight, highly reliable, and cost-effective mechanisms for the deployment of radiators, solar arrays, and other devices. To meet this need, Composite Technology Development, Inc. has developed TEMBO® Elastic Memory Composite (EMC) materials, which accommodate very high folding strains without damage, while providing very high deployed stiffness-and strength-to-weight ratios. Over the past few years, CTD has developed and performed extensive ground testing on a TEMBO® EMC deployment hinge for radiators, solar arrays and other deployable spacecraft components. The present paper will discuss the details of two flight experiments to validate the TEMBO® EMC hinge design on-orbit. In particular, the paper will discuss: 1) detailed design of the flight hardware for both experiments; 2) ground-verification and acceptance testing of the flight hardware; and 3) status of the flight missions. Future small spacecraft will have a need for lightweight, highly reliable, and costeffective mechanisms for the deployment of radiators, solar arrays, and other devices. To meet this need, Composite Technology Development, Inc. has developed TEMBO ® Elastic Memory Composite (EMC) materials, which accommodate very high folding strains without damage, while providing very high deployed stiffness-and strength-to-weight ratios. Over the past few years, CTD has developed and performed extensive ground testing on a TEMBO ® EMC deployment hinge for radiators, solar arrays and other deployable spacecraft components. The present paper will discuss the details of two flight experiments to validate the TEMBO ® EMC hinge design on-orbit. In particular, the paper will discuss: 1) detailed design of the flight hardware for both experiments; 2) ground-verificati...

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The construction of world magnetic charts entails the adoption for the chosen epoch of dip pole positions and of secular‐change patterns in their vicinity, thereby specifying implicitly the rates and directions of their motions. In the procedure leading to the forthcoming charts for epoch 1965.0, azimuthal components of the field vector are derived for both the northern and southern polar regions, and their isolines are used to establish field configurations to be incorporated with data for other areas in a final mapping based on spherical harmonic analysis. The paper describes details of the special polar techniques and reports the adopted positions and drifts of the dip poles. Currently, the north magnetic clip pole is moving in a northerly direction at a rate of approximately 12 kilometers per year, and the south magnetic dip pole is moving in a northwesterly direction at about 14 kilometers per year.

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