CALCULATED WEIGHT, BALANCE AND MOMENTS OF INERTIA
Abstract
The report contains weight and balance and aircraft moment of inertia data in summary and in detail. The summary data is given for several fuel, flight test instrumentation combinations considered compatible with the flight test program. Performance requirements were written for endurance missions of 20 and 45 minutes and therefore weights data are given for the aircraft with fuel to perform these missions with flight test instrumentation included. The design gross weight of the aircraft is 9200 lbs., and therefore data is given for this weight. Approximately 85 percent of the aircraft weight was obtained from measurement of component and sub-assembly weights. In addition, the aircraft itself was weighed and this actual weight has been used to derive various gross weight loading conditions. The Weight Empty given includes only those items required by the Aircraft Specification. It does not, for instance, include the auxiliary fuel tank nor instrumentation or other temporary items installed for initial flight test purposes. Horizontal distances used were measured from fuselage station zero. Vertical distances are measured from a theoretical plane 100 inches below the fuselage horizontal reference plane.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1964
- Accession Number
- AD0654041
Entities
Organizations
- General Electric