Finite element analyses were performed during design anddevelopment of the F22 AMAD gearbox to ensure a design free ofdamaging resonant responses within its operating speed range.Ideally, design with respect to resonance characteristics wouldhave no natural frequencies within the operating speed range.However, the wide speed range (from 1445 to 17 93 1 rpm) combinedwith the weight and geometric constraints imposed by theapplication (the F-22 is an advanced technology, next generation,fighter aircraft) made it impossible to attain this goal directlyin the F-22 AMAD design.
The analysis and evaluation therefore involved severalinterrelated iterative steps which included detuning by geometricmodification, evaluation of gear to forced vibration, and dampingtreatment to develop an optimum, lightweight design free ofdamaging resonant responses within 15% of the operating speedrange.
This paper discusses the overall analytical approach, analyticaimethods and evaluation of gear response to achieve acceptableaccessory gear designs. Design modifications, includingdevelopments in the modeling techniques required to accommodate theunique characteristics of these relatively small (compared to theusual helicopter main power gear) gears are also discussed . Testand analyticai results are also presented and compared.
- Edition:
- 96
- Published:
- 10/01/1996
- Number of Pages:
- 18
- File Size:
- 1 file , 1.5 MB
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