F. Demonstrator Performance Estimates It is now possible to estimate the performance of the demonstrator aircraft through a fairly simple analysis of the
masses and inspection of pilot operating handbook data. Table 3 lists the pertinent data and assumptions related to the candidate demonstrator performance. Note that the fuel mass to maximum gross weight metric was calculated assuming the crew and instrumentation mass of 180kg, as specified in the initial assumptions. The fuel flow was calculated based on the cruise efficiency of the motors, and the fuel-to-electric efficiency was calculated for the
Criteria Im po
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aw k
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p ow
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s
Te cn
m a
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6T –
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le p
ow er
sy st
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na 3
37 w
/ o ne
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gi ne
re pl
ac ed
O V-
10 w
ith p
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st al
la tio
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Airframe acquisition & NASA processing: cost impact to program M 3 2 2 2 2 1 Airframe acquisition & NASA processing: schedule impact to program H 3 2 3 3 2 1 Airframe acquisition & NASA processing: uncertainty/risk impact to program H 3 3 2 2 3 1 Propulsion (motor, propeller, and accessories): cost impact to program M 3 5 2 2 3 4 Propulsion (motor, propeller, and accessories): schedule impact to program H 3 5 3 3 3 4 Propulsion (motor, propeller, and accessories): uncertainty/risk impact to program H 3 5 4 4 4 5 Power system (SOFC & balance of plant): cost impact to program M 3 4 2 5 4 4 Power system (SOFC & balance of plant): schedule impact to program H 3 3 2 4 3 4 Power system (SOFC & balance of plant): uncertainty/risk impact to program H 3 3 3 4 3 4 Number of US vs. foreign manufacturers for demonstrator & components M 3 4 3 3 4 4 Mass and volume margin with new motor & power system H 3 4 4 5 5 5 Aircraft range with fuel at maximum gross weight L 3 2 3 3 3 3 Cruise speed L 3 1 2 2 3 3 Safety of flight impact H 3 3 4 2 5 4 Public perception (“wow” factor) M 3 2 3 3 1 1 TOTAL WEIGHTED SCORE (higher is better) 108 121 104 116 118 118
D ow
nl oa
de d
by E
M B
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