曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

rotation rate did achieve greater altitude gains as the climb continued.
For the enroute descent case, a rapid rotation resulted in a 60 foot altitude loss versus 80 feet
for the normal rotation rate. The time below the entry altitude was 3.1 seconds versus 4.7
seconds. And, the aircraft with the rapid rotation rate was 140 feet above the normal rotation
rate aircraft as it returned to the entry altitude.
Pilot Comments
SIMULATOR - Pulling smoothly at the standard 3 deg/sec did not produce enough g for
maximum performance. Pulling at 6 deg/sec to 20 degrees of pitch provided 1.6g to 2.0g in
the simulator. If pull-ups were made more aggressively, pitch attitude would overshoot into
the 25 to 30 degree nose high range, and there were several pitch oscillations noted.
AIRCRAFT - Different entry g levels were evaluated, pulling up to a target pitch attitude of
17.5 degrees. At the higher g levels, precisely matching the pitch attitude at 17.5 was
difficult, and would often result in a pitch overshoot of 2-3 degrees. The best run appeared to
be run 3, where at the end of the run, pitch was exactly at 17.5 degrees, which was right at the
pitch limit indicator (PLI), which is the threshold for stick shaker activation. Minimum
altitude loss below the pull up altitude (10,000 Ô) was observed to be about 100 feet on run 3.
On run 7, a near maximum performance pull up to 30 degrees nose high was executed,
activating the stick shaker. The airplane stagnated in climb at 10,900Õ and 105 kts with full
thrust. While this run gave the maximum initial pitch rate, it bled off energy rapidly, resulting
in complete loss of climb performance after a 900Õ altitude gain. During all of these
maneuvers, maximum thrust was applied at the beginning of the pull up. It nominally took 3-
4 seconds for the engines to come to full thrust, which usually occurred at about 15 deg nose
during the maneuver.
Revision 14.0 17
Conclusions
The evaluation team preferred the flight envelope limiting features (Òsoft limitsÓ) of the B777
design to a Òhard limitÓ design. This was a subjective judgement based on the premise that
there may be situations unforeseen by the designers where the pilot might need to achieve full
aerodynamic capability as opposed to being software/control law limited.
V. Lessons Learned
A. Simulation
1. The use of an engineering simulator was beneficial in developing recovery
techniques and assessing the ability to perform the recovery maneuver without
overstressing the aircraft. This was very necessary in the build up phase to
avoid or assess the potential for damage to the test aircraft.
2. The use of fixed based simulators did not provide any motion cues and thus
was not a true simulation of the dynamics of the aggressive maneuvers being
tested or developed. A Òquick lookÓ evaluation was performed with a full
motion Airbus A-320 and a Boeing 777 simulator at the United Airlines Flight
Center, but these simulators did not have the necessary data acquisition
capability required for the test program.
B. Aircraft Flight Test
1. It was difficult to consistently obtain a pitch rate of 3 degrees/second over a variety of
airspeeds without considerable practice and finesse (both aircraft have a long moment
arm and there is no cockpit indication of pitch rate). The pitch rate attained at higher
airspeeds (250 to 300 KIAS) tended to be underestimated by the pilot. The evaluation
pilots felt that specifying a pitch rate of 3 degrees/second for line operations without a
parameter display is impractical. The motion cues and g onset rates played a very
important role in the closed loop performance.
2. Flight time to perform the evaluation was very limited. Because of this, detailed
coordination preplanning and performance were required to achieve the test
objectives.
3. Some of the coordination was international and this contributed to the communications
difficulties. Some final issues could only be raised and resolved face to face and this
resulted in some significant, last minute changes to the test card.
4. Flexibility in the test was required since our evaluators had limited control of the
aircraft configuration and test cards.
5. Last minute test constraints due to structural safety concerns raised during the flight
briefing required last minute modifications to the test cards. Care had to be taken to
maintain like maneuver comparisons in spite of last minute maneuver modifications.
Revision 14.0 18
C. General
1. Manufacturer and FAA test pilots and purchasing company management pilots have
traditionally evaluated most aircraft. The Airline Pilots Association has played more
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：FLIGHT TEST RESULTS OF THE CFIT AVOIDANCE IN FLY-BY-WIRE TRA(7)