Of the various testing and evaluation methods, flight test is by far one of the most important in the development, design, and validation of an
aircraft. Mathematical models, safety, comfort, and performance targets are verified through specific testing of each aircraft system under real flight operating conditions.
An airplane’s structure, landing gear, engines, electric, hydraulic and other systems are evaluated, as well as real-time monitoring of temperature, pressure, vibration, load, displacement, flow, and other physical quantities. Tests explore and
validate the flight envelope, structural flutter, aircraft stability, natural stalls, handling qualities, and others. Data is typically stored by on-board data acquisition systems and backed up on the ground via telemetry stations.
Flight tests are very costly, as testing time allotment and number of prototypes are limited. Extensive preparation and meticulous prior setup for such tests are absolutely critical, and there is little margin for error. To ensure the best possible
results, separate measurement validation channels must be incorporated into the design of the measurement system itself.
There are many instrumentation challenges encountered when acquiring physical measurements in the extremely demanding environments typical of most flight tests. Of such challenges, Dr. Patrick L. Walter, dynamic measurement instrumentation expert, noted,
“For an aircraft, a test engineer might encounter temperatures on the tarmac as high as +54 °C (+130 °F). In flight, external temperatures may drop to -35 °C (-30 °F), …and rocket systems encounter much greater temperature
extremes. Aside from influencing various sensors, these temperature variations can result in internal condensation and/or ice formation, which attempts to lower electrical impedances in the components of the on-board measurement system. Additionally,
strain and acceleration are induced into a flight system’s structure at various times due to turbulence, engine and motor burns, jettisoning of equipment, ordnance release, sonic booms, staging separation, and more. Acoustic noise is transmitted
through the air frame or structure to its interior. Some events in the preceding list that induce acceleration can result in high levels of pyrotechnic shock. At both anticipated and unanticipated times in flight, radars may illuminate the flight
vehicle. In addition, radio frequency transmissions can be received by and emitted from the vehicle. Thunder and lightning storms, as well as snow and sleet, can be randomly encountered, producing mechanical, thermal, and electrical inputs to
the flight vehicle. Lastly, flight test vehicles can contain as much as 50 miles of routed instrumentation wiring. A significant number of these wires carry only millivolt-level signals, exacerbating the challenge of maintaining an adequate signal-to-noise
Within this often volatile measurement environment, perhaps the most demanding of flight test instrumentation challenges is successful acquisition of dynamic measurements, such as sound and vibration data, which is typically achieved via accelerometers.
Two types of accelerometers typically employed are piezoelectric (sometimes called AC responding); and capacitive or piezoresistive (often called DC responding). Their roles are dictated by the frequency ranges at which they are capable of making
For instance, flutter testing, which most often involves global structural modes at low frequencies, is routinely accomplished using either AC or DC response accelerometers. Rigid body acceleration measurements can only be made using DC response sensors,
since piezoelectric sensors don’t accurately characterize events below their specified low frequency limit.
Standard DC response flight test accelerometers can be calibrated using a combination of three methods:
- An accelerometer can be flipped 180°, ensuring it accurately measures the earth’s gravitational field.
- The sensor can be excited on a calibration shaker and its output compared to a reference accelerometer at multiple frequencies.
- For dynamic range calibrations (at a frequency of 0 Hz), an accelerometer can be installed in a centrifuge and its amplitude measurement capabilities calibrated.
The piezoelectric (AC) accelerometers used in flight test can be calibrated in two ways:
- Much like the “flip” test described above for the DC accelerometer, a piezoelectric accelerometer can be mounted onto an appropriate fixture and dropped from an elastic suspension, so that it accelerates in the earth’s gravitational
field. This change from 0 to 1 g can be used to ensure accelerometer sensitivity is stable over time. This test also characterizes the accelerometer time constant, which is a function of the accelerometer’s associated amplifier.
- Similar to the second option above, the AC accelerometer can be mounted onto a calibration shaker, excited at various frequencies and its output compared to that of a reference accelerometer. This can be used to calibrate both accelerometer sensitivity
and its phase accuracy with respect to the reference accelerometer.