Initial military flight tests of the X-22A VSTOL research aircraft

1969 ◽  
Author(s):  
W. RHODES
Keyword(s):  
Flight Tests ◽  
Research Aircraft

Relationships between flying qualities and flight tests parameters for the F/A-18 aircraft

2007 ◽  
Vol 111 (1118) ◽  
pp. 281-282
Author(s):  
R. M. Botez ◽  
M. Rotaru
Keyword(s):  
Technical Note ◽  
System Research ◽  
Flight Tests ◽  
Flying Qualities ◽  
Research Aircraft ◽  
Mach Numbers

In this Technical Note, is shown that relationships exist between flying qualities levels 1, 2 and 3 and flight conditions expressed in terms of Mach numbers, altitudes and angles-of-attack for the F/A-18 SRA (System Research Aircraft). These relationships are helpful in detecting if derivatives are well calculated for flight tests intermediate conditions.

Initial military flight tests of the X-22A VSTOL research aircraft

1970 ◽  
Vol 7 (2) ◽  
pp. 169-174
Author(s):  
WILLIAM B. RHODES
Keyword(s):  
Flight Tests ◽  
Research Aircraft

scholarly journals Laboratory and Flight Tests of 2D Imaging Probes: Toward a Better Understanding of Instrument Performance and the Impact on Archived Data

2018 ◽  
Vol 35 (7) ◽  
pp. 1533-1553 ◽  
Author(s):  
Colin Gurganus ◽  
Paul Lawson
Keyword(s):  
Laboratory Tests ◽  
Sample Volume ◽  
Cloud Particle ◽  
Flight Tests ◽  
Data Archives ◽  
Imaging Probes ◽  
Research Aircraft ◽  
Water Drops ◽  
2D Imaging ◽  
Archived Data

AbstractTwo-dimensional (2D) imaging probes, such as the 2D stereo (2D-S) probe and the cloud imaging probe (CIP), are routinely used to provide in situ measurements of cloud particle properties. The basic measurement is shadowgraphs of water drops and ice particles from which particle size distributions, projected particle area, and mass concentrations are determined. These data permeate data archives of domestic and foreign government agencies, universities, and the private sector. This paper provides results from laboratory tests and flight tests on a Learjet research aircraft that give new insights into the performance of the 2D imaging probes, and how their performance may have impacted measurements collected in data archives. The laboratory tests are conducted with the aid of two devices: 1) a droplet generator that provides known concentrations of water drops from 15 to 65 µm ± 1 µm that can be positioned in the probe’s sample volume with 10-µm precision; and 2) a motorized spinning platform that supports transparent disks with small opaque features (i.e., a “spinning disk”), which replicates the effect of particles transecting the probe’s sample volume at translational speeds up to 190 m s−1. The flight tests were conducted with a Learjet research aircraft that collected cloud particle data at true airspeeds from 99 to 170 m s−1. The results provide new insights into how probe optics, time response, and data throughput of the 2D-S and CIP electro-optics impact the measurements of cloud particles. The results, summarized in the conclusions, suggest how archived data are impacted.

Cessna Citation X simulation turbofan modelling: identification and identified model validation using simulated flight tests

2019 ◽  
Vol 123 (1262) ◽  
pp. 433-463 ◽  
Author(s):  
Ruxandra Mihaela Botez ◽  
Paul-Alexandre Bardela ◽  
Thomas Bournisien
Keyword(s):  
Dynamic Model ◽  
Flight Dynamics ◽  
Flight Test ◽  
Federal Aviation Administration ◽  
Aviation Industry ◽  
System Response ◽  
Model Parameters ◽  
Flight Tests ◽  
Proposed Model ◽  
Research Aircraft

ABSTRACTThe aviation industry relies on accurate models. These models are used to predict an aircraft system’s outputs, and thus allow an understanding of the parameters involved, which could lead to system improvements. This study focuses on the engine modelling of an aircraft, and on its experimental validation using the Cessna Citation X Research Aircraft Simulator designed by CAE Inc., equipped with a level D Flight Dynamics toolbox. Level D is the highest rank attributed by the Federal Aviation Administration FAA certification authorities for flight dynamics. The proposed model aims to predict the thrust and the fuel consumption for various altitudes, Mach numbers and throttle lever angles (TLA). Different generic static models, which correspond to their steady state, from the literature, were used in this study; however, most of them were validated under restricted hypotheses. An optimisation algorithm was used in order to tune the static model parameters with the set of identification flight test data. Another set of data was then used in order to validate the identified model. Furthermore, a dynamic model corresponding to the transient operations was identified. TLA steps, impulses and ramp perturbations were performed in order to identify the system response, and to validate system dynamic model with other flight tests than the identification tests.

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