Determination of aerodynamic parameters of a fighter airplane from flight data at high angles of attack

1983 ◽  
Author(s):  
V. KLEIN ◽  
J. BATTERSON
Keyword(s):  
Flight Data ◽  
Aerodynamic Parameters ◽  
High Angles Of Attack

scholarly journals Alignment determination of the Hayabusa2 laser altimeter (LIDAR)

2021 ◽  
Vol 73 (1) ◽  
Author(s):  
Hirotomo Noda ◽  
Hiroki Senshu ◽  
Koji Matsumoto ◽  
Noriyuki Namiki ◽  
Takahide Mizuno ◽  
...  
Keyword(s):  
Altimeter Data ◽  
Gravity Assist ◽  
Laser Altimeter ◽  
Trajectory Error ◽  
Flight Data ◽  
Camera Image ◽  
Operation Period ◽  
The Cross ◽  
Along Track

AbstractIn this study, we determined the alignment of the laser altimeter aboard Hayabusa2 with respect to the spacecraft using in-flight data. Since the laser altimeter data were used to estimate the trajectory of the Hayabusa2 spacecraft, the pointing direction of the altimeter needed to be accurately determined. The boresight direction of the receiving telescope was estimated by comparing elevations of the laser altimeter data and camera images, and was confirmed by identifying prominent terrains of other datasets. The estimated boresight direction obtained by the laser link experiment in the winter of 2015, during the Earth’s gravity assist operation period, differed from the direction estimated in this study, which fell on another part of the candidate direction; this was not selected in a previous study. Assuming that the uncertainty of alignment determination of the laser altimeter boresight was 4.6 pixels in the camera image, the trajectory error of the spacecraft in the cross- and/or along-track directions was determined to be 0.4, 2.1, or 8.6 m for altitudes of 1, 5, or 20 km, respectively.

Method and Hardware-Software for Measuring Altitude of Aircraft and Descent Facilities with Increased Accuracy

2020 ◽  
Vol 25 (5) ◽  
pp. 452-464
Author(s):  
A.V. Makshakov ◽  
◽  
Yu.I. Shtern ◽  
O.S. Volkova ◽  
K.A. Vasilchenko ◽  
...  
Keyword(s):  
Measurement Errors ◽  
Original Method ◽  
Measured Data ◽  
Height Measurement ◽  
Automatic Data ◽  
Accuracy Of Measurements ◽  
Aerodynamic Parameters ◽  
Atmospheric Phenomena ◽  
Test Result

Reliable, accident-free operation of extra light aviation, drone aircraft, the parachute equipment for landing of people and loads, demands to increase an accuracy of determination of height for the purpose of their safe maneuvering, descent and landing. In the work the critical analysis of existing methods of the height measurement has been carried out for the purpose of defining the most accurate ones and the preference has been given to the barometric method. To decrease the measurement errors, the smart altimeter sensors (SAS) intellectual sensors have been developed, and on their basis the prototype of a barometric altimeter have been designed. In the course of computer modeling and prototyping it has been determined that in designing the altimeter it is necessary to use several SAS, and the accuracy of measurements is essentially affected by an arrangement of sensors on a flying object. The developed method of the height measurement using SAS includes the hardware-software compensation of the errors, caused by the atmospheric phenomena and aerodynamic parameters of the flying object design. The hardware – software for processing the measured data has been developed as well as the software for functioning of intelligent pressure sensor, automatic data processing and the information output to the altimeter display. The tests on the offered technique and hardware – software have been carried out in actual practice of operation. The developed altimeter has been installed on the equipment of a parachutist. In the test result it has been determined that the developed original method and the hardware – software permit to significantly decrease the errors of measurements, which do not exceed 1 meter while the airflow moving at speeds up to 8 meters per second 5 meters up to 70 meters per second

In situ determination of wind fields from sailplane flight data

2010 ◽  
Author(s):  
Ni Zhang ◽  
Rick P. Millane ◽  
Alan J. Hunter
Keyword(s):  
Wind Fields ◽  
Flight Data

A hybrid frequency-time domain technique for ground effect identification

2010 ◽  
Vol 114 (1156) ◽  
pp. 377-385
Author(s):  
A. Vitale ◽  
N. Genito ◽  
L. Garbarino ◽  
U. Ciniglio ◽  
F. Corraro
Keyword(s):  
Time Domain ◽  
Flight Control ◽  
Ground Effect ◽  
Model Parameters ◽  
Flight Data ◽  
Aerodynamic Model ◽  
Hybrid Frequency ◽  
Effect Model ◽  
Aerodynamic Derivatives ◽  
Aerodynamic Parameters

Abstract The estimation from flight data of aerodynamic parameters for vehicle in steady-state conditions, perturbed by an identification manoeuvre, is a well-established technology, whereas system identification from dynamic flight data is a subject of continuous interest. This paper presents a hybrid frequency and time domain technique for identification of vehicle longitudinal aerodynamic model, including the ground effect. Identification is performed in the framework of a multi-step approach, in which, first aerodynamic coefficients are estimated in the frequency domain, using an equation error method; then time domain techniques are applied to identify out of ground effect aerodynamic derivatives and ground effect model parameters. The technique was successfully applied to flight data of an experimental ultra light aircraft. Identification results showed that the proposed method works properly also in the dynamic phases of the flight or when no dedicated identification manoeuvres are executed. Moreover, the identified longitudinal aerodynamic model was used to design the flight control system that successfully performed many autonomous landings.

Sign in / Sign up

Export Citation Format

Share Document