High Altitude Altimeter Flight Test

1978 ◽  
Author(s):  
W. G. Martin
Keyword(s):  
High Altitude ◽  
Flight Test

High Altitude Balloon Flight Test of the GRAD Experiment

1990 ◽  
Author(s):  
Robert J. Hicks ◽  
David H. Jenkins
Keyword(s):  
High Altitude ◽  
Flight Test ◽  
Balloon Flight

Cost-Effective High-Altitude Scientific Balloon Development and its Flight Test

2018 ◽  
Vol 46 (4) ◽  
pp. 345-358
Author(s):  
Jungpyo Kang ◽  
Gyujin Shim ◽  
Hweeho Kim ◽  
Yongseon Lee ◽  
Kwanjung Yee
Keyword(s):  
High Altitude ◽  
Cost Effective ◽  
Flight Test

scholarly journals Project of high altitude balloon launched micro glider: Aircraft design, control and flight test

2020 ◽  
Vol 12 ◽  
pp. 175682932097995
Author(s):  
Zhengyu Qu ◽  
Cuichun Li ◽  
Yong Hao ◽  
Feng Yan ◽  
Yanchu Yang
Keyword(s):  
High Altitude ◽  
System Design ◽  
Target Position ◽  
Aircraft Design ◽  
Flight Test ◽  
Roll Angle ◽  
Guidance System ◽  
Circuit Board ◽  
Wind Condition ◽  
Flight Tests

This paper presents the design details and flight tests validation of printed circuit board fabricated micro gliders. The purpose of the micro glider is to be launched from a super pressure balloon at high altitude, glide to the target position to collect data and upload data to the staying balloon. The mission demand requires the micro glider to finish precise landing with small size and low fabrication cost. To complete this concept, we designed a PCB fabricated aircraft with limited sensors including GPS and IMU. The first part of the article describes the aerodynamic design methods. The second part introduced the control and guidance system design by controlling the roll angle and flight path angle to complete the precise landing. In the simulation results presented in the third part, launch with no wind condition shows desirable precise landing ability. As a contrast, wind direction and magnitude have significant effects on the guidance ability and accuracy. In the last part, two real flight tests conducted in Inner Mongolia of China are described to compare the flight performance with the current aerodynamics and control system design. Returned data indicated the micro gliders could successfully fly at high altitude. The control algorithm can compute the command roll angle only with GPS and IMU, but some design details still need to be improved to achieve precise landing ability.

scholarly journals Design and Performance Evaluation of Propeller for Solar-Powered High-Altitude Long-Endurance Unmanned Aerial Vehicle

2018 ◽  
Vol 2018 ◽  
pp. 1-23 ◽  
Author(s):  
Donghun Park ◽  
Yunggyo Lee ◽  
Taehwan Cho ◽  
Cheolwan Kim
Keyword(s):  
Wind Tunnel ◽  
High Altitude ◽  
Test Data ◽  
Design Method ◽  
Wind Tunnel Test ◽  
Flight Test ◽  
Cfd Analysis ◽  
Aerial Vehicle ◽  
Solar Powered ◽  
Long Endurance

Design, wind tunnel test, computational fluid dynamics (CFD) analysis, and flight test data analysis are conducted for the propeller of EAV-3, which is a solar-powered high-altitude long-endurance unmanned aerial vehicle developed by Korea Aerospace Research Institute. The blade element momentum theory, in conjunction with minimum induced loss, is used as a basic design method. Airfoil data are obtained from CFD analysis, which takes into account the low Reynolds number effect. The response surface is evaluated for design variables by using design of experiment and kriging metamodel. The optimization is based on desirability function. A wind tunnel test is conducted on the designed propeller. Numerical analyses are performed by using a commercial CFD code, and results are compared with those obtained from the design code and wind tunnel test data. Flight test data are analyzed based on several approximations and assumptions. The propeller performance is in good agreement with the numerical and measurement data in terms of tendency and behavior. The comparison of data confirms that the design method, wind tunnel test, and CFD analysis used in this study are practically useful and valid for the development of a high-altitude propeller.

scholarly journals Analysis and test for thermal performance of High Altitude Super Pressure Balloons during ascending process

2018 ◽  
Vol 189 ◽  
pp. 03014
Author(s):  
Da Zhao ◽  
Dong-xu Liu ◽  
Kai Feng ◽  
Ming Zhu
Keyword(s):  
High Altitude ◽  
Dynamic Model ◽  
Thermal Performance ◽  
Thermal Characteristics ◽  
Flight Test ◽  
Adjustment Process ◽  
Test Results ◽  
Free Expansion ◽  
The Real

A two-node model for thermal characteristics and a dynamic model of High Altitude Super Pressure Balloon (HASPB) during ascending process are established. The thermal performance of HASPB during ascending process is analyzed. Several simulations are conducted under the same conditions with the real flight test. Results show that supercool phenomenon occurs during ascending caused by free expansion of gas, and the value is about 10-15 K. Once the balloon reaches the design height and becomes over-pressured, the temperature of balloon rises rapidly, and this adjustment process lasts for about 10 minutes. The real flight test to 20000 m validates the reliability of the two-node model.

scholarly journals Preliminary flight test correlations of the X-HALE aeroelastic experiment

2015 ◽  
Vol 119 (1217) ◽  
pp. 855-870 ◽  
Author(s):  
J. R. Jones ◽  
C. E. S. Cesnik
Keyword(s):  
High Altitude ◽  
Risk Reduction ◽  
Flight Test ◽  
Nonlinear Behaviour ◽  
Geometrically Nonlinear ◽  
University Of Michigan ◽  
Flight Tests ◽  
Remotely Piloted Aircraft ◽  
Long Endurance ◽  
The Way

AbstractAn experimental, remotely-piloted aircraft has been designed and fabricated at University of Michigan that is aeroelastically representative of very flexible aircraft. Known as X-HALE, this Experimental High-Altitude Long-Endurance aircraft exhibits geometrically nonlinear behaviour and displays specific aeroelastic characteristics designed into the experiment. This paper presents the data from the initial flight tests of the lightly instrumented X-HALE Risk Reduction Vehicle that confirm the expected aeroelastic characteristics. This opens the way for future flight tests with a fully-instrumented platform which will provide data to support validation of coupled, nonlinear aeroelastic/flight dynamic codes.

Project Zephyrus: Developing a rapidly reusable high-altitude flight test platform

2018 ◽  
Author(s):  
Hunter Hall ◽  
Benjamin Donitz ◽  
Leon Kim ◽  
Divya Srivastava ◽  
Keenan Albee ◽  
...  
Keyword(s):  
High Altitude ◽  
Flight Test ◽  
Test Platform

Contrast of Filament Bright Rims

1994 ◽  
Vol 144 ◽  
pp. 365-367
Author(s):  
E. V. Kononovich ◽  
O. B. Smirnova ◽  
P. Heinzel ◽  
P. Kotrč
Keyword(s):  
High Altitude ◽  
Line Profile ◽  
Line Center ◽  
Magnetic Structures ◽  
The Mean

AbstractThe Hα filtergrams obtained at Tjan-Shan High Altitude Observatory near Alma-Ata (Moscow University Station) were measured in order to specify the bright rims contrast at different points along the line profile (0.0; ± 0.25; ± 0.5; ± 0.75 and ± 1.0 Å). The mean contrast value in the line center is about 25 percent. The bright rims interpretation as the bases of magnetic structures supporting the filaments is suggested.

Sign in / Sign up

Export Citation Format

Share Document