scholarly journals F-14 Re-Engining With the F110 Engine

1985 ◽  
Author(s):  
O. T. Castells ◽  
J. T. Strong
Keyword(s):  
Flight Test ◽  
Test Results ◽  
Design Features ◽  
Engine Design ◽  
Engine Development ◽  
F 14

The advantages of re-engining the F-14 aircraft with the F110 engine is presented. The areas of improvement and the engine development philosophy are explained. A summary description of the pertinent engine design features of the F110 are presented. The flight test results on inlet/engine compatability, afterburner operation, airplane performance, and maintainability/reliability/durability are interpreted. Finally, a description of the proposed version of the F110 engine for the F-14 is presented.

scholarly journals F-14 Inlet Development Experience

1982 ◽  
Author(s):  
R. H. Tindell ◽  
C. A. Hoelzer ◽  
D. Alexander
Keyword(s):  
Wind Tunnel ◽  
Flight Test ◽  
Test Results ◽  
Development Experience ◽  
F 14

This paper reviews the F-14 inlet design and discusses the wind tunnel and flight test results of investigations that can contribute to more advanced inlet designs.

F-14 Inlet Development Experience

1982 ◽  
Vol 104 (4) ◽  
pp. 751-759
Author(s):  
R. H. Tindell ◽  
C. A. Hoelzer ◽  
D. Alexander
Keyword(s):  
Wind Tunnel ◽  
Flight Test ◽  
Test Results ◽  
Development Experience ◽  
F 14

This paper reviews the F-14 inlet design and discusses the wind tunnel and flight test results of investigation that can contribute to move advanced inlet design.

Flight Development of the RTM 322 Engine

1990 ◽  
Author(s):  
Peter Sewell ◽  
Paul E. Scears
Keyword(s):  
Dynamic Characteristics ◽  
Flight Test ◽  
Test Results ◽  
Important Ingredient ◽  
Flight Testing ◽  
Development Status ◽  
Early Stages ◽  
Engine Design

The RTM 322 engine, under development by Rolls-Royce Turbomeca Ltd, is a viable candidate engine for future incorporation in S-70, H-60, EH101 and NH90 helicopters. An important ingredient in the development of the engine is its flight testing, currently being carried out in a Sikorsky S-70C (Civil version of the U S Army UH60 BLACK HAWK). This has not only served realistically to uncover and correct at very early stages those types of problem common to the development of all new engines but has also equally afforded an early look at installation, control and engine/airframe dynamic characteristics which, of course, will simplify later Production Series incorporation. A brief description of the RTM 322 engine design and its development status is given followed by a summary of the installation and flight testing in the S-70C. Ground and flight test results in the S-70C are discussed and data and photographs presented.

Flight test results for a high-capacity single-groove heat pipe

1992 ◽  
Author(s):  
J. AMBROSE ◽  
H. HOLMES ◽  
R. CIMA ◽  
M. KAPOLNEK
Keyword(s):  
Heat Pipe ◽  
High Capacity ◽  
Flight Test ◽  
Test Results

Design a Robust RST Controller for Stabilization of a Tri-Copter UAV

2016 ◽  
Vol 5 (1) ◽  
Author(s):  
Zain Anwar Ali ◽  
Dao Bo Wang ◽  
Muhammad Aamir
Keyword(s):  
Control Algorithm ◽  
Control Structure ◽  
Flight Test ◽  
System Control ◽  
Test Results ◽  
Output Control ◽  
Aerial Robot ◽  
Mimo Model

<span>Research on the tri-rotor aerial robot is due to extra efficiency<span> over other UAV’s regarding stability, power and size<span> requirements. We require a controller to achieve 6-Degree<span> Of Freedom (DOF), for such purpose, we propose the RST<span> controller to operate our tri-copter model. A MIMO model<span> of a tri-copter aerial robot is challenged in the area of control<span> engineering. Ninestates of output control dynamics are treated<span> individually. We designed dynamic controllers to stabilize the<span> parameters of an UAV. The resulting system control algorithm<span> is capable of stabilizing our UAV to perform numerous<span> operations autonomously. The estimation and simulation<span> implemented inMATLAB, Simulink to verify the results. All<span> real flight test results are presented to prove the success of<span> the planned control structure.<br /><br class="Apple-interchange-newline" /></span></span></span></span></span></span></span></span></span></span></span></span></span></span>

scholarly journals Optical Navigation Sensor for Runway Relative Positioning of Aircraft during Final Approach

Sensors ◽  
2021 ◽  
Vol 21 (6) ◽  
pp. 2203
Author(s):  
Antal Hiba ◽  
Attila Gáti ◽  
Augustin Manecy
Keyword(s):  
Optical Sensors ◽  
Inertial Sensor ◽  
Image Data ◽  
Flight Test ◽  
Image Features ◽  
Wide Field ◽  
Test Results ◽  
Wide Field Of View ◽  
Final Approach ◽  
Marker Detection

Precise navigation is often performed by sensor fusion of different sensors. Among these sensors, optical sensors use image features to obtain the position and attitude of the camera. Runway relative navigation during final approach is a special case where robust and continuous detection of the runway is required. This paper presents a robust threshold marker detection method for monocular cameras and introduces an on-board real-time implementation with flight test results. Results with narrow and wide field-of-view optics are compared. The image processing approach is also evaluated on image data captured by a different on-board system. The pure optical approach of this paper increases sensor redundancy because it does not require input from an inertial sensor as most of the robust runway detectors.

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