scholarly journals Flight in the Jovian Stratosphere: Engine Concept and Flight Altitude Determination

2021 ◽  
pp. 1-6
Author(s):  
Nedislav S. Veselinov ◽  
Martin N. Karanikolov ◽  
Vladislav V. Shihskin ◽  
Dimitar M. Mladenov
Keyword(s):  
Flight Altitude ◽  
Engine Concept

scholarly journals Appropriate Drone Flight Altitude for Horse Behavioral Observation

Drones ◽  
2021 ◽  
Vol 5 (3) ◽  
pp. 71
Author(s):  
Tomoko Saitoh ◽  
Moyu Kobayashi
Keyword(s):  
Avoidance Behavior ◽  
Correlation Coefficients ◽  
Behavioral Observation ◽  
Animal Research ◽  
Behavioral Data ◽  
Flight Altitude ◽  
Recording Time ◽  
Livestock Management ◽  
Behavioral Observations ◽  
Video Observations

Recently, drone technology advanced, and its safety and operability markedly improved, leading to its increased application in animal research. This study demonstrated drone application in livestock management, using its technology to observe horse behavior and verify the appropriate horse–drone distance for aerial behavioral observations. Recordings were conducted from September to October 2017 on 11 horses using the Phantom 4 Pro drone. Four flight altitudes were tested (60, 50, 40, and 30 m) to investigate the reactions of the horses to the drones and observe their behavior; the recording time at each altitude was 5 min. None of the horses displayed avoidance behavior at any flight altitude, and the observer was able to distinguish between any two horses. Recorded behaviors were foraging, moving, standing, recumbency, avoidance, and others. Foraging was the most common behavior observed both directly and in the drone videos. The correlation coefficients of all behavioral data from direct and drone video observations at all altitudes were significant (p < 0.01). These results indicate that horse behavior can be discerned with equal accuracy by both direct and recorded drone video observations. In conclusion, drones can be useful for recording and analyzing horse behavior.

Exergy analysis of a turboprop engine at different flight altitude and speeds using novel consideration

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Ali Dinc ◽  
Yousef Gharbia
Keyword(s):  
Fuel Consumption ◽  
Thermal Efficiency ◽  
Exergy Efficiency ◽  
Specific Fuel Consumption ◽  
Flight Altitude ◽  
Fuel Flow ◽  
Turboprop Engine ◽  
Shaft Power ◽  
Two Parameters ◽  
The Relationship

Abstract In this study, exergy efficiency calculations of a turboprop engine were performed together with main performance parameters such as shaft power, specific fuel consumption, fuel flow, thermal efficiency etc., for a range of flight altitude (0–14 km) and flight speeds (0–0.6 Mach). A novel exergy efficiency formula was derived in terms of specific fuel consumption and it is shown that these two parameters are inversely proportional to each other. Moreover, a novel exergy efficiency and thermal efficiency relation was also derived. The relationship showed that these two parameters are linearly proportional to each other. Exergy efficiency of the turboprop engine was found to be in the range of 23–33%. Thermal efficiency of the turboprop engine was found to be around 25–35%. Exergy efficiency is higher at higher speeds and altitude where the specific fuel consumption is lower. Conversely, exergy efficiency of the engine is lower for lower speeds and altitude where the specific fuel consumption is higher.

scholarly journals Multi-platform app-embedded model for hybrid air-breathing rocket-cycle engine in hypersonic atmospheric ascent

2021 ◽  
pp. 1-23
Author(s):  
S.E. Tsentis ◽  
V.G. Gkoutzamanis ◽  
A.D. Gaitanis ◽  
A.I. Kalfas
Keyword(s):  
Specific Impulse ◽  
Performance Parameters ◽  
Interested Reader ◽  
Component Level ◽  
Air Breathing ◽  
Evaluation Of Performance ◽  
Embedded Model ◽  
The Impact ◽  
Rocket Technology ◽  
Engine Concept

ABSTRACT This paper presents a performance analysis on a novel engine concept, currently under development, in order to achieve hybrid air-breathing rocket technology. A component-level approach has been developed to simulate the performance of the engine at Mach 5, and the thermodynamic interaction of the different working fluids has been analysed. The bypass ramjet duct has also been included in the model. This facilitates the improved evaluation of performance parameters. The impact of ram drag induced by the intake of the engine has also been demonstrated. The whole model is introduced into a multi-platform application for aeroengine simulation to make it accessible to the interested reader. Results show that the bypass duct modelling increases the overall efficiency by approximately 7%. The model calculates the specific impulse at approximately 1800 seconds, which is 4 times higher than any chemical rocket.

Analysis of a pulsed normal detonation wave engine concept

2001 ◽  
Author(s):  
Donald Wilson ◽  
Frank Lu ◽  
Hyungwon Kim ◽  
Ramakanth Munipalli
Keyword(s):  
Detonation Wave ◽  
Engine Concept

Considerations of the All Electric (Accessory) Engine Concept

1995 ◽  
Vol 209 (4) ◽  
pp. 273-280 ◽  
Author(s):  
R I Jones
Keyword(s):  
System Component ◽  
Electrical Machine ◽  
Main Shaft ◽  
Switched Reluctance Machine ◽  
Switched Reluctance ◽  
Design Considerations ◽  
Reluctance Machine ◽  
Starter Generator ◽  
Engine Concept ◽  
Engine Type

The concept of the all electric (accessory) engine (AEE) involves the use of an electrical machine integrated on an engine main shaft acting as a starter generator, providing power to both engine and airframe systems. Through removal of the various constraints caused by the present mechanical accessory drives, this concept apparently provides a number of advantages. However, the concept of an AEE has been around for some years and yet has not been adopted to-date. A brief review of electrical machine types previously considered as internally mounted starter/generators highlights basic problems of the concept. The reasons for favouring the Switched Reluctance Machine for this application are then explained and some present and planned developments on this basis outlined. An approximate sizing of starter/generators to replace shaft off-takes alone and bleed in additions in a civil turbofan application is presented, showing more detailed design considerations. Other system component aspects and concerns are also covered before addressing the effects on the ease of adopting the AEE concept of likely future changes to civil engines. Major differences relative to the civil case are indicated for other engine type applications. Conclusions are then drawn on the likely future of the AEE concept.

A Small Displacement DI Diesel Engine Concept for High Fuel Economy Vehicles

1997 ◽  
Author(s):  
David L. Boggs ◽  
Richard C. Belaire ◽  
Bernd Bartunek ◽  
Manfred Dürnholz ◽  
Hermann-Josef Ecker
Keyword(s):  
Diesel Engine ◽  
Fuel Economy ◽  
Small Displacement ◽  
Di Diesel Engine ◽  
Engine Concept
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