A method of determining propulsion system requirements for long-range, long-endurance aircraft.

1965 ◽  
Vol 2 (6) ◽  
pp. 499-508 ◽  
Author(s):  
J. A. BOGDANOVIC ◽  
A. FEDER ◽  
R. J. WHEATON
Keyword(s):  
Long Range ◽  
Propulsion System ◽  
System Requirements ◽  
Long Endurance

Propulsion System Requirements for Quiet, Long Range, Supersonic Aircraft

2003 ◽  
Author(s):  
Michael J. Brear ◽  
Jack L. Kerrebrock ◽  
Alan H. Epstein
Keyword(s):  
Fuel Consumption ◽  
Long Range ◽  
Individual Component ◽  
Weight Ratio ◽  
Propulsion System ◽  
Supersonic Aircraft ◽  
Engine Thrust ◽  
System Requirements ◽  
Further Development ◽  
Bypass Ratio

This paper discusses the requirements for the propulsion system of supersonic cruise aircraft that are quiet enough to fly over land and operate from civil airports, have trans-pacific range in the order of 6000 nmi (11,112 km), and payload in the order of 10,000 lb (4,545 kg). It is concluded that the resulting requirements for both the fuel consumption and engine thrust/weight ratio for such aircraft will require high compressor exit and turbine inlet temperatures, together with bypass ratios that are significantly higher than typical supersonic-capable engines. Several technologies for improving both the fuel consumption and weight of the propulsion system are suggested. Some of these directly reduce engine weight whilst others, by improving individual component performance, will enable higher bypass ratios. The latter should therefore also indirectly reduce the bare engine weight. It is emphasized, however, that these specific technologies require considerable further development. Whilst the use of higher bypass ratio is a significant departure from more usual engines designed for supersonic cruise, it is nonetheless considered to be a practical option for an aircraft of this kind.

Propulsion System Requirements for Long Range, Supersonic Aircraft

2005 ◽  
Vol 128 (2) ◽  
pp. 370-377 ◽  
Author(s):  
Michael J. Brear ◽  
Jack L. Kerrebrock ◽  
Alan H. Epstein
Keyword(s):  
Fuel Consumption ◽  
Long Range ◽  
Individual Component ◽  
Weight Ratio ◽  
Propulsion System ◽  
Supersonic Aircraft ◽  
Engine Thrust ◽  
System Requirements ◽  
Further Development ◽  
Bypass Ratio

This paper discusses the requirements for the propulsion system of supersonic cruise aircraft that are quiet enough to fly over land and operate from civil airports, have trans-pacific range in the order of 11,112km(6000nmi), and payload in the order of 4545kg(10,000lb.). It is concluded that the resulting requirements for both the fuel consumption and engine thrust/weight ratio for such aircraft will require high compressor exit and turbine inlet temperatures, together with bypass ratios that are significantly higher than typical supersonic-capable engines. Several technologies for improving both the fuel consumption and weight of the propulsion system are suggested. Some of these directly reduce engine weight while others, by improving individual component performance, will enable higher bypass ratios. The latter should therefore also indirectly reduce the bare engine weight. It is emphasized, however, that these specific technologies require considerable further development. While the use of higher bypass ratio is a significant departure from more usual engines designed for supersonic cruise, it is nonetheless considered to be a practical option for an aircraft of this kind.

Aircraft for Long Range and Long Endurance Missions

1964 ◽  
Author(s):  
Richard Q. Boyles ◽  
Lane Barnett
Keyword(s):  
Long Range ◽  
Long Endurance

scholarly journals The Shaft Coupled Lift/Cruise Fan Propulsion System for Navy Multimission V/STOL Aircraft

1977 ◽  
Author(s):  
S. M. Hudson
Keyword(s):  
Power Distribution ◽  
General System ◽  
Propulsion System ◽  
Special Design ◽  
Design Considerations ◽  
System Requirements ◽  
Lift Control ◽  
Large Aircraft

The Navy has promoted requirements for aircraft capable of operating from ships smaller than the CV class of large aircraft carriers. The subsonic roles within these requirements may be met by a multimission V/STOL aircraft powered by an integrated lift cruise fan propulsion system using advanced turboshaft engines and shafting for power distribution. General system requirements, unique features and characteristics, and special design considerations relating to V/STOL, such as propulsive lift control, engine sizing and engine out ratings, are presented.

scholarly journals OCEANIDS: Building Next Generation Maritime Autonomous Systems

2018 ◽  
Author(s):  
M Furlong ◽  
R Marlow ◽  
S McPhail ◽  
A Munafo ◽  
M Pebody ◽  
...  
Keyword(s):  
Long Range ◽  
Autonomous System ◽  
Technological Development ◽  
Autonomous Systems ◽  
Deep Ocean ◽  
Next Generation ◽  
Hazardous Environments ◽  
Long Duration ◽  
Navigational System ◽  
Long Endurance

Oceanids is a 4-year programme for the technological development of innovative Maritime Autonomous System (MAS) platforms and associated sensors that will include next generation robotic AUVs, sensors and networks to undertake ambitious, long-range, long-endurance deployments in extreme and hazardous environments, such as the deep ocean or under-ice environments. This paper describes the design of two new types of robotic AUVs, the Autosub 2000 Under-Ice and the Autosub Long Range 1500 vehicles that are being developed under the programme. Two key components of the AUVs are described, the autonomy framework and the navigational system, which relies on a newly developed terrain-aided navigation (TAN) system. At-sea results of the TAN are also reported as obtained during long duration operational deployments done in 2017. 

scholarly journals Electric vertical take-off and landing fixed wing unmanned aerial vehicle for long endurance or long range?

2019 ◽  
Vol 31 ◽  
pp. 99-107
Author(s):  
Dimo Zafirov
Keyword(s):  
Mathematical Models ◽  
Long Range ◽  
Unmanned Aerial Vehicle ◽  
Field Conditions ◽  
Flight Duration ◽  
Flight Range ◽  
Wing Load ◽  
Aerial Vehicle ◽  
Long Endurance

An analysis of requirements to electric vertical take-off and landing unmanned aerial vehicle with fixed wings is carried out in this article. These aircraft have to fulfil requirements of users and to be convenient for operation in any field conditions. Long flight duration and long flight range are important for most missions. Mathematical models for both cases are presented and it has been found that the requirements for the wing load are different. It is recommended to use a type of UAV (Unmanned Aerial Vehicle) that is modular and allows performing flights with different configurations and payload depending on the mission in order to fulfill these requirements.

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