Aerospace Vehicle Development Applications of Atmospheric Thermodynamic Inputs

Vaughan, William W.; Johnson, Dale L.

doi:10.5028/jatm.v6i1.279

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…This study was based on the conditional vertical distribution of the thermodynamic air parameters in the Earth's atmosphere known as the International Standard Atmosphere [23,24]. Therefore, we will assume that with the flight altitude, the environmental parameterspressure p, temperature T and air density ρ -are changing according to the law shown in the graphs in Fig.…”

Section: Starting Positions and Backgrounds For Analytical Calculationsmentioning

confidence: 99%

Study of super/turbocharger system for helicopter diesel engine

Прохоренко¹,

Vrublevskyi²,

Grytsyuk³

et al. 2021

Diagnostyka

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The article demonstrates a rational scheme of the supercharging system in a helicopter diesel engine with a power of 100 kW, regardless of the flight altitude, and proposes a method for assessing the power losses for a diesel engine depending on the flight altitude using a mathematical model. There are three variants of an engine supercharger scheme with a single-stage turbocharger, a two-stage one with parallel or sequential compressor drive and a turbo-blower. As a result of the computational analysis according to the original method, it was shown that from the point of view of the least energy consumption two-stage scheme with a compressor and a sequential drive is the most rational. To reduce energy losses in the drive with two-stage supercharging, a concept for controlling the pressure system was proposed, which includes changing the rotational speed of the compressor drive and adjusting the throttles. Simulation of the engines running during the climb / descent of the helicopter showed that the proposed pressure scheme and control concept is effective. In order to improve the quality of regulation, the possibility to use an electric drive with the first stage compressor is being considered.

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Section: Starting Positions and Backgrounds For Analytical Calculationsmentioning

confidence: 99%

Study of super/turbocharger system for helicopter diesel engine

Прохоренко¹,

Vrublevskyi²,

Grytsyuk³

et al. 2021

Diagnostyka

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show abstract

“…Johnson (2008), Pearson et al (1996), Smith and Adelfang (1998), Smith et al (1982), Vaughan and Brown (1983), Von Braun (1967) and Potter (1984) document various terrestrial environment (0 to 49 nmi (0 to 90 km) altitude) guidelines for engineering to use (with the proper interpretation) when starting a new project such as a launch or space vehicle. In particular, Johnson (2008) compiled a great amount of general guideline criteria for the terrestrial environment that have been used in many NASA and other organization's aerospace vehicle programs (Vaughan and Johnson 2013;2014). Similarly, Anderson and Smith (1994) document design guidelines for the general space environment (>49 nmi (>90 km) altitude).…”

Section: Data Sources and Considerations For Developing Natural Envirmentioning

confidence: 99%

The Role of Terrestrial and Space Environments in Launch Vehicle Development

Johnson

Vaughan

2019

J.Aerosp. Technol. Manag.

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Natural (Terrestrial & Space) Environment (NE) phenomena play a significant role in the design and flight of aerospace vehicles and in the integrity of the associated aerospace systems and structures. Natural environmental design criteria guidelines described here are based on measurements and modeling of atmospheric and climatic phenomena relative to various aerospace vehicle development and mission/operational procedures, and for vehicle launch locations. Both the terrestrial environment (0-90 km altitude) and the space environment (Earth orbital altitudes) parameters and their engineering application philosophy are given with emphasis on launch vehicle-affected terrestrial environment elements. This paper also addresses the basis for the NE guidelines presented, the interpretation of the guidelines, and application to the development of launch or space vehicle design requirements. This paper represents the first of three on this subject.

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Developing a Mathematical Modelling Code for Keeping the Power of Multi Turbocharged Engines at Flight Altitudes

Roueini

Mirzabozorg

Kheradmand

2020

J.Aerosp. Technol. Manag.

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In this paper, a code is developed in C++ programming language aiming to select and introduce a well-chosen propulsion system for appropriate operation in an aircraft. By using a suitable turbocharged engine, the inlet pressure of the engine manifold will increase to a level equal to the pressure at sea level. Therefore, the aircraft engine will not notice the drop of pressure caused by the increase in altitude. Consequently, the engine power will not be reduced. On the other hand, at high altitude, using only one turbocharger is not adequate to supply engine inlet pressure and flow rate equivalent to sea level conditions, requiring the use of more turbochargers. The code developed in this study will be able to introduce the appropriate turbocharged engine based on the flight altitude and the required power engine of an air vehicle. The altitude defined in this code ranges from 5 to 30 kilometers, which leads to a selection of one to three turbochargers plus a number of intercoolers, according to user input parameters. The objective function of this optimization problem is defined as a function of turbochargers efficiency. However, this objective function can be modified according to the user requests and requirements.

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Aerospace Vehicle Development Applications of Atmospheric Thermodynamic Inputs

Cited by 3 publications

References 7 publications

Study of super/turbocharger system for helicopter diesel engine

Study of super/turbocharger system for helicopter diesel engine

The Role of Terrestrial and Space Environments in Launch Vehicle Development

Developing a Mathematical Modelling Code for Keeping the Power of Multi Turbocharged Engines at Flight Altitudes

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