The document discusses the Zero Emission Hyper Sonic Transport (ZEHST), a supersonic passenger airliner project envisioned to fly from London to Japan in less than 3 hours by 2050. It would use biofuel and oxygen/hydrogen propulsion systems, including turbofans for takeoff, rocket boosters, and under-wing supersonic ramjets to reach Mach 4 speeds. The document outlines the various propulsion systems, highlights design considerations like reducing risks through a holistic approach, and provides computer renderings of what the ZEHST may look like. It concludes that a holistic design process is essential to understand the challenges of such a radical concept.

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SEMINAR ON
Z.E.H.S.T. - 2050
Submitted in partial fulfillment of
award degree of B.TECH(M.E)
Under gracious guidance of:-
PROF. ANKIT DUA ( MECH. DEPTT.)
SUBMITTED BY:-
PARAG PRIYANK
75114037
B.TECH M.E
2011-2015

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ZERO EMISSION HYPER SONIC
TRANSPORT - 2050
WELCOME TO FUTURE TRANSPORTATION
SYSTEM

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WHAT IS IT ALLABOUT ???
 The Zero Emission Hyper Sonic Transport or ZEHST is
a supersonic passenger airliner project by EADS and Japan.
 It can be seen as a descendant of the Concorde airliner.

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 The plane is envisaged to be propelled by biofuel made from
seaweed and by oxygen/hydrogen.
 Using turbofans for take off would make ZEHST no more noisy than
current-day ordinary planes.
 ZEHST is envisaged to fly by 2050 and would fly from London to
Japan in less than 3 hours
 Unveiled on 18 June 2011 by EADS at Le Bourget air show, it is
projected to fly at Mach 4, 32 km above the ground, carrying 150 to 200
people.
 It would combine three propulsion systems: two turbofans/turbojet for
take-off and up to Mach 0.8, then rocket boosters up to Mach 2.5, then
two under-wing supersonic ramjets would accelerate it to Mach 4.

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PROPULSION SYSTEM

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1. TURBOJET ENGINE:-
 The turbojet is an airbreathing jet engine, usually used in aircraft. It consists of
a gas turbine with a propelling nozzle
 The gas turbine has an air inlet, a compressor, a combustion chamber, and
a turbine (that drives the compressor). The compressed air from the compressor
is heated by the fuel in the combustion chamber and then allowed to expand
through the turbine.
 The turbine exhaust is then expanded in the propelling nozzle where it is
accelerated to high speed to provide thrust
 The jet engine is only efficient at high vehicle speeds.
 Turbojet engines have been used in isolated cases to power vehicles other than
aircraft, typically for attempts on land speed records

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2. RAMJET ENGINE
 A ramjet, sometimes referred to as a flying stovepipe or an athodyd (an
abbreviation of aero thermodynamic duct), is a form of airbreathing jet
engine that uses the engine's forward motion to compress incoming air
without an axial compressor.
 Ramjets cannot produce thrust at zero airspeed; they cannot move an aircraft
from a standstill. A ramjet powered vehicle, therefore, requires an assisted
take-off like a rocket assist to accelerate it to a speed where it begins to
produce thrust.

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 Ramjets work most efficiently at supersonic speeds around Mach 3 (2,284 mph;
3,675 km/h). This type of engine can operate up to speeds of Mach 6 (2,041.7 m/s;
7,350 km/h).
 Ramjets generally give little or no thrust below about half the speed of sound, and
they are inefficient (less than 600 seconds) until the airspeed exceeds 1,000
kilometres per hour (280 m/s; 620 mph) due to low compression ratios.

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3. CRYOGENIC/LIQUID ROCKET ENGINE
 A cryogenic rocket engine is a rocket engine that uses a cryogenic
fuel or oxidizer, that is, its fuel or oxidizer (or both) are gases liquefied
and stored at very low temperatures.
 The major components of a cryogenic rocket engine are the combustion
chamber (thrust chamber), pyrotechnic initiator, fuel injector,
fuel cryopumps, oxidizer cryopumps, gas turbine, cryo valves,
regulators, the fuel tanks, and rocket engine nozzle
 Various cryogenic fuel-oxidizer combinations have been tried, but the
combination of liquid hydrogen (LH2) fuel and the liquid oxygen (LOX)
oxidizer is one of the most widely used.

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SPECIFIC IMPULSE:-
By definition, it is the impulse delivered per unit of propellant consumed,
and is dimensionally equivalent to the thrust generated per unit
propellant flow rate.

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DESIGN CONSIDERATIONS:-
 The specificity of the ZEHST program is to approach hypersonic transport
design with a holistic view. In addition to the traditional hypersonic
conceptual design focused on propulsion, aerodynamics and materials.
 The rationale for this choice is to reduce the risks associated with such a
radically new concept by allowing a full exploration of the design field;
covering not only the vehicle key design parameters but, beyond this, all
of its operating and regulatory key factors.
 To minimize the development risks and costs and to be on the market as
soon as possible, it was decided to select as a starting point a well-defined
Spaceplane baseline rather than a blank sheet of paper.

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NARROW IDEA WHAT IT WILL BE:-

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WHAT IT MAY LOOK LIKE:- (COMPUTER RENDERINGS)

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CONCLUSION:-
From the design perspective, the holistic approach selected for the design of
the ZEHST hypersonic transport clearly demonstrates the value of this
method to explore the uncharted territories of such a radical and ambitious
project. As the boundaries, constraints and sizing cases may be completely
different from those of a well-known design, it is crucial to explore the
whole design space, not only in terms of vehicle sizing, but also of
operating environment in a wider sense (including certification and
environment), in order to gain a sound understanding of the problem and to
identify the key drivers of the design.
A holistic approach is thus essential to understand the true design drivers of
such a radical design and explicitly highlight the challenges and the design
levers to tackle them.
This is clearly a core utilization of all the technical master-mind in world
we have.

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