HYPERSONIC VEHICLES

1. TERM PAPER
PRESENTATION
HYPERSONIC VEHICLES
BY : KHUSHIN LAKSHKAR

2. WHAT ARE HYPERSONIC
VEHICLES?

3. Regime Mac mph Km/h m/s General plane characteristics
Subsonic <0.8 <610 <980 <270 Most often propeller-driven and
commercial turbofan aircraft with high
aspect-ratio (slender) wings, and rounded
features like the nose and leading edges
Transsonic 0.8-
1.2
610-915 980-
1470
270-
670
Transonic aircraft nearly always
have swept wings that delay drag-divergence,
and often feature designs
adhering to the principles of the
Whitcomb Area rule
Supersonic 1.2-
5.0
large differences in their aerodynamic
design because of the radical differences
in the behaviour of flows above Mach 1.
Sharp edges, thin aerofoil-sections, and
all-moving tailplane/canards are common.
Modern combat aircraft must compromise
in order to maintain low-speed handling;
"true" supersonic designs include the F-
104 Starfighter and
BAC/Aérospatiale Concorde

4. Regime Mac mph Km/h m/sec General plane characteristics
Hypersonic
vehicles
5.0-
10.0
7680 12300 7410 Cooled nickel-titanium skin; highly integrated
(due to domination of interference effects:
non-linear behaviour means that
superposition of results for separate
components is invalid), small wings, see X-51A
Waverider and HyperSoar
Highhyperson
ic
vehicles
10.0-
25.0
7680
-
6250
12
1230
0-
3074
0
Thermal control becomes a dominant design
consideration. Chemically reacting flow can
also cause corrosion of the vehicle's skin, with
free-atomic oxygenfeaturing in very high-speed
flows. Hypersonic designs are often
forced into blunt configurations because of the
aerodynamic heating rising with a
reduced radius of curvature.
Re-entry >25.0 Ablative heat shield; small or no wings; blunt
shape

5. HISTORY OF HYPERSONIC
VEHICLES
• First Hypersonic vehicle : V2 Rocket, 8228kmh
• X-15, 1959, 7424kmh, Mac 5to Mac 6-7
• First human travel at Hypersonic speed : Yuri Gagrein,
1961, Vostok
• 14X
• Aurora (aircraft) Avatar (spacecraft), Ayaks
• Bristol Spaceplanes
• DARPA Falcon Project
• Fictional military aircraft
• GLL-8 (Gll-VK) Igla
• NASA X-43

6. LATEST HYPESONIC VEHICLES
Boeing X-51
• Engine : SJY-61 Scramjet
• Maximum speed: >3,900 mph (>6,200 km/h)
• Maximum speed: Mach >5.1
• Range: 460 miles (740 km)
• Service ceiling: 70,000 ft (21,300 m)

7. INDIAN MISSILES
BRAHMOS - II
• Engine Scramjet
range
• 300 km (186.4
mi)SpeedMach 7Launch
platform
• Ship, submarine, aircraft
and land-based mobile
launchers
• fastest cruise missile in the
world
Shaurya
• EngineTwo stage, solid-fueled
rocket motorsOperational
range
• 700 km@ 1000 kg and 1900
km @ 180 kg Flight altitude40
Km SpeedMach 7.5 [2Guidance
system
• Ring laser gyroscopeLaunch
platform
• Canisterized launch from TEL
or underground silo[2]

8. SCRAMJET - ENGINE

9. SCRAMJET ENGINE

12. SPECIAL
COMPOSITE MATERIALS
•Why we need special material?

13. • Reinforced carbon–carbon (RCC), in the nose capg gear doors, the
arrowhead aft of the nose landing gear door, and the wing leading edges.
Used where re-entry temperature exceeded 1,260 °C (2,300 °F).
• High-temperature reusable surface insulation (HRSI) tiles, used on the
orbiter underside. Made of coated LI-900 Silica ceramics. Uses where
reentry temperature was below 1260 °C.
• Fibrous refractory composite insulation (FRCI) tiles, used to provide
improved strength, durability, resistance to coating cracking and weight
reduction. Some HRSI tiles were replaced by this type.
• Flexible Insulation Blankets (FIB), a quilted, flexible blanket-like surface
insulation. Used where reentry temperature was below 649 °C (1,200 °F).
• Low-temperature Reusable Surface Insulation (LRSI) tiles, formerly used on
the upper fuselage, but were mostly replaced by FIB. Used in temperature
ranges roughly similar to FIB.
• Toughened unipiece fibrous insulation (TUFI) tiles, a stronger, tougher tile
which came into use in 1996. Used in high and low temperature areas.
• Felt reusable surface insulation (FRSI). White Nomex felt blankets on the
upper payload bay doors, portions of the midfuselage and aft fuselage
sides, portions of the upper wing surface and a portion of the
OMS/RCSpods. Used where temperatures stayed below 371 °C (700 °F).

14. Some physical aspects of
Hypersonic flow
• Thin shock layer
•Entropy layer
•Viscous Intereraction
•High Tempreture Effects
•Low densityFlow

15. THANK YOU