TERM PAPER PRESENTATION

HYPERSONIC VEHICLES

BY : KHUSHIN LAKSHKAR

WHAT ARE HYPERSONIC VEHICLES?

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

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

Highhypersonicvehicles

10.0-25.0

7680-625012

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

HISTORY OF HYPERSONICVEHICLES

• 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

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)

INDIAN MISSILES

BRAHMOS - II• Engine Scramjet

range

• 300 km (186.4 mi)SpeedMach 7Launchplatform

• Ship, submarine, aircraft and land-based mobile launchers

• fastest cruise missile in the world

Shaurya• EngineTwo stage, solid-fueled

rocket motorsOperationalrange

• 700 km@ 1000 kg and 1900 km @ 180 kg Flight altitude40 Km SpeedMach 7.5 [2Guidancesystem

• Ring laser gyroscopeLaunchplatform

• Canisterized launch from TELor underground silo[2]

SCRAMJET - ENGINE

SCRAMJET ENGINE

SPECIALCOMPOSITE MATERIALS

•Why we need special material?

• 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 theOMS/RCSpods. Used where temperatures stayed below 371 °C (700 °F).

• Thin shock layer

•Entropy layer

•Viscous Intereraction

•High Tempreture Effects

•Low densityFlow

Some physical aspects of Hypersonic flow

THANK YOU