In 1921, the Army Aviation Company’s Workshops (FMV) at Malmen/Malmslätt near Linköping got an  preliminary order of ten reconnaissance aircraft of Henry Kjellson’s design. The aircraft got the designation S 21 (S = ”Spaning” = ”Reconnaissance” - 21 = 1921, the year of the design). The aircraft had a crew of two - pilot and observer. In these days, aircraft engines was an article in short supply in Sweden. When 22 airship (!) engines type Maybach IVA (260 hp) eventually were obtained from Germany, Kjellson, the chief engineer of FMV, had to design an airframe which suited this engine.

The first S 21 was delivered in 1922. During the trials, several shortcomings were discovered. After some amendments, the other nine airframes were built in 1923-1924. Notwithstanding a long tail, the aircraft was nose-heavy. In the end of 1924, three of the ten aircraft were written(Read More)......

The IITM  Summer Fellowship Programme of two months with stipend is designed to enhance awareness and interest in high quality academic research among young Engineering, Management, Sciences and Humanities students through a goal oriented summer mini project
undertaken at the Indian Institute of Technology Madras.

Eligibility: 

Candidates pursuing third year of B.E./B.Tech./B.Sc.(Engg)/Integrated
M.E./M.Tech. programme, first year of M.Sc./M.A, MBA with 

(Read more....)

JNTU-HYD : B.Tech 2-1(R07,R05,RR,NR) Results Are Out

   

Check ur results from below links

II Year B.Tech. I Semester (R07) Results - November, 2009

II Year B.Tech. I Semester (R05) Results - November, 2009

II Year B.Tech. I Semester (RR) Results - November, 2009 

II Year B.Tech. I Semester (NR) Results - November, 2009

NOTE : Last date for Recounting/Revaluation: 03-03-2010

Any discrepancy should be forwarded through the Principal before 3rd-Mar-2010 and
no request will be entertained after due date.B.Tech 2-1 Supplementary Exams will be conducted from 7th JUNE-2010 To 26th JUNE-2010

 

 

Helicopters come in many sizes and shapes, but most share the same major components. These components include a cabin where the payload and crew are carried; an airframe, which houses the various components, or where components are attached; a powerplant or engine; and a transmission, which, among other things, takes the power from the engine and transmits it to the main rotor, which provides the aerodynamic forces that make the helicopter fly. Then, to keep the helicopter from turning due to torque, there must be some type of antitorque system. Finally there is the landing gear, which could be skids, wheels, skis, or floats. This chapter is an introduction to these components.

 THE MAIN ROTOR SYSTEM
The rotor system found on helicopters can consist of a single main rotor or dual rotors. With most dual rotors,
the rotors turn in opposite directions so the torque from one rotor is opposed by the torque of the other. This
cancels the(Read More).....

 Specifications of,

Boeing 787 Dreamliner Long-Range, Mid-Size Airliner, USA.

Key Data:
Crew                                  2
Passenger Capacity          290 to 330 (787-3),
                                           210 to 250 (787-8),
                                           250 to 290 (787-9)
Maiden Flight                   15 December 2009

Dimensions:
Length                      56m, 57m (787-3 and 787-8),
                                  63m (787-9)
Wingspan                  52m (787-3), 60m (787-8), 
                                  63m (787-9)
Fuselage Cross-Section        5.74m
Height                          17.4m, 17m
                                    (787-3 and 787-8 and 787-9)

Cabin:
Configuration               Twin-aisle

Performance:
Maximum Take-Off Weight     165,000kg (787-3),
                                                    219,540kg (787-8),
                                                    244,940kg (787-9)
Range                             14,800km to 15,750km (787-9),
                                        4,650km to 5,650km (787-3),
                                        14,200km to 15,200km (787-8)
Speed                              Mach 0.85

Cargo:
Total Cargo Volume        4,400ft³ (787-3 and 787-8),
                                          5,400ft³ (787-9)

Featured Suppliers:

Aviation Technical Center of Almaty International Airport - Aircraft Maintenance and Aircraft Component and Structural Repair Services
Data Device Corporation - MIL-STD-1553 and ARINC 429 Aerospace Products

 

AgustaWestland AW101 Medium-Lift Helicopter, Italy / United Kingdom

Specification of AW101 are as follows ,

Dimensions:
Length, Rotors Turning       22.8m (74.8ft)
Height Overall                      6.63m (21.75ft)
Length Fuselage                  19.63m (64.4ft)
Width, Overall                     5.67m (18.6ft)
Main Rotor Diameter        18.6m (61ft)
Tail Rotor Diameter           4m (13.11ft)
Number of Blades               5/4
(Main / Tail)

Weights:
Maximum Gross Weight           14,600kg (32,188lb)
(Internal / External Load)
Basic Empty Weight                  8,600kg (18,960lb)
Maximum Useful Load              6,000kg (13,228lb)
Sling Load                                  4,536kg (10,000lb)

Engines:
Type                                  3 x GE CT7-T6A
Take-Off, Rating              3 x 1491kW (3 x 2,000shp)
Maximum Continuous,     3 x 1283kW (3 x 1,720shp)
Rating

Performance:
Maximum Speed                280km/h (150kt)
Rate of Climb                     10.16m/s (2,000ft/min)
Hovering IGE                      2,316m (7,600ft)
Hovering OGE                    1,067m (3,500ft)
Service Ceiling                    4,575m (15,000ft)
Maximum Range                Over 1,389km (750nm)
(Internal Fuel Tank)
Maximum Endurance          6 hours
(Internal Fuel Tank)

Featured Suppliers:
Data Device Corporation - MIL-STD-1553 and ARINC 429 Aerospace Products
Evonik Foams - SOLIMIDE Polyimide Acoustical and Thermal Aircraft Insulation Foam
TITAL - Titanium Investment Castings, Aluminium Investment Castings, HERO Premium Casting and Rapid Prototyping
Wheelabrator Group - Peening and Surface Engineering Solutions.

First Flight: March 17, 1966
Mission: Test viability of ducted lift propellers for VTOL aircraft
Major Accomplishments:  Provided long term test bed for VTOL research

Power Source: 4 GE YT58-GE-8D shaft turbine engines
Wing Span: (Front:) 22' 11"
Wing Span: (Rear:) 39" 3"
Length: 39' 6"
Weight (Loaded): 18,016 lbs
Maximum Achieved Speed: 255 mph
Additional Information: 2 X-22a were constructed. The first suffered heavy damage in August of 1965 and remaining parts were used to complete the second X-22a. Flights were conducted from March, 1966 to October, 1984.