Advanced Medium Combat Aircraft (AMCA) model exhibited at Aero India 2019

 

Advanced Medium Combat Aircraft displayed at Aero India 2019

The Advanced Medium Combat Aircraft (AMCA) is an Indian single-seat, twin-engine, all-weather fifth-generation stealth, multirole combat aircraft being developed for the Indian Air Force and the Indian Navy. AMCA is designed as a single-seat, twin-engine combat aircraft. The AMCA is currently the only 5th generation fighter under development in India.

• The AMCA Mark 1 will come equipped with 5th generation technologies.
• The AMCA Mark 2 will have the incremental 6th generation technology upgrades.

Advanced Medium Combat Aircraft model exhibited at Aero India 2019

DESIGN:-

The AMCA is designed with shoulder mounted diamond shaped trapezoidal wings, a profile with substantial area-ruling to reduce drag at transonic speeds, and a stabilator V-tail with large fuselage mounted tail-wing. Flight control surfaces include leading and trailing-edge flaps, ailerons, rudders on the canted vertical stabilizers, and all-moving tailplanes; these surfaces also serve as air brakes. The cockpit features a single seat configuration which is placed high, near the air intakes and wings of the aircraft to provide good visibility to the pilot with a single bubble canopy. A leading-edge root extension (LERX), which is a small fillet, is situated on the front section of the intake and wings of the aircraft. It has a typically roughly rectangular shape, running forward from the leading edge of the wing root to a point along the fuselage. The aircraft features a tricycle landing gear configuration. The weapons bay is placed on the underside of the fuselage between the nose and main landing gear. The AMCA is designed to produce a very small radar cross-section, to accomplish this it features "S-shaped" air-intakes to reduce radar exposure to the fan blade which increases stealth, uses an internal weapons bay and features the use of composites and other materials. The flight control surfaces are controlled by a central management computer system. The AMCA design has inherent radar stealth, achieved through twin-tail layout, platform edge alignment and serration, body conformal antenna and low intercept radar, diverterless supersonic inlet (DSI) with serpentine ducts which conceal engine fan blades, internal weapons bay and extensive use of composites in airframe. It will also use radar-absorbent materials wherever necessary.

AVIONICS:-

The AMCA is expected to have distributed passive sensors with Artificial intelligence (AI) assisted multi-sensor data fusion to increase situational awareness and to work in tandem with the advanced electronic warfare (EW) suite onboard AMCA. The AMCA has a distributed processing system employing fast processors and smart subsystems. The AMCA will also have an integrated vehicle health monitoring system which works on sensor fusion. AMCA will be equipped with a larger and powerful variant of the Uttam AESA Radar which will use gallium nitride (GaN) technology. It will be mounted on a mechanically steerable mount. An onboard condition monitoring system is also planned to be included in the AMCA. The platform will be equipped with a quadruple digital fly-by-optics control system using fibre optic cables to reduce weight, increase the rate of data transfer and reduce electromagnetic interference.

PROPULSION:-

The AMCA is to be powered by two afterburning turbofan engines. The plan is to equip General Electric F414 afterburning turbofan engine on AMCA Mark-1, while a more powerful joint venture (JV) engine is planned for AMCA Mark-2.

National Wind Tunnel Facility (NWTF)

 

National Wind Tunnel Facility Fan

The National Wind Tunnel Facility (NWTF) was established in 1999 at IIT Kanpur, India, to meet the national needs in areas of aeronautical and non-aeronautical R&D activities. The NWTF is a closed-return, continuous, atmospheric wind tunnel equipped with several auxiliary systems for different testing needs. The test section of NWTF is 2.25m high, 3m wide and 8.75m long and is split into two parts; an upstream (5.75m) and a downstream (3m) part. Air speed up-to 80m/s in the test section is produced by a single-stage 12-bladed axial-flow fan powered by a 1000kW variable speed DC motor. Four fine mesh screens placed downstream of the honeycomb and upstream of a 9:1 contraction ensure a flow of exceptionally low turbulence  (u’/U<0.08%). 

Important features of NWTF

1. String type model support system with five independent motions 
2. Turntable systems for aerospace and non aerospace applications
3. Laser light sheet generation system for flow visualization 
4. 3D Stereoscopic PIV system 
5. Hot wire anemometry 

Special Capabilities of NWTF 

1. Full model testing with sting support system 
2. Half model testing with external balance 
3. Two-dimensional model testing using turntables 
4. Gust and cross wind simulation 
5. Aero-acoustic testing 
6. Engine intake studies using suction mass flow system 
7. Can be configured as open jet facility

National Wind Tunnel Facility (NWTF), IIT Kanpur

Wind tunnel test section

Wind tunnel test section (Year-2020)

NWTF, IIT Kanpur (Year-2020)

Piper PA-32R

Piper Sarotoga II HP (registration: VT-ETL) at IIT Kanpur Flight Laboratory Hangar

The Piper PA-32R is a six or seven seat high-performance, single engine, all-metal, fixed-wing aircraft produced by Piper Aircraft, Vero Beach, Florida, USA. The aircraft is powered by a single Lycoming IO-540-K1G5D 6 cylinder, direct drive, horizontally opposed, air cooled engine. The aircraft is used for personal use, air taxi & freight aircraft. The landing gears are retractable. The early production version of Piper PA-32R are known as Piper Lance, while later models as shown in this blog images are known as Piper Saratoga. Saratoga models provided improved avionics, engine and interior touches but retained the same airframe design. Production of the Saratoga was discontinued in 2009. The PA-32R was built under license by Embraer in Brazil as the Embraer EMB-721 Sertanejo.

Inside the Cockpit

Cockpit Instruments 

Inside the aircraft

Performing Flight Mechanics related experiments with the aircraft

IIT Kanpur Flight Laboratory Hangar (Year-2020)

Pipistrel Sinus

The above image is of a Pipistrel Sinus 912 glider (Registration:-VT-GII) in the IIT Kanpur Flight Laboratory hangar (Year-2020)

The Pipistrel Sinus is a two-seat, single-engine, ultralight, cantilever monoplane motor glider. The wing and fuselage were designed by the Italian aerodynamicist Franco Orlando. It has good short take-off and landing (STOL) characteristics and it can be equipped with a full airframe emergency recovery parachute system. The first flight of the prototype took place on October 16, 1996. It is constructed using composite materials. The Pipistrel Sinus comes with either nose-wheel or taildragger landing gear configuration. The aircraft is built by Slovenian light aircraft manufacturer 'Pipistrel'. Its facilities are located in Slovenia and Italy. In April 2022, the company was purchased by Textron.

General Characteristics (as in Pipistrel Company Website)

1. Wing Span- 14.97 m
2. Length- 6.6 m
3. Height- 1.70 m
4. Wing Area- 12.26 m^2
5. Aspect Ratio- 18.3
6. Service Ceiling- 8800 m
7. Endurance (standard tanks)- 5.8 hours (348 minute)
8. Range distance- 1200 km
9. take off run- 88 m
10. take off run over 15 m obstacle- 148 m
11. Powerplant- Rotax 912 UL2 

Meaning of dimensions mentioned in this article:- 1 inch = 0.0254 m; 1 foot = 0.3048 m; 1 inch = 0.0833333 foot; 1 pound = 0.453592 kg; 1 nautical miles (nm) = 1.852 km

Pipistrel Sinus 912 glider at IIT Kanpur flight laboratory hangar (Year-2020)

Glider

Dassault Rafale at Aero India 2019

Selfie with Rafale displayed at Aero India 2019 air show

The Rafale fighter jet shown in the above image belongs to the French Air Force (Armée de l'air) was displayed during Aero India 2019 (February) Air show held at Bangalore's Yelahanka Air Force Station.

The Dassault Rafale is a twin engine, canard delta wing fighter aircraft designed and built by Dassault Aviation. The Rafale is fitted with two Snecma M88 engines, each capable of providing up to 50 kilonewtons (11,000 pounds-force) of dry thrust and 75 kN (17,000 lbf) with afterburners. The first prototype of Rafale (also known as Rafale A) which was powered by 2 General Electric F404 engines made it's first flight on 4 July 1986. The Rafale A was used until January 1994, and was retired after 867 sorties

Rafale B is two-seater version for the French Air and Space Force. Rafale C is same as Rafale B but single-seat version for the French Air and Space Force. Rafale M is similar to Rafale C, but with modifications to allow operations from CATOBAR – equipped aircraft carriers. For carrier operations, the M model has a strengthened airframe, longer nose gear leg to provide a more nose-up attitude, larger tailhook between the engines, and a built-in boarding ladder. Consequently, the Rafale M weighs about 500 kg (1,100 lb) more than the Rafale C. It is the only non-US fighter type cleared to operate from the decks of US carriers, using catapults and their arresting gear, as demonstrated in 2008 when 6 Rafales from Flottille 12F integrated into the USS Theodore Roosevelt Carrier Air Wing interoperability exercise.

In December 2000, the French Naval Aviation received its first two Rafale M fighters. In April 2005, the French Air Force received its first three F2 standard Rafale Bs. 

The other operators of this aircraft are India, Croatia, Egypt, Qatar, and Greece.

Video of the France Air Force Rafale jet on display at Aero India 2019

Rafale and India

 As of June 2022, 36 Rafale fighters are in service with the Indian Air Force. The Rafale DH is the two-seater version for the Indian Air Force and Rafale EH is the single-seat version for the Indian Air Force. 

The No. 17 Squadron (Golden Arrows) stationed at the Ambala Air Force Station and the No. 101 Squadron (Falcons) based at the Hasimara Air Force Station operates the Dassault Rafale. 

In July 2023, the Indian Ministry of Defence revealed that the Defence Acquisition Council had granted Acceptance of Necessity for 22 Dassault Rafale M fighters and 4 Dassault Rafale DH conversion trainers for the Indian Navy.

Cessna 206H

 

Myself with Cessna 206H at IIT Kanpur Flight Laboratory Hangar (Year-2020)

The Cessna 206H is a single-engine, general aviation aircraft with three fixed landing gear having an ability to carry maximum 6 passengers. The Cessna 206H is powered by a Lycoming IO-540-AC1A powerplant while the turbocharged T206H is powered by a Lycoming TIO-540-AJ1A engine. Production of the 206H ended in 2013 with a total of 369 being produced. An improved version of the T206H known as the Turbo Stationair HD was introduced in July 2016 with gross weight increased by 189 lb (86 kg). As of 2023, the T206H Turbo Stationair HD is the only model still in production, with 1,264 being built as of 2017. The Cessna 206H aircraft has a pilot entry door and a rear double clamshell door for access to the middle and back seats. The Cessna 206H can operate from remote, undeveloped airfields without the aid of expensive ground facilities. Hence Cessna 206H falls under the category of bush planes.

The high wings of Cessna 206H allows ease loading and unloading of both passengers and cargo from the cockpit. Another advantage of high wing design is that it gives pilot in the cockpit, a good downward visibility during landing and take-off of the aircraft which reduces chances of aircraft accidently encountering any obstacle in the ground. Cessna 206H is equipped with a lift strut. On a high-wing aircraft, a lift strut connects an outboard point on the wing with a point lower on the fuselage to form a rigid triangular structure. While in flight the strut acts in tension to carry wing lift to the fuselage and hold the wing level, while when back on the ground it acts in compression to hold the wing up. For aircraft of moderate engine power and speed, lift struts represent a compromise between the high drag of a fully cross-braced structure and the high weight of a fully cantilevered wing.

The aircraft is popular with air charter companies and small cargo air carriers, and is operated by private individuals and companies. The Cessna 206 aircraft is also operated by military of  USA , Paraguaya , Pakistan, Uruguay, Venezuela, Guyana.

General characteristics for Cessna Turbo Stationair HD 

1. Length-28 ft 3 in (8.6 m)
2. Height-9 ft 4 in (2.8 m)
3. Width- 1.08 m
4. Wingspan-36 ft (10.97 m)
5. Wing Area-174 sq ft (16.17 sq m)
6. Maximum Takeoff Weight-3,789 lb (1,719 kg)
7. Maximum Landing Weight-3,600 lb (1,633 kg)
8. Maximum Payload-1,235 lb (560 kg)
9. Maximum Range-703 nm (1,302 km)
10. Service Ceiling-26,000 ft (7,925 m)
11. Maximum Cruise Speed-161 ktas (298 km/h)
12. Take off Distance- 600 m
13. Ground roll- 323 m
14. Landing Distance- 425 m
15. Ground Roll- 224 m

Meaning of dimensions mentioned in this article:- 1 inch = 0.0254 m; 1 foot = 0.3048 m; 1 inch = 0.0833333 foot; 1 pound = 0.453592 kg; 1 nautical miles (nm) = 1.852 km

The takeoff distance consists of two parts, the ground run, and the distance from where the vehicle leaves the ground to until it reaches 50 ft (or 15 m). The sum of these two distances is considered the takeoff distance.

KTAS:- Knots True Airspeed/True Airspeed (TAS) of an aircraft is the speed of the aircraft relative to the air mass through which it is flying.

IIT Kanpur Airport (Year-2020)

Cessna 206H (registration:-VT-IIT) at the IIT Kanpur Airfield apron

NAL Hansa

 

NAL Hansa aircraft registration VT-XIW at HAL Museum, Bangalore (Year-2021)

The Hansa is a 2 seater aircraft designed by India with a low wing and tricycle landing gear configuration constructed using composite materials. The first prototype based on Hansa-2 made its initial flight on 23 November 1993. On 11 May 1998, a second prototype, based on the Hansa-3 design, joined the flight test programme; it featured various refinements, including the use of a variable-pitch propeller instead of a fixed counterpart, and a more powerful Rotax 914-F3 powerplant. 

The initial design was Hansa-1 that adopted a pusher configuration, but was discontinued as severe problems were revealed during wind tunnel testing.

On 3 September 2021, the prototype Hansa-NG (Next generation) performed its maiden flight. This aircraft featured various improvements and changes, including the addition of a glass cockpit, digitally-controlled Rotax 912 ISC engine, electrically-operated flaps, and greater endurance.

The Hansa aircraft has been displayed frequently at Aero India Air shows held at Bangalore. The Hansa has been marketed to various sectors, including flight training, coastal surveillance, and private owner-pilots. Multiple specialised variants, including unmanned models, have also been worked on.

General characteristics of the Hansa-NG Aircraft:- 

1. Length: 7.658 m 
2. Height: 2.614 m  
3. Wingspan: 10.47 m
4. Wing area: 12.47 m^2
5. Cabin width: 1.07 m
6. Gross weight: 750 kg (1,653 lb)
7. Max cruise speed: 200 km/hr (108 KTAS)
8. Range: 926 km (500 nm)
9. Endurance: 6 hours
10. Take off distance: 450 m (1476 ft)
11. Landing Distance: 600 m (1968 ft)
12. Service ceiling: 3,048 m (10,000 ft)
13. Maximum rate of climb: 198 m/min (650 ft/min)
14. Engine: Rotax 912 iSc 3 sport

Meaning of dimensions mentioned in this article:- 1 inch = 0.0254 m; 1 foot = 0.3048 m; 1 inch = 0.0833333 foot; 1 pound = 0.453592 kg; 1 nautical miles (nm) = 1.852 km

KTAS:- Knots True Airspeed/True Airspeed (TAS) of an aircraft is the speed of the aircraft relative to the air mass through which it is flying.

NAL Hansa 'VT-XIW' exhibited at HAL Museum, Bangalore (Year-2021)

According to the website Warbirds of India, the aircraft on display VT-XIW at HAL Museum, Bangalore was the first prototype of the Hansa II. It first flew in November 93 and flew a total of 128 hours of test flying before it was ‘retired’. NAL then donated the aircraft to HAL for display here. 

Video of Hansa-NG first flight on 3rd September, 2021