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Purpose Amphibian Aircraft © 2018 JETIR October 2018, Volume 5, Issue 10 www.jetir.org (ISSN-2349-5162) CONCEPTUAL DESIGN OF MUTLI- PURPOSE AMPHIBIAN AIRCRAFT 1Sai Vinay Sandapeta, 2Sai Kiran Parre, 3A Sai Nikhil, 4Mariyada Vamshi Krishna Reddy, 5Saniya Moinuddin 1UG Student, 2UG Student, 3UG Student, 4UG Student, 5UG Student 1Department of Aeronautical Engineering, 1Insitute of Aeronautical Engineering, Hyderabad, India Abstract : In this paper, we describe the conceptual design of an Amphibian aircraft which is capable of the multi-purpose missions (i.e. Passenger mission and Air-Sea Rescue mission). The aircraft is to be based and operated out of Juhu Airport (ICAO Code: VAJJ) in Mumbai. As India has more than 200 lakes, reservoirs, and ponds, several of which have the potential to be utilized for operation of amphibian aircraft. So, amphibious aircraft can be used as air transport services which could extensively improve connectivity between the islands and the mainland as they have a minimum of infrastructure requirement. IndexTerms - Amphibian aircraft, Conceptual Design, Aircraft Design , FAR23 COMMUTER Aircraft. 1. INTRODUCTION An amphibious aircraft can be defined as an aircraft that can take off and land on either land or water. There are historically two classes of amphibious aircraft: flying boats and floatplanes. a. Pure Floatplane: A pure floatplane is defined as an aircraft which can only take off/land from/on water and derives its flotation from discrete floats. b. Amphibious Floatplane: An amphibious floatplane is defined as in ‘a’ above but is equipped with wheels to enable it to take off/ land from/on land in addition to water. (See in Fig 1) Fig 1: Amphibious Floatplane c. Pure Flying boat: A pure flying boat is defined as an aircraft which can only take off/land from/on water and derives its flotation from a specially configured fuselage. d. Amphibious Flying boat: An amphibious flying boat is defined as in 'c’ above but is equipped with wheels to enable it to take off/land from/on land in addition to water. (See in Fig 2) Fig 2: Amphibious Flying boat JETIR1810361 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 353 © 2018 JETIR October 2018, Volume 5, Issue 10 www.jetir.org (ISSN-2349-5162) In the general aviation (GA) field, amphibian aircrafts have always occupied a small but important niche in the marketplace, used primarily for operations into and out of remote areas where lakes were more plentiful than airports. India has more than 200 lakes, reservoirs and ponds, several of which have the potential to be utilized for operation of amphibian aircraft. Several cities along India’s coastline and in the Lakshadweep and Andaman and Nicobar Islands do not have access to much airport infrastructure. Air transport services could extensively improve connectivity between the islands and the mainland. Since the coast and the islands have access to large bodies of water, amphibious aircraft can be used as they have a minimum of infrastructure requirement. Aside from civilian operations, the scope of military applications is also immense for an amphibious aircraft such as Air-Sea Rescue (ASR) and littoral warfare operations. Today, most such aircraft tend to be ‘floatplanes’, aircraft originally designed for land operation to which have been added rather large floats to replace the conventional wheeled undercarriage. Such aircraft are usually considerably slower in flight and more limited in performance than their original designs due to the added weight and drag of the floats. In attempts to get better overall performance, a few specialty aircraft have been designed as amphibians with a hull fuselage. However, the compromises required to allow both land and water operations have still resulted in added weight and complexity, and a lower cruise speed than conventional land-based aircraft designs. 2. PROBLEM STATEMENT To design of an amphibian aircraft which is capable of multiple missions, viz., Passenger mission (Pax) and Air-Sea Rescue (ASR) mission. The aircraft is to be based and operated out of Juhu Airport (ICAO Code: VAJJ) in Mumbai. The Pax mission would involve two daily return flights to Pavana Lake (Ref. Fig 3). The ASR mission would involve a three hour search over the off- shore rigs located in the DCS Block and Panna-Bassein Blocks of Bombay High Oilfield (Ref. Fig 4). Fig 3: Passenger mission (Pax) mission Fig 4: Air-Sea Rescue (ASR) mission 3. REQUIREMENTS These are requirements identified as per missions which follows as : Table 1. Requirements S.No Critical Requirement Desired Feature 1. Airport ICAO CODE VAJJ 2. DESIGN CODE FAR 23 COMMUTER 3. Payload weight 1225kgs 4. Seat Configuration 13 5. Loiter time 60 mins 6. Operational limit Sea State 04 7. Endurance 180 mins 8. Service Ceiling FL 100 9. Atmosphere Indian Reference Atmosphere JETIR1810361 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 354 © 2018 JETIR October 2018, Volume 5, Issue 10 www.jetir.org (ISSN-2349-5162) 3.1 Airport ICAO CODE : VAJJ Table 2. Airport ICAO CODE Airport type CIVIL Temperature (F) 86 Wind speed 6 Runway distance 1,143m From this we estimate the max landing and takeoff distances. 3.2 Design Code : FAR 23 COMMUTER From this we can limit the design to certain parameters for aerodynamics, propulsion, structure and stability & control. Such as Engine : TURBOPROP 3.3 Payload weight : 1225kgs This is max. Payload weight estimated from Requirements which is about 1225 kgs ( see Table 1). So from we can estimate the max. take-off weight of aircraft. 3.4 Seat Configuration : 13 This is max seat configuration estimated from Requirements which is about 13 ( see Table 1). so from this we can estimate the cabin size . 3.5 Loiter time : 60 mins This is Loiter time given in Requirements ( see Table 1) , so from this we can estimate the fuel capacity. 3.6 Operational Limit : Sea State 04 The WMO sea state code largely adopts the 'wind sea' definition of the Douglas Sea Scale. The following is table representing it : ( see Table 3) . So, sea state 04, wave height = 0.5- 1.25 m from this we can estimate the hull design. Table 3. Douglas Sea Scale 3.7 Endurance: 180 mins This is max endurance given in Requirements (see Table 1) , so from this we can estimate the fuel consumption. 3.8 Service Ceiling: FL100 The height at which a particular type of aircraft can sustain a max rate of climb. FL= Flight Level 1FL = 100 ft So, FL100 = 10,000ft From , this we must estimate the max rate of climb. JETIR1810361 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 355 © 2018 JETIR October 2018, Volume 5, Issue 10 www.jetir.org (ISSN-2349-5162) 3.9 Atmosphere: Indian Reference Atmosphere For the purpose of aircraft performance the average Indian reference atmosphere is taken as: 1. Ref temp for take-off and landing: ISA+20 2. Sea level mean temp: ISA+15 3. Upper air operating temp: ISA+15 4. Lapse rate: 6.50C/Km from SL to 16 Km 5. Temp at 16 Km: -740C 6. Lapse rate from 16 Km to 20 Km: - 2.50C/Km 7. Mean sea level pressure: 1005 hPa 4. MISSION PROFILES There two missions considered for design i.e.; pax mission and asr mission profiles are shown in below figures. (see fig 5 and fig 6 respectively). Fig 5: Passen ger mission (Pax) Mission Profile Fig 6: Air-Sea Rescue (ASR) Mission Profile 5. INFORMATION RETRIEVAL Here, the surveys of various existing amphibian aircrafts are considered to have working out statistics in order to bring trend functions to plot various graphs to get various parameters. Following the tables made of some amphibian aircrafts that meet the given missions. Table 4 : Comparison of Various Amphibian aircrafts Aircraft specifications Beriev Be-12 Beriev Be-200 Altair PBY-5A Seastar CD-2 JRF-5 Goose Crew 2 2 10 1 3 Passengers Capacity 0 44 0 12 7 Wingspan 29.84 m (97 ft 11 in) 32.8 m (107 ft 7 in) 31.70 mt (104 ft 0 in) 17.74 m (58 ft 2 in) 14.94 m (49 ft 0 in) Wing area 99.0 sq m 117.4 sq m 130 sq m 30.6 sq m 34.9 sq m Empty weight 24,000 kg (52,800 lb) 27,600 kg (60,850 lb) 9,485 kg (20,910 lb) 2,900 kg (6,393 lb) 2,466 kg (5,425 lb) Max. takeoff weight 36,000 kg (79,200 lb) 41,000kg (90,390 lb) 16,066 kg (35,420 lb) 4,600 kg (10,141 lb) 3,636 kg (8,000 lb) Powerplant Selected 2 Turbo Props 2 Turbo Fans 2 Piston Engines 2 Turbo Props 2 Piston Engines Maximum speed 530 km/h (330 mph) 700 km/h (435 mph) 314km/h (196 mph) 335 km/h (208mph) 324 km/h (301 mph) Range 3300 km (1800 nmi) 2100 km (1134 nmi) 4030 km (2176 nmi) 1741 km (940 nmi) 1,030 km (557 nmi) Service ceiling 8000 m (26,247 ft) 8,000 ft (26,246 ft) 4000 m(15,800 ft) 4500 m (14,800 ft) 6,494 m (21,300 ft) Wing loading 298 kg/sq m 235 kg/sq m 123.6 kg/sq m 95 kg/sq m 104 kg/sq m Airfoil NACA 23020 TsAGI 16% NACA 21 NACA 23018 NACA 23015 R/C 15.2m/s 17m/s 5.1 m/s 6.6m/s 5.6 m/s Aspect ratio 8.9 9.1 7.73 10.3 6.4 Length 30.11 m (98 ft 9 in) 32 m (105 ft) 19.46 m (63 ft 10 in) 12.70 m (41 ft 8 in) 11.74 m (38 ft 6 in) JETIR1810361 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 356 © 2018 JETIR October 2018, Volume 5, Issue 10 www.jetir.org (ISSN-2349-5162) Height 7.94 m (26 ft 1 in) 8.9 m (29 ft 2 in) 6.15 m (21 ft 1 in) 4.83 m (15 ft 10 in) 4.93 m (16 ft 2 in) cruise speed 473 km/h (356 mph) 560 km/ h (348 mph) 201 km/h (125 mph) 333 km/h (207 mph) 308 km/h (191mph) Endurance 3 hours 4 hours 31 hrs 45 min.
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