3 rd EASN Association International Workshop on AeroStructures

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1 3 rd EASN Association International Workshop on AeroStructures ESTOLAS PROJECT Analysis of the design features and flying -technical characteristics of the ESTOLAS hybrid aircraft prototype Speaker Vladimir Petrov 0 9 th -11 th October 2013, Milan, Italy

2 ESTOLAS Construction Keys 1 center section; 2, 3 flaperon; 4 rudder; 5 tail beam; 6 elevation rudder; 7 cockpit; 8 inlet hatch; 9, 10 jet flap; 11,12 ski-wheel gear; 13 - flexible skirt; 14 main propulsion systems; 15 propeller;16 lift propulsion systems; 17 lifting rotor; 18 inlet hatch. 1

3 ESTOLAS Construction Keys 2 1 center section; 2, 3 flaperon; 4 rudder; 5 tail beam; 6 elevation rudder; 7 cockpit; 8 inlet hatch; 9, 10 jet flap; 11,12 ski-wheel gear; 13 - flexible skirt; 14 main propulsion systems; 15 propeller;16 lift propulsion systems; 17 lifting rotor; 18 inlet hatch.

4 Small ESTOLAS ESTOLAS Prototypes Small-ESTOLAS, side view 3 Small-ESTOLAS, top view Small-ESTOLAS, isometric view

5 Small ESTOLAS ESTOLAS Prototypes Basic geometrical parameters of the small-estolas aircraft No. Parameter Dimensions of the aircraft, m: Parameter value 1. Length L 10 Wing span l 11 Height H 2,6 2. Center-section: center section diameter Dd, m 4.6 4

6 ESTOLAS Prototypes Small ESTOLAS Flight characteristics and performance of the small-estolas aircraft No. Parameter Parameter value 1. Flight, cruising: flight altitude H Takeoff and landing data: 250 km/h Up to 3000 m takeoff speed V (takeoff), km/h up to landing speed V (landing), km/h 55 takeoff run, m 50 landing run, m Requirements for a landing ground (runway) Natural ground: lake, river, swamp, farm field, etc. 4. Flight range with full payload, km Up to Flight range for ferry technical flight (2 pilots on board), km 3000

7 Small ESTOLAS ESTOLAS Prototypes Small-ESTOLAS, prototype layout Small-ESTOLAS, prototype layout Takeoff weight, kg 2000 Operating empty weight, kg 1100 Payload weight, kg Fuel Weight, kg 300

8 Small ESTOLAS ESTOLAS Prototypes Small-ESTOLAS, basic geometric parameters 7 Small-ESTOLAS, prototype layout

9 Small ESTOLAS ESTOLAS Prototypes Basic performance predictions for the prototype: - when two Teledyne Continental ES engines with the fuel consumption of ~58 kg/h are used as a basic propulsion system, estimated time of flight in cruising regime with payload capacity is 5 hours; - estimated flight range in cruising regime is ~1200 km taking into consideration the operation of takeoff and landing device engine; - maximum flight height of 3000 meters can be an obstacle when operating in mountainous terrain. 8

10 Medium ESTOLAS ESTOLAS Prototypes Medium-ESTOLAS, side view 9 Medium-ESTOLAS, top view Mediuml-ESTOLAS, isometric view

11 Medium ESTOLAS ESTOLAS Prototypes Medium ESTOLAS prototype has the following features: The carrying capacity of the center section is increased by increasing its camber; The carrying capacity of the outer wings is increased by applying a high-lift airfoil TsAGIР-III-18; An unsymmetrical high-lift airfoil TsAGIР-II-14 for horizontal tail with upper position (instead of middle position on the analogue) and enlarged arm is applied; Single-piece side pivot sections of horizontal tail performing the function of elevons (instead of movable side sections of horizontal tail with rudders-elevons on the analogue) are installed; The relative dimensions of the cockpit (length and width) are increased; The relative dimensions and volume of the inflatable landing torus are increased; The transverse base of wheel-ski supports is increased, while their longitudinal base is decreased. 10

12 ESTOLAS Prototypes Medium ESTOLAS Flight characteristics of the medium-estolas aircraft 1. Parameter Parameter value Fligh cruising speed: 250 km/h flight altitude H Up to 3000 m (Рн = 0.93 kg/m 3 ) Takeoff and landing data: takeoff speed V (takeoff), km/h up to landing speed V (landing), km/h 55 takeoff run, m 75 landing roll, m Requirements for a landing ground (runway) Natural ground: lake, river, swamp, farm field, etc.

13 ESTOLAS Prototypes Medium ESTOLAS Basic geometrical parameters of medium-estolas aircraft No. Parameter Parameter value Dimensions of the aircraft, m: Length L 12.6 Wing span l 16.0 Height H 3.4 Lifting areas, m 2 : General including center section 64.0 center section 41.4 Wing panels 22.6 Center-section: center section diameter Dd, m 6.0 Length, m 4.9 Width, m 2.6 Height, m 2.0 Volume, m3 18.0

14 Medium ESTOLAS ESTOLAS Prototypes Mediuml-ESTOLAS, prototype layout Medium-ESTOLAS, cabin layout Takeoff weight, kg 3500 Operating empty weight, kg 1700 Payload weight 850 (or 10 passengers with luggage) Fuel Weight, kg

15 Medium ESTOLAS ESTOLAS Prototypes 14 Medium-ESTOLAS, basic geometric parameters

16 ESTOLAS Prototypes Medium ESTOLAS Basic performance predictions for the prototype: - Medium ESTOLAS prototype is intended for the needs of national economy; the main advantage of the prototype is the possibility of off-airfield location and the possibility of takeoff and landing from/on unprepared surface. Basic performance predictions for the prototype: 15 When two PT6A engines with fuel the consumption of ~200 kg/h are used as a basic propulsion system, estimated time of flight in cruising regime with payload capacity is 3 hours; Flight range in cruising regime is 750 km; Maximum flight height of 3000 meters can be an obstacle when operating in mountainous terrain.

17 16 ESTOLAS CAD Model

18 Large ESTOLAS ESTOLAS Prototypes Large-ESTOLAS, side view Large-ESTOLAS, top view Large-ESTOLAS, isometric view 17

19 Large ESTOLAS ESTOLAS Prototypes The aircraft has a shape of a flying wing of mixed type the main part of which is represented by a disk-shaped center section. It mostly contains buoyant gas (helium). A lift system and a cargo hold are placed in the center of the center section, in the duct; a cockpit, wing panels and tail fins are installed on the sides. A combined takeoff and landing device is placed below: wheel-ski supports and an air-cushion undercarriage. The shape of a disk allows to reduce the dimensions of the gas-bearing body by times in comparison with classic cigar-shaped airships, and at the same time it allows to decrease the lateral windage of the prototype almost by an order of magnitude. 18

20 ESTOLAS Prototypes 1. Large ESTOLAS Flight characteristics of the Large-ESTOLAS aircraft No. Parameter Parameter value Flight, cruising: 180 km/h flight altitude H Up to 500 m Takeoff and landing data: takeoff speed V (takeoff), km/h landing speed V (landing), km/h takeoff run, m 75 landing run, m Requirements for a landing ground (runway) Natural ground: lake, river, swamp, farm field, etc. 4. Flight range with full payload 60 tonns, km Up to 1000 km 19 5 Flight range for ferry technical flight (2 pilots on board), km km

21 ESTOLAS Prototypes Large ESTOLAS Basic geometrical parameters of Large-ESTOLAS aircraft No. Parameter Parameter value Dimensions of the aircraft, m: 1. Length L 72 Wing span l 70,5 Height H 20 20

22 Large ESTOLAS ESTOLAS Prototypes Large-ESTOLAS, front-view No. Parameter Parameter value, Tons 1. Takeoff weight Operating empty weight Aerostatic volume 7000 m 3 3. Payload weight

23 ESTOLAS Prototypes Large ESTOLAS Basic performance predictions for the prototype: Large ESTOLAS prototype is intended for carrying from 45 to 60 tons of cargo. The experimental aircraft uses several principles of lift generation, which sets additional requirements for its operation when two ТВД АИ-20к engines with fuel the consumption of ~2000 kg/h are used as a basic propulsion system, estimated time of flight in cruising regime with the payload capacity of 45 tones is 7 hours; - estimated flight range in cruising regime is ~1100 km taking into consideration the operation of takeoff and landing device engine; - the maximum flight height of 500 meters can be a serious obstacle when operating both in mountainous terrains and places that have average factors for relative height.

24 ESTOLAS Prototypes Large ESTOLAS Defining the parameters of aerostatic unloading with the use of helium gas 23 Defining geometrical parameters and calculating the volume for gas on the CAD model

25 ESTOLAS Prototypes Large ESTOLAS Defining the parameters of aerostatic unloading with the use of helium gas Large ESTOLAS aircraft is able to hold in its aerostatic unloading tank up to 6600 m 3 of helium. The calculation of aerostatic lift is made according to the formula: whereρ liquid (gas) density, kg/m 3 ; g free fall acceleration 9.8 m/s 2 ; submerged body volume m 3. Air densityρair under the temperature of 15Сis equal to kg/m 3, helium densityρhel = kg/m 3. The lift force created by the helium tank is equal to: FA = (ρ air -ρhel )*g*v = ( ) * 9.8 * 6600 = N, or kg of aerostatic unloading. 24

26 Thank You for Your Attention! 25 9 th -11 th October 2013, Milan, Italy

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