Russian version


Aircraft's design and features

The author of the project, as a result of the theoretical and experimental research, was able to come up with the conceptual design of a flying device combining the best qualities of an airship, a plane, a helicopter and a hovercraft.

This aircraft is a mixed type "flying wing " the basic part of which is the diskshaped centerplane. In general it serves as a receptacle of elevating gas (helium). In the channel of its center there are a jacking system and a cargo cabin and on the edges there are a pilot-passenger cabin, cantilevered wings and a tail. The combined takeoff and landing device is placed underneath: wheel and ski bearers and air cushioned landing gear.

The disk shape of this aircraft allows to reduce the overall dimensions of gas tankage body by 3,0 to 3,5 times in comparison with the classical cigar-shaped form of an airship and at the same time to reduce considerably the lateral air blown surface.

Presence of plane elements such as the cantilevered wing and tail provides necessary stability and controllability in a horizontal flight, and due to load-bearing properties of the cantilevered wing and diskshaped body together with aerostatic unloading of the design achieves high transport efficiency on weight feedback and specific productivity.

Positioning the propeller in the central channel of the disk allows to realize the properties of vertical takeoff airplanes, including helicopters.

Presence of elements of an air cushioned plane, air cushioned landing gear alongwith supercharger activated by the propeller, provides for off-airfield operations and basing of aircrafts, i.e. movement, landing and takeoff from water, marshes, any flat ground, snow covered surface, etc.

Absense of a regular airfield and presence onboard of the technological self-servicing block-module placed in a cargo cabin, ensures the autonomy of operation: there is no need for docking facilities and tiedown devices, takeoff and landing runways, platforms and other elements of the infrastructure, typical for regular airships, planes and helicopters.

Positioning of the elevating powerplant in the channel of the disk and the cruise engine on the back part of the disk - centerplane allows to create the most successful configuration of the powerplant as a whole, providing all the necessary thrust characteristics during all flight regimes with simultaneous support of stabilization and control.

Three principles of creating the lifting force: aerostatic, aerodynamic and jet, used on this aircraft, possibility of landing on an all-terrain flat surface, airflow over the systems of control and stabilization generated by the powerplant's propellers, rather low specific loading on bearing surfaces with simultaneous use of modern aviation control systems and navigation allow to achieve high reliability and safety of operation.

Thus, the given concept of a heavy load-carrier, being built on the basis of modern achievements in aviation engine building, control systems, constructional materials and technologies can be realized already today.

The submitted material may be used for working out a business - plan in any sphere of economic activities.

Major advantages

The basic advantages of a plane with aerostatic unloading in comparison to a regular one are:

  • takeoff and landing from any natural terrestrial surface: sea, lake, river, marsh, farm field, runway, highway etc.;

  • the super short takeoff run and landing roll with a possibility of vertical takeoff and landing;

  • high load ratio: 1,5 - 2,0 times higher if compared to the turbojet transport planes such as "IL - 76" and 2,5 - 3,5 times higher in comparison with the turbo-propeller planes such as "AN";

  • the empty design has 20 - 70 % aerostatic unloading depending on type/size;

  • cargo-passenger delivery to the remote regions of Russia: Far North, Eastern Siberia and the Far East;

  • global flight range with an opportunity of cargo delivery to any place on the Earth without refueling;

  • delivery expenses are similar to those of a railroad;

  • expensive airport infrastructure is excluded: service is carried out with the help of the mobile technological blocks - modules established in any part of the Earth;

  • highly effective in preventing and liquidation of emergency situations of natural and technogenic character such as: industrial and forest fires, earthquakes and flooding, sea spills of petroleum and oil products, etc.

Basic geometrical data

The plane F-10 F-15 F-20 F-25 F-30 F-35
Overall dimensions:
length L, m 48 72 96 120 144 168
length L, m 46 71 94 118 141 165
height H, m 13 20 27 33 50 47
Bearing areas:
general, m2 776 1742 3102 4880 6987 9513
disk of centerplane, m2 620 1392 2478 3898 5582 7600
outer wing, m2 156 350 624 982 1405 1913
Centerplane:
diameter, m 25,8 38,6 51,5 64,6 77,3 90,2
Channel dimensions:
entrance diameter, 10 15 20 25 30 35
exit diameter, m 12,9 19,3 25,8 32,2 38,6 45,1
height, m 8,3 12,5 16,7 21,0 25,1 29,3
Cabin passenger-cargo, nose:
length, m 11,0 16,5 22,0 27,5 34,0 39,0
width, m 3,5 4,0 5,0 6,0 7,0 8,0
height, m 6,0 8,0 11,0 14,0 17,0 20,2
volume, m3 231 528 1210 2310 4046 6240
Central cargo compartment:
base diameter, m 8,3 12,5 16,7 20,8 25,0 29,2
height, m 6,1 9,2 12,2 15,3 18,3 21,4
volume, m3 182 694 1655 3114 5550 8846
Tail cargo compartments (2 piece):
length, m 11,0 16,5 22,0 27,5 34,0 39,0
width, m 1,75 2,0 2,5 3,0 3,5 4,0
height, m 3,0 4,0 5,5 7,0 8,5 10,0
volume, m3 115x2 264x2 6052 1155x2 2043x2 3120x2
Aerostatic volume:
general, m3 2070 6960 16530 32320 55890 88800
centerplane, m3 1710 5750 13660 26710 46190 73390
wing, m3 235 768 1870 3650 6315 10030
tail, m3 125 425 1000 1960 3385 3380

Comparative data: Fialka - 10

The plane Fialka - 10 AN-8 AN-72
takeoff weight, m 35 38 34
weight of an empty (equipped) plane, 10 26 17
aerostatic volume, thousand m3 2 - -
Powerplants:
total capacity, kw, or thrust, daN including: 3680 7620 12740
cruise engine 21175 2x3810 2x6370
lifting 2665 - -
Quantity, type and mark of engines:
cruise engine 2TVD TV - 117 2TVD AI-20D 2TRDD D-36
lifting 2GTD - 3F - -
Load on propeller airblown area, ( daN/ m2 ) 70 - -
Cruiser speed, km/hr 180 520 720
flight altitude, km up to 3 up to 6 8-10
ferring range, km 15000 - -
mission payload, , at range 24,0 L=850
14,4 L=4400
11,0 L=850
2,7 L=4400
10,0 L=850
7,5 L=4400
full load ratio, % 77 32,6 50
Aerostatic unloading of an empty structure, % 20 - -
Dimensions:
length, m 40 31 28
span, m 46 37 32
height, m 13 10 8
Takeoff-landing data:
liftoff speed, km/hr 55-60 240 250
landing speed, km/hr 55-60 250 260
takeoff run, m 50 - -
landing roll, m 40 - -
runway (strip) requirements any natural platform: lake, river, bog, farm field etc. specially prepared runway: concrete or ground specially prepared runway: concrete or ground

Comparative data: Fialka - 15

The plane Fialka - 15 AN-128
takeoff weight, m 81 61
weight of an empty (equipped) plane, 22 37
aerostatic volume, thousand m3 7 -
Powerplants:
total capacity, kw, or thrust, daN, including: 8180 12520
cruise engine 22625 43130
lifting 21465 -
Quantity, type and mark of engines:
cruise engine 2TVD AI-20k 4TVD AI-20m
lifting 2TV Z-117 -
load on propeller airblown area, ( daN/ m2 ) 70 -
Cruiser speed, kms /hr 180 520
Flight altitude, km up to 3 4,5-6
Ferring range, km 20000 -
Mission payload, , at range 60 at L=1000
45 at L=3350
20 at L=750
10 at L=3350
Full weight feedback, % 83 39
Aerostatic unloading of an empty structure, % 32 -
Dimensions:
length, m 72 33
span, m 70,5 38
height, m 20 10,5
Takeoff-landing data:
liftoff speed, kms/hr 55-60 230
landing speed, kms/hr 55-60 220
takeoff run, m 75 1200
landing roll, m 60 940
runway (strip) requirements any natural platform: lake, river, bog, farm field etc. specially prepared runway: concrete or ground

Comparative data: Fialka - 20

The plane Fialka - 20 Ul - 76
Takeoff weight, m 148 157
Weight of an empty (equipped) plane, 39 70
Aerostatic volume, thousand m3 16,5 -
Powerplants:
Total capacity, kw, or thrust, daN, including: 14560 48000
cruise engine 24675 4x12000
lifting 22600 -
Quantity, type and mark of engines:
cruise engine 2TVD V-22 4TRDD D-30
lifting 2GTD SH-53E -
Load on propeller airblown area, (daN/m2) 70 -
Cruise speed, kms/hr 180 850
Flight altitude, km up to 3 9-12
Ferring range, km 22000 -
Mission payload, , at range 70 at L=5000
88 at L=3000
40 at L=5000
Full weight feedback, % 85 55
Aerostatic unloading of an empty structure, % 42 -
Dimensions:
length, m 96 47
span, m 94 50
height, m 27 16
Takeoff-landing data:
liftoff speed, km/hr 55-60 215-230
landing speed, km/hr 55-60 190-235
takeoff run, m 100 850
landing roll, m 80 450
runway (strip) requirements any natural platform: lake, river, bog, farm field etc. specially prepared runway: concrete or ground

Comparative data: Fialka - 25

The plane Fialka - 25 AN-22
Takeoff weight, m 238 225
Weight of an empty (equipped) plane, 63 120
Aerostatic volume, thousand m3 32 -
Powerplants:
total capacity, kw, or thrust, ( daN/m2), including: 22710 44000
cruise engine 34855 4x11000
lifting 24070 -
Quantity, type and mark of engines:
cruise engine 3TVD V-22 4TVD NK-12MT
lifting 2GTD D-25V -
Load on propeller airblown area, ( daN/m2) 70 -
Cruise speed, km/hr 180 550
Flight altitude, km up to 3 4,5-6,0
Ferring range, km 26000 9000
Target loading, , at range 147 at L=3100
112 at L=5250
60 at L=3100
40 at L=5250
Full weight feedback, % 87 47
Aerostatic unloading of an empty structure, % 51 -
Dimensions:
length, m 120 57
span, m 118 64
height, m /TD> 33 12,5
Takeoff-landing data:
liftoff speed, km/hr 55-60 240
landing speed, km/hr 55-60 250
takeoff run, m 125 -
landing roll, m 100 -
runway (strip) requirements any natural platform: lake, river, bog, farm field etc. specially prepared runway: concrete or ground

Comparative data: Fialka - 30

The plane Fialka - 30 C-5A(USA)
Takeoff weight, m 353 323
Weight of an empty (equipped) plane, 90 145
Aerostatic volume, thousand m3 56 -
Powerplants:
total capacity, kw, or thrust, ( daN/m2), including: 32800 74400
cruise engine 210540 4x18600
lifting 33910 -
Quantity, type and mark of engines:
cruise engine 2TVD NK-12MV 4TRDD
lifting 3GTD D-25V -
Load on propeller airblown area, ( daN/m2) 70 -
Cruise speed, km/hr 180 815
Flight altitude, km up to 3 10-13
Ferring range, km 31000 -
Mission payload, , at range 174 at L=5600
283 at L=1000
100 at L=5600
Full weight feedback, % 90 55
Aerostatic unloading of an empty structure, % 62 -
Dimensions:
length, m 144 75
span, m 141 68
height, m 40 18
Takeoff-landing data:
liftoff speed, km/hr 55-60 220
landing speed, km/hr 55-60 230
takeoff run, m 150 -
landing roll, m 120 -
runway (strip) requirements any natural platform: lake, river, bog, farm field etc. specially prepared runway: concrete or ground runway lengh = 3400m

Comparative data: Fialka - 35

The plane Fialka -35 AN-124 AN-225
Takeoff weight, m 493 405 600
Weight of an empty (equipped) plane, 123 - -
Aerostatic volume, thousand m3 89 - -
Powerplants:
Total capacity, kw, or thrust, ( daN/m2), including: 44670 92000 138000
cruise engine 47175 4x23000 6x23000
lifting 27980 - -
Quantity, type and mark of engines:
cruise engine 2GTD D-136 4TRDD D-18T 6TRDD D-18T
lifting 2GTD D-136 - -
Load on propeller airblown area, ( daN/m2) 70 - -
Cruise speed, km/hr 180 800-850 700-850
Flight altitude, km up to 3 10-12 10-12
Ferring range, km 40000 16500 14700
Mission payload, , at range 286 at L=4500
417 at L=1000
125 at L=4500 200 at L=4500
Full weight feedback, % 93 - -
Aerostatic unloading of an empty structure, % 72 - -
Dimensions:
length, m 168 69 84
span, m 165 74 89
height, m 47 21 18
Takeoff-landing data:
liftoff speed, km/hr 55-60 240 250
landing speed, km/hr 55-60 250 260
takeoff run, m 175 - -
landing roll, m 140 - -
runway (strip) requirements any natural platform: lake, river, bog, farm field etc specially prepared runway with high bearing ability specially prepared runway with high bearing ability

Data technical charts

Development prospects

The following conclusions can be drawn with the respect to the data given above.

Introduction of the off-airfield plane with the aerostatic unloading opens wide prospects of development of the air transport on essentially new technological level.

Usage of such aircraft as an air vehicle will allow:

  • to reduce significantly consumption of the hydrocarbonic raw material used by the air transport in general;

  • to stop using expensive airport facilities and at the same time to reduce substantially the cost of running operations there;

  • to give up the construction of railroads and highways on the Far North, Siberia and the Far East of Russia;

  • the air transport to become an alternative (with the use of such aircrafts) to the Northern sea transport;

  • to lower significantly transport expenses at the development of oil and gas fields in the remote regions of Russia;

  • to provide effective protection of the population in extreme situations of technogenic and natural character.


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