THE AIRCRAFT OF
VERTICAL TAKE-OFF AND LANDING WITH SPECIFIC CARRYING CAPACITY IN 2-4 TIMES
HIGHER, THAN AT THE BEST GLOBAL ANALOGS
The concept and basic
principle solutions of creation of a lifting force are worked by a new way
through the alternative formation of controlled flows of air interacting with
conceptually new elements of an aircraft, that will allow to create specific lifting
capacity of 54 kg/kW of expended energy, that exceeds the best world samples
more than twice.
The small power
expenditures are reached due to the fact that the lifting force is formed not
by the second's consumption of working gas and not by circulation of a flow on
an outline of a lifting surface, but by a new alternative way. The arrangement
of basic aggregates and units of the aircraft differs from classical
constructions.
The small power
expenditures for creation of a lifting force provide vertical take-off,
capability of long hovering in the air, fast speed of a climb and all this at
small specific propellant consumption.
The new arrangement will
also supply a large part of a payload concerning weight of the aircraft. At
start it can multiple exceed take-off weight.
The profit from the
completed work will be created at the expense of sizeable decrease of the
operating costs and from realization of batch production, and also from sale of
the licenses on manufacturing of new aircrafts at the expense of decrease of
contamination of the environment and it can make from several billions up to
tens billions $.
Comparative operational and
technical characteristics:
|
¹ of items |
Name of parameters and characteristics |
YAK-42 |
TU-134A |
Alternative aircraft |
|
1. |
Quantity of the passengers |
100 |
76 |
400 |
|
2. |
Take-off weight, t |
52 |
47 |
300 |
|
3. |
Cruising speed, km / hour |
820 |
850 |
850 |
|
4. |
Distance of flight, km |
1850 |
2500 |
10000 |
|
5. |
Propellant consumption on 1 passenger-kilometer, g |
41 |
55 |
9 |
|
6. |
Specific gravity of a design, kg/passenger |
250 |
375 |
120 |
|
7. |
Specific lifting capacity, kg/kW |
10 |
15 |
54 |
The payment of the know-how
makes US $10 million, creation of the first experimental sample with the
engineering specifications and flight tests – US $6 million, term of
manufacturing - 1,5 year.