Drive system for a propeller driven transport aircraft

Details Drive system for a propeller driven transport aircraft Drive system for a propeller driven transport aircraft

1998-04-16

2001-08-28

Jordan, Charles T. (Department: 3644)

Aeronautics and astronautics

Aircraft power plants

Transmission of power

Reexamination Certificate

active

06279852

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to a drive system for a propeller driven transport aircraft which is intended to be propelled horizontally, and is particularly applicable to transport aircraft having an even number of propellers greater than or equal to four.
2. Summary of the Prior Art
In propeller driven transport aircraft each propeller is connected to and driven by a propulsion engine. Each engine usually comprises a gas generator and a drive turbine driving a single propeller, and the engine and propeller units are mounted on the aircraft wings.
For satisfactory operation the aircraft must always remain balanced. In particular, in the event of an engine failure the engine stoppage must not lead to the balance of the aircraft being upset by the asymmetrical thrust produced by the engines which are still in operation.
For example, in the case of an aircraft having four turboprop engines disposed symmetrically on the wings on opposite sides of the aircraft fuselage, the engines must be overdimensioned to ensure that the failure of any engine can be compensated for by an increase in the thrust provided by the three engines which are still in operation.
SUMMARY OF THE INVENTION
It is an object of the invention to provide a novel drive system for a propeller driven transport aircraft which can maintain the balance of the aircraft in the event of an engine failure and make it possible to use only two engines to drive four propellers instead of the four engines normally required, so that the cost of the propulsion system is reduced.
Another object of the invention is to provide a drive system for a propeller driven transport aircraft such that even if one engine fails the residual propulsion remains symmetrical.
Yet another object of the invention is to provide a drive system for a propeller driven transport aircraft such that its infrared signature is weaker than in the case of conventional propulsion systems, and engine maintenance costs are lower.
Accordingly, the invention provides a drive system for a propeller driven transport aircraft having a fuselage defining a central longitudinal axis of the aircraft and wings extending from said fuselage on opposite sides of said longitudinal axis, said drive system comprising first and second propeller doublets mounted in the plane of said aircraft wings, each of said first and second propeller doublets comprising two propellers disposed symmetrically on opposite sides of said central longitudinal axis of said aircraft, first and second engine units disposed side by side in said fuselage parallel to said central longitudinal axis, and first and second drive trains respectively connecting said first and second engine units to said first and second propeller doublets whereby said first and second propeller doublets are driven independently of one another by said first and second engine units respectively, each of said first and second drive trains comprising transverse drive shafts and gearboxes through which the two propellers of the respective propeller doublet are drivingly connected to the respective engine unit.
Thus, the invention resides in using two engine units to drive two propeller doublets independently of one another, the propellers of each doublet being arranged symmetrically on opposite sides of the aircraft. The engine units are disposed side by side in the aircraft fuselage and the propeller doublets are driven through two independent drive trains, each of which comprises transverse shafts, which are preferably flexible, interconnecting the propellers of the respective doublet through gearboxes and speed reduction gears providing satisfactory speed adaptation between the engine units and the propellers driven thereby.
Preferably, and especially for military use, the two engines are disposed in the upper part of the fuselage so as to be naturally hidden from detection by any ground-based infrared missile installation and also to protect the engines against intake of foreign bodies from a runway surface not prepared for the take-off and landing of military transport aircraft.
Other preferred features and advantages of the invention will become apparent from the following non-limitative description of the preferred embodiments with reference to the accompanying drawings.


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