SK13882000A3 - FLIGHT EQUIPMENT DRIVE SYSTEM - Google Patents

Abstract

The two small internal combustion engines (4, 5) have reduced overall dimensions (e.g. approximately 500 x 250 x 300 mm). The engines directly next to one another have an identical structure and the same power and drive by means of a toothed belt (7,8) and a common drive shaft (9) for the compressor (1). If one of the engine fails, the power of the second engine is sufficient for an emergency landing.

Description

Aircraft propulsion system

The present invention relates to a propulsion system for an aircraft device, in particular to an aircraft device that is maintained in summer by a jet of air generated by a turbine compressor, with a motor-driven arrangement and transmission means for the lifting and forward propulsion unit of the aircraft device.

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When driving aircraft equipment, the highest requirements for operational and / or operational safety are imposed on the drive and / or engine.

For example, the problem can be solved by using two completely independent motors. Due to the weight, this is only possible today for higher performance.

In propulsion systems with only one internal combustion engine, a relatively expensive dual ignition is required which is effective but only against certain disturbances in the ignition system.

In single-engine propulsion systems, the observable power failure is virtually equivalent to a total power failure.

For VTOL aircraft, in particular for smaller aircraft maintained in the summer by means of an air or gas stream, only one engine is possible to drive. The engine failure is equivalent here to a total failure and thus to a fall. Here, too, a solution with two separate engines is out of the question for weight and, above all, for cost reasons.

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It is therefore an object of the present invention to provide a propulsion system which can overcome the prior art problems.

In a propulsion system of the initially defined kind, the task could be solved according to the invention by the features set forth in claim 1.

The particular embodiments of the drive system according to the invention are defined in the dependent claims.

Surprisingly, the solution according to the invention has shown that the new concept, in comparison with single-engined airplanes, can significantly increase safety without incurring unacceptably high costs. Due to the drive system according to the invention, the size of the individual motors can be chosen such that both the motors or all the motors together give the desired overall power. The cost of such engines would nevertheless be very high if they were only made for aircraft. However, if an individual engine is also suitable for other purposes (eg to drive small motor vehicles such as a motorcycle), the number of pieces can be produced that keep the cost of an individual engine unexpectedly low.

The propulsion system according to the invention is suitable for small airplanes in which, for reasons of weight and cost, two conventional engines are out of the question, but are replaced by two or more independent light engines arranged directly next to each other, mechanically synchronizing with each other on the common propeller shaft. What is important here is the forced or automatic disconnection of one motor which has fallen out of the common drive shaft. At least this provides another flight sufficient for an emergency landing after disconnection of the failed engine. This is possible because the power of the remaining engines is no longer affected by loss of operation of the inoperable engine.

The invention is explained in more detail with reference to the exemplary embodiment shown in the drawing.

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shows:

1 shows a side view, purely schematically, of a drive system according to the invention and FIG

Fig. 2 is a bottom view of the arrangement of Fig. 1.

The propulsion system according to the invention shown in the drawing is intended for small VTOL aircraft devices or drives for which two separate drives have not been considered for reasons of weight and cost.

The propulsion system shown in Figures 1 and 2 serves as a propeller 1 with a vane wheel 3 with an air duct 2 (part of the thrust nozzle system) for light VTOL - flying devices. Two small internal combustion engines 4 and 5 are provided for propulsion of the impeller 3, which are synchronized to one another by a mechanical connection, for example a toothed belt 6. Each of the two internal combustion engines 4, 5 has small overall dimensions (e.g. about 500 x 250 x 300). mm). The motors 4, 5 arranged directly next to each other have identical construction and the same power. The motors 4, 5 each drive a common drive shaft 9 for the compressor 1 via its own drive coupling 7, 8 (for example a toothed belt) (the drive can be effected from the shaft 9, for example by means of a belt drive 10 on the shaft 11, vane 3).

The power of both engines 4, 5 is designed so that flight propulsion is possible. If one of the two engines 4, 5 fails, the power of the other engine is sufficient for at least an emergency landing.

In order to ensure this in the event of a limited power output of the motors 4, 5, in the event of a failure of one engine, its drive connection to the common propeller shaft 9 of the front-end propulsion unit (compressor 1) must be interrupted. inoperative engine.

The drive coupling between the motors 4, 5 and the shaft 9 can be interrupted by the interruption points in the coupling, the automatic clutch and the like. (at any point between the motor outlet and the shaft 9 connection).

The drive coupling is interrupted automatically, for example when braking force occurs in the coupling (torque-dependent control).

Claims (5)

1. A propulsion system for an aircraft, in particular an aircraft, which is maintained in summer by means of an air stream created by a propeller compressor with an arrangement of the motor drive and transmission means for the lifting and forward propulsion unit of the aircraft, including the loading unit. that the motor drive arrangement has at least two mutually independent, jointly synchronized motors of equal or similar power each acting on a common propulsion shaft of the front-end propulsion assembly and provided with means which, in the event of failure of one of the two engines, interrupt its propulsion connection to a common drive shaft. Drive system according to claim 1, characterized in that the interruption means in each drive connection between the independent motors and the common drive shaft consist of a forced interruption point in the drive connection. Drive system according to claim 2, characterized in that the interruption means in each drive connection between the independent motors and the common drive shaft consists of a preferably self-acting clutch in the drive connection. Propulsion system according to claims 1 to 3, characterized in that the independent engines are internal combustion engines in which, in the event of a single engine failure, the propulsion of the remaining engines is sufficient for the aircraft to fly further or at least soft land. Drive system according to one of Claims 1 to 4, characterized in that the independent motors are of the same construction.