DE2045999A1 - Convertible plane - Google Patents

Description

Description of the application for a grant under aircraft with characteristics for vertical and steep take-off or landing are aircraft with the designation Convertible aircraft (combination aircraft) became known. The invention relates to a novel such aircraft.

B'in such an aircraft should have the best possible horizontal speed s-partial and vertical. Combine take-off and landing properties of the helicopter aircraft.

Such aircraft have been proposed, which are also, for example, collapsible Have propellers housed in a nacelle in the wing. With these are the propellers z..B.

connected by a shaft and rotate in opposite directions which eliminates the need for a tail rotor. The propeller turbine air jet engines (P.T.L. or turboprop) remain unused during the thrust drive.

These well-known proposals for convertible aircraft have i.a. the following disadvantages: The installed engine energy to drive the propeller is used during most of the use, e.g. unused in level flight carried along, which is known to have an adverse effect on the operational safety of the Starting the engine, e.g. for landing. The long elles to the Gondolas in the wings require a significant structural effort. the Vibration freedom of this Weller requires complex measures, especially because Vibrations of these waves together with those of the wings have an unfavorable effect. Do not use a jet propeller on the wing tips on theirs Application will be discussed later for the proposed lifting screw, so are two oppositely rotating or Kälemende or separate lifting screws or a lateral drain screw required. The foldable ones that have become known for this Screws also require precautionary measures, e.g. for braking or for radial sliding into one another or pull and or

or the achievement of a flag position. It doesn't seem to make sense Possibility to use three and multi-wing screws. Also is a flight stabilizing Effect via a V-position when collapsing and unfolding the screw wings does not given. Versions of such aircraft do not come with just one 'propeller the end. There is no cheap possibility of swept wing adjustment. Wishes one the aerodynamic execution of the "clean wing" so is this with these Propellers that can be folded up in wing nacelles are also not possible. It seems also not meaningful possible the performance necessary for the vertical take-off also to be used as best as possible for the thrust performance initially up to about 1 ach or more.

The invention is based on the object of addressing the disadvantages addressed above to avoid or reduce such convertible planes. This object is achieved according to the invention solved by the fact that one or more extendable and retractable, extendable and switchable and collapsible and unfoldable, vertically acting propellers which is or are attached approximately parallel to the vertical axis. one or several propeller turbine air jet engines (P.T.L.) is driven or that either drive the propeller or propellers or deliver a thrust when the propeller is retracted, swiveling through ice formed thrust tube a counter torque is supported and a control effect can also be achieved with it.

In the drawings Fig.l and Fig.2: (1) engine (P.T.L.) with swivel nozzle, (2) shaft, (3) coupling, (4) bearing (5) bevel gear, (6) friction wheel cone for synchronization, (7) ball pin to disengage the cone (6), (8) bevel gear with conical synchronization surface and hinge bracket for struts (9) of the propeller (10), (11) auxiliary motor for lift (electric, hydraulic or pneumatic), (12) base plate on the fuselage tigt, (13) chain drive for elevator spindles (14), (15) guide rod for platform (17), (16) Ring bearer at the BumpS attached, (17) elevator platform with fixed Hollow shaft and bearing for bevel gear (8) at both ends, (18) drive motor as (ll) designed for swiveling device of the propeller blades via (19) guide rod as drive shaft for chain drive with chain wheel, axially adjustable by bearing on (17), inside (20) spindle shaft with sprocket mounted on both hollow shaft ends from (17), (21) nut thread ring axially displaceable through (2t), through axial ribbing (21) is connected to (17) whereby (21) prevents it from rotating and disks of the Axial bearings (22) are axially displaceable. Storage of the axial bearing (22) is through Axial ribs positively connected to (8). By means of ribs through axial slots going from (8), the hub (23) can be moved axially and the screw wing (10) inevitably swiveled with (9). By axial ribbing of (8) with (23) torque is transferred to (23). tend to have high axial and radial forces can also e.g.

a spherical roller thrust bearing can be used.

Description of the engine for propeller drive or optionally thrust.

According to the invention, a propeller turbine jet engine (P.T.L.) Can be used as the engine. known design, for example, a two- or three-shaft engine with Axial compressors with independent turbines can be used. With an independent power turbine their speed can decrease when loaded by the vertical take-off without at the same time reduce the compressor speed, resulting in reduced air flow and therefore smaller Performance would result. Especially for the vertical take-off performance can before the power turbine is injected again with fuel for intermediate combustion will. Can the power turbine rotate freely after the propeller has been switched off this means that almost the entire pressure gradient in the power turbine is no longer turned into rotary power but implemented in thrust. With a clutch in or in front of the air inlet the drive shaft for the lifting screw can also be shut down in the case of a linear actuator. for the optional use of a P.T.L.-engine for torque or thrust so far no cause and prerequisite. One does not lay according to the invention the propeller with hub, gear, clutch and fairings in sufficient Distance from the air inlet opening of the compressor on a shaft of the power turbine, so the air intake or the forehead resistance or both are largely worsened and the air throughput, especially for the thrust performance, is not satisfactory. the known constructive measures to increase performance and improve efficiency of the thrust, such as "nozzle needle adjustment", "secondary flow", "afterburner" etc. can are used here, provided that they do not require the design of the thrust tube as a swivel nozzle However, it can also, for example, affect a multi-stage turbine jet engine axial and single-stage centrifugal compressors can be used. Such engines can have an annular "inlet" that the engine, respectively. the hec cross-section circular A compound engine can also be used in which e.g. in the upper half of the fuselage stern a P.T.L. is attached to me air inlet above and both sides and in which a thrust engine in the lower half of the hump tail is provided with Ijuft inlet of. below and both sides. Will the propeller can be switched off by lowering it. beforehand via an angle drive with the coupling of the compressor of the thrust engine can be coupled, the entire Provides compression work for the thrust engine. Such a convertible aircraft can also in place of the described drives in the longitudinal axis a disengageable pressure jacket screw with rudder and rudder, axially to the propeller axis on the propeller shell cross-like stored, received. However, this assumes that the jack screw has no support of the torque is required, e.g. with ramjet propulsion on the wing tips. The pressure jacket rear screw can also be designed with such a ramjet drive will. It is obvious that such a convertible aircraft with retracted Vertical screw in relation to the horizontal speed described for the time being t Jet propulsion convertible aircraft inferior to helicopter aircraft is. The drive by e.g. two stern engines on both sides of the fuselage leaves make yourself advantageous too.

The inlet is here in a streamlined manner. The ellen can be tangential to the ring carrier (16) and there two bevel gears via two angular drives drive as (5) dianietrally mounted (8), in which case the two engines are force-locked tied together are. Hypoid or worm gears can be used as angular drives can be used, creating different options in terms of saucer and determination of the position of the shafts or the propulsion units are given0 The proposed Swivel nozzle to support the counter torque of the lifting propeller is not required if you use the propeller as known, e.g. with a ram jet or compressed air jet or other jet propels at the wing tips.

The constructive prerequisites for this are also proposed here fold up, and given retractable propeller. The at the wing tips e.g. attached ramjet engines can consequently with a rectangular cross-section be installed there in an aerodynamically favorable manner. For the improvement of such drives rotor blades of helicopters have become known., the slot-shaped (rasstrahlaustritte have the entire length of the rotor, with air inlets at the leading edge are provided, in which one with the same buoyancy with a smaller propeller circle gets by. For example, the following solution is used according to the invention for guiding the fuel line suggested.

A pump first conveys the fuel through a riser pipe, for which purpose one or the fixed guide tube like (19) is used. Will the platform (17) pressed against the ring carrier (16), the fuel can flow out of a radial opening Continue to flow at right angles into a radial line in or on the platform.

The guide bush in (17) must be above and below the radial The opening can be sealed by radial directional rings or sealing sleeves. At the end of this radial line, the fuel is fed into an annular groove which protrudes a rib axially of the gear (8) or vice versa. From here the Fuel also through centrifugal acceleration in radial lines to the hinge joints the swivel struts (9) distributed. The one through central channels of the standing hinge bolts Escaping fuel can be protected against the joint bushing through a shaft seal are sealed and reaches the struts or struts through integrated pipelines. the propeller wings end to the wing. The electrical current for the igniter The ramjet engines are operated in the same way, only pedaling analogously instead of the contact seal or sliding seal contact or sliding contacts. As is known, the fuel pump should be used for pumping and suction to be able to empty the line before lowering it through (17). It The auxiliary motor (l8) for the swivel device can also be used as a starter for the turbine be used.

In this case, the auxiliary motor can not only drive the shaft (19), but also in place of this, by actuating a known changeover gear, a light parallel to this, which is stored in (12) and (16). At the end of the wave a spur gear (pinion) is attached to an overrunning clutch and engages into a ring gear below the bevel gearing of (8) Overtakes the speed of the screw that of the auxiliary motor, the latter can be switched off, whereby because the spur gear continues to turn idle. But it can also be an engagement and disengagement device used as it is known e.g. from the automotive starter construction. As the drive shafts the auxiliary motors for adjusting the propeller or the starter of the engine ¢ lie in a sector of 900 of the base plate and these drives never at the same time are required, one can also use one or two auxiliary engines and a manual gearbox for the optional distribution of the frictional connection to the three cells.

The selected embodiment according to Fig.l and 2 is also as follows according to the mode of action e.g. during transition from vertical flight (e.g. take-off) described in the Wagrechtflug.

The power flow of the P.T.L. (1) goes over the shaft (2), the small bevel gear (5) on the gear (8), with the Hohlwellenfortsastz. The power flow comes from the hollow shaft (8) onto the hub (23) which can be displaced in the axial grooves. The P.T.L. first lifts over the vertically acting propeller moves the aircraft to a desired altitude, whereby the gas outlet of the P.T.L. exerts a slight thrust. As long as not enough The aircraft can pass through the flow velocity at the tail surfaces becomes effective the gas outlet of the P.T.L., designed as a swivel nozzle. and the V position of the propeller be held in the appropriate attitude. Due to the arrangement of the tail unit this is blown by the radial air flow of the propeller.

After reaching the desired flight altitude by vertical or steep take-off the low-speed facilities are extended.

By slightly lowering the gear wheel (S) using the pull-up device the power flow from (5) to (8) is interrupted and lowered by further and Swing in the propeller wing the propeller with decreasing self-rotation completely retracted until, for example, the platform (17) hits the base plate (l2) a disc brake ring on the top of part (17) on part (8) and thereby causes complete standstill earlier. The power turbine can now rotate freely and the torque is converted into horizontal thrust. Previously, the lift of the wings was complete via a flat gliding flight effective, whereupon the slow flight facilities can be retracted.

The transition from level flight to vertical flight or landing takes place the following masses: When the engine is throttled, the slow-flight facilities are extended and transition in a flat gliding flight with the winged wing when folded Propeller extended and initially brought into a V-position. Once the propeller wing ends protruding from the fuselage, the wind begins to rotate itself and it can A steeper glide or spiral flight to a vertical or steep landing will. The bevel gear (8) is connected to the bevel gear (5) for lowering the recilt landing Lifting engaged via the synchronizer. The speed the two bevel gears (5) and (8) can be adjusted by adjusting the propeller V-position and regulation of the gliding speed or the turbine shaft speed to synchronism for unrestrained engagement. When the gears are fully engaged the friction wheel contact of the synchronization device is established by the ball pin (7) interrupted.

By regulating the speed, V-position of the propeller through the Swiveling device and control by the Schweflkdüse can be vertical, as with a helicopter to be landed.

There is also the option of rotating the propeller itself and to start with full thrust not vertically but steeply and with self-rotation to land steeply. The actuation of the swivel nozzle can be carried out with the actuation of the rudder (e.g.

Elevator-rudder- or aileron) can be switched off. Hydraulic, electric or compressed air motors can be used as auxiliary motors, which, as is well known, switch off and lock themselves automatically by a stop.

The aerodynamically clad landing skids of such an aircraft can also be designed as air or compressed air tanks; you open at Attachment for landing exhaust devices. this container, so is a landing with. higher landing speed, based on the principle of hovercraft, possible.

Due to the air reservoir, the present aircraft can have amphibian properties obtain.

Claims (13)

PATENT CLAIMS 1. convertible aircraft, characterized in that one or more during of the flight can be extended and retracted, switched on and off, and collapsible and unfoldable vertically acting propeller or screw whose axis is approximately parallel to the Vertical axis runs or runs from one or more propeller turbines Air jet engine (PTL) # is or will be driven, either the propeller or the propellers drive or deliver a thrust when the propeller is retracted, whereby and the counter torque is supported by a pivotable thrust tube ei tax effect can be achieved with it. 2. convertible aircraft according to claim X; characterized in that a Propeller turbines Air jet engine (1) over the shaft (2) the small bevel gear (5) drives the bevel gear (8), the shaft extension of which is ribbed with the propeller hub (23) is connected and thereby axially displaceable on the shaft extension of (8) is or that white at the stern laterally algebraic PTL with two waves e.g. over two Hypoid or worm gears are guided tangentially to (16) and two small ones Bevel gears like (5) diametra; mounted the bevel gear: (8) drive. 3. convertible aircraft according to claim 2, characterized in that the gas outlet of the engine (l » The counter torque is supported by a swiveling thrust tube (nozzle) and a control effect can be achieved with it. 4. convertible aircraft according to claim 3, characterized in that by the auxiliary motor (18 »via the rotatably mounted guide rods (19) in (17) or on part (17) mounted sprocket that drives with ribs an axial groove in (19) is frictionally connected and through (17), on (19) axially is adjustable and the chain wheel (20) of a screw spindle by a chain drive can drive in both directions of rotation. 5. Reversible aircraft according to claim 4, characterized in that the Screw spindle axially shift the ring nut (21) can, where rotate this by ribbing with the upright shaft extension of (17) is prevented and by the connecting pieces passing through axial slots the discs of the axial bearing (22) are axially adjustable. Connection pieces of the wave washer of the axial bearing passing through the axial slots of (8) transmit the axial movement on the propeller hub (23), whereby the support by the struts (9) are connected by hinge joints with (8) and (10), the wings by approx. 900 axially can be pivoted. 6. convertible aircraft according to claim 5, characterized in that the Auxiliary motor (11) via a chain drive, the screw spindle (14) optionally in both Direction of rotation drives, whereby platform (17) with part (8), the swivel device and the pivoted propeller can be lowered to the bottom plate (l2) can. 7. convertible aircraft according to claim 6, characterized in that by Lowering the part (8) the engagement with (5) is interrupted, whereby the shaft (2); with the independent. The power turbine can rotate freely and not the whole pressure gradient more in torque rather. is only implemented in thrust, and also by means of a clutch the shaft (2) with bevel gear (5) can be stopped in the air inlet. 8. convertible aircraft according to claim 7, characterized in that at Raise the platform (17) the bevel gear (8) with bevel gear (5) first via a friction wheel synchronization device is brought into engagement, with full engagement z.3. through a ball pin (7) through the conical surface at (8) the friction wheel contact between (6) and (8) axial ¢ displacement is interrupted. 9. convertible aircraft according to claim 8, characterized in that landing skids be designed as air or compressed air tanks that the convertible aircraft Except for amphibious properties in an emergency, thanks to air outlet ducts as in hovercraft enables a landing at a higher landing speed. 10. convertible aircraft according to claim 9, characterized in that at Propulsion by ramjet engines or a compressed air or hot air jet in the wing tips of the propeller the delivery line of the fuel or one Blasting medium e.g. from a pump through a fixed guide tube like (19) first reaches a radial line in (17) via a radial branch, wherein the junction is sealed above and below by a sleeve seal is, the fuel in an annular groove in the one sealed by a shaft seal axial annular rib protrudes in front of (9) and accelerated centrifugally through radial lines in (9) and (10) to the ramjets, where he consists of the standing hinge bolts leaking fuel is sealed against the hinge sleeves. 11. convertible aircraft according to claim 10, characterized in that in addition to the fuel supply, there is also an ignition current analogous to that of the ramjet is performed, with contact contacts instead of the sleeve seals for ignition current are provided and sliding contacts are used at the transitions with shaft seals are. 12. convertible flight according to claim 7, characterized in that a turbine Jet engine with a ring-shaped air section which the engine or the tail cross-section circular also optionally encloses a turning force or a pushing force can deliver if for the. in the latter case the power turbine with its shaft through Interruption of the flow of power to the propeller can rotate freely. 13. convertible aircraft according to claim 12, characterized in that in the upper half of the fuselage stern a P.T.L. is attached with air intake from above and both sides and in which a thrust engine in the lower half of the fuselage stern is attached with air inlet from below and both sides, whereby the propeller can be switched off by lowering the part (8) after beforehand via an angular drive with a coupling of the compressor of the thrust engine was engaged, which does all or part of the compression work for the thrust engine supplies.