DE1136582B - Aircraft - Google Patents

Description

The invention relates to aircraft with pivotable thrusters for optional generation of uplift or propulsion.

The thrusters can move forward beyond a vertical position so that the Angular movement of the thrusters is on the order of 100 °, so that the thrust in a Direction downward and a little forward can be directed during the transition from forward flight to hovering or descending flight in preparation for landing.

The invention is concerned with the adjustment of the Thrust nozzles at the transition from a vertical take-off or from a take-off on an exceptionally steep slope Angle to forward flight and vice versa from forward flight to hovering or descending flight, for example for the purpose of landing.

When taking off vertically or when taking off at low forward speed, the wing surfaces carry of the aircraft does not contribute to the lift to any significant extent, so that the aircraft must necessarily pass through a transition stage between vertical flight and forward flight, where the thrusters still take up the greater part of the on-air vehicle

Applicant:

Hawker Aircraft Limited,

Kingston-upon-Thames, Surrey

(Great Britain)

Representative: Dipl.-Ing. E. Schubert, patent attorney,
Siegen, Oranienstr. 14th

Roland Henry Chaplin, Weybridge, Surrey

(Great Britain),
has been named as the inventor

It is preferred to have the alignment or adjustment of the nozzles by the pilot using a hand operated The lever in the pilot's cabin

drive, but to leave the aircraft as 25, whereby the device operated by the pilot the

Can have the form of a control box.

The invention will now be described in more detail with reference to the drawing which shows it for example

The sequence of the thrust nozzle orientation changes to the forward flight, during which time the Wing surfaces gradually take over the lift.

It is important that during the transition from vertical flight to forward flight the speed of FIG
Forward flight to hover or vertical flight
- for example downwards - the adjustment
should be done quickly, if possible at the same time 35
Decelerate the airspeed.

The purpose of the invention is quite generally to create a control device which at Press the alignment speed of the

Thrust nozzles when moved from a vertical 40 lines AA or BB in Fig. 5. or an almost vertical position into a horizontal position.

Position automatically reduces and which are described in order to reverse the nozzle alignment with a gas turbine, from which the housing is shown schematically horizontal into a vertical or almost vertical position and denoted by the reference numeral 1 causes. Essentially, the invention consists in that the gas turbine in or above the difficult finding is that a damping device is arranged in front of the aircraft and one is seen, which has the pivoting movement of the thrust pair of nozzles 2, which is in front of the heavy nozzles from the lift position to the propulsion point, while a second pair of nozzles 2 a slows position. Preferably, a hydraulic is arranged behind the center of gravity, the lischer damper being provided, which ejects the alignment 50 front pair of nozzles 2 air, which slows down in one direction, but remains inactive in the opposite direction to a fan or compressor of the gas turbine . is supplied, whereas the rear pair of nozzles 2 α Aus

209 640/33

are explained, namely shows

Fig. 2 is a plan view,

3 is an incomplete, schematic diagram of a system for nozzle adjustment;

4 is a diagrammatic representation of the pilot control device for nozzle adjustment,

5 shows a side view of the control device in section,

6 and 7 sectional views along the

3 4

exhaust gases from the turbine, and the one Teleflex control 26 connects the levers 13

Nozzles are designed for simultaneous alignment and 15 with the control devices of the air

by pipe couplings 3, which allow an alignment of motors 4.

of the nozzles at an angle of at least 90 ° to- The pilot who change the nozzle position

even if this movement is desired up to 180 °, carries out the following operations:

can be increased to the maximum value of the thrust * τ, ■ ■ -, _ΛΤ .. ,, V _{1 Λέ1} ■ _Λ ·

to be able to use for braking purposes. With the in * · movement; of the preselection stop 16 m dxe

The arrangement shown in Fig. 1, however, the nozzles are the desired nozzle position. This can be done accordingly

for simultaneous alignment around. run at an angle from ^the pilot's habit. 100 ° set up. 'io 2. At the desired time at which the nozzles

In order to turn the aircraft during the vertical drainage, the main control

ges and at other times when the flight control lever 13 is pushed back against the stop

surfaces are ineffective, stabilize, are on or 16 and is automatically locked there. The pilot

near the nose and the end of the tail as well as at the can do this without looking. U.N-

Wing tips downwardly directed control 15 depending on how fast the lever is for the

nozzles are provided, and air is moved by the compressor at low swivel speed,

promoted to these nozzles. These control nozzles form the damper, the necessary gear

which, however, is not part of the invention, but rather prescribes speed,

this rather deals with the controlled loading 3. The overrun lever 15 gives a visual display

movement of nozzles 2 and 2 a. 20 from the nozzle position and allows it in an emergency

Any suitable device can be used to couple the trap to the pilot in case of getting stuck

two pairs of nozzles are used, so that they can "overtake" or in the damper

can be aligned in space at the same time; since the swivel speed has to be reduced if necessary

but the nozzles of course in aircraft longitudinal and large. -Lateral direction are far apart, will be 25

The marks on the housing near the slots which will work satisfactorily there, the angular position of the nozzles relative to the horizontal where a substantial extent of the gas turbine right, the nozzles, when the lever 13 in the housing, is preferably used is present in the aircraft longitudinal as well as the transverse position shown with solid lines. 3 °, point to the rear and when the lever is one of the proposed systems for the off in the dashed position, set up a position or adjustment of the nozzles, which take place in Fig. 3, in which they are at an angle of 100 ° is shown, has an air motor 4, which drives a against the horizontal downward and forward geGlenkwelle 5, which are directed via gears. A movement of the lever 13 is connected by the transverse shafts 6 and 7, which chain 35 extended into the dashed position will have a wheels 8 which, with the help of chains 9, cause the nozzles to be aligned quickly, as is the case with the rear ones Nozzles are connected, the transition stage between forward and plumb while chains 9 a with additional sprockets 8 α right flight is necessary, the lever movement in are connected, which sit on shafts 10, which carry a slow AusKettenräder 8 b in the opposite direction, which with the front nozzles 4 <> direction of the nozzles in the transition stage between connected by chains 9. Provides vertical and forward flight and the Ge-As shown in FIGS. 4 to 7, soft a preferred speed as required by actuating the form of a pilot control device for the alignment overtaking lever 15 can be increased by hand, direction or adjustment of the nozzles in the desired In FIGS. 5 to 7, which show details of the direction, the control system for the pilot shown in FIG. 4 consists of a housing 11 with a main device, the levers 13 and 15 are around a common device Axis breached or main slot 12 for movement 17 in housing 11 rotatably mounted. The lever 13 of the main control lever 13 and from an auxiliary slot has a pin-and-slot connection 18 with a 14 for the movement of a manual overtaking and frame 19, of which the side components are provided with trailing levers 15 .

The latter, as its name suggests, follows the loading The side members are at one end with each other

movement of the lever 13 in each of the two directions connected by a cross pin 21 and stop

and also provides for manual overhaul, and their opposite ends shorter pins or pins.

although for operation in an emergency when the pilot is there bolt 22. The pins 21 and 22 penetrate

for some reason wishes to remove the 55 slots 20.

directional speed of the nozzles in one the pins 21 and 22 penetrate through slots 23 in

Direction beyond the speed to the walls of a tubular inner housing 24,

large, soft from the damper, whose mode of operation which at one end has a bearing 25 for the inner

to be described is predetermined. part of the Teleflex control 26 has.

The slot 12 contains a preselection stop 16, 60. The inner housing 24 holds on its counter-softer can be adjusted to the movement set end a piston rod 27 with a KoI-des Lever 13 to limit in one direction and ben 28, which slides in a cylinder 29, the so that the nozzle orientation angle in this is rigidly connected to a pipe part 30, which Limit direction ^. slidably seated in the inner housing 24 and with Schlit-Das Housing is calibrated to a visual display 65 zen 31 in its walls for the passage or for the angular position of the nozzles, which is equipped to accommodate pins 21 and 22. as a result of a certain movement of the cylinder 29 contains air or a hydraulic dial stop 16 is reached. ical fluid and is with O-rings

32 at its ends through which the piston rod 27 passes.

The pin 21 penetrates through a plate 33, on which one end of a compression coil spring 34 rests, from which presses the other end against a second plate 35 holding the pins 22 and on one shoulder stored on component 30. The plate 33 is also seated on an end cap which is opposite to the component 30 End closes.

The piston 28 is designed so that a free flow of fluid past the piston in Direction of arrow, but an obstructed flow takes place in the opposite direction to the required Cause damping effect.

Lever 15 has a pivot pin connection 36 with an arm 37 on a bracket 38, which inward has directional pins 39 which pass through longitudinal slots (not shown) in the housing 24 and interact with component 30. In this way, the follower lever 15 becomes the straight one Follow movement of component 30, controlled by the damping device. But he can can also be moved by hand in order to overtake the effect of the damping device if necessary and to operate the Teleflex control immediately.

The lever 13 is with the usual spring-loaded pin detent with a series of notches or grooves in the slot, releasing the lever by pushing in the downward direction. A similar arrangement is provided for the preselection button 16.

During take-off, for example, and for the transition between vertical and forward flight the lever 15 is moved to the left in FIG. As a result, the spring 34 is compressed and a low flow of fluid past the piston initiated, with an ensuing result slow axial movement of the component 30 and the Teleflex control 26, which a slow adjustment the nozzles. Moving the lever to the right allows fluid to flow to the The piston will flow by freely and the nozzles will consequently move quickly through the preselected angle adjusted.

Claims (7)

PATENT CLAIMS: 1. Aircraft with pivotable thrusters for the optional generation of lift or propulsion, characterized by a damping device which slows the pivoting movement of the thrusters from the lift position into the propulsion position. 2. Aircraft according to claim 1, characterized by a main control lever (13) which can be moved back and forth between two end positions, which are the end positions of the thrust nozzles correspond, with an actuation of the main control lever in the sense of an increase in propulsion the Sets the damping device in action. 3. Aircraft according to claim 2, characterized by a preselection stop (16) for the Main control lever (13) to limit its movement in the direction that a slow Pivoting the thrusters causes. 4. Aircraft according to claim 2 or 3, characterized by an overtaking and caster lever, to increase the swivel speed of the thrusters if necessary, if the Damping device does not work effectively. 5. Aircraft according to claim 1 to 4, characterized in that the damping device consists of a cylinder containing a piston and hydraulic fluid, wherein the piston is adapted to allow fluid to flow freely in one direction allows past the piston, in the opposite direction, however, only a limited flow allows. 6. Aircraft according to claim 1 to 5, characterized in that the main control lever (13) actuates a Teleflex control that controls the direction of rotation of an air motor that controls the Propels thrusters through a system of drive chains and sprockets. 7. Aircraft according to claim 1 to 6, characterized by a calibrated scale next to the Main control lever that shows the set position of the thrust nozzles. For this purpose 2 sheets of drawings © 209 640/33 9.