DE1270412C2 - Closing flaps, in particular for the outlet opening of a lift engine shaft of an aircraft - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

PATENT LETTERING

Int. a .:

B64d.

F 16k

DeutscheK!.: 62 b-37/02

Number: 1270412

File number: P 12 70 412.0-22 Filing date: September 3, 1965 Open date: June 12, 1968 Issue date: January 9, 1969 The patent specification corresponds to the patent specification

In conventionally built aircraft, the desired high flight speeds inevitably also high take-off and landing speeds are achieved, due to the high-speed flights trained wings. The helicopters are an exception, but for today's terms they are do not reach high airspeeds. Aircraft were therefore developed that had both advantages combine, namely vertical take-off and high flight speeds. This type of aircraft, known as a whiz, is independent of long runways. There were Vertical take-off aircraft built, which are propelled by jet engines, which are located in the fuselage or are housed in lifting gondolas and after taking off from the take-off place in the forward position be pivoted, if not separate forward engines are arranged, so that the lifting engines are only required for take-off and landing will.

However, the operation of these lift engines raises a number of problems, such as enormous dust formation, Signs of erosion on the runway, sucking in foreign bodies and also during a test run the hot exhaust gases are sucked back in very quickly. This recirculation causes great difficulties and can lead to unacceptably high engine inlet temperatures. This appearance is also unusable during the test run, since the engines have different power outputs An undesirable roll moment can be imposed on the aircraft and thereby the setting of the Equal thrust in the left and right gondola is falsified.

Closing flaps are provided on the air inlet side and on the gas outlet side of the lifting gondolas. to protect the engines of the aircraft in park position and in high-speed flight from harmful influences to protect and reduce their resistance. When the engines are put into operation these flaps open. In order to start the engines at the booth and with increased To be able to run speed, one tries to reduce the propulsion gases of the jet engines with the help of the flaps divert on the exit side. Designs of lifting gondolas are known in which the closing flaps on the outlet side can be brought into a position that allows the propellant gas flow derive backwards. However, this is not possible in those cases where the backwards flowing hot propellant gases can be affected or the aircraft parts

Shutters, especially for the
Outlet opening of a lift engine shaft
of an airplane

Patented for: Dornier G. m. B. H., 7990 Friedrichshafen Named as inventor: Anton Buchstaller, 7990 Friedrichshafen

horizontal thrust component occurring due to the thrust deflection is undesirable.

Lifting gondolas have also been proposed in which the propellant gases are controlled by appropriate steering

a »the outlet flaps to the side of the aircraft can flow away. These flaps are to designed that they are pivotable to both sides and of different sizes, the inner, longer flap for the purpose of deflection

• 5 of the motive gas jet can be pivoted into the motive gas jet, while the outer, shorter closure flap, pivoted outward and upward, opens the way for the deflected motive gas jets.
The invention relates to VerscWiißklappen for the outlet opening of a lift engine shaft for aircraft, which can be pivoted from their locking position into a first position in which one flap is open by more than 90 ° and the other flap is opened by less than 90 °, and in a second stadion can be pivoted, in which both flaps are open by about 90 °. The invention consists in that a power-operated rocker is provided for pivoting the flaps, which can be pivoted about an axis parallel to the flap axes, in its central position lies approximately parallel to the plane of the opening and is connected to the flaps by a link each the link for the flap that can be opened by more than 90 ° forms an extension of the rocker when it is opened to the greatest extent, while the link for the other flap is essentially at right angles to the rocker in all positions of the same. In order to be able to pivot the closing flaps for the outlet opening of a lifting engine shaft together with the flaps of an inlet opening of the engine, according to a further embodiment of the invention, the rocker is fed with pressure medium by the piston

Claims (3)

Moved cylinder, on the rear face of which a second cylinder is attached to a second piston, the piston rod of which engages a fixed joint, while the second cylinder actuates the flaps of the inlet port. What is achieved thereby is that the closing flaps for the inlet opening as well as for the outlet opening can be pivoted together, the outlet flaps assuming different open positions, while the inlet flaps remain fully open. The invention will be explained in more detail using an exemplary embodiment. It shows Fig. 1 a lifting engine nacelle with closed inlet and outlet flaps, Fig. La the associated circuit diagram for the flap actuation, Fi g. 2 the test position of the flaps, F i g. 2 a the associated circuit diagram, FIG. 3 the flap position during stroke generation, F i g. 3 a the associated circuit diagram. In addition to the actual engine, the lifting engine nacelles also contain the power unit used to control the air inlet flaps and the propellant gas outlet flaps and the associated linkage and levers. The air inlet flaps 1 are mounted pivotably about the axes 14 on the lifting gondola and have only two end positions, namely "open" and "closed". On these air inlet flaps 1 pivot bearings 15 are arranged, on which rods 2 a and 2 b engage, which are articulated at the other end on the angle lever 3 with the bearing 16 and 17, respectively. The angle lever 3 is rotatably attached to the bearing with the frame system and engages the floating pressure cylinder 5 via the bearing pin 19 and the handlebar 4. The piston 20 of the pressure cylinder half 5 a is connected to the fitting 8 of the nacelle structure via the piston rod 6. On the propellant gas outlet side, the screening flap 13 and the jet deflecting flap 12 are mounted on the lifting gondola so as to be pivotable about the axes 22. At pivot bearings 23, 24 handlebars 10 and 11 engage, which are connected at their other ends to the rocker arm 9 by the bearings 25 and 26. The rocker 9 is pivotably mounted on the nacelle structure via the bearing 28. The piston rod 7 is articulated to the rocker 9 through the bearing 27. The piston rod 7 is firmly connected to the control piston 21. Flexible pipes are used for the pressure supply and the return line so that the floating pressure cylinder 5 is not hindered in its oscillating movement. If one assumes the closed flap position to explain the mode of operation, then, as shown in FIG. 1 shows the position valves, which can be actuated hydraulically, mechanically or pneumatically in a known manner, for example brought into a position which pressurizes the rear of the two pressure pistons 20 and 21. This causes the pressure cylinder 5 to be pushed upwards because the piston 20, which is connected to the nacelle structure, cannot be displaced. The direction of force is deflected by the angle lever 3, and the air inlet flaps are kept closed via the rods 2 a, 2 b. At the same time, the piston valve is also pushed upwards. The rocker 9, which is connected to the piston 21 via the piston rod 7, is carried upwards, so that the rods 10 and 11 hold the chipping flap 13 and the outlet flap 12 in the closed position. As a further step, as shown in FIG. 2, the air inlet flaps are fully opened S and the motive gas outlet flaps are brought into the trial installation. For this purpose it is necessary that the control valves are in the position shown in FIG. 2 position drawn. It is now that part of the pressure cylinder part 5 a is put under pressure, which is under the piston 20 ίο. The pressure in the pressure cylinder part 5 b must be maintained. As a result of this switching, the pressure cylinder 5 is pressed down and the air inlet flaps open completely. Since the printing cylinder moves downwards, the piston 21 is also pressed downwards, although it does not move in the printing cylinder half. This has the effect that the rocker 9 pivots about the bearing point 27 and thus opens the screening flap 13 into the test run position via the linkage 11. The ao bearing 27, the axis of rotation 25 and the hinge axis 23 are now on a straight line, the barn door 13 has reached its outermost position. The beam deflection flap 12, however, has not yet reached its extreme position through half the piston travel; it remains in the approximately half-open position, and both flaps thus form the drive gas deflection position for the test run. The last phase for completely opening the propellant gas outlet is the process shown in FIG. 3 position drawn by the directional control valves. The pressure in the pressure cylinder part 5 a is maintained and in the pressure cylinder part 5 b the chamber above the piston head 21 is now pressurized. The pressure cylinder remains unchanged in its position. The piston 21 is now pressed down and the rocker 9 is deflected further. Because the culmination point for the pivoting movement of the screening flap 13 has been exceeded, the screening flap 13 pivots back inward again, and the beam deflection flap 12 pivots further downwards. Now both flaps for the vertical outlet of the engine gas flow form the operating position for the aircraft to take off from the take-off site. After the transition to forward flight, when the lift engines are no longer required, the flaps of the lift gondolas are closed again in reverse order. A device is provided to ensure that if the power unit fails, the flaps are in the open position, as shown in FIG. 3 shown, remain, for. B. by spring balancer, which was not shown in the drawing for the sake of simplicity. Thus, in the event that the power unit fails, there is the possibility of still being able to land safely. A particular advantage is the fact that the flaps, when opened, can be brought into positions which are adapted to the requirements of the respective operating state of the lifting mechanisms. In addition to the closed position of all flaps, it is possible, with the air inlet flaps open, to bring the outlet flaps once into a jet deflecting position and into a lifting engine operating position. <s patent claims: 1. Closure flaps, which around opposite edges of an opening from their closing position ment can be pivoted into a first position in which a flap by more than 90 ° and the other flap is opened by less than 90 °, and can be pivoted into a second position, in of the two flaps by about 90 °. are open, s in particular for the outlet opening of a lifting engine shaft of an aircraft, characterized in that a power-operated rocker arm for pivoting the flaps (9) is provided, which can be pivoted about an axis (27) parallel to the valve axes, in its central position is approximately parallel to the plane of the opening and with the flaps through one each Link (10, 11) is connected, the link (11) for the flap which can be opened by more than 90 ° (13) at the largest opening of the same forms an extension of the rocker arm, while the handlebars (10) for the other flap (12) in all positions of the same essentially at right angles to The swing arm is standing. ao 2. Closure flaps according to claim I for the outlet opening of a lifting engine shaft, with which the flaps of an inlet opening of the engine are pivoted together, characterized in that the rocker (9) is moved by the piston (21) of a cylinder (5 b) fed with pressure medium , at the rear end of which a second cylinder (5 a) with a second piston (20) is attached, the piston rod (6) of which engages a fixed joint, while the second cylinder actuates the flaps (1) of the inlet opening. 3. Closure flaps according to claim 1 and 2, characterized in that a device is provided that in the event of failure of the power unit, the flaps in the open position keep. Legacy Patents Considered:
German Patent No. 1 225 503. 1 sheet of drawings