JPS6128559B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a vertical take-off and landing aircraft that takes off and lands by performing vertical or short-distance glide using jet reaction force.

As shown in Figure 1, this type of vertical take-off and landing aircraft obtains lift in the vertical direction as a reaction force by ejecting the jet exhaust 1a and 2a of the installed engines 1 and 2 downward. . However, in the vicinity of the ground 3, this jet jet hits the ground and rises again, so the high-temperature exhaust gases 4 and 5 enter the engine together with the air from the air intake ports 1b and 2b of the engines 1 and 2. Being sucked in may cause the engine's thrust to decrease significantly, or even cause the engine to stop. This degree becomes more noticeable as the jet exhaust ports 1c and 2c are closer to the air intake ports 1b and 2b, and the closer the air intake ports 1b and 2b are to the ground.

On the other hand, the air intake port 2b of the engine 2 is also used during cruising, but this arrangement is inconvenient because the rising flow 5 of exhaust gas is sucked into the air intake port 2b.

The present invention was made in view of the above-mentioned problems, and its purpose is to prevent the above-mentioned upflow from being sucked in, and to provide an air intake section that does not cause problems in engine operation during cruising. The objective is to provide vertical take-off and landing aircraft.

Next, embodiments of the present invention will be described with reference to the drawings. In this specification, up and down and front and back mean up and down and front and back when the aircraft maintains a normal horizontal position. do.

2 to 4 show an example in which the present invention is applied to a subsonic aircraft. In these figures, reference numerals 1 and 2 are gas turbine engines similar to those described in connection with FIG. It constitutes a main jet jet device that sends out a downward jet jet 2a during vertical takeoff and landing as shown in FIG. 3, or a backward jet jet 2d during cruise as shown in FIG.

The engine 2 is provided in a duct 8 provided, for example, on both sides of the fuselage 7, and the duct 8 is provided with an air intake portion 9 at its front end and a jet exhaust portion 10 at its rear end. Jet exhaust section 10
An exhaust flow direction changing section 11 is provided in the exhaust gas flow direction converting section 11 so that the jet exhaust gas can be directed downward or rearward. The direction changing section 11 is composed of several hollow members that can be folded in a superposed state.
This direction changing section 11 can use any known structure.

As shown in an enlarged view in FIG. 5, the air intake portion 9 of the duct 8 is provided with an air intake port 9a facing forward and an air intake port 9b facing upward. These air intake ports 9a and 9b are connected to the door 12.
It is designed to be selectively closed by
The upper edge of the air intake 9a and the front edge of the air intake 9b are in the same position near the front edge 8' of the duct 8 and are secured to the door 12 by means of the pivot pin 13 in that position.
The proximal end of is pivotally connected. In the solid line position shown in FIGS. 5 and 6, the door 12 closes the upward air intake port 9b and opens the forward facing air intake port 9a, and in the chain line position, where the door 12 rotates downward around the pin 13, it opens the upward air intake port 9b and opens the forward air intake port 9a. The front air intake 9b is opened and the front air intake 9a is closed. 6th
As shown in the figure and FIG. 7, the rotation of the door 12 is as follows.
This is performed by expanding and contracting an actuator 14, such as a hydraulic cylinder, whose both ends are connected to the base end and the front edge 8' of the duct. An air intake switching mechanism is constituted by the air intake ports 9a, 9b and a door 12 that selectively closes one of them.

In this embodiment, during takeoff and landing, as shown in FIG. 3, the engine 2 is operated by rotating the door 12 downward and the exhaust flow direction converting part 11 is directed downward, and the engine 1 is also operated. . This allows for vertical take-off and landing, but in this case the door 12 is forward facing air intake 9.
a is closed, the air intake section 9 takes in air only from the upward air intake port 9b, as shown in FIG. Therefore, as explained with reference to FIG. It becomes low because the inlet 9a is closed.

On the other hand, in the cruising state, the door 12 is rotated upward as shown in FIG. 4 and FIG. turn to This allows the flight to proceed without any problems.

8 to 12 show examples in which the present invention is applied to a supersonic aircraft. In FIG. 8, a duct 8 having a gas turbine engine therein (not shown) has a forward air intake 9a and an upward air intake 9b at its front end air intake 9, as in the previous embodiment. have. At the front edge of the upward air intake 9b (that is, at the upper edge of the forward air intake 9a), one end of a pair of actuators 15, 16 consisting of hydraulic cylinders or the like is connected to a pin 17,
18, and the other ends of these actuators 15, 16 are pivotally connected to doors 19, 20 by pins 21, 22, respectively. on the other hand,
The base ends of the doors 19 and 20 are attached to the pin 2 on the front edge 8' of the duct.
3 and 24. Doors 19, 20
constitutes the first door device. The first door device has a length spanning the front half of the upward air intake port 9b.

On the other hand, the base ends of doors 27 and 28 are pivotally attached to the rear edge of the upward air intake port 9b by pins 25 and 26. The door 27 is pivotally connected to one end of an actuator 29, such as a hydraulic cylinder, by a pin 30, and the other end of the actuator 29 is pivotally connected to the duct 8 by a pin 31. Also, door 28
is pivotally connected to one end of an actuator 33 consisting of a hydraulic cylinder or the like by a pin 32, and the other end of the actuator 33 is pivotally connected to the duct 8 by a pin 34. Doors 27 and 28 constitute a second door device. This second door device has a length spanning the rear half of the upward air intake port 9b. Therefore,
When the first and second door devices assume the horizontal position, the upward air intake 9b will be closed by both door devices.

The length of the first door device 19, 20 is dimensioned such that when it is pivoted downward, it can close the previous air intake 9a. Note that the actuators 15, 16, 29, and 33 can each be operated independently.

In the case of a supersonic aircraft, it is necessary to efficiently decelerate the supersonic free stream at the air intake and guide it to the engine at a speed below the speed of sound. To this end, in this embodiment, each door device has two It consists of two doors.

In this embodiment, in the case of vertical takeoff and landing, the forward air intake is closed by the first door devices 19, 20, and the second door devices 27, 28 are rotated upward, as shown in FIG. to open the upward air intake port 9b. This solves the problem of upflow, similar to the previous embodiment.

During subsonic cruising, as shown in FIG.
fully open.

FIG. 11 shows the state at supersonic speed. In this case, in the state shown in FIG. 10, only the doors 20 and 28 are rotated somewhat downward to take an intermediate position, and a shock wave is generated at the air intake to efficiently decelerate the airflow and the duct 8. to be introduced within. Furthermore, the 11th
In the case of the figure, the rear outer door 27 is slightly inside (downward)
Rotate it to slightly open the upward air intake, and the bleed can be removed from here.

FIG. 12 shows a case where the aircraft takes off and lands while gliding to some extent on the runway, similar to a normal aircraft. In this case, the first door device 19, 20
The front half of the upward air intake is closed, and the second door devices 27 and 28 are rotated slightly upward. This allows the required amount of air to be efficiently sucked in from the upward air intake.

As described above with respect to the embodiments, the present invention avoids sucking upflow containing hot exhaust gas into the engine during vertical takeoff and landing, and prevents adverse effects on the engine. This results in a structure that does not impede the intake of air at any time.

Further, according to the present combined invention, in addition to the above-mentioned points, it is possible to take in air at supersonic speeds with deceleration, and to improve the efficiency of air pumping during takeoff and landing by glide.

[Brief explanation of the drawing]

Figure 1 is an explanatory diagram of the upwelling flow during vertical takeoff and landing.
2 is a partially sectional plan view of an aircraft according to an embodiment of the present invention, FIG. 3 is a partially sectional side view of FIG. 2, and FIG. 4 is a view similar to FIG. 3 showing a different state. 5
The figure is an enlarged view of the main part of FIG. 4, FIGS. 6 and 7 are views of the main part of FIG. 5 in a further enlarged view in different states, and FIG. 8 is a main part showing another example of the present invention An enlarged longitudinal cross-sectional view, FIG. 9 is a diagram showing the state of the aircraft with the configuration shown in FIG. 8 during vertical takeoff and landing, and FIGS. 10 to 12 are diagrams showing the state during subsonic cruising, supersonic cruising, and taxiing, respectively. FIG. DESCRIPTION OF SYMBOLS 1... Downward jet jet generator (gas turbine engine), 2... Main jet jet generator (gas turbine engine), 4, 5... Upstream flow, 8... Duct, 9... Air intake section, 10 ……
Jet exhaust section, 11... Exhaust flow direction conversion section, 9
a...Front air intake, 9b...Upward air intake, 12...Door, 9a, 9b, 12...Air intake switching mechanism, 14...Hydraulic cylinder, 1
5, 16... Hydraulic cylinder, 19, 20... 1st
door device, 27, 28... second door device, 29,
33...Hydraulic cylinder, 23, 24, 25, 26
... Pivot pin.

Claims (1)

[Scope of Claims] 1. A main jet jet generating device consisting of a longitudinal duct having an air intake section at the front and a jet exhaust section at the rear, a gas turbine engine installed in the middle of this duct, and the jet exhaust In a vertical take-off and landing aircraft, the vertical take-off and landing aircraft comprises: an exhaust flow direction converter that is adjustable between a downward position and a rearward position; and a downward jet jet generator comprising a gas turbine engine located in front of the duct. An aircraft characterized in that the air intake section of the aircraft is provided with an air intake switching mechanism for switching between a state in which the air intake opening faces forward and a state in which the air intake opening faces upward. 2. Air intake switching with a forward facing air intake, an upward facing air intake, and a door that can be freely pivoted between the air intakes to selectively close these intakes. An aircraft according to claim 1 comprising a mechanism. 3. A main jet jet generating device consisting of a front-rear duct having an air intake section at the front and a jet exhaust section at the rear, a gas turbine engine installed in the middle of this duct, and the jet exhaust section facing downward and rearward. an air intake section of the duct, the vertical take-off and landing aircraft comprising: an exhaust flow direction converter adjustable between positions; and a downward jet jet generating device located forward of the duct and comprising a gas turbine engine; is provided with an air intake switching mechanism for switching between a state in which the air intake opening faces forward and a state in which the air intake opening faces upward; An air intake that opens upwards, an air intake that opens upwards, a position where the front half of the upwardly facing air intake is closed, and an air intake that faces forward. 1. An aircraft comprising: a first door device that is rotatable between a closed position and a second door device that opens and closes a rear half of an upwardly facing air intake; 4. The base of the first door device was pivoted along the leading edge of the upwardly facing air intake, and the base of the second door device was pivotally mounted along the trailing edge of the upwardly facing air intake. An aircraft according to claim 3. 5 Both the first door device and the second door device,
The aircraft according to claim 4, comprising two doors that can be rotated separately.