JPH0288396A - Jet propulsion type aircraft - Google Patents

Abstract

PURPOSE: To improve performance of an aircraft, especially flight stability by composing vertical stabilizer plate surfaces to be apart from each other for an equivalent distance to width of a secondary stream on the downstream of propulsion jet and wings. CONSTITUTION: An aircraft 1 has two drum parts 2, two triangular side part half wings 3 are extended from the body parts 2 outward, and a center wing 4 provided with a flap 5 and installed to be rotatable around a lateral shaft of a structural body of the aircraft 1 is provided between the drum parts 2 to compose configuration of a triangular flying wing. Back ends of the drum parts 2 have vertical stabilizer plate surfaces 10, and these are protruded downward to be extended right under a gravity center of the aircraft 1. In this constitution, the stabilizer plate surfaces 10 are securely placed to be directly adjacent to a mixed stream on the downstream of the wings. The aircraft 1 can thus be securely assured to be self-stabilized with relation to tendency to take a transverse attitude to a flight direction.

Description

DETAILED DESCRIPTION OF THE INVENTION (Industrial Application Field) The present invention relates to a jet propulsion type aircraft, specifically, a jet propulsion type aircraft, which has a wing and a jet propulsion means, and a propulsion jet is attached to the trailing edge of the wing. It is directed over the back surface of the adjacent wing, creating additional lift due to the supercirculation flow induced in the wing and the downward deflection of the jet caused by the Coanda effect just downstream of the wing, as well as the primary The fluid consists of the jet, the secondary fluid consists of the relative air flow over the wing, and the continuous zone of expansion, mixing and recompression of the ejector is defined by a single active surface consisting of the rear part of the wing. The present invention relates to a known type of jet-propelled aircraft configured with a single-plane ejector system.

(Prior Art) Aircraft of the above type are disclosed in U.S. Patent No. 447 in the name of the applicant.
No. 8378 and its corresponding European patent application EP-A-00
No. 78245, and due to the above features, it has the advantage of being able to take off and land in an extremely short distance and being extremely easy to maneuver.

(Problems to be Solved by the Invention) An object of the present invention is to improve the performance of the aircraft, particularly flight stability.

(Means for Solving the Problems) As a means for achieving the object, the present invention provides an aircraft of the type described above, which includes two fuselage sections and a center wing that is located between the circular fuselage sections and constitutes a wing toward which a propulsion jet is directed. It has the general outline of a triangular flying-wing aircraft, with two rear ends of the fuselage section projecting downward and having two vertical stabilizer surfaces extending directly below the center of gravity of the aircraft, with the long axis of the aircraft in the direction of flight. The vertical stabilizer surfaces are aligned with the propulsion jet and the two downstream of the blades in order to abut the sides of the mixed flow so as to create a self-stabilizing effect that immediately corrects the tendency to cross the The aircraft are separated from each other by a distance substantially corresponding to the width of the downstream mixed flow.

(Function) Due to the above structure, the aircraft according to the present invention is extremely stable in flight. In particular, when an aircraft exhibits a tendency to adopt an attitude with its long axis transverse to the direction of flight, the relative airflow is reduced to a mixed flow between the secondary flow (sucked in from the propulsion jet by the ejector effect) and the downstream of the wing. Obtain the lateral component held by . The action of this lateral component, directed onto the vertical stabilizer plane, imparts yaw and rolling moments to the aircraft that return the aircraft to a correct flight attitude aligned with the direction of flight. In other words, the mixed flow downstream of the center wing of the aircraft constitutes a kind of rail drawn laterally by the two vertical stabilizer surfaces, and all aircraft attempting to assume an attitude transverse to the direction of flight 's propensity is automatically corrected. Since the two vertical stabilizers fly directly adjacent to the flow downstream of the wing, any tendency of the aircraft to adopt a sideways transversal attitude is immediately corrected.

BRIEF DESCRIPTION OF THE DRAWINGS The invention will now be described with reference to the accompanying drawings, which illustrate an example of the invention, together with other features and advantages.

(Example) In the figure, an aircraft indicated by 1 generally has two fuselage parts 2, and two triangular side half wings 3 from the fuselage parts.
extending outwardly and having between said fuselage parts a central wing 4 having a flap 5 and mounted pivotably about a transverse axis 6 (see FIGS. 3 and 4) of the structure of the aircraft; It has the outline of a flying wing aircraft.

In the illustrated embodiment, the aircraft propulsion unit 7 is attached to the wing structure and is displaced with the wing as the wing pivots about the axis 6. The propulsion unit 7 has two rear nozzles 8 which generate a wide, flat jet which is directed onto the rear surface near the trailing edge of the central wing 4.

Of course, the propulsion unit may be provided in a fixed state together with the means for deflecting the jet, or it may be possible to use a plurality of propulsion units, some of which are fixed and other units which are adjustable. The side surfaces of the wings 4 are regulated by the vertical surfaces of the two fuselage sections 2.

This arrangement ensures that the flow of the propulsion jet onto the blades 4 is such that the primary fluid is +lI in the propulsion jet and the secondary fluid is transferred over the blades, as previously described in my U.S. Pat. No. 4,478,378. consisting of a relative air flow of, and
The continuous zone of expansion, mixing and recompression of the ejector results in a single plane ejector system consisting of a single active surface consisting of the back of the wing. Additionally, because the propulsion jet is directed toward the back of the wing close to the trailing edge, the Coanda effect creates a sharp downward drift of the jet downstream of the wing, as already described in the aforementioned U.S. patent. let

These characteristics allow the aircraft to be driven by the circulation induced on the wing by the propulsion jets directed onto the wing, and also by the fact that the flow of the jet deflected downstream of the wing has a significant vertical component. This vertical component is the wing 4
Due to the increased thrust of the propulsion jet generated by the ejector effect that occurs above, it has a very high lift force. To ensure that a very large ejector effect occurs even when the wing 4 is rotated downwards, the side edges of the wing are joined to the fuselage section 2, as shown in FIG. 4, even when the wing is lowered. Preferably, seals 9 are provided on both sides of the wing 4 so that the space above the wing is side-closed.

By allowing the wings 4 to pivot, it is possible to control the direction of the aerodynamic forces caused by the deflected propulsion jet.

The aft ends of the two fuselage sections 2 have vertical stabilizer surfaces 10 which project downwardly and extend directly below the center of gravity of the aircraft I. This configuration ensures that the stabilizer surface is located directly adjacent to the mixed flow downstream of the blade. This ensures that the aircraft is reliably self-stabilizing with respect to its tendency to assume an attitude transverse to the direction of flight.

In FIG. 4, the secondary streams sucked in by the propulsion jets due to the ejector effect are indicated by F, and the dashed line area indicated by S corresponds to the mixing area with the secondary streams of these propulsion jets.

Aircraft l has a front fuselage support 11 with a pair of wheels 12
and two rear landing gears 13 supported by the center wing 4.

(Effects of the Invention) As is clear from the above explanation, according to the present invention, it is possible to impart a self-stabilizing effect to the tendency of an aircraft to take a posture transverse to the flight direction, thereby stabilizing the flight of the aircraft. It can significantly improve your sexual performance.

[Brief explanation of drawings]

1 and 2 are perspective views showing two different flight states of the aircraft according to the present invention, and FIGS. 3 and 4 are parts corresponding to the two flight states of FIGS. 1 and 2, respectively. FIG. 1 - aircraft, 2 - fuselage section, 3 - side half wing, 4 - center wing,
5 - flap, 6 - horizontal axis, 7 - propulsion unit, 8 - rear nozzle, 9 - seal, 10 - vertical stabilizer surface. Patent Applicant: Aerikria Socheta Aerospaziale Italiana Belgia Accioni

Claims (5)

[Claims] (1) having a wing (4) and a jet propulsion means (7),
The jet propulsion means is arranged such that the propulsion jet is directed onto the dorsal surface of the wing adjacent to the trailing edge of the wing (4), and the supercirculation flow induced in the wing and the downward direction of the jet caused by the Coanda effect immediately downstream of the wing are controlled. The primary fluid consists of the jet, the secondary fluid consists of the relative airflow over the blades, and the continuous zone of expansion, mixing and recompression of the ejector is connected to the blades (4 ) in a jet-propelled aircraft configured to constitute a single plane ejector system defined by a single active plane consisting of the rear part of the aircraft, said aircraft generally comprising two fuselage sections (2); It has the outline of a triangular flying wing aircraft with a central wing (4) between which constitutes the wing towards which the propulsion jets are directed, with the two rear ends of the fuselage section (2) projecting downward and directly below the center of gravity of the aircraft. having two vertical stabilizer surfaces (10) extending in the vertical direction, the stabilizer surfaces are mixed so as to create a self-stabilizing effect that immediately corrects the tendency of the long axis of the aircraft to become transverse to the direction of flight; said vertical stabilizer surface (10) to be adjacent to the side of the flow;
are separated from each other by a distance substantially corresponding to the width of the mixed flow of the propulsion jet and the secondary flow downstream of the wing. (2) The center wing (4) is the transverse axis (6) of the aircraft structure.
2. A jet-propelled aircraft according to claim 1, wherein the jet-powered aircraft is capable of turning around. (3) A jet-propelled aircraft according to claim 2, wherein the jet propulsion means is supported by the central wing (4). (4) Connect the side edges of the center wing (4) to the fuselage section (2) so that the space above the center wing (4) is closed on the sides even when the wing (4) is rotated downward. Jet-propelled aircraft according to claim 3, characterized in that a sealing element (9) is provided. (5) The jet propulsion aircraft according to claim 4, wherein the front fuselage support section of the aircraft has a pair of wheels.