CN112224400B - Novel tilt rotor aircraft and working method thereof - Google Patents

Abstract

The invention discloses a novel tilting rotor aircraft and a working method thereof, belongs to the technical field of aviation, and provides power by adopting three pairs of tilting rotors. In a helicopter mode, vertical ascending and descending are realized by the total pitch control of a main rotor, forward flying and backward flying are realized by the longitudinal cyclic pitch control of the main rotor, side flying is realized by the transverse cyclic pitch control of the main rotor, and reaction torque and yaw are balanced by a deflection rudder; in the fixed wing mode, the yaw control is realized by the deflection ailerons, the pitch control is realized by the deflection elevator and the yaw control is realized by the deflection rudder. The tilting vertical tail type aircraft has the advantages that the tilting vertical tail type aircraft adopts the tilting vertical tail scheme, the problem that the reaction torque of the tilting three rotors is not easy to balance is reasonably solved, the advantages of simple and compact structure, light weight, low comprehensive energy consumption, high-speed cruising, long endurance time and the like of the common tilting three rotor aircraft are inherited, the course stability of the tilting three rotors is improved, and the tilting vertical tail type aircraft has wide application prospect in the field of shipboard aircraft.

Description

A new type of tilt-rotor aircraft and its working method

technical field

The invention belongs to the field of aviation technology, and specifically refers to a novel tilt-rotor aircraft and a working method thereof.

Background technique

Tilt-rotor is a new type of aircraft that integrates fixed-wing aircraft and helicopter. It has both the vertical take-off and landing and aerial hovering capabilities of ordinary helicopters, and the high-speed cruise flight of turboprop aircraft. Most of the development of tilt-rotor aircraft are concentrated on the tilt-two-rotor and the tilt-quad-rotor, and the research on the tilt-three-rotor is relatively rare. However, tilt-tri-rotors have many advantages over tilt-twin and tilt-quad rotors. Under the premise of meeting the mission requirements, the tilting tri-rotor has a simpler and more compact structure, and the take-off weight increases. At the same weight, the floor space is much less than that of the tilting dual-rotor, which is especially suitable for shipborne use. Compared with tilting quadrotors, tilting trirotors are lighter in weight, lower in overall energy consumption, can cruise at higher speeds, and have longer battery life. At present, most of the research on tilting tri-rotors, in order to solve the problem of balancing the anti-torque, either adopts the scheme of controlling the magnitude and direction of the pulling force of the third sub-rotor, or adopts the scheme of tilting the third sub-rotor to the left and right. However, for the former, due to the asymmetric reaction torque caused by the mechanical structure itself, higher requirements are placed on the control system to balance the reaction torque, and it is extremely difficult to meet the stable flight in various states; for the latter, although The counter-torque can be balanced by the mechanical structure, but since the third sub-rotor is only tilted to the left and right, if the rotor axis is in the vertical plane, it cannot generate forward thrust, and if the rotor axis is in the horizontal plane, it cannot generate lift, which will greatly affect the tilt. The performance of the rotating trirotor does not meet the original intention of the tilting trirotor configuration.

SUMMARY OF THE INVENTION

In view of the above-mentioned deficiencies of the prior art, the purpose of the present invention is to provide a new type of tilt-rotor aircraft and a working method thereof, so as to solve the problem of balancing the counter-torque of the tilt-rotor in the prior art, so that the three-rotors are in each In this flight state, it can not only balance the anti-torque to achieve stable flight, but also do not sacrifice the performance advantages of the tri-rotor.

For achieving the above object, the technical scheme adopted in the present invention is as follows:

A new type of tilt-rotor aircraft includes a fuselage, the upper end of the fuselage is provided with a wing, and the two ends of the wing are provided with a nacelle tilting system; The rear end of the stabilizer is provided with a deflectable elevator; the tail of the fuselage is also provided with a vertical tail tilting system, and the vertical tail tilting system can tilt relative to the fuselage;

The vertical tail tilting system includes a vertical tail tilting mechanism, the vertical tail tilting mechanism is connected to the vertical tail tilting shaft, and the vertical tail tilting shaft is installed on the vertical tail tilting mechanism and can rotate along the axis; The vertical tail tilting shaft is connected with the vertical stabilizer; the rear end of the vertical stabilizer is provided with a rudder, and the wingtip above the vertical stabilizer is provided with a rear rotor system, which includes a motor and a transmission mechanism for driving the rear rotor to rotate;

The vertical tail tilting mechanism drives the tilting of the vertical tail tilting shaft, which in turn drives the up and down tilting of the rear rotor system and the vertical stabilizer; the rear rotor of the rear rotor system is tilted to be perpendicular to the fuselage axis When the rear rotor of the rear rotor system and the fuselage axis are at a non-perpendicular angle, it is the fixed-wing mode. Specifically, in the fixed-wing mode, the rear rotor maintains a certain angle with the axis of the fuselage, and the generated pulling force can be decomposed into forward thrust and upward lift, which can not only supplement a certain forward thrust for the main rotor, but also provide some The lift is unloaded for the wings and the tail, and the vertical stabilizer is in the wake of the rear rotor, which increases the air speed at the vertical tail and increases the heading stability; in the helicopter mode, the rear rotor tilts to the vertical upward. , to generate upward lift, the rudder behind the vertical stabilizer is in the downwash of the rear rotor, and the side force can be generated by deflecting the rudder to balance the back torque of the rear rotor and perform heading control.

Further, the tail part of the fuselage is fixedly connected with a tail beam, and the horizontal stabilizer is fixedly installed on the tail beam.

Further, the nacelle tilting system is a left-right symmetrical structure, including a nacelle tilting axis, the nacelle tilting axis passes through the interior of the wing, and both ends extend out of the left and right wingtips of the wing, and the left and right of the nacelle tilting axis. Left and right nacelles are respectively arranged at both ends, and left and right rotor systems are respectively arranged at the front ends of the left and right nacelles; the middle part of the nacelle tilting shaft is connected with the nacelle tilting mechanism. The left and right nacelles are respectively installed at both ends of the nacelle tilting axis, symmetrical to the plane of symmetry of the fuselage, and contain an engine and a transmission mechanism that drive the rotor to rotate.

Further, the left and right nacelles and the left and right rotor systems can tilt up and down relative to the wing. Specifically, the nacelle tilting mechanism drives the nacelle tilting shaft to tilt up and down, and then drives the left and right nacelles connected with the nacelle tilting axis. and the up and down tilt of the left and right rotor systems. This method can provide both lift in helicopter mode and forward thrust in fixed-wing mode.

Further, the wing is installed above the middle of the fuselage, and the upper single-wing layout is adopted, which can effectively prevent the rotor from hitting the ground in the fixed-wing mode.

Further, the nacelle tilting mechanism and the vertical tail tilting mechanism both adopt the worm gear transmission mode, which can make the transmission smooth, the noise is low, and it has self-locking.

Further, the wing tail adopts an inverted T-shaped tail configuration, and the horizontal stabilizer is fixed on the tail beam and does not tilt with the rotor, thereby reducing the structural weight.

The invention also discloses a working method of a novel tilt-rotor aircraft, characterized in that the method is specifically:

When both the left and right rotor systems and the rear rotor system are tilted upward, it is the helicopter mode. At this time, the three rotors jointly generate upward pulling force to provide upward lift for the aircraft. Helicopter mode can be used during take-off, landing and low-speed flight. ;

In a balanced state, the left and right rotors of the left and right rotor systems rotate in opposite directions, the rotational speed and the collective pitch are the same, and the generated counter torques can cancel each other. Realize the hovering of the aircraft;

In the vertical flight state, the collective pitch of the left and right rotor systems and the rotational speed of the rear rotor system can be changed at the same time to change the pulling force of the three rotors, thereby realizing the vertical ascent and descent of the aircraft;

In the state of level flight, the forward and reverse flight of the aircraft can be realized by the longitudinal periodic pitch change of the left and right rotor systems, the side flight of the aircraft can be realized by the lateral periodic pitch change of the left and right rotor systems, and the side force can be changed by the deflection of the rudder, thereby changing the The magnitude of the anti-torque to control the yaw of the aircraft;

When both the left and right rotor systems and the rear rotor system are tilted forward, it is the fixed-wing mode. At this time, the three rotors jointly generate forward thrust to provide speed for the aircraft, so that the wings generate upward lift. The upward pull component can also provide some lift;

In the fixed-wing mode, the roll is controlled by the aileron, the pitch is controlled by the elevator, and the yaw is controlled by the rudder.

Beneficial effects of the present invention:

The invention discloses a novel tilt-rotor aircraft and a working method thereof. The aircraft is composed of a fuselage, a wing, a nacelle tilting system, a horizontal stabilizer, an elevator, a vertical tail tilting system, etc. Rotor provides power. In the helicopter mode, vertical ascent and descent are realized by the collective pitch control of the main rotor, forward and reverse flight are realized by the longitudinal periodic pitch control of the main rotor, and side flight is realized by the lateral periodic control of the main rotor. The counter-torque and yaw are balanced by the deflection of the rudder; in the fixed-wing mode, the roll control is realized by the deflection of the aileron, the pitch control is realized by the deflection of the elevator, and the yaw control is realized by the deflection of the rudder. Compared with the existing tilting three-rotor aircraft, the aircraft adopts the tiltable vertical tail solution, which not only reasonably solves the problem that the anti-torque of the tilting three-rotor is not easy to balance, but also inherits the simple and compact structure of the ordinary tilting three-rotor aircraft. It has the advantages of light weight, low comprehensive energy consumption, high-speed cruise, long battery life, etc., and increases the heading stability of the tilting tri-rotor.

The invention not only inherits the advantages of simple and compact structure, light weight, low comprehensive energy consumption, high-speed cruising, long battery life, etc. of ordinary tilting trirotor aircraft, but also further reasonably solves the problem that the anti-torque of the tilting trirotor is not easy to balance. On this basis, the heading stability of the tilting trirotor is also increased, which has broad application prospects in the field of carrier-based aircraft.

Description of drawings

Fig. 1 is the helicopter mode schematic diagram of the tilting tri-rotor aircraft with tiltable vertical tail of the present invention;

Fig. 2 is the fixed wing mode schematic diagram of the tilting tri-rotor aircraft with tiltable vertical tail of the present invention;

Figure 3 is a schematic diagram of the nacelle tilting system;

Figure 4 is a schematic diagram of the vertical tail tilting system;

Among them, 1-fuselage, 2-wing, 3-nacelle tilting system, 4-horizontal stabilizer, 5-elevator, 6-vertical tail tilting system, 7-nacelle tilting mechanism, 8-nacelle Tilt axis, 9-left and right nacelles, 10-left and right rotor system, 11-tail boom, 12-vertical tail tilting mechanism, 13-vertical tail tilting shaft, 14-vertical stabilizer, 15-rudder, 16-rear rotor system .

Detailed ways

In order to facilitate the understanding of those skilled in the art, the present invention will be further described below with reference to the embodiments and the accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation or a specific orientation. construction and operation, and therefore should not be construed as limiting the invention. The terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be a direct connection The connection can also be indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood in specific situations.

As shown in Figures 1 to 4, a novel tilt-rotor aircraft of the present invention and its working method are composed of a fuselage 1, a wing 2, a nacelle tilting system 3, a horizontal stabilizer 4, an elevator 5, a vertical Tail tilting system 6 and other components; wherein the wing 2 is installed above the middle of the fuselage 1, and the two ends of the wing 2 are provided with a nacelle tilting system 3; the tail of the fuselage 1 is provided with a horizontal stabilizer 4, specifically The horizontal stabilizer 4 is fixedly mounted on the tail beam 11 of the tail of the fuselage 1 . The rear end of the horizontal stabilizer 4 is provided with a deflectable elevator 5 ; the tail of the fuselage 1 is also provided with a vertical tail tilting system 6 , which can tilt relative to the fuselage 1 .

As shown in FIG. 3 , the nacelle tilting system 3 includes: a nacelle tilting mechanism 7 , a nacelle tilting shaft 8 , left and right nacelles 9 , and a left and right rotor system 10 , wherein the nacelle tilting mechanism 7 is installed on the wing 2 In the middle of the connection with the fuselage 1, the nacelle tilting shaft 8 passes through the wing 2, the two ends extend out of the left and right wing tips of the wing 2, and the middle part is connected with the nacelle tilting mechanism 7, and the left and right nacelles 9 are respectively installed in the nacelle tilting. The two ends of the rotating shaft 8 are symmetrical to the symmetry plane of the fuselage 1, and contain the engine and the transmission mechanism for driving the rotor to rotate.

As shown in FIG. 4 , the vertical tail tilting system 6 includes: a vertical tail tilting mechanism 12, a vertical tail tilting shaft 13, a vertical stabilizer 14, a rudder 15, and a rear rotor system 16, wherein the vertical tail tilting mechanism 12 is installed on the On the tail beam 11 of the tail of the fuselage 1, the vertical tail tilting shaft 13 is installed on the vertical tail tilting mechanism 12 and can be rotated along the axis. The vertical stabilizer 14 is fixedly installed on the vertical tail tilting shaft 13, and the rear rotor system 16 is fixedly installed on the The wingtip above the vertical stabilizer 14 contains a motor and a transmission mechanism for driving the rotation of the rear rotor.

The wing 2 is installed above the middle of the fuselage 1, and adopts an upper single-wing layout, which can effectively prevent the rotor from hitting the ground in the fixed-wing mode.

The nacelle tilting mechanism 7 and the vertical tail tilting mechanism 12 adopt the worm gear and worm transmission mode, which has stable transmission, low noise and self-locking.

The left and right nacelles 9 and the left and right rotor systems 10 can be tilted up and down by the nacelle tilting mechanism 7 through the nacelle tilting shaft 8, which can not only provide lift in the helicopter mode, but also provide forward lift for the fixed-wing mode. thrust.

The tail fin adopts an inverted T-shaped tail fin layout, and the horizontal stabilizer 4 is fixed on the tail beam 11 so as not to tilt with the rotor, thereby reducing the structural weight.

The rear rotor system 16 and the vertical stabilizer 14 can be driven to tilt up and down by the vertical tail tilting mechanism 12 through the vertical tail tilting shaft 13 . In the fixed-wing mode, the rear rotor maintains a certain angle with the axis of the fuselage, and the generated pulling force can be decomposed into forward thrust and upward lift. The wings and tail are unloaded, and the vertical stabilizer 14 is in the wake of the rear rotor, which increases the air speed at the vertical tail and increases the heading stability; in the helicopter mode, the rear rotor is tilted to the vertical upward, resulting in Upward lift, the rudder 15 behind the vertical stabilizer 14 is in the downwash of the rear rotor, and can generate lateral force by deflecting the rudder 15 to balance the reverse torque of the rear rotor and perform heading control.

The working method of the present invention is:

When both the left and right rotors and the rear rotors are tilted upward, it is the helicopter mode. At this time, the three rotors jointly generate upward pulling force to provide upward lift for the aircraft. Helicopter mode can be used during takeoff, landing and low speed flight.

In a balanced state, the left and right rotors rotate in opposite directions, the rotational speed and collective pitch are the same, and the generated counter-torques can cancel each other. .

In the vertical flight state, the collective pitch of the left and right rotors and the rotational speed of the rear rotors can be changed at the same time to change the pulling force of the three rotors, thereby realizing the vertical ascent and descent of the aircraft.

In the state of level flight, the forward and reverse flight of the aircraft can be realized by the longitudinal periodic pitch change of the left and right rotors, the side flight of the aircraft can be realized by the lateral periodic pitch change of the left and right rotors, and the side force can be changed by the deflection of the rudder, thereby changing the counter torque size to control the yaw of the aircraft.

When the left and right rotors and the rear rotor are tilted forward, it is the fixed-wing mode. At this time, the three rotors jointly generate forward thrust to provide the aircraft with speed, so that the wings generate upward lift, and the rear rotor generates upward thrust. The pull component can also provide some lift.

The control of the fixed-wing mode is similar to that of ordinary fixed-wing aircraft. The roll control is realized by the aileron, the pitch control is realized by the elevator, and the yaw control is realized by the rudder.

There are many specific application ways of the present invention, the above is only the preferred embodiment of the present invention, it should be pointed out that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements can also be made, These improvements should also be regarded as the protection scope of the present invention.

Claims (7)

1. A novel tilt rotor aircraft comprises an aircraft body (1), and is characterized in that the upper end of the aircraft body (1) is provided with a wing (2), and two ends of the wing (2) are provided with a nacelle tilt system (3); a horizontal stabilizing surface (4) is arranged at the tail part of the machine body (1), and a deflectable elevator (5) is arranged at the rear end of the horizontal stabilizing surface (4); the tail part of the fuselage (1) is also provided with a vertical fin tilting system (6), and the vertical fin tilting system (6) can tilt relative to the fuselage (1);

the vertical tail tilting system (6) comprises a vertical tail tilting mechanism (12), the vertical tail tilting mechanism (12) is connected to a vertical tail tilting shaft (13), and the vertical tail tilting shaft (13) is arranged on the vertical tail tilting mechanism (12) and can rotate along an axis; then is connected with a vertical stabilizing surface (14) through a vertical tail tilting shaft (13); a rudder (15) is arranged at the rear end of the vertical stabilizing surface (14), and a rear rotor system (16) is arranged at the wingtip above the vertical stabilizing surface (14);

the vertical tail tilting mechanism (12) drives the vertical tail tilting shaft (13) to tilt, and then drives the rear rotor system (16) and the vertical stabilizing surface (14) to tilt up and down; the rear rotor of the rear rotor system (16) is in a helicopter mode when tilting to be vertical to the axis of the fuselage and upwards; the rear rotor of the rear rotor system (16) is in a fixed wing mode when the axis of the rear rotor and the axis of the aircraft body are in a non-vertical angle;

the working method of the novel tilt rotor aircraft specifically comprises the following steps:

when the left rotor system (10), the right rotor system (10) and the rear rotor system (16) tilt upwards, the helicopter mode is adopted, at the moment, the three rotors jointly generate upward pulling force to provide upward lifting force for the aircraft, and the helicopter mode can be adopted during take-off, landing and low-speed flight;

in a balanced state, the rotating directions of a left rotor and a right rotor of the left rotor system and the right rotor system (10) are opposite, the rotating speed and the total distance are the same, the generated reactive torques can be mutually offset, and the reactive torque generated by the rear rotor system (16) can be balanced by generating a lateral force through a steering rudder, so that the hovering of the aircraft is realized;

in a vertical flight state, the total distance of the left rotor system (10) and the right rotor system (10) and the rotating speed of the rear rotor system (16) can be changed simultaneously to change the tension of the three rotors, so that the vertical ascending and descending of the aircraft are realized;

under the flat flight state, the front flight and the back flight of the aircraft can be realized through the longitudinal cyclic variable pitch of the left and right rotor systems (10), the side flight of the aircraft can be realized through the transverse cyclic variable pitch of the left and right rotor systems (10), the side force is changed through the deflection of the rudder (15), and the yaw of the aircraft is controlled through changing the magnitude of the reactive torque;

when the left rotor system (10), the right rotor system (10) and the rear rotor system (16) are tilted forwards, the fixed wing mode is adopted, at the moment, the three rotors jointly generate forward thrust to provide speed for the aircraft, so that the wings generate upward lift force, and in addition, the upward tension component generated by the rear rotor can also provide partial lift force;

the fixed wing mode is controlled by the ailerons to realize rolling control, the elevator to realize pitching control and the rudder to realize yawing control.

2. The novel tilt rotor aircraft according to claim 1, wherein the tail of the fuselage (1) is fixedly connected with a tail boom (11), and the horizontal stabilizer (4) is fixedly mounted on the tail boom (11).

3. The novel tilt rotor aircraft according to claim 1, wherein the nacelle tilt system (3) is of a bilateral symmetry structure and comprises a nacelle tilt shaft (8), the nacelle tilt shaft (8) passes through the inside of the wing (2), two ends of the nacelle tilt shaft (8) extend out of left and right wingtips of the wing (2), left and right end portions of the nacelle tilt shaft (8) are respectively provided with a left nacelle (9) and a right nacelle (9), and the front ends of the left nacelle (9) and the right nacelle (9) are respectively provided with a left rotor system (10) and a right rotor system (10); the middle part of the nacelle tilting shaft (8) is connected with the nacelle tilting mechanism (7).

4. The novel tilt rotor aircraft according to claim 3, wherein the left and right nacelles (9) and the left and right rotor systems (10) can tilt up and down relative to the wing (2), and specifically, the nacelle tilting mechanism (7) drives the nacelle tilting shaft (8) to tilt up and down, thereby driving the left and right nacelles (9) connected with the nacelle tilting shaft (8) and the left and right rotor systems (10) to tilt up and down.

5. A new tiltrotor aircraft according to claim 1, wherein said wings (2) are mounted above the middle of the fuselage (1) in a single wing configuration.

6. The novel tilt rotor aircraft according to claim 3, wherein the nacelle tilting mechanism (7) and the vertical tail tilting mechanism (12) both adopt a worm and gear transmission mode.

7. The aircraft with the novel tilt rotor wing according to claim 1, is characterized in that the tail wing adopts an inverted T-shaped tail wing layout, and the horizontal stabilizer (4) is fixed on the tail beam (11) and does not tilt along with the rotor wing.

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