CN114856854A - A single-engine aircraft based on vector nozzle and method thereof - Google Patents

Abstract

The invention discloses a vector nozzle-based single-engine aircraft and a method thereof, wherein the aircraft comprises an engine and a mounting frame; the mounting frame is of an annular frame structure, an engine is coaxially and vertically mounted in the center, and a tail spray pipe of the engine is positioned below the mounting frame; the tail nozzle can freely rotate within the included angle of 20 degrees and the circumferential 360 degrees of the axis of the engine and is used for changing the thrust direction. Compared with the prior art, the single engine is adopted to provide lift force, and the steering engine is used for controlling the tail spray pipe to rotate, so that the thrust vector control is realized by guiding airflow. The invention has the advantages of simple structure, light structure weight, low manufacturing cost, economy and convenience.

Description

A single-engine aircraft based on vector nozzle and method thereof

technical field

The present invention relates to the technical field of unmanned aerial vehicles, in particular to a single-engine aerial vehicle based on a vectoring nozzle and a method thereof.

Background technique

Unmanned aerial vehicles usually have the advantages of small size, low cost, convenient use, and low maintenance cost, and are widely used in disaster rescue and material transportation. Thrust vectoring technology can provide aircraft with vertical take-off and landing capabilities and additional maneuvering performance, and increase the ability of unmanned aerial vehicles to cope with small-scale air transport, urban transport and other flight missions with small space and many obstacles.

At present, most UAVs controlled by thrust vectoring technology combine vector nozzles with fixed wings. The lift is provided by the fixed wings. The vector nozzles are only used to provide part (or all) of the force required to change direction, which cannot be achieved in narrow space, such as flying between trees or under the canopy. Chinese patent CN113277079A adopts four turbojet engines, uses rotatable arc-shaped nozzles to divert the wake of the engine, converts horizontal force into vertical force, so as to achieve flight, by rotating arc-shaped nozzles , resulting in a lateral force. But the use of four engines increases the structural weight, reduces the efficiency of thrust utilization, and increases manufacturing costs. Arc nozzle diversion can result in thrust loss. And in order to ensure that the air intake is not disturbed, the symmetrical installation of the engine will cause the size of the aircraft to be larger, which conflicts with the requirements of the aircraft to fly in a narrow space.

SUMMARY OF THE INVENTION

The purpose of the present invention is to overcome the above-mentioned defects of the prior art and provide a single-engine aircraft based on a vectoring nozzle and a method thereof. The invention adopts a single engine for propulsion, and on the basis of satisfying load requirements and endurance requirements, the size of the unmanned aerial vehicle is reduced, the structural weight is reduced, and the manufacturing cost is reduced. In the future, it will have an important impact on the fixed-point delivery of relief materials and the rapid transfer of materials during the rescue process.

The concrete technical scheme adopted in the present invention is as follows:

In a first aspect, the present invention provides a single-engine aircraft based on a vectoring nozzle, including an engine and a mounting frame; the mounting frame is an annular frame structure, the center is coaxially and vertically mounted with the engine, and the tail nozzle of the engine is located in the mounting frame. The tail nozzle can be freely rotated within 20° of the included angle of the engine axis and 360° in the circumferential direction to change the thrust direction.

Preferably, a plurality of aircraft support frames that can be extended and retracted along the engine axis are uniformly fixed on the bottom of the mounting frame; the bottom of the aircraft support frame when it is at the stretch limit position exceeds the port of the tail nozzle, which is used for landing support.

Further, the aircraft support frame includes a first support rod, a second support rod, a third connecting rod and a transmission block; one end of the first support rod is fixed at the bottom of the mounting frame, and the other end is coaxial with the second support rod A telescopic third connecting rod is fixed on the outside of the first support rod and the second support rod, and the third connecting rod is provided with a transmission block for controlling its expansion and contraction; through the transmission The block controls the expansion and contraction of the third link to drive the relative sliding of the first support rod and the second support rod.

Further, the bottom of the aircraft support frame is provided with a flexible block for landing buffering.

Preferably, the tail nozzle is connected with the engine through an annular first connecting rod hinged on the outer periphery of the upper part thereof.

Preferably, the outer periphery of the tail nozzle is connected to different steering gears through a plurality of second connecting rods, and the second connecting rods can be driven by the steering gear to deflect the tail nozzle so as to change the thrust direction;

Further, there are four second connecting rods in total, which are evenly distributed on the outer circumference of the tail nozzle, and the end of each second connecting rod connected to the tail nozzle is located on the same radial cross-section; all the second connecting rods can be respectively The deflection angle of the tail nozzle in the orthogonal direction is controlled, so that the tail nozzle has a 360° circumferential movement capability.

Preferably, a fuel tank, a control unit and a communication device are arranged on the outer ring of the mounting frame for fuel supply, flight control and ground communication.

Preferably, the engine includes, but is not limited to, a turbojet engine, a piston engine or a ducted engine.

In a second aspect, the present invention provides a method for flight and landing of a single-engine aircraft based on any one of the vector nozzles of the first aspect, which is specifically as follows:

Before the aircraft takes off, the engine is suspended by the retractable aircraft support frame arranged at the bottom of the mounting frame, the engine axis is perpendicular to the ground, and the direction of the nozzle of the tail nozzle is controlled vertically downward; then the ignition operation is performed, the engine is started, and the increase is gradually increased. The rotation speed makes the aircraft rise vertically; after the aircraft is off the ground at a certain height, the aircraft support frame is retracted, and the thrust direction of the nozzle is changed by changing the rotation of the tail nozzle, so as to realize the hovering and lifting motion of the aircraft; when the aircraft needs to land , first make it in a hovering state, and then gradually reduce the fuel supply of the engine, so that the aircraft slowly descends; when the aircraft lands smoothly, turn off the engine.

Compared with the prior art, the present invention has the following beneficial effects:

1. The present invention uses a single engine to provide the lift required for flight and the lateral force required for direction change, and the production cost is low compared to multi-engine aircraft. At the same time, since there is only one engine, there is no need to consider the problem of mutual interference between the engines and additional design of the structure can be performed, and a relatively simple structure can be adopted, which can effectively reduce the weight of the structure and reduce the size of the structure. The engine is installed vertically, which can effectively reduce thrust loss.

2. In the present invention, the steering gear pulls the connecting rod to drive the vector nozzle to rotate and change the direction of the thrust. The flight direction can be directly changed without changing the flight attitude, and the design of the control system is relatively simple. At the same time, the corresponding speed of the steering gear is relatively fast, and the thrust direction change can be completed quickly and accurately.

Description of drawings

Fig. 1 is the structural representation of the present invention;

Fig. 2 is the structural representation of the engine tail in the present invention;

FIG. 3 is a schematic view of the structure of a part of the aircraft support rod in the present invention;

Description of symbols in the figure: 1. Engine, 2. Nozzle, 3. First connecting rod, 4. Steering gear, 5. Second connecting rod, 6. Mounting frame, 7. Aircraft support frame, 8. First support Rod, 9, second support rod, 10, third link, 11, transmission block, 12, flexible block.

Detailed ways

The present invention will be further elaborated and described below with reference to the accompanying drawings and specific embodiments. The technical features of the various embodiments of the present invention can be combined correspondingly on the premise that there is no conflict with each other.

Example

As shown in FIG. 1 , it is a single-engine aircraft based on a vector nozzle provided by the present invention, and the aircraft mainly includes an engine 1 and a mounting frame 6 . The mounting frame 6 is an annular frame structure, the engine 1 is vertically installed at the central ring, and the engine 1 and the mounting frame 6 are coaxially arranged. The nozzle of the tail nozzle 2 of the engine 1 is directed downward and the nozzle is located below the mounting bracket 6 to prevent the mounting bracket 6 from blocking the thrust generated by the tail nozzle 2 during flight. In this embodiment, the mounting frame 6 is formed by splicing profiles, using an aluminum alloy material, and the connection between the engine 1 and the mounting frame 6 is fixed connection.

In this embodiment, a plurality of aircraft support frames 7 are uniformly fixed at the bottom of the mounting frame 6 in the circumferential direction, the aircraft support frames 7 can be extended and retracted along the axial direction of the engine 1, and the bottom of the aircraft support frame 7 in the tensile limit position exceeds the tail The port of the nozzle 2 is used to support the aircraft when landing, and the engine 1 including the tail nozzle 2 can be erected in the air as a whole to prevent the engine 1 from contacting the ground and causing damage due to friction. The aircraft support frame 7 can be made of an aluminum alloy material, and is fixedly connected with the mounting frame 6 . The outer ring of the mounting frame 6 is arranged with a fuel tank, a control unit and a communication device, etc., which are used for engine fuel supply, flight control and ground communication.

As shown in FIG. 3, the present embodiment provides a structure of an aircraft support frame 7, which is as follows:

The aircraft support frame 7 includes a first support rod 8 , a second support rod 9 , a third link 10 and a transmission block 12 . One end of the first support rod 8 is fixed on the bottom of the mounting frame 6 , and the other end is coaxially sleeved and connected with the second support rod 9 . The first support rod 8 and the second support rod 9 can slide relative to each other in the axial direction to change the length of the entire aircraft support frame 7 . The retractable third link 10 is fixed to the outer side of the first support rod 8 and the second support rod 9 , and a transmission block 12 is provided on the third link 10 for controlling its expansion and contraction. The third link 10 is controlled to extend and retract by the transmission block 12 to drive the relative sliding of the first support rod 8 and the second support rod 9 . In practical application, the transmission block 12 can be remotely controlled by a remote controller. In addition, a flexible block 12 is provided at the bottom of the aircraft support frame 7, and the flexible block 12 can play a buffering role when the aircraft is landing. The flexible block 12 can be made of rubber material to achieve soft landing and self-adaptation with the ground.

As shown in Figure 2, the tail of the engine 1 is a tail nozzle 2 that can freely rotate at an angle of 20° with the engine axis and within 360° in the circumferential direction, so as to provide the thrust required for changing the direction. The tail nozzle 2 is connected to the engine 1 through a ring-shaped first connecting rod 3 hinged on its upper outer periphery. The first connecting rod 3 can drive the tail nozzle 2 to rotate, and the tail nozzle 2 can rotate relative to the first connecting rod 3 .

The outer periphery of the tail nozzle 2 is connected with different steering gears 4 through a plurality of second connecting rods 5, and the steering gears 4 are located on the lower peripheral side of the engine 1, and are moved by different steering gears 4 to drive the corresponding second connecting rods 5 to move. , the second connecting rod 5 pulls the tail nozzle 2 to deflect it, changes the angle of the cross section where the nozzle is located, and then changes the thrust direction. When the tail nozzle 2 is vertically downward, the connecting rod 5 should be in a non-relaxed and unstressed state.

In this embodiment, there are four second connecting rods 5 , which are evenly distributed on the outer circumference of the tail nozzle 2 , and one end of each second connecting rod 5 connected to the tail nozzle 2 is located on the same radial cross section. All the second connecting rods 5 can respectively control the deflection angle of the tail nozzle 2 in the orthogonal direction, so that the tail nozzle 2 has a circumferential movement capability of 360°. The engine 1 includes, but is not limited to, a turbojet engine, a piston engine, or a bypass engine.

The movement position of the steering gear 4 corresponds to the deflection angle of the tail nozzle 2 one-to-one, and the position of the steering gear 4 strictly corresponds to the direction of the tail nozzle 2 . The direction of the angular velocity of the deflection of the tail nozzle 2 should be opposite to the direction of the lodging moment caused by the balance disturbance.

The main working states of the unmanned aerial vehicle proposed by the present invention are:

(1) Working state during takeoff

Step Ⅰ: Check that each system is in normal state, the fuel filling is completed, and the battery is fully charged.

Step Ⅱ: Start the remote control through the remote control, control the direction of the nozzle of the tail nozzle downward through the remote control, then perform the ignition operation, start the engine, gradually increase the speed, and the aircraft slowly rises vertically.

Step Ⅲ: After the aircraft is a certain height off the ground, use the remote control to control the aircraft support frame to shorten.

(2) Working state during flight

Steps: Control the rotation of the steering gear through the remote control or the controller, and pull the connecting rod to change the direction of the nozzle to realize the hovering and lifting motion of the aircraft.

(3) Working state when landing

Step 1: When the aircraft is in a non-hovering state, use the remote control to control the extension of the aircraft support frame and control the throttle to make the aircraft hover in the air.

Step II: Gradually reduce the fuel supply of the engine to make the aircraft descend slowly.

Step Ⅲ: Finally, the aircraft landed smoothly, and the engine was turned off.

To sum up, the present invention can reduce the structural weight and production cost as much as possible while meeting the load requirements of the aircraft through the design of materials, structures and power. The mounting frame and the aircraft support frame are made of high-strength and light-weight aluminum alloy materials or composite materials to reduce the weight of the aircraft as much as possible on the premise of ensuring reliability. The single-engine power system not only reduces the complexity of the structure, but also effectively reduces the cost of the aircraft and improves the economy of the aircraft.

Matters not addressed in the present invention are known in the art.

The above-mentioned embodiment is only a preferred solution of the present invention, but it is not intended to limit the present invention. Various changes and modifications can also be made by those of ordinary skill in the relevant technical field without departing from the spirit and scope of the present invention. Therefore, all technical solutions obtained by means of equivalent replacement or equivalent transformation fall within the protection scope of the present invention.

Claims (10)

1. A single-engine aircraft based on a vector nozzle, characterized in that it comprises an engine (1) and a mounting frame (6); the mounting frame (6) is an annular frame structure, and the center is coaxially and vertically mounted with an engine ( 1), the tail nozzle (2) of the engine (1) is located under the mounting frame (6); the tail nozzle (2) can rotate freely within the included angle of the axis of the engine (1) of 20° and the circumferential direction of 360°, Used to change thrust direction. 2 . The single-engine aircraft based on a vectoring nozzle according to claim 1 , wherein a plurality of aircraft supports that can be extended and retracted in the axial direction of the engine ( 1 ) are uniformly fixed in the circumferential direction of the bottom of the mounting bracket ( 6 ). 3 . frame (7); when the aircraft support frame (7) is at the tensile limit position, the bottom exceeds the port of the tail nozzle (2), which is used for landing support. 3. A single-engine aircraft based on a vectoring nozzle according to claim 2, wherein the aircraft support frame (7) comprises a first support rod (8), a second support rod (9), a first support rod (9), a Three connecting rods (10) and a transmission block (12); one end of the first support rod (8) is fixed to the bottom of the mounting frame (6), and the other end is coaxially sleeved and connected to the second support rod (9), and the two The retractable third connecting rod (10) is fixed on the outside of the first supporting rod (8) and the second supporting rod (9), and the third connecting rod (10) is provided with the A telescopic transmission block (12); the transmission block (12) controls the expansion and contraction of the third connecting rod (10) to drive the relative sliding of the first support rod (8) and the second support rod (9). 4. A single-engine aircraft based on a vectoring nozzle according to claim 2, characterized in that, a flexible block (12) is provided at the bottom of the aircraft support frame (7) for landing buffering. 5. A single-engine aircraft based on a vectoring nozzle according to claim 1, characterized in that, the tail nozzle (2) is connected to the engine through an annular first connecting rod (3) hinged on its upper outer periphery (1) Connection. 6 . The single-engine aircraft based on a vectoring nozzle according to claim 1 , wherein the outer periphery of the tail nozzle ( 2 ) is connected to different steering gears ( 4 ) through a plurality of second connecting rods ( 5 ). 7 . The second connecting rod (5) can be driven by the steering gear (4) to deflect the tail nozzle (2), so as to change the thrust direction. 7. The single-engine aircraft based on a vectoring nozzle according to claim 6, wherein there are four second connecting rods (5), which are evenly distributed on the outer circumference of the tail nozzle (2), and The end of each second connecting rod (5) connected to the tail nozzle (2) is located in the same radial cross section; all the second connecting rods (5) can respectively control the deflection of the tail nozzle (2) in the orthogonal direction angle, so that the tail nozzle (2) has a circumferential movement capability of 360°. 8. A vector nozzle-based single-engine aircraft according to claim 1, characterized in that a fuel tank, a control unit and a communication device are arranged on the outer ring of the mounting frame (6) for fuel supply, flight control and ground communications. 9 . The single-engine aircraft based on a vector nozzle according to claim 1 , wherein the engine ( 1 ) includes but is not limited to a turbojet engine, a piston engine or a ducted engine. 10 . 10. A method for flying and landing using the vector nozzle-based single-engine aircraft according to any one of claims 1 to 9, wherein the details are as follows: Before the aircraft takes off, the engine (1) is suspended through the retractable aircraft support frame (7) arranged at the bottom of the mounting frame (6), the axis of the engine (1) is perpendicular to the ground, and the direction of the nozzle of the tail nozzle (2) is controlled to be vertical straight down; then perform the ignition operation, start the engine (1), gradually increase the rotational speed, and make the aircraft rise vertically; after the aircraft is at a certain height from the ground, retract the aircraft support frame (7), and change the tail nozzle (2) ) to change the thrust direction of the nozzle to realize the hovering and lifting motion of the aircraft; when the aircraft needs to be landed, first make it in a hovering state, and then gradually reduce the fuel supply of the engine (1), so that the aircraft slowly descends; After the aircraft has landed smoothly, turn off the engine (1).

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