An unmanned aerial vehicle using a small turbojet engine to achieve vertical take-off and attitude control

Abstract

The utility model discloses a kind of unmanned aerial vehicle for realizing vertical take-off and attitude control using small turbojet engine, small turbojet engine is installed at wing tip of wing, small turbojet engine is installed at the back of fuselage (or in front of fuselage) two sides;Small turbojet engine is made to produce upward thrust by vertical rotation 90 ° using turbine worm drive mechanism or motor with self-locking holding torque, and unmanned aerial vehicle vertical take-off is realized;Unmanned aerial vehicle has aileron installed at the trailing edge of left and right wing tips, and the differential deflection of aileron makes unmanned aerial vehicle tilt rotation around longitudinal axis, and the direction of thrust of small turbojet engine is deflected using turbine worm drive mechanism, to realize the flight state stabilization and flight attitude control of unmanned aerial vehicle, so that unmanned aerial vehicle has good maneuverability;Horizontal stabilizer and elevator are omitted, vertical stabilizer and rudder are omitted, so as to reduce flight resistance, which is conducive to improving the flight speed and effective load of unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model relates to a drone that utilizes a small turbojet engine to achieve vertical takeoff and landing and attitude control. Its aerodynamic layout consists of small turbojet engines mounted on the wings and rear sides of the fuselage. The nozzles of the small turbojet engines can be deflected upwards and downwards via a worm gear transmission mechanism or a motor with a self-locking holding torque, until the nozzles are deflected downwards by 90°, thus achieving vertical takeoff and landing. The differential movement of the ailerons enables the tilting of the drone's fuselage. The simultaneous deflection of the nozzles of the small turbojet engines mounted at the rear of the fuselage enables the pitching of the fuselage. The flight attitude of the drone is controlled by the differential movement of the ailerons and the vertical deflection of the nozzles of the small turbojet engines at the rear of the fuselage. Background Technology

[0002] Currently, most fixed-wing UAVs have horizontal and vertical stabilizers for stable flight attitude, and elevators and rudders for flight attitude control using the aerodynamics of the UAV. This makes the maneuverability control of the UAV related to its aerodynamic characteristics, thus limiting its maneuverability. The flight speed of some propeller-driven UAVs is limited by the aerodynamics of the propeller, making it difficult to achieve higher flight speeds. The inability to take off and land vertically also limits the tactical applications of UAVs. Summary of the Invention

[0003] Two small turbojet engines are mounted at the wingtips, and two more small turbojet engines are mounted on either side of the rear fuselage. The two small turbojet engines (1) mounted at the wingtips have a hollow shaft (2) in the casing. A bearing seat for the hollow shaft (2) is fixed inside the wingtips. The hollow shaft (2) can rotate the small turbojet engine (1) upwards and downwards around the hollow shaft (2) via a meshing worm gear transmission mechanism or a motor with a self-locking torque, until it deflects downwards by 90° with the nozzle pointing downwards. Two small turbojet engines (1) are mounted at the rear fuselage, and the casing for the small turbojet engines (1) has a hollow shaft (2). Inside the rear fuselage, there is a bearing seat for a hollow rotating shaft (2). The hollow rotating shaft (2) can be driven by a meshing worm gear transmission mechanism or a motor with a self-locking holding torque to make the small turbojet engine deflect upward and downward around the hollow rotating shaft (2) until it deflects downward by 90° and the nozzle points downward. The nozzles of these four small turbojet engines deflect vertically downward by 90° to generate upward thrust. The thrust center of the four small turbojet engines is placed at the center of gravity of the UAV. When the combined thrust of the four small turbojet engines is equal to or greater than the weight of the UAV, the UAV can take off and land vertically. The base of the worm gear transmission mechanism or the motor with self-locking torque is fixed to the wingtips and fuselage of the UAV. The hollow shaft (2) of the casing for mounting the small turbojet engine is directly meshed with the shaft of the worm gear transmission mechanism or the motor with self-locking torque. Through the bearing seat fixed to the fuselage, the hollow shaft (2) is deflected. The UAV fuselage tilts around the longitudinal axis of the fuselage through the differential of the UAV ailerons (3, 11). The nozzles of the small turbojet engines (1) on both sides of the rear of the fuselage are simultaneously deflected downwards (upwards) by the worm gear transmission mechanism or the motor with self-locking torque mounted on the fuselage. The fuselage will produce a pitch yaw around the transverse axis of the center of gravity, tilting downwards (tilting upwards); when the small turbojet engines are installed in front of the fuselage, when the nozzles of the two small turbojet engines deflect downwards (upwards) at the same time, the fuselage will produce a pitch yaw around the transverse axis of the center of gravity, tilting upwards (tilting downwards); the differential deflection of the ailerons (3, 11) causes the fuselage to tilt around the longitudinal axis of the UAV, and the simultaneous up-and-down deflection of the nozzle of the small turbojet engine (1) at the rear of the fuselage achieves the pitch yaw of the UAV. The differential deflection of the ailerons (3, 11) and the simultaneous up-and-down deflection of the nozzle of the small turbojet engine (1) at the rear of the fuselage achieve the control of the UAV's flight attitude.

[0004] The beneficial effects of this invention are: it utilizes four small turbojet engines to achieve vertical take-off and landing and flight attitude control of the UAV, enabling the UAV to have higher flight speed and better maneuverability; it eliminates the need for a horizontal stabilizer and elevator, as well as a vertical stabilizer and rudder, thereby reducing flight drag and improving the UAV's flight speed and payload. Attached Figure Description

[0005] Figure 1 This is a top view of a drone that uses a small turbojet engine to achieve vertical takeoff and landing and attitude control. The drone's nose is facing upwards. In the figure, 1 is a small turbojet engine installed in the casing at the wingtip of the left wing; 2 is the hollow shaft of the casing that houses the small turbojet engine; 3 is the aileron of the left wing; 4 is the left wing; 5 is the fuselage; 10 is the right wing; and 11 is the aileron of the right wing. Figure 2 This is a frontal view of the tail of a UAV that uses a small turbojet engine to achieve vertical takeoff and landing and attitude control. In this view, 1 is a small turbojet engine mounted in a casing at the wingtip of the left wing; 2 is the hollow shaft of the small turbojet engine casing; 3 is the aileron of the left wing; 4 is the left wing; 5 is the fuselage; 10 is the right wing; 11 is the aileron of the right wing; 14 is the left landing gear; 15 is the nose landing gear; and 16 is the right landing gear. Figure 3 This is a left view of a UAV that uses a small turbojet engine to achieve vertical takeoff and landing and attitude control. In this view, 1 is a small turbojet engine installed in the wingtip casing of the left wing; 3 is the aileron of the left wing; 4 is the left wing; 5 is the fuselage; 14 is the left landing gear; and 15 is the nose landing gear. Figure 4 This is a top view of a UAV that uses a small turbojet engine for vertical takeoff and landing and attitude control, with the nozzle of the small turbojet engine deflected vertically downwards by 90°, and the UAV's nose pointing upwards. In the figure, 1 is the small turbojet engine installed in the wingtip casing of the left wing; 2 is the hollow shaft of the small turbojet engine casing; 3 is the aileron of the left wing; 4 is the left wing; 5 is the fuselage; 10 is the right wing; and 11 is the aileron of the right wing. Figure 5 This is a frontal view of the tail of a UAV that uses a small turbojet engine to achieve vertical takeoff and landing and attitude control. The nozzle of the small turbojet engine is deflected vertically downward by 90°. 1 is the small turbojet engine mounted in a casing at the wingtip of the left wing; 2 is the hollow shaft of the small turbojet engine casing; 3 is the aileron of the left wing; 4 is the left wing; 5 is the fuselage; 10 is the right wing; 11 is the aileron of the right wing; 14 is the left landing gear; 15 is the nose landing gear; and 16 is the right landing gear. Figure 6This is a left view of a UAV that uses a small turbojet engine to achieve vertical takeoff and landing and attitude control. The small turbojet engine is deflected vertically downwards by 90°. In the image, 1 is the small turbojet engine installed in the wingtip casing of the left wing; 3 is the aileron of the left wing; 4 is the left wing; 5 is the fuselage; 14 is the left landing gear; and 15 is the nose landing gear. Figure 7 This is a front view of a worm gear mechanism that enables vertical takeoff and landing and attitude control using a small turbojet engine. The mechanism is designed to deflect the small turbojet engine. In this view, 17 is the worm shaft; 18 is the worm; 19 is the worm wheel; 20 is the hollow worm wheel shaft, which is the hollow rotating shaft of the casing; and 21 is the drive motor for the worm. Figure 8 This is a top view of the worm gear mechanism that enables the deflection of a small turbojet engine, where 17 is the worm shaft; 18 is the worm; 19 is the worm wheel; 20 is the hollow worm wheel shaft, which is the hollow rotating shaft of the casing; and 21 is the drive motor for the worm. Figure 9 This is a left view of the worm gear mechanism that enables the deflection of a small turbojet engine, where 17 is the worm shaft; 18 is the worm; 19 is the worm wheel; 20 is the hollow worm wheel shaft, which is the hollow rotating shaft of the casing; and 21 is the drive motor for the worm. Figure 10 This is a front view of the casing for mounting a small turbojet engine. 22 is a fastener for the casing; 23 is a fastener with a hollow shaft portion; and 24 is the hollow shaft of the casing, which is integrated with the hollow worm gear shaft. Figure 11 This is a top view of the casing for mounting a small turbojet engine, where 22 is a fastener for the casing; 23 is a fastener for the casing with a hollow shaft section; and 24 is the hollow shaft of the casing. Figure 12 This is a left view of the casing for mounting a small turbojet engine, where 25 are the fixing screws for the casing fasteners. Detailed Implementation

[0006] By using a worm gear transmission mechanism or a motor with a self-locking holding torque to deflect the thrust direction of a small turbojet engine, vertical takeoff and landing and attitude control of the UAV can be achieved. The small turbojet engine is installed inside a casing with a hollow shaft (2). The bearing housing corresponding to the hollow shaft (2) is fixed inside the wingtip and the rear fuselage. The rigidity and strength of the casing and the hollow shaft are designed according to the weight, geometry, aerodynamic drag and thrust of the small turbojet engine. The base of the worm gear transmission mechanism or the motor with self-locking torque is fixed to the wingtip and fuselage of the UAV. The hollow shaft (2) of the casing that mounts and fixes the small turbojet engine (1) is directly meshed with the shaft of the worm gear transmission mechanism or the motor with self-locking torque. The thrust deflection of the small turbojet engine is achieved by driving the hollow shaft (2) of the casing through the worm drive motor (21) or the motor with self-locking torque. The hollow shaft (2) of the casing is also used for the small turbojet engine fuel supply conduit and control system cables. There are two implementation schemes for the worm gear transmission mechanism or the motor with self-locking torque that enables the deflection of the small turbojet engine (1) at the wingtip of the left and right wings: First, the bearing seat of the hollow rotating shaft (2) of the casing is installed inside the wingtip of the left and right wings, and the worm gear transmission mechanism or the motor with self-locking torque is fixedly installed nearby inside the wing. Its worm gear shaft meshes with the hollow rotating shaft (2) of the casing, and the two worm gear transmission mechanisms or the motor with self-locking torque are fixed to the wingtip respectively. Inside the wing, the thrust direction of the small turbojet engine at the wingtip is deflected by a worm gear drive motor (21). In the second option, a bearing housing for a hollow shaft (2) is installed inside the wingtip of the left and right wings. A worm gear transmission mechanism or a motor with self-locking torque is installed and fixed inside the fuselage. The worm gear transmission shaft extends to both sides to the wingtip and meshes with the hollow shaft (2) of the casing at the wingtip to deflect the small turbojet engine (1) at the wingtip. Since the transmission shaft needs to extend a long distance from the wing to the wingtip, the wing beam in the span direction will bend due to overload during flight. Therefore, the transmission shaft inside the wings needs to use a variable length universal joint coupling to accommodate the bending deformation of the wing beam in the span direction due to overload during UAV flight. Small turbojet engines (1) mounted on both sides of the rear of the fuselage share a common worm gear transmission mechanism or a motor with self-locking holding torque installed inside the fuselage. The transmission shaft extends to both sides and, through bearing seats installed inside the fuselage, meshes with the hollow rotating shafts (2) of the casings of the small turbojet engines (1) on both sides of the rear of the fuselage, thereby achieving the deflection of the small turbojet engines mounted on both sides of the rear of the fuselage. Utilizing... Figure 12The screw (25) shown in the figure secures the two parts of the casing together. The differential ailerons of the left and right wings are deflected using a servo motor. In terms of the configuration of the flight control system, the UAV that uses thrust steering of a small turbojet engine and differential aileron to achieve vertical take-off and landing and attitude control has the same configuration as the flight control system of existing UAVs. According to the attitude signal output by the attitude sensor of the UAV, the pitch direction is adjusted by the thrust direction of the small turbojet engine in the rear fuselage through a worm gear transmission mechanism or a motor with self-locking holding torque, so as to realize the pitch direction adjustment of the UAV; at the same time, the tilt adjustment of the UAV around the longitudinal axis of the fuselage is achieved by differential aileron, so as to realize the flight state stability control and flight attitude control of the fixed-wing UAV when there is no aerodynamic flight attitude stabilization and adjustment control components.

Claims

1. A type of unmanned aerial vehicle (UAV) that utilizes a small turbojet engine to achieve vertical takeoff and landing and attitude control, characterized in that: Small turbojet engines are mounted on the wingtips and on both sides of the rear fuselage. The UAV uses four small turbojet engines for steering to achieve vertical take-off and landing and flight attitude control, eliminating the need for a horizontal stabilizer and elevator, as well as a vertical stabilizer and rudder, thereby reducing flight drag and enabling the UAV to have higher flight speed, better maneuverability and payload.

2. The UAV that utilizes a small turbojet engine to achieve vertical takeoff and landing and attitude control according to claim 1, characterized in that: Small turbojet engines mounted at the wingtips and on both sides of the rear fuselage can rotate 90° vertically to generate upward thrust, enabling the drone to take off and land vertically.

3. The UAV that utilizes a small turbojet engine to achieve vertical takeoff and landing and attitude control according to claim 1, characterized in that: The drone has ailerons mounted on the trailing edge of the wingtips of the left and right wings. The differential deflection of the ailerons causes the drone to tilt and rotate around its longitudinal axis.

4. The UAV that utilizes a small turbojet engine to achieve vertical takeoff and landing and attitude control according to claim 1, characterized in that: By using a worm gear transmission mechanism or a motor with a self-locking holding torque to deflect a small turbojet engine, the flight status of the UAV can be stabilized and its flight attitude controlled.

5. The UAV that utilizes a small turbojet engine to achieve vertical takeoff and landing and attitude control according to claim 1, characterized in that: The casing for mounting and securing a small turbojet engine has a hollow shaft through which fuel supply ducts and control system cables pass.

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