Tailstock type vertical take-off and landing aircraft with telescopic tail

Abstract

The invention belongs to the field of vertical take-off and landing aircrafts, and relates to the field of vertical take-off and landing aircrafts, the vertical take-off and landing aircrafts comprise an airframe, the front end of the airframe is provided with a set of coaxial variable-pitch reverse propeller power device, the two sides of the airframe are symmetrically provided with a left wing and a right wing, the left wing is internally provided with a power guide rail left bearing guide piece and a power guide rail left moving piece, and the right wing is internally provided with a power guide rail right bearing guide piece and a power guide rail right moving piece; a tail seat capable of moving front and back is arranged behind the aircraft body, the tail seat can be moved backwards by a certain distance to change the shape through the power guide rail left moving part and the power guide rail right moving part, the shape of the aircraft with the changed shape is close to that of a conventional fixed-wing aircraft, and the performance of the aircraft is close to that of the conventional fixed-wing aircraft.

Description

Technical Field

[0001] The invention belongs to the technical field of vertical take-off and landing horizontal flight aircraft, and in particular relates to a tail-seat type vertical take-off and landing aircraft with a retractable tail. Background Art

[0002] Tail-seat vertical take-off and landing aircraft have a high center of gravity during take-off and landing, which is not conducive to maintaining balance during take-off and landing. In order to lower the center of gravity during vertical take-off and landing, maintain balance and improve safety, and retain good maneuverability and flexibility during horizontal cruising flight, a tail-seat vertical take-off and landing aircraft with a retractable tail is proposed. Summary of the invention

[0003] The invention discloses a tail-seat retractable tail vertical take-off and landing aircraft, which adopts a tail-seat retractable tail design, lowers the center of gravity during vertical take-off and landing, maintains balance and improves safety, and maintains good maneuverability and energy saving during horizontal attitude cruising flight.

[0004] In order to provide a tail-seat retractable tail vertical take-off and landing aircraft with relatively flexible and reliable control and relatively safe operation, the present invention provides the following technical solutions: The invention provides a tail-seat type retractable tail vertical take-off and landing aircraft, comprising an aircraft body, wherein a set of coaxial variable pitch reverse propeller power device is arranged at the front end of the aircraft body.

[0005] Preferably, a left wing and a right wing are symmetrically provided on both sides of the aircraft, a left aileron is provided on the outside of the rear edge of the left wing, and a right aileron is provided on the outside of the rear edge of the right wing.

[0006] Preferably, the trailing edges of the left wing and the right wing are flush with the rear end of the fuselage.

[0007] Preferably, a power rail left bearing guide is provided inside the left wing, between the left aileron and the fuselage, and close to the left aileron, and the power rail left bearing guide is parallel to the fuselage.

[0008] Preferably, the power guide rail left bearing member is equipped with a power guide rail left moving member, and the power guide rail left moving member is provided with guide rail power by the power guide rail left bearing member and can perform forward and backward parallel movement.

[0009] Preferably, a power rail right guide is provided inside the right wing, between the right aileron and the fuselage, close to the right aileron, and the power rail right guide is parallel to the fuselage.

[0010] Preferably, the power guide rail right bearing member is equipped with a power guide rail right moving member, and the power guide rail right moving member is provided with guide rail power by the power guide rail right bearing member and can perform forward and backward parallel movement.

[0011] Preferably, a horizontal tail is connected between the rear ends of the left moving part of the power rail and the right moving part of the power rail. The horizontal tail is in the same plane as the left wing and the right wing, and a horizontal rudder is provided at the rear edge of the horizontal tail.

[0012] Preferably, a left vertical tail is provided at the rear end of the left moving part of the power guide rail, and a right vertical tail is provided at the rear end of the right moving part of the power guide rail. The left vertical tail and the right vertical tail are perpendicular to the horizontal tail to form an H-shaped configuration.

[0013] Preferably, a left vertical rudder is provided at the trailing edge of the left vertical tail wing, and a right vertical rudder is provided at the trailing edge of the right vertical tail wing.

[0014] Preferably, a No. 1 supporting foot and a No. 3 supporting foot are respectively provided at both ends of the left vertical tail wing, and a No. 2 supporting foot and a No. 4 supporting foot are respectively provided at both ends of the right vertical tail wing.

[0015] Preferably, the left vertical tail, the right vertical tail, the horizontal tail, the first supporting foot, the second supporting foot, the third supporting foot, and the fourth supporting foot together constitute a tail stock, which can lower the center of gravity, improve balance safety, and support the load-bearing function of the entire machine when the tail stock is close to the fuselage for vertical takeoff and landing.

[0016] Preferably, after the tail seat is moved backward a certain distance and locked, the horizontal rudder wing, the left vertical rudder wing, and the right vertical rudder wing arranged thereon cooperate with the left aileron and the right aileron to control the flight attitude of the aircraft. It can perform horizontal movements during vertical take-off and landing, and can perform conventional movements such as pitching, rolling, and turning during horizontal cruising.

[0017] Preferably, the aircraft is completely symmetrical left to right and belly to back, which is beneficial to dynamic balance when adjusting posture during vertical take-off and landing operations.

[0018] Preferably, after the tail seat is moved backwards a certain distance and locked, the shape of the aircraft changes, and its shape is close to that of a conventional fixed-wing aircraft, and its performance is also close to that of a conventional fixed-wing aircraft.

[0019] The beneficial effects of the present invention are: This type of tail-seat retractable tail vertical take-off and landing aircraft adopts a vertical take-off and landing mode to meet flight needs when there is no runway; the aircraft adopts a symmetrical structure and a coaxial variable-pitch reverse propeller power device is arranged at the nose as the only source of pulling force, which is beneficial to the balance of the center of gravity during vertical take-off and landing, thereby improving the safety factor; the aircraft adopts a horizontal attitude level flight mode of the fuselage to achieve relatively high-speed flight; the aircraft is equipped with fixed wings to provide the main lift, which can reduce lift energy consumption, thereby reducing power energy consumption and increasing the range; the aircraft adopts a tail-seat retractable tail design, which lowers the center of gravity to maintain balance and improve safety during vertical take-off and landing, and maintains good maneuverability and energy saving during horizontal attitude cruising flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0021] In the attached picture: Figure 1 Schematic diagram of the aircraft back structure when the tail seat has been extended Figure 2 Schematic diagram of the belly structure of the aircraft when the tail seat has been extended Figure 3 This is a schematic diagram of the right side structure of the aircraft when the tail seat has been extended. Figure 4 This is a schematic diagram of the left side structure of the aircraft when the tail seat has been extended. Figure 5 Schematic diagram of the aircraft tail seat structure Figure 6 A schematic diagram of the back of the aircraft when the tail seat is not extended Figure 7 This is a schematic diagram of the right side of the aircraft when the tail seat is not extended. Figure 8 This is a diagram of the aircraft's attitude when the tail seat is extended and level flight Fig. 9 Schematic diagram of the aircraft taking off, level flight, and landing posture changes In the figure: 1, fuselage 2, horizontal tail 3, coaxial variable pitch reverse propeller power device 4, horizontal rudder 5, left wing 6, right wing 7, left aileron 8, right aileron 9, left bearing guide of power rail 10, right bearing guide of power rail 11, left moving part of power rail 12, right moving part of power rail 13, left vertical tail 14, right vertical tail 15, No. 1 support foot 16, No. 2 support foot 17, No. 3 support foot 18, No. 4 support foot 19, left vertical rudder 20, right vertical rudder DETAILED DESCRIPTION

[0022] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0023] Example: Figure 6 Figure 7 Fig. 9 As shown, the tail-seat retractable tail vertical take-off and landing aircraft starts the coaxial variable pitch reverse propeller power device 3 to generate an upward pulling force, and controls the coaxial variable pitch reverse propeller power device 3 to increase the pulling force. When the upward pulling force is greater than the overall gravity of the aircraft, the aircraft leaves the ground and moves upward.

[0024] Further, if Figure 1 Figure 4 Figure 7 Fig. 9 As shown, when the aircraft rises to a certain height, the power guide left bearing member 9 and the power guide right bearing member 10 are synchronously started to push the tail seat to the rear of the fuselage 1 for a certain distance and then lock it through the power guide left moving member 11 and the power guide right moving member 12, thereby changing the aircraft into a shape close to that of a conventional fixed-wing aircraft.

[0025] Further, as 1 Fig. 9 As shown, the horizontal rudder wing 4 is controlled to rotate a certain angle, at which time the downward airflow generated by the coaxial variable pitch reverse propeller power device 3 is deflected, so that the aircraft generates an angle of attack, and at this time the aircraft moves in the direction of the angle of attack.

[0026] Further, if Figure 8 Fig. 9 As shown, the angle of attack is gradually reduced and the aircraft enters a level flight cruising state when it approaches a horizontal attitude, and a certain angle of attack is maintained to provide the aircraft with a suitable lift. During level cruising, the horizontal rudder wing 4, the left vertical rudder wing 19, and the right vertical rudder wing 20 are controlled as needed to cooperate with the left aileron 7 and the right aileron 8 to change the flight attitude, and conventional actions such as forward climbing, forward diving, rolling, and turning can be performed.

[0027] Further, if Figure 8 Figure 7 Fig. 9 As shown, when flying forward to a high altitude close to the destination, the horizontal rudder wing 4 is controlled, and the airflow generated backward by the coaxial variable pitch reverse propeller power device 3 is deflected, causing the tail of the aircraft to gradually droop until the aircraft turns into a vertical posture.

[0028] Further, if Fig. 9 As shown, the coaxial variable pitch reverse propeller power device 3 is controlled to make the upward pulling force generated equal to the overall gravity of the aircraft, and then fine-tuned to make the aircraft hover vertically in the air.

[0029] Further, if Fig. 9As shown, the horizontal rudder wing 4, the left vertical rudder wing 19, and the right vertical rudder wing 20 are manipulated to slightly change the posture of the aircraft so that the aircraft moves horizontally to just above the landing point.

[0030] Further, if Fig. 9 As shown, the coaxial variable pitch reverse propeller power device 3 is controlled so that the upward pulling force generated is slightly smaller than the overall gravity of the aircraft, so that the aircraft slowly descends.

[0031] Further, if Figure 1 Figure 4 Figure 7 Fig. 9 As shown, when descending to a certain height, the left power guide rail bearing member 9 and the right power guide rail bearing member 10 are synchronously started, the left power guide rail moving member 11 and the right power guide rail moving member 12 are unlocked to move the tail seat toward the fuselage 1 until it is close to the fuselage 1. At this time, the aircraft returns to the shape before vertical take-off.

[0032] Further, if Figure 7 Fig. 9 As shown, when the aircraft is about to reach the ground, the coaxial variable pitch reverse propeller power device 3 is controlled to slightly increase the lift force to offset the falling inertia of the aircraft and land smoothly on the landing point. At this time, the landing operation is completed.

[0033] Further, if Fig. 9 As shown, after the aircraft is stabilized, the coaxial variable pitch reverse propeller power device 3 is shut down, and the flight process ends.

[0034] The above description is only a specific embodiment of the present invention, and the present invention is described in detail. Parts not described in detail are conventional technologies.

Claims

1. A tail-seat retractable tail vertical take-off and landing aircraft, characterized in that: The invention comprises a machine body 1, wherein a coaxial variable pitch reverse propeller power device 3 is provided at the front end of the machine body 1, a left wing 5 and a right wing 6 are symmetrically provided on both sides of the machine body, and the rear edges of the left wing 5 and the right wing 6 are flush with the rear end of the machine body 1, a power guide left bearing member 9 is provided in the left wing 5, and the power guide left bearing member 9 is parallel to the machine body 1, and the power guide left bearing member 9 is equipped with a power guide left moving member 11, and the power guide left moving member 11 is provided with a guide rail power by the power guide left bearing member 9 and can move forward and backward in parallel, and a power guide right bearing member 10 is provided in the right wing 6, The right guide member 10 of the power guide rail is parallel to the body 1, and the right guide member 10 of the power guide rail is equipped with a right moving member 12 of the power guide rail. The right moving member 12 of the power guide rail is provided with a guide rail power by the right guide member 10 of the power guide rail, and can move forward and backward in parallel. A horizontal tail 2 is connected between the rear end of the left moving member 11 of the power guide rail and the rear end of the right moving member 12 of the power guide rail. The horizontal tail 2 is in the same plane as the left wing 5 and the right wing 6. A horizontal rudder 4 is provided at the rear edge of the horizontal tail 2. A left vertical tail 13 is provided at the rear end of the left moving member 11 of the power guide rail The rear end of the right moving part 12 of the power guide rail is provided with a right vertical tail 14, the left vertical tail 13 and the right vertical tail 14 are perpendicular to the horizontal tail 2 to form an H-shaped configuration, the rear edge of the left vertical tail 13 is provided with a left vertical rudder 19, the rear edge of the right vertical tail 14 is provided with a right vertical rudder 20, the two ends of the left vertical tail 13 are respectively provided with a first support foot 15 and a third support foot 17, the two ends of the right vertical tail 14 are respectively provided with a second support foot 16 and a fourth support foot 18, the left vertical tail 13, the right vertical tail 14, the horizontal tail 2, The No. 1 supporting foot, the No. 2 supporting foot, the No. 3 supporting foot, and the No. 4 supporting foot together constitute a tail seat, which can lower the center of gravity and improve the balance safety and support the load-bearing function of the entire aircraft when the tail seat is close to the body 1 for vertical take-off and landing. After the tail seat is moved backward for a certain distance and locked, the horizontal rudder wing 4, the left vertical rudder wing 19, and the right vertical rudder wing 20 arranged thereon cooperate with the left aileron 7 and the right aileron 8 to control the flight of the aircraft to perform horizontal movements during vertical take-off and landing, and to perform conventional movements such as pitching, rolling, and turning during horizontal cruising.

2. According to claim 1, a tail-seat retractable tail vertical take-off and landing aircraft, the aircraft is completely symmetrical left and right, and completely symmetrical belly and back, which is conducive to dynamic balance when adjusting the posture during vertical take-off and landing operations.

3. According to claim 1, a tail-seat retractable tail vertical take-off and landing aircraft, after the tail seat is moved backward a certain distance and locked, the shape of the aircraft changes, and its shape is close to that of a conventional fixed-wing aircraft, and its performance is also close to that of a conventional fixed-wing aircraft.

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