Gravity telescopic tailstock and vertical take-off and landing tilting flat flight aircraft

Abstract

The invention relates to the field of vertical take-off and landing aircrafts, in particular to a gravity telescopic tail base and a vertical take-off and landing tilting flat flight aircraft, which comprise an aircraft body, a coaxial reverse propeller power device is arranged at the front end of the aircraft body, a left wing and a right wing are symmetrically arranged on two sides of the aircraft body, and the gravity telescopic tail base is arranged at the central axis position of the aircraft body. The gravity telescopic tail base can do telescopic motion through gravity during vertical take-off and landing, the gravity telescopic tail base moves backwards by a certain distance to change the shape, 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 aircraft, and in particular relates to a gravity-retractable tail seat and a vertical take-off and landing tilt-and-level flight aircraft. Background Art

[0002] A tail-seat vertical take-off and landing aircraft has 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 stability and safety, a gravity-retractable tail seat and a vertical take-off and landing tilt-level flight aircraft are proposed. Summary of the invention

[0003] The present invention discloses a gravity-retractable tail seat and a vertical take-off and landing tilt-rotating horizontal flight aircraft. The tail seat type retractable tail design is adopted. Lowering the center of gravity during vertical take-off and landing is beneficial to maintaining balance and improving safety. When used in combination with a vertical take-off and landing tilt-rotating body horizontal cruise aircraft, the tail extended during tilting to a horizontal posture cruising flight can also maintain good maneuverability.

[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 gravity-retractable tail seat, comprising a machine body, wherein a cylindrical movable machine body is arranged at the central axis position of the machine body.

[0005] Preferably, a freely rolling upper rear arc groove roller and a lower rear arc groove roller are provided at the rear of the body, the upper rear arc groove roller and the lower rear arc groove roller pair clamp the movable body, the upper rear arc groove roller is provided with a No. 2 roller shaft, the No. 2 roller shaft is fixed in the body, and the lower rear arc groove roller is provided with a No. 4 roller shaft, the No. 4 roller shaft is fixed in the body.

[0006] Preferably, a freely rolling front upper arc groove roller and a front lower arc groove roller are provided slightly forward of the rear upper arc groove roller and the rear lower arc groove roller, and the front upper arc groove roller and the front lower arc groove roller pair clamp the movable body, the front upper arc groove roller is provided with a No. 1 roller shaft, and the No. 1 roller shaft is fixed in the body, and the front lower arc groove roller is provided with a No. 3 roller shaft, and the No. 3 roller shaft is fixed in the body.

[0007] Preferably, the movable body can only move forward and backward under the joint limiting action of the rear upper arc groove roller and the rear lower arc groove roller, and the front upper arc groove roller and the front lower arc groove roller.

[0008] Preferably, a linear slide rail is provided in parallel below the movable body, two guide rail columns are provided on the lower side of the front end of the movable body, and the linear slide rail is between the two guide rail columns to limit the movable body from rotating when the movable body moves forward and backward.

[0009] Preferably, there is a tail seat behind the movable body, and the tail seat is composed of a tail wing and a tail seat, and the tail seat has the functions of both the tail wing and the tail seat.

[0010] Preferably, an upper tail, a lower tail, a left tail and a right tail are respectively provided on the upper, lower, left and right sides of the rear portion of the movable body as components of the tail, which are in a cross-shaped configuration, but can also be set to an X-shaped, Y-shaped, I-shaped or H-shaped configuration as needed. Support feet are provided on the outer side of each tail, and the support feet, as part of the tail seat, play a role of supporting balance.

[0011] Preferably, the rear end of the movable body has a load-bearing function and is located at the center of gravity when the body is vertical, bearing most of the weight of the aircraft and forming the tail seat together with the supporting feet.

[0012] Preferably, a positioning column is provided on the upper side of the front end of the movable body, and the positioning column is provided with a circular positioning column hole.

[0013] Preferably, before the aircraft takes off vertically or after it lands vertically, when the tail wings are against the fuselage, the movable body is in the final stroke of forward movement relative to the body. At this time, the positioning column hole on the positioning column is correspondingly provided with a front screw stepper motor, and the front screw stepper motor drives the front screw on the front screw stepper motor to be inserted into the positioning column hole to lock the movable body.

[0014] Preferably, after the aircraft takes off vertically or before it lands vertically, when the movable body moves backward to an appropriate distance, a travel limit column is correspondingly arranged behind the positioning column. At this time, the movable body is at the final travel distance that it can move backward relative to the body. At this time, the positioning column hole on the positioning column is correspondingly provided with a rear screw stepper motor. The rear screw stepper motor drives the rear screw on the rear screw stepper motor to insert into the positioning column hole to lock the movable body.

[0015] Preferably, when the aircraft takes off vertically, the body rises upward, and due to the effect of gravity, the unlocked movable body will automatically extend from the body, and will be locked after extending to a suitable stroke. Preferably, when the aircraft lands vertically, the tail seat of the unlocked movable body stops moving when it touches the ground, and due to the effect of gravity, the body continues to move downward, and the movable body retracts into the body by itself, and is locked after retracting to an appropriate stroke.

[0016] The present invention also provides a vertical take-off and landing tilt-and-level flight aircraft, which is a vertical take-off and landing tilt-and-level flight aircraft using a gravity-retractable tail seat.

[0017] Preferably, a left wing and a right wing are provided on both sides of the fuselage, and a coaxial counter-propeller power device is provided at the front end of the fuselage.

[0018] Preferably, after the gravity-retractable tail seat moves backward a certain distance, the shape of the aircraft changes, and its shape is close to that of a conventional fixed-wing aircraft. When the fuselage is tilted for horizontal flight, the performance is also close to that of a conventional fixed-wing aircraft.

[0019] The beneficial effects of the present invention are: The gravity-retractable tail seat and vertical take-off and landing tilt-and-level flight aircraft adopt a gravity-retractable tail seat. Lowering the center of gravity during vertical take-off and landing is beneficial to maintaining balance and improving safety. The tilt-body can also maintain good maneuverability 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 A schematic diagram of the back structure of the aircraft when the tail seat has been extended Figure 2 This is a schematic diagram of the right side structure of the aircraft when the tail seat has been extended. Figure 3 This is a schematic diagram of the back structure of the aircraft when the tail seat is not extended. Figure 4 This is a schematic diagram of the right side structure of the aircraft when the tail seat is not extended. Figure 5 for Figure 2 Enlarged diagram of point A in the middle Figure 6 for Figure 5 Schematic diagram of the cross section at point B Figure 7 for Figure 5 Schematic diagram of cross section at C in the middle Figure 8 Schematic diagram of the aircraft's takeoff, level flight, and landing posture changes In the figure: 1, body 2, movable body 3, linear guide rail 4, front screw stepper motor 5, rear screw stepper motor 6, front upper arc groove roller 7, No. 1 roller shaft 8, rear upper arc groove roller 9, No. 2 roller shaft 10, left wing 11, right wing 12, left tail 13, upper tail 14, right tail 15, lower tail 16, front lower arc groove roller 17, No. 3 roller shaft 18, rear lower arc groove roller 19, No. 4 roller 20, positioning column 21, guide column 22, travel limit column 23, rear screw 24, positioning column hole 25, front screw 26, coaxial reverse propeller power device 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 4 Figure 5 Figure 6 Figure 8 As shown, before take-off, the front screw stepper motor 4 is started to make the front screw 25 leave the positioning column hole 24 and unlock the movable body 2.

[0024] Furthermore, the coaxial reverse propeller power device 26 is started to control the body 1 to move upward.

[0025] Further, if Figure 2 Figure 4 Figure 5 Figure 6 Figure 8 As shown, when the body 1 rises to a certain height, the movable body 2 extends automatically until the positioning column 20 moves to contact the travel limit column 22, and then the rear screw stepper motor 5 is started to drive the rear screw 23 to insert into the positioning column hole 24 to lock the movable body 2. At this time, the aircraft has been changed into a shape close to that of a conventional fixed-wing aircraft.

[0026] Further, if Figure 1 Figure 2 Figure 8 As shown, the aircraft continues to accelerate and rise, and the rudders on the left tail 12 and the right tail 14 are manipulated to adjust the aircraft to a level flight cruising attitude. During the level flight cruising process, the aircraft can be manipulated according to the conventional fixed-wing aircraft manipulation method.

[0027] Further, if Figure 1 Figure 2 Figure 8 As shown, when flying forward to a high altitude close to the destination, the rudders on the left tail 12 and the right tail 14 are manipulated to adjust the aircraft to a vertical attitude.

[0028] Further, if Figure 2 Figure 5 Figure 8 As shown, the rear screw stepping motor 5 is started to drive the rear screw 23 to leave the positioning column hole 24 to unlock the movable body 2.

[0029] Further, if Figure 2 Figure 8 As shown, the coaxial reverse propeller power device 26 is controlled to slowly descend the aircraft until the tail seat touches the ground.

[0030] Further, if Figure 2 Figure 4 Figure 8 As shown, the coaxial reverse propeller power device 26 is controlled to make the body 1 continue to descend. Due to the effect of gravity, the movable body 2 is retracted into the body 1 during the descent of the body 1 until the tail wings contact the body 1. At this time, the positioning column 20 moves to a predetermined position corresponding to the front screw stepper motor 4, and the front screw stepper motor 4 is started to insert the front screw 25 into the positioning column hole 24 to lock the movable body 2.

[0031] Further, if Figure 1 Figure 8 As shown, after the aircraft is stabilized at a stop, the coaxial reverse propeller power device 26 is shut down, and the flight process ends.

[0032] The above is only a specific implementation of the present invention, and the unexplained parts are conventional technologies, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention and ordinary technicians in the technical field should be included in the protection scope of the present invention without departing from the principle of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A gravity retractable tailstock, characterized in that: The invention comprises a machine body 1, wherein a cylindrical movable machine body 2 is provided at the central axis position of the machine body 1; a rear upper arc groove roller 8 and a rear lower arc groove roller 18 which can roll freely are provided at the rear of the machine body 1, wherein the rear upper arc groove roller 8 and the rear lower arc groove roller 18 clamp the movable machine body 2, wherein the rear upper arc groove roller 8 is provided with a No. 2 roller shaft 9, wherein the No. 2 roller shaft 9 is fixed in the machine body 1, and the rear lower arc groove roller 18 is provided with a No. 4 roller shaft 19, wherein the No. 4 roller shaft 19 is fixed in the machine body 1; a freely rolling front upper arc groove roller 6 and a front lower arc groove roller 16 are provided a little forward of the rear upper arc groove roller 8 and the rear lower arc groove roller 18, wherein the front upper arc groove roller 6 and the front lower arc groove roller 16 are connected to each other. The arc groove roller 16 clamps the movable body 2, the front upper arc groove roller 6 is provided with a No. 1 roller shaft 7, the No. 1 roller shaft 7 is fixed in the body 1, the front lower arc groove roller 16 is provided with a No. 3 roller shaft 17, the No. 3 roller shaft 17 is fixed in the body 1; the movable body 2 can only move forward and backward under the joint limiting action of the rear upper arc groove roller 8 and the rear lower arc groove roller 18, the front upper arc groove roller 6 and the front lower arc groove roller 16; a linear slide rail 3 is provided in parallel below the movable body 2, and two guide rail columns 21 are provided on the lower side of the front end of the movable body 2. The linear slide rail 3 is between the two guide rail columns 21, and its function is to move the movable body 2 forward and backward when the movable body 2 moves forward and backward The movable body 2 is restricted from rotating during movement; the rear of the movable body 2 is a tail seat, which is composed of a tail wing and a tail seat, and has the functions of both the tail wing and the tail seat; a positioning column 20 is provided on the upper side of the front end of the movable body 2, and the positioning column is provided with a circular positioning column hole 24; before the vertical take-off or after the vertical landing of the aircraft, when the tail wing is against the body 1, the movable body 2 is in the final stroke of forward movement relative to the body 1, and at this time, the positioning column hole 24 on the positioning column 20 is correspondingly provided with a front screw stepper motor 4, and the front screw stepper motor 4 drives the front screw 25 on the front screw stepper motor 4 to be inserted into the positioning column hole 24 to lock the movable body 2 ; After the aircraft takes off vertically or before landing vertically, when the movable body 2 moves backward to a suitable distance, a travel limit column 22 is correspondingly arranged behind the positioning column 20. At this time, the movable body 2 is at the final travel of the movable body 2 relative to the body 1. At this time, the positioning column hole 24 on the positioning column 20 is correspondingly provided with a rear screw stepper motor 5. The rear screw stepper motor 5 drives the rear screw 23 on the rear screw stepper motor 5 to be inserted into the positioning column hole 24 to lock the movable body 2; When the aircraft takes off vertically, the body 1 rises upward. Due to the action of gravity, the unlocked movable body 2 will automatically extend from the body 1, and will be locked after extending to a suitable travel;When the aircraft lands vertically, the tail seat of the unlocked movable body 2 stops moving when it touches the ground. Due to the effect of gravity, the body 1 continues to move downward, and the movable body 2 will automatically retract into the body 1, and will be locked after retracting to a suitable stroke. ; 2. The gravity-retractable tailstock according to claim 1, characterized in that: An upper tail 13, a lower tail 15, a left tail 12, and a right tail 14 are respectively provided on the upper, lower, left, and right sides of the rear part of the movable body 2 as components of the tail, which are in a cross-shaped configuration, but can also be set to an X-shaped, Y-shaped, I-shaped, or H-shaped configuration as needed. Support feet are provided on the outer side of each tail, and the support feet, as part of the tail seat, play a supporting and balancing role; the rear end of the movable body 2 has a load-bearing function, is located at the center of gravity when the body 1 is vertical, bears most of the weight of the aircraft, and together with the support feet constitute the tail seat.

3. The present invention also provides a vertical take-off and landing tilt-and-level flight aircraft, characterized in that: A vertical take-off and landing tilt-rotate and level-fly aircraft comprising a gravity-retractable tail seat as described in any one of claims 1-2.

4. A vertical take-off and landing tilt-rotate and level-fly aircraft according to claim 3, characterized in that: A left wing 10 and a right wing 11 are provided on both sides of the fuselage, and a coaxial reverse propeller power device 26 is provided at the front end of the fuselage.

5. A vertical take-off and landing tilt-rotate and level-fly aircraft according to claim 3, characterized in that: After the gravity-retractable tail seat moves backwards a certain distance, the shape of the aircraft changes, and its shape is close to that of a conventional fixed-wing aircraft. When the body is tilted for horizontal flight, the performance is also close to that of a conventional fixed-wing aircraft.

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