Modularized reconfigurable wide-working-condition aircraft

Abstract

The modularized reconfigurable wide-working-condition aircraft comprises a fuselage, wings, detachable canards, detachable connecting rods, a detachable horizontal tail wing, a detachable undercarriage, an optical pod and a tail rotor, the wings are arranged on the two sides of the fuselage correspondingly, and detachable power rods are arranged on the upper sides of the wings on one side of the fuselage; a detachable power rod is arranged on the upper side of a wing on the other side of the fuselage, three rotor wing modules are arranged below the power rod, a detachable power rod is arranged on the upper side of the wing on the other side of the fuselage, and three rotor wing modules are arranged below the power rod, so that the fuselage layout of a six-rotor-wing structure is formed. The power rod arranged on the upper side of the wing is replaced with an arc-shaped connecting rod after being detached, the detachable horizontal tail is arranged on the topmost portion, and after the undercarriage arranged on the lower side of the fuselage is detached and folded, the aircraft structure is changed, and modular reconstruction is achieved. Mounting and dismounting are carried out through the detachable modules on the upper sides of the wings, and tool-free switching of two aircraft configurations, namely the horizontal vertical aircraft and the catapult-assisted take-off aircraft, is achieved.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to tool-free switching between two aircraft configurations, wherein a detachable module is used to switch between aircraft with or without rotary wings, thereby realizing modular reconfigurable wide-operating-condition flight. Background Art

[0002] With the continuous development of technology, manned aircraft have been widely developed and applied in the military and civilian fields of countries around the world. Common manned aircraft mainly include fixed-wing aircraft and rotary-wing aircraft. Fixed-wing aircraft have long range and high speed; rotary-wing aircraft are flexible, stable and highly controllable in take-off and landing. In recent years, vertical take-off and landing fixed-wing aircraft that combine fixed-wing and rotary-wing have also appeared one after another.

[0003] The existing vertical take-off and landing fixed-wing aircraft has a large wingspan, so the volume occupied during transportation and take-off and landing is large; the existing vertical take-off and landing fixed-wing aircraft generally use the method of changing the relative thrust direction or using two propulsion systems to achieve the attitude adjustment process of vertical to horizontal flight, which will cause hidden dangers such as high system complexity, weight redundancy, and reduced reliability of the tilting mechanism. Once an accident such as engine failure occurs in the existing vertical take-off and landing aircraft, it will be difficult to land safely in an emergency. Summary of the invention

[0004] The present invention aims to solve the technical problems existing in the prior art and proposes a modular reconfigurable wide-operating-condition aircraft, which is an aircraft that can switch between rotor and fixed-wing configurations without tools. It can solve the problems of existing vertical take-off and landing fixed-wing aircraft occupying a large space during transportation and take-off and landing, and the complex tilting structure and difficulty in emergency landing.

[0005] The technical solution adopted by the present invention is as follows: A modular reconfigurable wide-operating-mode aircraft, comprising a fuselage, a tail rotor, a power system in the fuselage, and a wing disposed on each side of the fuselage, characterized in that it comprises a detachable power rod, a detachable horizontal tail, and a pair of detachable canards disposed on both sides of the fuselage head; Removable power rods are symmetrically arranged on the upper sides of the left and right wings of the fuselage, and three sets of rotor modules are arranged under the power rods, thereby forming a fuselage layout with six sets of rotor configurations; The power rods arranged on the left and right sides of the wing are disassembled and replaced with an arc-shaped connecting rod respectively. A detachable horizontal tail is arranged at the top to connect the arc-shaped connecting rod together. After the pair of canards are disassembled and folded, the aircraft configuration changes, that is, the rotor configuration is transformed into a fixed-wing configuration.

[0006] Furthermore, the detachable power rod is fixed to a mounting platform on the upper side of the wing and is respectively located at the outermost end of the detachable canard.

[0007] Furthermore, the arc-shaped connecting rod is inclined at an angle of 120° from the horizontal direction toward the upper rear of the fuselage.

[0008] Furthermore, a landing gear is installed below the fuselage under the rotor configuration.

[0009] Furthermore, the rotor module includes a motor and a propeller, the central axis of the power rod is parallel to the central axis of the fuselage, and the propeller is evenly installed on the power rod.

[0010] Furthermore, the wings on both sides of the fuselage form an upward angle when installed.

[0011] Furthermore, the installation angles of the six rotor modules are all inclined at a certain angle toward the center of gravity of the fuselage to improve the wind resistance of the aircraft.

[0012] Furthermore, the power system includes an electrical system and a fuel system; the electrical system is respectively connected to the six groups of rotor modules to achieve vertical take-off under this configuration; the fuel system is connected to the tail rotor at the tail of the fuselage and provides the thrust required for horizontal flight for two aircraft of different configurations.

[0013] Furthermore, the canard is provided with an adjustable control surface, and the attitude of the aircraft can be adjusted by deflecting the control surface on the same side.

[0014] Furthermore, a fully movable tail wing is installed at the tail of the arc-shaped connecting rod, and the fully movable tail wing adjusts the pitch angle of the aircraft during flight by adjusting the offset angle.

[0015] The present invention realizes tool-free switching configuration through multiple detachable modules. When vertical take-off is required, power rods with 6 mounting platforms are installed on both sides of the wing, the rotor modules form a 6-rotor configuration, and a landing gear device is set at the bottom of the fuselage for landing; when a fixed-wing configuration is required, the arc-shaped connecting rod is installed and the horizontal tail is installed on the top, and the landing gear and canard are removed, that is, the fixed-wing catapult take-off configuration is switched. When taking off in the 6-rotor configuration, the 6 rotor modules provide power, and the power generated is controlled to take off vertically without a runway; after adjusting to the fixed-wing configuration through tool-free switching configuration, that is, the fixed-wing level flight state, the aircraft adopts a single propulsion system with low redundancy. The goal of dual-purpose of one machine is achieved through flexible configuration switching; the detachable parts reduce the envelope volume of the aircraft and realize flexible disassembly and assembly of the split parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A three-dimensional diagram of a modular reconfigurable wide-operating-condition aircraft in a six-rotor configuration according to an embodiment of the present invention; Figure 2 A side view of the modular reconfigurable wide-operating-mode aircraft in a 6-rotor configuration according to an embodiment of the present invention; Figure 3A top view of the modular reconfigurable wide-operating-condition aircraft in a 6-rotor configuration according to an embodiment of the present invention; Figure 4 A three-dimensional diagram of a modular reconfigurable wide-operating-condition aircraft in a fixed-wing configuration according to an embodiment of the present invention; Figure 5 It is a front view of the modular reconfigurable wide-operating-condition aircraft in a fixed-wing configuration according to an embodiment of the present invention; Figure 6 It is a side view of the modular reconfigurable wide-operating-condition aircraft in a fixed-wing configuration according to an embodiment of the present invention. DETAILED DESCRIPTION

[0017] The technical solution of the present invention is described in detail below. The embodiments of the present invention are only used to illustrate the specific structure, and the scale of the structure is not limited by the embodiments.

[0018] like Figures 1 to 6 As shown, a horizontal aircraft can implement tool-free switching between two aircraft configurations, including a fuselage 100, a detachable rotor module, a detachable horizontal tail, a detachable connecting rod and a power system. A wing 150 is installed on each side of the fuselage 100, and a mounting platform 130 is provided on both sides of the front of the fuselage 100. A pair of detachable horizontal canards 140 are installed on the platform. The canards are provided with adjustable control surfaces. The same-side deflection of the control surface can adjust the pitch attitude of the aircraft, solving the problem of difficult layout of the pitch control surface.

[0019] The mounting platforms are symmetrically arranged on the upper sides of the wings 150 on both sides, and are kept at the same horizontal line with the detachable horizontal canard 140 .

[0020] Among them, refer to Figure 1 , Figure 2 and Figure 3 , six rotor modules 220 including motors and propellers are installed on the installation platform below the detachable power rod 210, and the installation angles are all inclined at a certain angle to the center of gravity of the fuselage to improve the wind resistance of the aircraft. The detachable power rod 210 is fixed to the installation platform on the upper side of the wing 150, and is respectively located at the outermost end of the detachable horizontal canard 140. The three rotor modules 220 on both sides of the wing 150 are on an axis and parallel to the central axis of the fuselage 100. The propellers are driven by motors, and each motor is connected to a propeller to provide driving force. The control system is respectively connected to the six motors to adjust the speed and power of each motor to achieve the conversion of flight attitude. The power system is installed in the fuselage 100, and the power system includes an electric system and a fuel system, wherein the electric system is respectively connected to the power supply ends of the six motors to provide power, and the power system includes batteries, battery management modules and electrical equipment; the fuel system is used to provide power to the tail rotor 110 at the tail of the fuselage. A detachable landing gear 120 is provided below the fuselage, and an optical pod 160 is provided at the front end below the fuselage.

[0021] Among them, refer to Figures 4 to 6 , showing the state of the aircraft switching to a fixed-wing configuration without tools. When switching to the fixed-wing configuration, the mounting platforms 130 set on both sides of the front of the fuselage 100 need to remove a pair of detachable horizontal canards 140 installed on the platforms. The detachable landing gear under the fuselage also needs to be removed. At the same time, the detachable power rod on the mounting platform above the wing 150 is replaced with a detachable arc-shaped connecting rod 230, and the connecting rod is inclined at an angle of 120° from the horizontal direction to the upper rear of the fuselage. A detachable fully-movable horizontal tail 240 is installed at the top of the arc-shaped connecting rod 230. A fully-movable tail is installed at the tail of the arc-shaped connecting rod 230. This fully-movable tail adjusts the pitch angle of the aircraft during flight by adjusting the offset angle.

[0022] After the switch, the six rotor modules are removed, and the aircraft changes from a rotor configuration to a fixed-wing configuration. The power system in the power system is separated, leaving only the tail rotor 110 at the tail of the fuselage to provide power after the aircraft is ejected. Therefore, the aircraft switched to a fixed-wing configuration needs to be recovered by a net collision for landing.

[0023] Common rotorcraft generally require multiple rotor mechanisms and are difficult to disassemble and assemble. The rotor mechanism generally belongs to the drag surface when the aircraft is flying level. The aircraft of this embodiment uses tool-free switching to realize the reconstruction of the 6-rotor aircraft into a fixed-wing aircraft through modules, which increases the adaptability of the aircraft to working conditions, reduces costs, and increases flexibility.

[0024] The aircraft's wing forms an upward dihedral angle as a whole. At the same time, in the case of a 6-rotor configuration, the 6 rotor modules are tilted toward the fuselage at symmetrical angles, increasing the aircraft's wind resistance.

[0025] In addition, the fixed-wing configuration has the ability to take off and land horizontally, and realize the function of gliding and forced landing, which greatly improves the safety performance of the tail-seat aircraft.

[0026] The reconfigurable aircraft of this embodiment solves the problem of large space occupied by fixed-wing aircraft and rotary-wing aircraft during storage and transportation through modular combination.

[0027] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A modular reconfigurable wide-operating-mode aircraft, comprising a fuselage, a tail rotor, and a power system in the fuselage, wherein a wing is disposed on each side of the fuselage, and wherein: It includes a detachable power rod, a detachable horizontal tail, and a pair of detachable canards on both sides of the fuselage head; Removable power rods are symmetrically arranged on the upper sides of the left and right wings of the fuselage, and three sets of rotor modules are arranged under the power rods, thereby forming a fuselage layout with six sets of rotor configurations; The power rods arranged on the left and right sides of the wing are disassembled and replaced with an arc-shaped connecting rod respectively. A detachable horizontal tail is arranged at the top to connect the arc-shaped connecting rod together. After the pair of canards are disassembled and folded, the aircraft configuration changes, that is, the rotor configuration is transformed into a fixed-wing configuration.

2. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The detachable power rod is fixed to the mounting platform on the upper side of the wing and is respectively fixed to the outermost end of the detachable canard.

3. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The arc-shaped connecting rod is inclined at an angle of 120 degrees from the horizontal direction toward the upper rear of the fuselage.

4. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: A landing gear is installed below the fuselage under the rotor configuration.

5. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The rotor module comprises a motor and a propeller. The central axis of the power rod is parallel to the central axis of the fuselage, and the propeller is evenly mounted on the power rod.

6. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The wings on both sides of the fuselage form an upward angle when installed.

7. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The installation angles of the six rotor modules are all inclined at a certain angle toward the center of gravity of the fuselage to improve the wind resistance of the aircraft.

8. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The power system includes an electrical system and a fuel system; the electrical system is connected to the six rotor modules respectively to achieve vertical take-off under this configuration; the fuel system is connected to the tail rotor at the rear of the fuselage and provides the thrust required for horizontal flight for two aircraft of different configurations.

9. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The canard is provided with an adjustable control surface, and the attitude of the aircraft can be adjusted by deflecting the control surface on the same side.

10. The modular reconfigurable wide operating range aircraft according to claim 1, characterized in that: The arc-shaped connecting rod is equipped with a fully movable tail wing, and the fully movable tail wing adjusts the pitch angle of the aircraft during flight by adjusting the offset angle.

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