Vertical take-off and landing load carrier based on gyro precession and inertial force synthesis

Abstract

This invention provides a vertical takeoff and landing (VTOL) payload aircraft based on the synthesis of gyro precession and inertial force, including a power cabin. A payload compartment is located on the upper surface of the power cabin, and a spare compartment is located on the lower surface. Four inertial propulsion units are symmetrically arranged inside the power cabin, forming a centrally symmetrical redundant layout. A flight control unit is mounted on the power cabin, comprising a human-machine interface platform, a main control unit, a main power module, and an inertial measurement unit. The inertial measurement unit is located on the inner top wall of the power cabin. This invention utilizes a servo motor to drive an inertial mass block to rotate at high speed, combining centrifugal inertial force with controlled gyro precession to generate lift and thrust. This completely eliminates dependence on airborne lifting surfaces, enabling the aircraft to operate stably in non-atmospheric environments such as low pressure, vacuum, underwater, and enclosed cabins, filling the gap in environmental adaptability of traditional aircraft.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force. Background Technology

[0002] Traditional vertical takeoff and landing (VTOL) aircraft, represented by helicopters, multi-rotor UAVs, and tiltrotor aircraft, rely heavily on the interaction between their rotors or propellers and the air to generate lift and thrust. This aerodynamic drive mode has inherent drawbacks that are difficult to overcome in practical applications: It is highly dependent on the atmospheric environment. In non-standard atmospheric environments such as vacuum, thin atmosphere, underwater or sealed cabin, the rotor cannot generate effective aerodynamic force due to the lack of air medium, which leads to the complete failure of the aircraft and greatly limits the expansion of its application scenarios. Traditional rotor systems not only require complex transmission mechanisms, but also additional mechanical structures to counteract the counter-torque generated by the rotor (such as helicopter tail rotors). This directly leads to severe system vibration, high operating noise, severe mechanical wear, high maintenance costs, and limited overall reliability. In a hovering state, the aerodynamic efficiency is extremely low and the energy consumption is huge; and due to the structural characteristics of the exposed rotor, the resistance to wind disturbance is weak, making it very easy to collide when operating in complex urban environments or small enclosed spaces, resulting in extremely poor adaptability.

[0003] At the same time, some attempts have been made to develop propulsion devices that utilize rotational inertia or the gyroscopic effect, but these generally remain at the theoretical or preliminary experimental stage, with many engineering technical barriers that have not yet been overcome. First, the force transmission mechanism is unclear, and the rotational inertial force cannot be effectively converted into a directional and controllable thrust; Secondly, the precession process is uncontrollable and can easily lead to dynamic imbalance and violent oscillations. Again, the lack of a closed-loop control system based on real-time attitude feedback makes it impossible to achieve stable hovering and precise attitude adjustment; Finally, the issues of torque balance and redundancy safety under load conditions remain unresolved.

[0004] The aforementioned problems have prevented existing inertial propulsion technology from forming an engineerable flight technology solution with stable load-bearing capacity. Therefore, a vertical take-off and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force is proposed. Summary of the Invention

[0005] In view of this, embodiments of the present invention provide a vertical take-off and landing payload aircraft based on the synthesis of gyro precession and inertial force, in order to solve or alleviate the technical problems existing in the prior art, and at least provide a beneficial option.

[0006] The technical solution of this invention is implemented as follows: A vertical takeoff and landing (VTOL) payload aircraft based on the synthesis of gyro precession and inertial force includes a power cabin. A payload compartment is disposed on the upper surface of the power cabin, and a spare compartment is disposed on the lower surface of the power cabin. Four inertial propulsion units are symmetrically arranged inside the power cabin, forming a centrally symmetrical redundant layout. A flight control unit is disposed on the power cabin. The flight control unit includes a human-machine interface platform, a main control unit, a main power module, and an inertial measurement unit. The inertial measurement unit is disposed on the inner top wall of the power cabin, and the human-machine interface platform is disposed on the upper surface of the power cabin. The main control unit and the main power module are both disposed on the inner wall of the human-machine interface platform. The main control unit is electrically connected to the human-machine interface platform, the main power module, the inertial measurement unit, and the four inertial propulsion units via electrical wires.

[0007] In some embodiments, the inertial power unit includes a servo motor, a rotating block, four connecting rods, and four inertial mass blocks. The servo motor is disposed on the inner top wall of the power compartment, and the rotating block is disposed on the output shaft of the servo motor. One end of each of the four connecting rods is uniformly hinged to the outer wall of the rotating block via universal joints, and the four inertial mass blocks are uniformly disposed at the other end of the corresponding connecting rods. The tilt angle of the connecting rods ranges from 25° to 35°, and the main control unit is electrically connected to the servo motor via wires.

[0008] In some embodiments, the combined shape of the power compartment, the payload compartment, and the spare compartment is a streamlined inverted disc shape, and the shapes of the power compartment, the payload compartment, and the spare compartment are transitioned by peripheral arcs. The payload compartment and the spare compartment are made of carbon fiber composite material.

[0009] In some embodiments, the inertial mass block is made of a high-density alloy and is dynamically balanced.

[0010] In some embodiments, the servo motor is a high-torque closed-loop servo motor that supports closed-loop control of speed, position, and torque.

[0011] In some embodiments, the payload compartment is a panoramic transparent dome.

[0012] In some embodiments, the inner wall of the spare compartment is respectively provided with an emergency power module, a redundant controller and a parachute recovery system. The main control unit and the redundant controller are electrically connected to the emergency power module, the parachute recovery system, the servo motor, the human-machine interaction platform, the main power module and the inertial measurement unit via wires.

[0013] In some embodiments, the lower surface of the spare compartment is provided with support legs evenly distributed, and the bottom end of the support legs is provided with a support plate.

[0014] The embodiments of the present invention have the following advantages due to the adoption of the above technical solutions: I. This invention uses a servo motor to drive an inertial mass block to rotate at high speed, and utilizes the centrifugal inertial force and the precession of a controlled gyroscope to generate lift and thrust, completely eliminating the dependence on air lifting surfaces. This enables the aircraft to work stably in non-atmospheric environments such as low pressure, vacuum, underwater, and sealed cabins, filling the gap in environmental adaptability of traditional aircraft.

[0015] Second, by eliminating the traditional rotor, tail rotor and complex mechanical transmission mechanism, the core power only requires a servo motor, rotating block, connecting rod and inertial mass block. This minimalist mechanical structure fundamentally eliminates the interference of anti-torque, greatly reduces the mechanical failure rate and vibration noise, facilitates maintenance and significantly extends the service life.

[0016] Third, this invention utilizes the inherent gyro-axis fixation of the high-speed rotating inertial mass block, providing the aircraft with a natural physical anti-disturbance foundation; at the same time, the inertial measurement unit collects attitude data in real time, and the main control unit uses a vector synthesis algorithm to form a closed-loop control by adjusting the speed difference, phase difference and tilt angle difference, thereby correcting the attitude in real time and resisting external disturbances, achieving extremely high hovering accuracy and load stability.

[0017] Fourth, this invention achieves independent vector synthesis of lift and horizontal thrust through differential, phase and synchronous control of four inertial power units. It can complete vertical take-off and landing, forward, backward and left and right translation and yaw turning without tilting the fuselage. It does not require a runway and is extremely suitable for the operation needs between urban buildings, indoors and narrow and confined spaces.

[0018] Fifth, this invention uses four inertial power units evenly distributed around the central axis at 90° to form a centrally symmetrical redundant layout. When a local unit fails, the remaining units can still maintain the flight attitude and return safely through vector reconstruction. In addition, the spare compartment is equipped with an emergency power module, redundant controllers and a parachute recovery system, thus constructing a complete safety link from power fault tolerance to system-level backup and finally parachute deployment protection.

[0019] VI. This invention reduces wind resistance by adopting a streamlined inverted disc shape and a circular arc transition around the perimeter of the aircraft. The payload compartment and spare compartment are made of carbon fiber composite materials to achieve extreme structural lightweighting. The inertial mass block is made of high-density alloy and is dynamically balanced to maximize the moment of inertia within a limited volume, effectively improving the thrust-to-weight ratio and payload capacity of the aircraft.

[0020] The above overview is for illustrative purposes only and is not intended to be limiting in any way. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features of the invention will become readily apparent from the accompanying drawings and the following detailed description. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a structural diagram of the present invention; Figure 2 This is a side sectional view of the present invention from a first perspective; Figure 3 This is a side sectional view of the second perspective of the present invention.

[0023] Reference numerals: 1. Power compartment; 2. Payload compartment; 3. Reserve compartment; 4. Support leg; 5. Support plate; 6. Inertial power unit; 7. Flight control unit; 8. Emergency power module; 9. Redundant controller; 10. Parachute recovery system; 60. Servo motor; 61. Rotating block; 62. Linkage rod; 63. Inertial mass block; 70. Human-machine interface platform; 71. Main control unit; 72. Main power module; 73. Inertial measurement unit. Detailed Implementation

[0024] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of the invention. Therefore, the drawings and description are considered to be exemplary in nature and not restrictive.

[0025] It is important to note that terms such as "first," "second," "symmetric," "array," "set in," and "set with" are used only to distinguish between descriptive and positional descriptions and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, features specified with terms such as "first" or "symmetric" may explicitly or implicitly include one or more of that feature; similarly, when the quantity of certain features is not limited by words such as "two" or "three," it should be noted that such features also explicitly or implicitly include one or more features. In this invention, unless otherwise explicitly specified and limited, terms such as "installation," "connection," and "fixation" should be interpreted broadly; for example, they can refer to a fixed connection, a detachable connection, or an integral molding; they can refer to a mechanical connection, a direct connection, a welding connection, or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the accompanying drawings and specific circumstances.

[0026] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0027] like Figures 1-3 As shown, this embodiment of the invention provides a vertical takeoff and landing (VTOL) payload aircraft based on the synthesis of gyro precession and inertial force, including a power cabin 1. A payload compartment 2 is provided on the upper surface of the power cabin 1, and a spare compartment 3 is provided on the lower surface of the power cabin 1. Four inertial power units 6 are symmetrically arranged inside the power cabin 1, forming a centrally symmetrical redundant layout. A flight control unit 7 is provided on the power cabin 1. The flight control unit 7 includes a human-machine interface platform 70, a main control unit 71, a main power module 72, and an inertial measurement unit 73. The inertial measurement unit 73 is located on the inner top wall of the power cabin 1, and the human-machine interface platform 70 is located on the upper surface of the power cabin 1. The main control unit 71 and the main power module 72 are both located on the inner wall of the human-machine interface platform 70. The main control unit 71 is electrically connected to the human-machine interface platform 70, the main power module 72, the inertial measurement unit 73, and the four inertial power units 6 via wires.

[0028] In this embodiment, specifically, the main control unit 71 uses the real-time attitude of the inertial measurement unit 73 as feedback and employs a vector synthesis algorithm to adjust the speed difference, phase difference, and tilt angle difference to achieve six-degree-of-freedom control.

[0029] In this embodiment, specifically, the inertial power unit 6 includes a servo motor 60, a rotating block 61, four connecting rods 62, and four inertial mass blocks 63. The servo motor 60 is disposed on the inner top wall of the power compartment 1, and the rotating block 61 is disposed on the output shaft of the servo motor 60. One end of the four connecting rods 62 is evenly hinged to the outer wall of the rotating block 61 through universal joints, and the four inertial mass blocks 63 are evenly disposed on the other end of the corresponding connecting rods 62. The tilt angle range of the connecting rods 62 is 25°-35°. The main control unit 71 is electrically connected to the servo motor 60 through wires. The preferred tilt angle of the connecting rods 62 is 30°.

[0030] In this embodiment, the universal joint is specifically a cross-type or ball-joint type.

[0031] In this embodiment, specifically, the combined shape of the power compartment 1, the load compartment 2, and the spare compartment 3 is a streamlined inverted disc shape, and the shapes of the power compartment 1, the load compartment 2, and the spare compartment 3 are transitioned by a peripheral arc. The load compartment 2 and the spare compartment 3 are made of carbon fiber composite material.

[0032] In this embodiment, specifically, the inertial mass block 63 is made of a high-density alloy, and the inertial mass block 63 is dynamically balanced.

[0033] In this embodiment, specifically, the servo motor 60 is a high-torque closed-loop servo motor that supports closed-loop control of speed, position, and torque.

[0034] In this embodiment, specifically, the payload compartment 2 is a panoramic transparent dome.

[0035] In this embodiment, specifically, the inner wall of the spare compartment 3 is provided with an emergency power module 8, a redundant controller 9, and a parachute recovery system 10. The main control unit 71 and the redundant controller 9 are electrically connected to the emergency power module 8, the parachute recovery system 10, the servo motor 60, the human-machine interaction platform 70, the main power module 72, and the inertial measurement unit 73 via wires.

[0036] In this embodiment, specifically, the lower surface of the spare compartment 3 is uniformly provided with support legs 4, and the bottom end of the support legs 4 is provided with a support plate 5.

[0037] In this embodiment, specifically, the four inertial power units 6 are evenly distributed around the central axis at 90° to form a symmetrical power layout, ensuring torque balance and redundancy.

[0038] In this embodiment, specifically, the inertial measurement unit 73 collects angular velocity, acceleration, and attitude angle in real time; The main control unit 71 outputs instructions according to the vector synthesis algorithm, thereby controlling and adjusting the speed, phase, and torque of the servo motors 60 on the four inertial power units 6 to achieve closed-loop control of lift and attitude.

[0039] When the present invention is in operation: relevant personnel input commands through the human-machine interaction platform 70, and the human-machine interaction platform 70 controls the servo motors 60 in the four inertial power units 6 to start through the main control unit 71. The emergency power module 8 and the main power module 72 are used to supply power to the redundant controller 9, the parachute recovery system 10, the servo motors 60, the human-machine interaction platform 70, the main control unit 71, the main power module 72, and the inertial measurement unit 73. The redundant controller 9 is used for self-protection when the main control unit 71 fails, and the parachute recovery system 10 is used to ensure safety protection when the equipment fails completely.

[0040] The output shaft of the servo motor 60 drives the rotating block 61 to rotate, the rotating block 61 drives the four connecting rods 62 to rotate, and the connecting rods 62 drive the corresponding inertial mass blocks 63 to rotate. This causes the servo motor 60 to drive the inertial mass blocks 63 to rotate at high speed around the axis, thereby generating centrifugal inertial force. The constraint force of the power cabin 1 and the gravity of the power cabin 1 form an external torque, causing the rotating inertial mass block 63 to produce controlled precession, thereby the power cabin 1 outputs a vertical component force.

[0041] The servo motors 60 on the four inertial power units 6 operate synchronously / differentially. The inertial force and the precession force vector are superimposed to form the total lift of the power cabin 1. The inertial measurement unit 73 and the main control unit 71 introduce the horizontal component through phase difference / speed difference to realize the forward, backward, left and right translation of the power cabin 1. The inertial measurement unit 73 and the main control unit 71 use closed-loop control to correct the attitude in real time, resist external disturbances, and achieve stable hovering and loaded flight.

[0042] The servo motors 60 on the four inertial power units 6 accelerate and decelerate synchronously. The total lift of the power cabin 1 is greater than / equal to / less than gravity, which is used to make the power cabin 1 rise, descend, or hover. The servo motors 60 on the front / rear and left / right inertial power units 6 generate a phase difference / speed difference, thereby causing the power compartment 1 to generate a horizontal thrust component. The servo motor 60 on the diagonal inertial power unit 6 forms a differential speed, generating a yaw torque to achieve turning in place.

[0043] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various variations or substitutions within the technical scope disclosed in the present invention, and these should all be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force, comprising a power cabin (1), characterized in that: The upper surface of the power compartment (1) is provided with a payload compartment (2), and the lower surface of the power compartment (1) is provided with a spare compartment (3). Four inertial power units (6) are symmetrically arranged inside the power compartment (1), forming a centrally symmetrical redundant layout. A flight control unit (7) is provided on the power compartment (1). The flight control unit (7) includes a human-machine interface platform (70), a main control unit (71), a main power module (72), and an inertial measurement unit (73). The inertial measurement unit (73) is disposed on the inner top wall of the power compartment (1), and the human-machine interaction platform (70) is disposed on the upper surface of the power compartment (1); The main control unit (71) and the main power module (72) are both located on the inner wall of the human-computer interaction platform (70); The main control unit (71) is electrically connected to the human-computer interaction platform (70), the main power module (72), the inertial measurement unit (73), and the four inertial power units (6) via wires.

2. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force as described in claim 1, characterized in that: The inertial power unit (6) includes a servo motor (60), a rotating block (61), four connecting rods (62), and four inertial mass blocks (63), wherein, The servo motor (60) is disposed on the inner top wall of the power compartment (1), and the rotating block (61) is disposed on the output shaft of the servo motor (60); One end of each of the four connecting rods (62) is evenly hinged to the outer wall of the rotating block (61) via a universal joint, and the four inertial mass blocks (63) are evenly disposed at the other end of the corresponding connecting rods (62); The tilt angle of the connecting rod (62) is 25°-35°, and the main control unit (71) and the servo motor (60) are electrically connected by wires.

3. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force according to claim 1, characterized in that: The combined shape of the power compartment (1), the load compartment (2) and the spare compartment (3) is a streamlined inverted disc shape, and the shapes of the power compartment (1), the load compartment (2) and the spare compartment (3) are transitioned by a circular arc around the perimeter. The load compartment (2) and the spare compartment (3) are made of carbon fiber composite material.

4. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force according to claim 2, characterized in that: The inertial mass block (63) is made of a high-density alloy and is dynamically balanced.

5. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force according to claim 2, characterized in that: The servo motor (60) is a high-torque closed-loop servo motor that supports closed-loop control of speed, position and torque.

6. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force according to claim 1, characterized in that: The payload compartment (2) is a panoramic transparent dome.

7. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force according to claim 2, characterized in that: The inner wall of the spare compartment (3) is provided with an emergency power module (8), a redundant controller (9) and a parachute recovery system (10). The main control unit (71) and the redundant controller (9) are electrically connected to the emergency power module (8), the parachute recovery system (10), the servo motor (60), the human-machine interaction platform (70), the main power module (72) and the inertial measurement unit (73) via wires.

8. The vertical takeoff and landing heavy-duty aircraft based on the synthesis of gyro precession and inertial force according to claim 1, characterized in that: The lower surface of the spare compartment (3) is uniformly provided with support legs (4), and the bottom end of the support legs (4) is provided with a support plate (5).

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