A soft-hard coupling variable characteristic intelligent aircraft

Abstract

The invention discloses a soft-hard coupling variable characteristic intelligent aircraft, the aircraft comprises a head, a cabin, a differential bionic horizontal tail, a foldable deformable wing and a bionic vertical tail with a rudder surface; the front part of the cabin is provided with a tower wing shaft assembly and a shaft, which is used to drive a pair of foldable deformable wings on the left and right sides; the middle part of the cabin is provided with a flight controller, and a soft-hard coupling system of aircraft target characteristics is provided inside, which is used to automatically control the sweep angle of the foldable deformable wing and the distributed characteristic spectrum transmitter array according to the flight conditions, so as to simulate the radar characteristics of different target characteristics; the foldable deformable wing is composed of two left and right wings, which are unfolded at a maximum of 90 degrees on one side and fully retracted into the cabin at a minimum of 0 degrees; the foldable deformable wing is provided with a distributed characteristic spectrum transmitter array inside, which is used to customize the simulation of radar characteristics of different target characteristics. The invention can perform adaptive soft-hard coupling deformation control and simulate the radar characteristics of multiple intelligent aircraft and aircraft.

Description

Technical Field

[0001] The invention relates to a software-hardware coupled variable-feature intelligent aircraft system, belonging to the technical field of aviation aircraft. Background Art

[0002] At present, most intelligent aircraft systems are in a single fixed form, and their main function is to fly or glide on a fixed preset trajectory through rocket boosters or launchers. However, with the development of aircraft design concepts and the increase in actual needs, people have developed intelligent aircraft with deformable wings to achieve some new functions in order to make intelligent aircraft have high autonomy, high maneuverability, strong stealth, variable characteristics, and reconnaissance and strike functions to solve these problems. However, for intelligent aircraft with a new layout that can cruise and hover across speed ranges, how to flexibly camouflage across speed ranges and airspace to avoid detection by radar, satellites or fighters is an urgent problem to be solved. Summary of the invention

[0003] In order to solve the deficiencies of the prior art, an object of the present invention is to provide an intelligent aircraft with variable characteristics suitable for soft-hard coupling.

[0004] The present invention is achieved through the following technical solutions:

[0005] A soft-hard coupling variable characteristic intelligent aircraft, the aircraft comprises a head, a cabin, a differential bionic horizontal tail, a foldable deformable wing and a bionic vertical tail with rudder surfaces; a tower wing shaft assembly and a shaft are provided at the front of the cabin for driving a pair of foldable deformable wings on the left and right sides to extend and retract; a flight controller is provided in the middle of the cabin, and a soft-hard coupling system of aircraft target characteristics is provided inside, which is used to automatically control the sweep angle of the foldable deformable wing and a distributed characteristic spectrum transmitter array according to flight conditions, so as to simulate radar characteristics of different target characteristics; the foldable deformable wing consists of two left and right wings, which can be unfolded to a maximum of 90 degrees on one side and fully retracted to enter the cabin to a minimum of 0 degrees; a distributed characteristic spectrum transmitter array is provided inside the foldable deformable wing for customizing the simulation of radar characteristics of different target characteristics; an even number of engine nozzles are symmetrically embedded at the end of the cabin as the power source of the aircraft; the tail comprises a differential bionic horizontal tail and a bionic vertical tail with rudder surfaces, which are respectively used to control the pitch, roll and heading attitude of the aircraft during flight.

[0006] The foldable and deformable wings are coaxially stacked in a tower-like manner, and are independently driven by 8 pairs of left and right foldable and deformable wings of the flight controller. The variable angle range of one side is 0-90 degrees, which can realize the aerodynamic requirements across the speed range while achieving the change of target characteristics; and the wings on both sides can be completely overlapped and stored inside the aircraft. The length of one side of the wing is 0.6~0.98 times the diameter of the aircraft, and the entire wing surface is painted with bionic or camouflage.

[0007] The characteristic spectrum emission sources are arranged in columns inside the wing, and the data and power supply are connected in parallel with each other by wires. The type and strength of the active spectrum characteristic signal can be independently changed by the flight control system.

[0008] The aircraft target characteristic soft-hard coupling system is strongly coupled with the aircraft's foldable and deformable wing sweep angle, flight altitude, and speed. According to a preset aerodynamic-flight state-spectrum feature mapping library, when the flight conditions meet the response aerodynamic and flight state conditions, the corresponding spectrum features are automatically switched, thereby realizing full-process intelligent aircraft spectrum feature adaptive changes and flight control.

[0009] The distributed characteristic spectrum transmitter array is used to customize the simulation of radar characteristics of different target characteristics, including strong RCS reflection, fixed-wing type target characteristics (wing fully extended), fighter type target characteristics (wing half extended), delta wing type target characteristics (wing greatly retracted) or missile-shaped target characteristics (wing fully retracted).

[0010] The tower wing shaft assembly includes an upper section, a middle piece, and a lower section, which are respectively an upper section with a surface bearing with a flat ball, a middle piece with double-sided ball grooves, and a lower section with a flat ball bearing. The upper section is coaxial with the circular hole at the root of the foldable and deformable wing, and the middle piece is engaged with the flat ball surfaces of the upper and lower sections through grooves on both sides, wherein the upper and lower sections are respectively connected to the foldable and deformable wing by screws.

[0011] Beneficial effects of the present invention:

[0012] First, by directly using ducted or jet engine jet as the power source of intelligent aircraft, a continuous and stable power source can be provided for cross-domain advanced aircraft. Secondly, by combining the tower-type overlapping deformable wings with the embedded customizable characteristic spectrum signal generator array inside the wing, the physical change of the aerodynamic characteristics of the intelligent aircraft to the aerodynamic characteristics of the glider aircraft and the coupling of the software-defined characteristic spectrum signal changes can be achieved, which can meet the extreme needs of aerodynamics and stealth during cross-domain flight and improve the camouflage performance and detection difficulty of the intelligent aircraft. In addition, the design also simplifies the landing structure of the entire aircraft and achieves launch through catapult or rocket boost. There is no need to carry additional fixed landing gear and other mechanisms, which reduces the complexity of the structure and the weight of the entire aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a structural schematic diagram of a soft-hard coupled variable-feature intelligent aircraft.

[0014] Figure 2 It is a three-dimensional structural schematic diagram of the present invention.

[0015] Figure 3 It is a structural schematic diagram of a tower wing shaft assembly and a foldable and deformable wing.

[0016] Figure 4 It is a structural schematic diagram of a tower wing shaft assembly.

[0017] Figure 5 It is a schematic diagram of the soft-hard coupling adaptive deformation process of the soft-hard coupling variable characteristic intelligent aircraft in the low-speed cruise-subsonic cruise-supersonic penetration flight mode.

[0018] Figure 6 It is a schematic diagram of the algorithm flow of the aircraft's soft-hard coupling variable characteristic system inside the flight controller.

[0019] Figure 1 In the figure, there are head 1, cabin 2, differential bionic horizontal tail 3, tower wing shaft assembly 4, upper section of surface bearing with flat ball 4a, middle piece of double-sided ball groove 4b, lower section of flat ball bearing 4c, flat bearing 4d, circular hole at wing root 5, foldable deformable wing 6, distributed characteristic spectrum transmitter array 7, flight controller 8, engine nozzle 9, bionic vertical tail with rudder surface 10, and double-sided slots 11 of cabin. DETAILED DESCRIPTION

[0020] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] like Figure 1 As shown, a soft-hard coupling variable characteristic intelligent aircraft includes a head 1, a cabin 2, a differential bionic horizontal tail 3, foldable and deformable wings 6 and a bionic vertical tail 10 with a control surface.

[0022] A tower-type wing shaft assembly 4 and a shaft 5 are provided at the front of the cabin 2, which are used to drive a pair of foldable and deformable wings 6 on the left and right sides for extension and retraction; a flight controller 8 is provided in the middle of the cabin 2, and an aircraft target characteristic soft-hard coupling system is provided inside, which is used to automatically control the foldable and deformable wing sweep angle and the distributed characteristic spectrum transmitter array 7 according to the flight conditions, thereby simulating the radar characteristics of different target characteristics.

[0023] The foldable and deformable wing 6 consists of two left and right wings, which can be unfolded to a maximum of 90 degrees on one side and fully retracted to a minimum of 0 degrees to enter the interior of the cabin 2;

[0024] An even number of engine nozzles 9 are symmetrically embedded at the end of the cabin 2 to serve as a power source for the aircraft.

[0025] The tail portion includes a differential bionic horizontal tail 3 and a bionic vertical tail with rudder surfaces 10, which are respectively used to control the pitch, roll and heading attitude of the aircraft during flight.

[0026] The foldable and deformable wings 6 are coaxially stacked in a tower-like manner, and the flight controller 8 independently drives the left and right foldable and deformable wings 6. The variable angle range of one side is 0-90 degrees, which can achieve the aerodynamic requirements across the speed range while realizing the change of target characteristics; and the wings on both sides can be completely overlapped and stored inside the aircraft, the length of one side of the wing surface is 0.6~0.98 times the diameter of the aircraft, and the entire wing surface is painted with bionic or camouflage.

[0027] The characteristic spectrum transmitters 7 are arranged in a row inside the wing 6, and the data and power supply are connected in parallel with each other by wires. The type and strength of the active spectrum characteristic signal can be independently changed by the flight control system.

[0028] The aircraft target characteristic soft-hard coupling system is strongly coupled with the sweep angle, flight altitude and speed of the aircraft's foldable and deformable wing 6. According to the preset "aerodynamic-flight state-spectrum characteristic" mapping library, the corresponding aerodynamic sweep angle and spectrum characteristic type are automatically set according to the flight condition requirements, thereby realizing the full-process intelligent aircraft aerodynamic-spectrum characteristic coupling adaptive change.

[0029] The distributed characteristic spectrum transmitter array 7 is used to customize the simulation of radar characteristics of different target characteristics, including strong RCS reflection, fixed-wing type target characteristics (wing fully extended), fighter type target characteristics (wing half extended), delta wing type target characteristics (wing greatly retracted) or missile-shaped target characteristics (wing fully retracted).

[0030] like Figure 2 As shown, the power system of the variable characteristic intelligent aircraft adopts a four-engine arrangement with side air intake and tail air outlet. High-temperature combustion gas is ejected through an array nozzle 9, and pitch control and roll control are achieved through differential and linkage flow guidance on the left and right sides of the differential bionic horizontal tail 3, and heading control is performed through the bionic vertical tail 10 with rudder surfaces;

[0031] like Figure 3 As shown, the foldable and deformable wings 6 of the variable-feature intelligent aircraft can be retracted into the cabin 2 through the slots 11 on both sides of the cabin. The left notch is used to retract the left variable wing, and the right notch is used to retract the right variable wing, and the left and right notches are staggered up and down.

[0032] like Figure 4 As shown, the tower wing shaft assembly 4 includes an upper section, a middle piece, and a lower section, which are respectively an upper section 4a with a flat ball bearing, a middle piece 4b with double-sided ball grooves, and a lower section 4c with a flat ball bearing, which are coaxial with the circular hole at the root of the foldable deformable wing, and the middle piece 4b is engaged with the flat ball surfaces of the upper and lower sections through grooves on both sides, wherein the upper and lower sections are respectively connected to the foldable deformable wing by screws.

[0033] like Figure 5 As shown, the intelligent aircraft with soft-hard coupling variable spectrum characteristics adopts a tower shaft assembly 4 fixed to the wing driven by a servo to perform "low speed I-high speed II-ultra-high speed III" continuous deformation, wherein the deformations on both sides are controlled by independent servos, that is, differential sweep angles are supported for attitude control without rudder surfaces.

[0034] like Figure 6 As shown in the figure, the coupling control of the soft-hard coupled variable characteristic intelligent aircraft adopts the process of sequence preset-online sequence modification-sequence output, that is, after the intelligent aircraft mission starts, the characteristic parameter mapping of the wing sweep angle and the spectrum characteristic transmitting array at different altitudes and speeds is first preset at the ground station, and then the parameter mapping sequence file is loaded into the intelligent aircraft flight controller. By default, the intelligent aircraft outputs characteristics according to the preset sequence during the flight, and then avoids or interferes with local radars through different scattering characteristics; in addition, when the scattering characteristics of the intelligent aircraft in a certain area need to be temporarily changed during the flight, it only needs to be modified at the ground station and updated and uploaded to the intelligent aircraft through the encrypted wireless data communication link. The flight control on the intelligent aircraft side outputs the corresponding spectrum characteristics of the intelligent aircraft in sequence until the mission is terminated.

[0035] The embodiments described above can be further combined or replaced, and the embodiments are only descriptions of preferred embodiments of the present invention, and do not limit the concept and scope of the present invention. Without departing from the design concept of the present invention, various changes and improvements made by ordinary technicians in this field to the technical solution of the present invention belong to the protection scope of the present invention. The protection scope of the present invention is given by the attached claims and any equivalents thereof.

Claims

1. A soft-hard coupling variable characteristic intelligent aircraft, characterized by: The aircraft includes a head, a cabin, a differential bionic horizontal tail, foldable and deformable wings, and a bionic vertical tail with a rudder surface; The front of the cabin is equipped with a tower-type wing shaft assembly and a shaft for driving a pair of foldable and deformable wings on the left and right sides; The flight controller is located in the middle of the cabin, and the aircraft target characteristic soft-hard coupling system is installed inside, which is used to automatically control the sweep angle of the foldable and deformable wings and the distributed characteristic spectrum transmitter array according to the flight conditions, thereby simulating the radar characteristics of different target characteristics; The foldable and deformable wing consists of two wings, one on each side, which can be unfolded to a maximum of 90 degrees and fully retracted to a minimum of 0 degrees to enter the cabin. The foldable and deformable wing is equipped with a distributed characteristic spectrum transmitter array to customize the radar characteristics of different target characteristics; An even number of engine nozzles are symmetrically embedded at the end of the cabin to serve as the power source of the aircraft; The tail includes a bionic differential horizontal tail and a bionic vertical tail with rudder surfaces, which are used to control the pitch and heading attitude of the aircraft during flight.

2. A soft-hard coupling variable characteristic intelligent aircraft according to claim 1, characterized in that: The foldable and deformable wings are stacked in a coaxial tower, and the flight controller independently drives the left and right foldable and deformable wings. The variable angle range of one side is 0-90 degrees, and the wings on both sides can be completely overlapped and stored inside the aircraft. The length of one side of the wing is 0.6~0.98 times the diameter of the aircraft, and the entire wing surface is painted with bionic or camouflage.

3. A soft-hard coupling variable characteristic intelligent aircraft according to claim 1, characterized in that: The characteristic spectrum transmitters are arranged in rows inside the wing, and the data and power supply are connected in parallel with each other by wires. The type and strength of the active spectrum characteristic signal can be independently changed by the flight control system.

4. A soft-hard coupling variable characteristic intelligent aircraft according to claim 1, characterized in that: The aircraft target characteristic soft-hard coupling system is strongly coupled with the aircraft's foldable and deformable wing sweep angle, flight altitude, and speed. According to a preset aerodynamic-flight state-spectrum feature mapping library, when the flight conditions meet the response aerodynamic and flight state conditions, the corresponding spectrum features are automatically switched, thereby realizing full-process intelligent aircraft spectrum feature adaptive changes and flight control.

5. The soft-hard coupling variable characteristic intelligent aircraft according to claim 1, characterized in that: The distributed characteristic spectrum transmitter array is used to customize the simulation of radar characteristics of different target characteristics, including strong RCS reflection, fixed-wing type target characteristics, fighter type target characteristics, delta-wing type target characteristics or missile-shaped target characteristics.

6. The soft-hard coupling variable characteristic intelligent aircraft according to claim 1, characterized in that: The tower wing shaft assembly includes an upper section, a middle piece, and a lower section, which are respectively an upper section with a surface bearing with a flat ball, a middle piece with double-sided ball grooves, and a lower section with a flat ball bearing. The upper section is coaxial with the circular hole at the root of the foldable and deformable wing, and the middle piece is engaged with the flat ball surfaces of the upper and lower sections through grooves on both sides, wherein the upper and lower sections are respectively connected to the foldable and deformable wing by screws.

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