Unmanned transport aircraft with modular fuselage and design method thereof

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned transport aircraft with a modular fuselage and a design method thereof. The unmanned transport aircraft has wings on both sides of the fuselage, an engine nacelle mounted on each wing, tail support assemblies symmetrically arranged on both sides of the fuselage, each tail support assembly being respectively provided with a vertical tail, and a horizontal tail being arranged between the two vertical tails. The unmanned transport aircraft adopts a layout of two turboprop engines, a double tail strut, and a high horizontal tail, which meets the requirements for quick ground loading and unloading of cargo for the unmanned transport aircraft. Furthermore, when designing the horizontal tail of the unmanned transport aircraft, the aerodynamic characteristics of the wings and the axial position of the horizontal tail are taken into consideration to reasonably determine the installation height of the horizontal tail, ensuring that the rear cargo door at the rear of the fuselage leaves sufficient space for loading while avoiding the problem of reduced elevator control efficiency of the horizontal tail due to downwash generated by the wings, thereby ensuring the stability and maneuverability of the unmanned transport aircraft during takeoff and landing.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles and discloses an unmanned transport aircraft adopting a modular fuselage and a design method thereof. Background Art

[0002] Air transport is a high-speed, safe and convenient mode of transportation. Traditional air transport makes extensive use of various types of manned aircraft. With the continuous advancement of aviation technology, unmanned aircraft has become the future development trend of aircraft. In recent years, countries around the world have explored converting manned transport aircraft into unmanned transport aircraft to meet the future needs of the air transport market. At the same time, they are also actively exploring the development of new unmanned transport aircraft.

[0003] In order to facilitate the loading and unloading of cargo, unmanned transport aircraft use high horizontal tails. When the air flows over the wings of the aircraft, it will generate downwash. When the downwash flows through the horizontal tail, it will have a very large impact on the horizontal tail, which may lead to a decrease in the elevator control efficiency of the horizontal tail. Therefore, the height of the horizontal tail of the unmanned transport aircraft needs to be reasonably set. Summary of the Invention

[0004] The purpose of the present invention is to provide an unmanned transport aircraft with a modular fuselage and a design method thereof, which can ensure that the rear cargo door at the tail of the fuselage leaves sufficient space for loading, while avoiding the problem of reduced horizontal tail elevator control efficiency due to the downwash airflow generated by the wing, thereby ensuring the stability and maneuverability of the unmanned transport aircraft during takeoff and landing.

[0005] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0006] A method for designing an unmanned transport aircraft using a modular fuselage, the unmanned transport aircraft comprising a fuselage and landing gear, wings being provided on either side of the fuselage, an engine nacelle being mounted on each wing, and a propeller being mounted at the front end of each engine nacelle; tail support assemblies being symmetrically provided on either side of the fuselage, each tail support assembly being respectively provided with a vertical tail, and a horizontal tail being provided between two vertical tails; the method for designing an unmanned transport aircraft comprising:

[0007] Analyze and obtain the lift line slope of the wing based on the design size parameters and design Mach number of the wing of the unmanned transport aircraft;

[0008] The vertical height of the horizontal tail relative to the wing chord plane is obtained by analysis based on the design size parameters of the wing, the slope of the lift line, the design axial distance of the horizontal tail relative to the wing, and the downwash angle value of the downwash airflow generated when the airflow flows over the wing.

[0009] Furthermore, the lift line slope C of the wing Lαaccording to The results are obtained by analysis, where K is the efficiency factor of the wing, and the value range of K is 0.8 to 1.0; AR is the aspect ratio of the wing, b is the span of the wing, S is the area of ​​the wing, M is the flight Mach number, λ 1 / 2 is the 1 / 2 chord sweep angle of the wing.

[0010] Furthermore, the vertical height of the horizontal tail relative to the wing chord plane is based on The analysis results show that z t is the vertical height of the horizontal tail relative to the chord plane of the wing, ε is the downwash angle of the downwash airflow generated when the airflow flows over the wing, α is the wing angle of attack, l t is the designed axial distance between the horizontal tail and the wing, k1 and k2 are coefficients, k1 ranges from 0.3 to 0.5, and k2 ranges from 0.1 to 0.3.

[0011] To achieve the above technical effects, the present invention further provides an unmanned transport aircraft with a modular fuselage, comprising:

[0012] A fuselage, wherein a cabin is provided in the fuselage, and the cabin of the fuselage is used to place transported items;

[0013] Wings, the wings are mounted on both sides of the fuselage, an engine nacelle is mounted on each wing, and a propeller is mounted at the front end of each engine nacelle;

[0014] Tail support assembly, there are two tail support assemblies, the two tail support assemblies are respectively arranged on both sides of the fuselage, and each tail support assembly is respectively provided with a vertical tail;

[0015] a horizontal tail, the horizontal tail being arranged between the two vertical tails, the vertical height of the horizontal tail relative to the wing chord plane being obtained by analyzing the unmanned transport aircraft design method according to any one of claims 1 to 3;

[0016] The landing gear is installed at the bottom of the engine compartment.

[0017] Furthermore, the wings on each side of the fuselage are fixed to the fuselage by bolts.

[0018] Furthermore, the trailing edge of each wing is movably provided with deflectable flaps and ailerons.

[0019] Furthermore, the landing gear includes two main landing gears and two front landing gears, and the two main landing gears and the two front landing gears are all installed on the engine compartment; the engine compartment is provided with a landing gear bay at the installation position of each front landing gear and each main landing gear; each front landing gear is retracted rearward into the landing gear bay corresponding to the engine compartment, and each main landing gear is retracted forward into the landing gear bay corresponding to the engine compartment.

[0020] Furthermore, a rudder is movably provided at the trailing edge of each vertical tail, and an elevator is symmetrically provided at the trailing edge of each horizontal tail.

[0021] Furthermore, a flip-up nose is provided at the front end of the fuselage, the top edge of the flip-up nose is movably connected to the front end position of the middle part of the fuselage through a hinge, and the bottom or side of the flip-up nose is fixedly connected to the fuselage through a limit locking mechanism; the tail of the fuselage is provided with a rolling-up rear cargo door.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. The present invention adopts two turboprop engines, twin tail struts, and a high horizontal tail layout to meet the requirements of quick ground loading and unloading of cargo by unmanned transport aircraft.

[0024] 2. When designing the horizontal tail of the unmanned transport aircraft of the present invention, the aerodynamic characteristics of the wing and the axial position of the horizontal tail are taken into consideration to reasonably determine the installation height of the horizontal tail. This ensures that the rear cargo door at the rear of the fuselage leaves sufficient space for loading, while avoiding the problem of reduced elevator control efficiency of the horizontal tail due to the downwash airflow generated by the wing, thereby ensuring the stability and maneuverability of the unmanned transport aircraft during takeoff and landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 Schematic diagram of the structure of an unmanned transport aircraft using a modular fuselage in an embodiment;

[0026] Figure 2 Schematic diagram of the installation structure of the wing and the fuselage in the embodiment;

[0027] Figure 3 Schematic diagram of the structure of the rear cargo door of the fuselage in the embodiment;

[0028] Among them, 1. Fuselage; 101. Nose; 102. Rear cargo door; 2. Wings; 201. Flaps; 202. Ailerons; 3. Engine compartment; 4. Propeller; 5. Tail support assembly; 6. Vertical tail; 601. Rudder; 7. Horizontal tail; 701. Elevator; 8. Bolts; 9. Main landing gear; 10. Front landing gear. DETAILED DESCRIPTION

[0029] The present invention will be described in further detail below with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the present invention to the following embodiments, as all technologies implemented based on the present invention fall within the scope of the present invention.

[0030] Example

[0031] See also Figure 1-Figure 3 A method for designing an unmanned transport aircraft using a modular fuselage, the unmanned transport aircraft comprising a fuselage 1 and landing gear, wings 2 being provided on either side of the fuselage 1, an engine nacelle 3 being mounted on each wing 2, and a propeller 4 being mounted at the front end of each engine nacelle 3; tail support assemblies 5 being symmetrically provided on either side of the fuselage 1, each tail support assembly 5 being provided with a vertical tail 6, and a horizontal tail 7 being provided between two vertical tails 6; the method for designing an unmanned transport aircraft comprising:

[0032] Analyze and obtain the lift line slope of the wing 2 according to the design size parameters and design Mach number of the unmanned transport aircraft wing 2;

[0033] The vertical height of the horizontal tail 7 relative to the chord plane of the wing 2 is obtained by analysis based on the design size parameters of the wing 2, the lift line slope, the design axial distance of the horizontal tail 7 relative to the wing 2, and the downwash angle value of the downwash airflow generated when the airflow flows through the wing 2.

[0034] In this embodiment, the unmanned transport aircraft can adopt two turboprop 4 engines, double tail struts, and a high horizontal tail layout to meet the requirements of quick ground loading and unloading of cargo for the unmanned transport aircraft; and when designing the horizontal tail 7 of the unmanned transport aircraft, the aerodynamic characteristics of the wing 2 and the axial position of the horizontal tail 7 are taken into consideration to reasonably determine the installation height of the horizontal tail 7 (the vertical height of the horizontal tail 7 relative to the chord plane of the wing 2), ensuring that the rear cargo door 102 at the tail of the fuselage 1 leaves sufficient space for loading, while avoiding the problem of reduced control efficiency of the elevator 701 of the horizontal tail 7 due to the downwash airflow generated by the wing 2, thereby ensuring the stability and maneuverability of the unmanned transport aircraft during takeoff and landing.

[0035] In this embodiment, the lift line slope C of the wing 2 is Lα according to The results are obtained by analysis, where K is the efficiency factor of the airfoil of wing 2, and the value range of K is 0.8 to 1.0; AR is the aspect ratio of wing 2, b is the span of wing 2, S is the area of ​​wing 2, M is the flight Mach number. The unmanned transport aircraft in this embodiment is a subsonic aircraft. M is less than 1, and λ 1 / 2 On this basis, the vertical height of the horizontal tail 7 relative to the chord plane of the wing 2 is calculated according to The analysis results show that z t is the vertical height of the horizontal tail 7 relative to the chord plane of the wing 2, ε is the downwash angle of the downwash airflow generated when the airflow flows through the wing 2 at the horizontal tail, α is the wing angle of attack, l t is the designed axial distance between the horizontal tail 7 and the wing 2, k1 and k2 are coefficients, respectively. k1 and k2 can be determined through wind tunnel testing or numerical simulation. Based on relevant engineering experience, the typical value range of k1 is 0.3-0.5, and the typical value range of k2 is 0.1-0.3.

[0036] Based on the same inventive concept, this embodiment also provides an unmanned transport aircraft using a modular fuselage 1, comprising:

[0037] A fuselage 1, wherein a cabin is provided in the fuselage 1, and the cabin of the fuselage 1 is used to place transported items;

[0038] Wings 2, the wings 2 are mounted on both sides of the fuselage 1, an engine nacelle 3 is mounted under each wing 2, and a propeller 4 is mounted at the front end of each engine nacelle 3;

[0039] Tail support assembly 5, there are two tail support assemblies 5, the two tail support assemblies 5 are respectively arranged on both sides of the fuselage 1, and each tail support assembly 5 is respectively provided with a vertical tail 6;

[0040] A horizontal tail 7, the horizontal tail 7 being disposed between the two vertical tails 6, and the vertical height of the horizontal tail 7 relative to the chord plane of the wing 2 being obtained by analyzing the unmanned transport aircraft design method;

[0041] The landing gear is installed at the bottom of the engine compartment 3.

[0042] In this embodiment, the wings 2 on each side of the fuselage 1 are fixed to the fuselage 1 by bolts 8. The fuselage 1 is mechanically connected to the front and rear beams of the wings 2 via four quick-release joints, and standardized interfaces such as electrical and communication interfaces are provided. This meets the requirements for the interchangeability of the fuselage 1, improves its adaptability to different missions, and also ensures the structural integrity of the fuselage 1.

[0043] In this embodiment, the trailing edge of each wing 2 is movably provided with deflectable flaps 201 and ailerons 202. Both flaps 201 and ailerons 202 are connected to the flight control system via a sophisticated mechanical transmission system. The flaps 201 adjust the lift coefficient of the wing 2, providing additional lift during takeoff and landing, further enhancing the aircraft's stability and safety. The ailerons 202 control the aircraft's roll motion. By differentially deflecting the left and right ailerons 202, roll maneuvers are achieved, meeting the requirements for the unmanned transport aircraft in various complex environments.

[0044] In this embodiment, the landing gear includes two main landing gears 9 and two nose landing gears 10. Both the two main landing gears 9 and the two nose landing gears 10 are mounted on the engine nacelle 3. The engine nacelle 3 is provided with a landing gear bay at the mounting location of each nose landing gear 10 and each main landing gear 9. Each nose landing gear 10 retracts rearward into the corresponding landing gear bay in the engine nacelle 3, while each main landing gear 9 retracts forward into the corresponding landing gear bay in the engine nacelle 3. When the aircraft is in flight, the landing gear is fully retracted into the landing gear bay, reducing air resistance and improving flight efficiency.

[0045] In this embodiment, a rudder 601 is movably provided at the trailing edge of each vertical stabilizer 6, and an elevator 701 is symmetrically provided at the trailing edge of each horizontal stabilizer 7. The rudder 601 is used to control the aircraft's yaw motion, adjusting the aircraft's heading by deflecting left and right to ensure that the aircraft can fly stably along the predetermined route during flight. The elevator 701 is responsible for controlling the aircraft's pitch motion, adjusting the aircraft's flight attitude by deflecting up and down to achieve climb, descent, or maintain level flight. The coordinated operation of the ailerons 202, rudder 601, and elevator 701 enables the unmanned transport aircraft to flexibly adjust its flight attitude in three-dimensional space, meeting the requirements of complex flight missions.

[0046] In this embodiment, the front end of the fuselage 1 is equipped with a tilting nose 101. The top edge of the tilting nose 101 is hingedly connected to the front end of the middle portion of the fuselage 1. The bottom or side of the tilting nose 101 is fixedly connected to the fuselage 1 via a limit locking mechanism. The rear end of the fuselage 1 is equipped with a rolling-up rear cargo door 102. This allows for the loading and unloading of large air containers, facilitating efficient loading and unloading. Furthermore, the design of the rolling-up rear cargo door 102 enables aerial delivery of cargo, facilitating the rapid supply of supplies to border crossings or islands without runways.

[0047] The above are only preferred embodiments of the present invention and are 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 scope of protection of the present invention.

Claims

1. A design method for an unmanned transport aircraft using a modular fuselage, the unmanned transport aircraft comprising a fuselage and landing gear, wings being provided on either side of the fuselage, an engine nacelle being mounted on each wing, and a propeller being mounted at the front end of each engine nacelle; tail support assemblies being symmetrically provided on either side of the fuselage, each tail support assembly being provided with a vertical tail, and a horizontal tail being provided between two vertical tails; characterized in that: The unmanned transport aircraft design method includes: Analyze and obtain the lift line slope of the wing based on the design size parameters and design Mach number of the wing of the unmanned transport aircraft; The vertical height of the horizontal tail relative to the wing chord plane is obtained by analysis based on the design size parameters of the wing, the slope of the lift line, the design axial distance of the horizontal tail relative to the wing, and the downwash angle value of the downwash airflow generated when the airflow flows over the wing.

2. The unmanned transport aircraft design method according to claim 1, characterized in that: The slope of the wing's lift line, C Lα according to The results are obtained by analysis, where K is the efficiency factor of the wing, and the value range of K is 0.8 to 1.0; AR is the aspect ratio of the wing, b is the span of the wing, S is the area of ​​the wing, M is the flight Mach number, λ 1 / 2 is the 1 / 2 chord sweep angle of the wing.

3. The unmanned transport aircraft design method according to claim 2, characterized in that: The vertical height of the horizontal tail relative to the wing chord plane is based on The analysis results show that z t is the vertical height of the horizontal tail relative to the chord plane of the wing, ε is the downwash angle of the downwash airflow generated when the airflow flows over the wing, α is the wing angle of attack, l t is the designed axial distance between the horizontal tail and the wing, k1 and k2 are coefficients, k1 ranges from 0.3 to 0.5, and k2 ranges from 0.1 to 0.

3.

4. An unmanned transport aircraft with a modular fuselage, characterized in that: include: A fuselage, wherein a cabin is provided in the fuselage, and the cabin of the fuselage is used to place transported items; Wings, the wings are mounted on both sides of the fuselage, an engine nacelle is mounted on each wing, and a propeller is mounted at the front end of each engine nacelle; Tail support assembly, there are two tail support assemblies, the two tail support assemblies are respectively arranged on both sides of the fuselage, and each tail support assembly is respectively provided with a vertical tail; a horizontal tail, the horizontal tail being arranged between the two vertical tails, the vertical height of the horizontal tail relative to the wing chord plane being obtained by analyzing the unmanned transport aircraft design method according to any one of claims 1 to 3; The landing gear is installed at the bottom of the engine compartment.

5. The unmanned transport aircraft according to claim 4, characterized in that: The wings on each side of the fuselage are fixed to the fuselage by bolts.

6. The unmanned transport aircraft according to claim 5, characterized in that: The trailing edge of each wing is movably provided with deflectable flaps and ailerons.

7. The unmanned transport aircraft according to claim 4, characterized in that: The landing gear includes two main landing gears and two front landing gears, and the two main landing gears and the two front landing gears are all installed on the engine compartment; the engine compartment is provided with a landing gear bay at the installation position of each front landing gear and each main landing gear; each front landing gear is retracted rearward into the landing gear bay corresponding to the engine compartment, and each main landing gear is retracted forward into the landing gear bay corresponding to the engine compartment.

8. The unmanned transport aircraft according to claim 4, characterized in that: A rudder is movably provided at the trailing edge of each vertical tail, and an elevator is symmetrically provided at the trailing edge of each horizontal tail.

9. The unmanned transport aircraft according to claim 4, characterized in that: The front end of the fuselage is provided with an upward-flipping nose, the top edge of the upward-flipping nose is movably connected to the front end position of the middle part of the fuselage through a hinge, and the bottom or side of the upward-flipping nose is fixedly connected to the fuselage through a limit locking mechanism; the tail of the fuselage is provided with a rolling-up rear cargo door.

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