Unmanned transport plane adopting modularized plane body and design method of unmanned transport plane

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle with a modularized fuselage and a design method thereof.The two sides of the fuselage of the unmanned aerial vehicle are provided with wings, each wing is provided with an engine compartment, and the two sides of the fuselage are further symmetrically provided with empennage supporting assemblies; each empennage supporting assembly is provided with a vertical empennage, and a horizontal empennage is arranged between the two vertical empennages. The layout form of two turboprop engines, double tail booms and a high horizontal tail is adopted, and the requirement for fast loading and unloading goods on the ground of the unmanned transport plane is met; when the horizontal tail of the unmanned transport plane is designed, the aerodynamic characteristics of the wings and the axial position of the horizontal tail are considered, so that the installation height of the horizontal tail is reasonably determined, and it is ensured that a rear cargo hold door at the tail of the plane body leaves sufficient space for loading; the problem that the control efficiency of the horizontal tail elevator is reduced due to downwash airflow generated by the wings is avoided, and the stability and maneuverability of the unmanned transport plane during takeoff and landing are guaranteed.

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] Unmanned transport aircraft use high horizontal tails for the convenience of loading and unloading of cargo. When air flows over the wings of the aircraft, downwash will be generated. When the downwash flows over 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 set reasonably. Summary of the invention

[0004] The object 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 control efficiency of the horizontal tail elevator 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 design method for an unmanned transport aircraft using a modular fuselage, the unmanned transport aircraft comprising a fuselage and a landing gear, wings being arranged on both sides of the fuselage, an engine nacelle being installed on each wing, and a propeller being installed at the front end of each engine nacelle; tail support assemblies being 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 two vertical tails; the design method for an unmanned transport aircraft comprising:

[0007] Analyze and obtain the lift line slope of the wing according to 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 through the wing.

[0009] Furthermore, the lift line slope C of the wing Lαaccording to The result is obtained by analysis, where K is the efficiency factor of the wing, and the value range of K is 0.8~1.0; 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 is 1 / 2 It 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 obtained, where z t is the vertical height of the horizontal tail relative to the wing chord plane, 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, k 1 , k 2 are coefficients, k 1 The value range is 0.3~0.5, k 2 The value range is 0.1 to 0.3.

[0011] In order to achieve the above technical effects, the present invention further provides an unmanned transport aircraft using 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] A tail support assembly, wherein 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, wherein the horizontal tail is arranged between the two vertical tails, and the vertical height of the horizontal tail relative to the wing chord plane is 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 compartment 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 compartment corresponding to the engine compartment, and each main landing gear is retracted forward into the landing gear compartment 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; a rolling-up rear cargo door is provided at the tail of the fuselage.

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

[0023] 1. The present invention adopts two turboprop engines, double 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, thereby ensuring that the rear cargo door at the rear of the fuselage leaves sufficient space for loading, while avoiding the problem of reduced control efficiency of the elevator 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 This is a 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 is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0030] Example

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

[0032] According to the design size parameters and design Mach number of the wing 2 of the unmanned transport aircraft, the lift line slope of the wing 2 is obtained by analysis;

[0033] According to the design size parameters of the wing 2, the slope of the lift line, 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, the vertical height of the horizontal tail 7 relative to the chord plane of the wing 2 is analyzed and obtained.

[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 rear 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 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 Lα according to The result is obtained by analysis, where K is the efficiency factor of the airfoil of wing 2, and the value range of K is 0.8~1.0; 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, λ 1 / 2 is the sweep angle of the chord line of the wing 21 / 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 over the wing 2 at the horizontal tail, α is the wing angle of attack, l t k is the designed axial distance between the horizontal tail 7 and the wing 2, 1 , k 2 are coefficients, k 1 , k 2 It can be determined through wind tunnel tests or numerical simulations. According to relevant engineering experience, k 1 The typical value range is 0.3~0.5, k 2 Typical values ​​range from 0.1 to 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 installed on both sides of the fuselage 1, an engine nacelle 3 is installed under each wing 2, and a propeller 4 is installed at the front end of each engine nacelle 3;

[0039] A tail support assembly 5, wherein the number of the tail support assemblies 5 is two, and 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, wherein the horizontal tail 7 is 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 is 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 wing 2 on each side of the fuselage 1 is fixedly mounted on the fuselage 1 by bolts 8. The fuselage 1 is mechanically connected to the front and rear beams of the wing 2 through four quick-release joints, and standardized interfaces such as electrical and communication are reserved to meet the replaceable requirements of the fuselage 1, improve the adaptability of different tasks, and also ensure the integrity of the structure of the fuselage 1.

[0043] In this embodiment, the trailing edge of each wing 2 is movably provided with a deflectable flap 201 and an aileron 202. The flap 201 and the aileron 202 are connected to the flight control system through a precise mechanical transmission system. The setting of the flap 201 can adjust the lift coefficient of the wing 2, thereby providing additional lift during take-off and landing, further enhancing the stability and safety of the aircraft. The aileron 202 is responsible for controlling the roll motion of the aircraft. The roll operation of the aircraft is achieved through the differential deflection of the left and right ailerons 202, meeting the use requirements of the unmanned transport aircraft in various complex environments.

[0044] In this embodiment, the landing gear includes two main landing gears 9 and two front landing gears 10, and the two main landing gears 9 and the two front landing gears 10 are installed on the engine compartment 3; the engine compartment 3 is provided with a landing gear compartment at the installation position of each front landing gear 10 and each main landing gear 9; each front landing gear 10 is retracted backward into the landing gear compartment corresponding to the engine compartment 3, and each main landing gear 9 is retracted forward into the landing gear compartment corresponding to the engine compartment 3. When the aircraft is in flight, the landing gear is completely retracted into the landing gear compartment, which reduces air resistance and improves flight efficiency.

[0045] In this embodiment, a rudder 601 is movably provided at the trailing edge of each vertical tail 6, and an elevator 701 is symmetrically provided at the trailing edge of the horizontal tail 7. The rudder 601 is used to control the yaw motion of the aircraft, and adjusts the heading of the aircraft by deflecting left and right to ensure that the aircraft can fly stably according to the predetermined route during flight. The elevator 701 is responsible for controlling the pitch motion of the aircraft, and adjusts the flight attitude of the aircraft by deflecting up and down to achieve climbing, descending or maintaining horizontal flight. The coordinated work of the aileron 202, the rudder 601 and the elevator 701 enables the unmanned transport aircraft to flexibly adjust the flight attitude in three-dimensional space to meet the needs of complex flight missions.

[0046] In this embodiment, the front end of the fuselage 1 is provided with an upward-flipping nose 101, the top edge of the upward-flipping nose 101 is movably connected to the front end of the middle part of the fuselage 1 through a hinge, and the bottom or side of the upward-flipping nose 101 is fixedly connected to the fuselage 1 through a limit locking mechanism; the tail of the fuselage 1 is provided with a rolling-curtain rear cargo door 102. Large-sized air containers can be loaded, especially the loading and unloading of air containers can be completed conveniently, thereby improving the loading efficiency. In addition, the design of the rolling-curtain rear cargo door 102 can realize the aerial delivery of goods, which is a rapid supply of materials for borders or islands without take-off and landing 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 protection scope of the present invention.

Claims

1. A design method for an unmanned transport aircraft with a modular fuselage, the unmanned transport aircraft comprising a fuselage and a landing gear, wings being arranged on both sides of the fuselage, an engine nacelle being installed on each wing, and a propeller being installed at the front end of each engine nacelle; tail wing support assemblies being symmetrically arranged on both sides of the fuselage, each tail wing support assembly being respectively provided with a vertical tail wing, and a horizontal tail wing being arranged between two vertical tail wings; characterized in that: The unmanned transport aircraft design method comprises: Analyze and obtain the lift line slope of the wing according to 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 through the wing.

2. The unmanned transport aircraft design method according to claim 1, characterized in that: The slope of the wing's lift line is C Lα according to The result is obtained by analysis, where K is the efficiency factor of the wing, and the value range of K is 0.8~1.0; 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 It 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 wing chord plane, 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 of the horizontal tail relative to 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; A tail support assembly, wherein 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, wherein the horizontal tail is arranged between the two vertical tails, and the vertical height of the horizontal tail relative to the wing chord plane is 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 compartment at the installation position of each front landing gear and each main landing gear; each front landing gear is retracted backward into the landing gear compartment corresponding to the engine compartment, and each main landing gear is retracted forward into the landing gear compartment corresponding to the engine compartment.

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

9. The unmanned transport aircraft according to claim 4, characterized in that: A flip-up nose is arranged 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; a rolling-up rear cargo door is arranged at the tail of the fuselage.

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