An integrated main body of an unmanned helicopter

Abstract

The present invention relates to an integrated main body of an unmanned helicopter, belonging to the technical field of unmanned aerial vehicles, and solves the technical problems of unreasonable force transmission, low space utilization rate and low weight efficiency of the main body of the unmanned helicopter. The main body of the unmanned helicopter of the present invention comprises an outer skin assembly of the main body, a main reduction platform, a fuel tank assembly and a frame beam assembly of the main body, which are respectively formed and integrally connected; the fuel tank assembly is arranged on the upper part of the frame beam assembly of the main body, and the fuel tank assembly and the frame beam assembly of the main body are connected to the inner wall surface of the outer skin assembly of the main body; the main reduction platform is arranged between the inner sides of the left fuel tank skin unit and the right fuel tank skin unit; the fuel tank assembly, the main reduction platform and the outer skin assembly of the main body together form the outer skin of the main body of the unmanned helicopter. The integrated structure design of the main body of the unmanned helicopter of the present invention and the fuel tank has good product consistency, a direct force transmission route, and can withstand and balance loads; the space utilization rate and the weight efficiency are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned helicopters, and particularly to an integrated main body of an unmanned helicopter. Background Art

[0002] The main body of an unmanned helicopter generally consists of an external skin and an internal space truss. The truss-type body structure inside the unmanned helicopter is usually welded by stainless steel or titanium alloy rods. The whole aircraft load is transmitted along the axial direction of the rods of the truss structure, and the external skin of the unmanned helicopter does not participate in the main load-bearing skin structure. The main body of the unmanned helicopter plays the roles of shaping, drag reduction, and flow rectification.

[0003] This type of unmanned helicopter main body with a truss-type internal structure has the characteristics of low cost and being convenient for bearing concentrated loads. However, it has poor bending and torsion resistance, low utilization rate of the internal space of the body, and low structural weight efficiency. The truss structure adopts a welding connection process, with poor processability, easy deformation, and unable to ensure product consistency.

[0004] In addition, the fuel tank of the unmanned helicopter, as an important oil storage device in the fuel system, is generally welded by metal materials and installed on the main body of the unmanned helicopter as an independent module, which needs to occupy the internal space of the truss structure, affecting the utilization rate of the internal space of the main body and the fuel carrying capacity. To ensure the reliable connection between the fuel tank and the main structure of the body, multiple groups of bolts and straps are used to connect the fuel tank and the body, with complex connections and a lot of connection structure weight.

[0005] With the increasingly wide application range of unmanned helicopters, it is necessary to improve the structure of the main body of the unmanned helicopter to solve the above problems. Summary of the Invention

[0006] In view of the above analysis, the present invention aims to provide an integrated main body of an unmanned helicopter to solve the problems of unreasonable force, low space utilization rate, and low structural weight efficiency of the main body of the unmanned helicopter.

[0007] The present invention is achieved through the following technical solutions:

[0008] An integrated main body of an unmanned helicopter includes an outer skin assembly of the main body, a main reduction platform, a fuel tank assembly, and a frame beam assembly of the main body. The fuel tank assembly is arranged on the upper part of the frame beam assembly of the main body, and both the fuel tank assembly and the frame beam assembly of the main body are connected to the inner wall surface of the outer skin assembly of the main body. The fuel tank assembly includes a left fuel tank skin unit and a right fuel tank skin unit. The main reduction platform is arranged between the left fuel tank skin unit and the right fuel tank skin unit. The outer skin assembly of the main body, the main reduction platform, the fuel tank assembly, and the frame beam assembly of the main body are respectively formed and integrally connected.

[0009] Further, the outer skin assembly of the main body includes a fairing, an upper body unit of the fuselage, and a lower body unit of the fuselage.

[0010] Further, the streamline of the fairing conforms to aerodynamics and is obtained through hydrodynamic analysis and calculation.

[0011] Further, the upper body unit of the fuselage includes a front upper body of the fuselage and a rear upper body of the fuselage; the lower body unit of the fuselage includes a front lower body of the fuselage and a rear lower body of the fuselage.

[0012] Further, the upper part of the main reduction platform and the fuel tank assembly is arranged between the front upper body of the fuselage and the rear upper body of the fuselage; the lower part of the fuel tank assembly is arranged between the front lower body of the fuselage and the rear lower body of the fuselage.

[0013] Further, the main structures of the left fuel tank skin unit and the right fuel tank skin unit are mirror-symmetrical and are both open box skin structures.

[0014] Further, both the left fuel tank skin unit and the right fuel tank skin unit include a fuel tank box body part and a fuel tank flanging part, and the fuel tank flanging part is connected to the outer skin assembly of the main body.

[0015] Further, the frame beam assembly of the main body includes a frame unit and a beam unit; the beam unit is arranged on the longitudinal section of the main body of the unmanned helicopter, and the frame unit is arranged on the transverse section of the main body of the unmanned helicopter.

[0016] Further, the beam unit includes a left front fuselage beam and a right front fuselage beam that are mirror-symmetrical, and a left rear fuselage beam and a right rear fuselage beam that are mirror-symmetrical.

[0017] Further, the frame unit includes a front fuselage connection frame, an upper half connection frame at the front of the middle fuselage, a connection frame at the rear of the middle fuselage, and a tail beam docking frame.

[0018] Further, a strengthening assembly is also included, and the strengthening assembly includes a landing gear fulcrum strengthening frame unit, a fuel tank internal strengthening frame unit, and a middle fuselage bottom strengthening unit.

[0019] Further, the landing gear fulcrum strengthening frame unit includes a left strengthening frame for the front fulcrum of the landing gear and a right strengthening frame for the front fulcrum of the landing gear, a left strengthening member for the rear fulcrum of the landing gear and a right strengthening member for the rear fulcrum of the landing gear.

[0020] Further, the left strengthening member for the rear fulcrum of the landing gear and the right strengthening member for the rear fulcrum of the landing gear respectively connect the connection frame at the rear of the middle fuselage to the left rear fuselage beam and the right rear fuselage beam on both sides of the main body of the unmanned helicopter, and the upper surfaces of the left strengthening member for the rear fulcrum of the landing gear and the right strengthening member for the rear fulcrum of the landing gear are respectively in direct or indirect contact with the lower surfaces of the rear parts of the fuel tank skin boxes in the left fuel tank skin unit and the right fuel tank skin unit.

[0021] Furthermore, the internal strengthening frame unit of the fuel tank includes a left internal strengthening frame of the fuel tank and a right internal strengthening frame of the fuel tank.

[0022] Furthermore, the bottom strengthening unit of the middle fuselage includes a left bottom strengthening member of the middle fuselage and a right bottom strengthening member of the middle fuselage; the left bottom strengthening member of the middle fuselage and the right bottom strengthening member of the middle fuselage are mirror-symmetrical structures, and their installation positions are mirror-symmetrical.

[0023] Furthermore, the units and parts in the outer skin assembly of the main fuselage, the main reduction platform, the fuel tank assembly, and the beam and frame assembly of the main fuselage are all made of composite materials, and are connected by medium-temperature secondary bonding or room-temperature adhesive riveting.

[0024] Furthermore, the integrated main fuselage of the unmanned helicopter has a direct load transfer structure, and the fairing 1, the main reduction platform 5, the fuel tank assembly, and the beam and frame assembly of the main fuselage together constitute the direct load transfer structure of the integrated unmanned helicopter.

[0025] Furthermore, the integrated main fuselage of the unmanned helicopter has an air flow channel structure; the air flow channel structure includes the front ventilation port frame, the long straight barrel-shaped space inside the main fuselage of the unmanned helicopter, and the opening at the rear lower side of the tail of the main fuselage of the unmanned helicopter.

[0026] Compared with the prior art, the present invention can at least achieve one of the following beneficial effects:

[0027] 1. The integrated main fuselage structure of the unmanned helicopter of the present invention uses composite materials, and the overall structure has high specific strength, high specific stiffness, good fatigue resistance, strong designability, and is convenient for large-area integral forming; it has the advantages of good processability and good product consistency, and can effectively reduce the structural weight of the unmanned helicopter.

[0028] 2. The integrated main fuselage of the unmanned helicopter of the present invention is connected to the fuel tank assembly and the outer skin assembly of the main fuselage through beams and frames, and the load transfer route is direct, and it has good ability to bear concentrated loads, bending moments, and torques.

[0029] 3. All the composite parts of the integrated main fuselage of the present invention are connected by medium-temperature secondary bonding or room-temperature adhesive riveting, effectively reducing the number of fuselage parts and fasteners, and improving the reliability and maintainability of the fuselage.

[0030] 4. The integrated main fuselage of the unmanned helicopter of the present invention includes an integrated fuel tank structure, and uses part of the fuel tank structure as part of the outer skin, while reducing the weight of the airframe, it wins space for the fuel carrying capacity on the unmanned helicopter, and improves the weight efficiency of the unmanned helicopter.

[0031] 5. The integrated main fuselage structure of the unmanned helicopter of the present invention is simple, easy to install, and has high space utilization rate.

[0032] Other features and advantages of the present invention will be set forth in the following description, and in part will be obvious from the description, or may be learned by practice of the present invention. The objectives and other advantages of the present invention can be realized and attained by the content particularly pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The drawings are only for the purpose of illustrating specific embodiments and are not considered as limitations of the present invention. Throughout the drawings, the same reference numerals denote the same components.

[0034] Figure 1 Schematic diagram of the integrated main body structure of the unmanned helicopter of the present invention Figure 1 ;

[0035] Figure 2 Schematic diagram of the remaining structure after hiding the front fuselage upper platform and covering the skin of the present invention;

[0036] Figure 3 Schematic diagram of the internal structure of the integrated main body of the unmanned helicopter of the present invention;

[0037] Figure 4 Schematic diagram of the frame beam assembly structure of the main body of the present invention;

[0038] Figure 5 Schematic diagram of the left and right fuel tank skin unit structures of the present invention;

[0039] Figure 6 Schematic diagram of the main reduction platform structure of the present invention;

[0040] Figure 7 Schematic diagram of the integrated main body structure of the unmanned helicopter of the present invention Figure 2 。

[0041] Reference numerals:

[0042] 1. Fairing; 2. Upper front fuselage; 3. Left fuel tank skin unit; 31. Left fuel tank box; 32. Flanged edge of left fuel tank; 4. Right fuel tank skin unit; 41. Right fuel tank box; 42. Flanged edge of right fuel tank; 5. Main reduction platform; 6. Upper rear fuselage; 7. Tail beam docking frame; 8. Left front fuselage beam; 9. Right front fuselage beam; 10. Left reinforcement frame for front landing gear support; 11. Right reinforcement frame for front landing gear support; 12. Front fuselage connection frame; 13. Upper half connection frame for front part of middle fuselage; 14. Internal reinforcement frame of left fuel tank; 141. First fuel tank reinforcement frame; 142. Second fuel tank reinforcement frame; 143. Third fuel tank reinforcement frame; 144. Fourth fuel tank reinforcement frame; 15. Internal reinforcement frame of right fuel tank; 16. Rear connection frame of middle fuselage; 17. Left reinforcement part for rear landing gear support; 18. Right reinforcement part for rear landing gear support; 19. Left rear fuselage beam; 20. Right rear fuselage beam; 21. Lower front fuselage; 22. Left reinforcement part at bottom of middle fuselage; 23. Right reinforcement part at bottom of middle fuselage; 24. Lower rear fuselage; 25. Front ventilation opening frame; 26. Maintenance opening; 27. Tail beam docking plane; 28. Main reducer installation point. Detailed implementation manner

[0043] The following will specifically describe the preferred embodiments of the present invention in conjunction with the accompanying drawings, where the accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principles of the present invention, rather than to limit the scope of the present invention.

[0044] In this embodiment, when the unmanned helicopter is parked on the ground, the top of the unmanned helicopter is regarded as the upper part, the bottom as the lower part, the head of the unmanned aircraft as the front, and the tail as the rear.

[0045] The following, in conjunction with Figures 1-7 , will more specifically describe the technical solution of the present invention:

[0046] The main body of the unmanned helicopter mainly provides installation interfaces and supports for mass modules such as engines, transmissions, rotors, fuel, tail structures, landing gears, and airborne equipment, and maintains the overall shape of the whole machine.

[0047] The main body of the unmanned helicopter is the main load-bearing structure of the unmanned helicopter, which bears and balances the aerodynamic loads of the whole machine and the loads transmitted from the above-mentioned mass blocks. Specifically, it includes: 1 bearing aerodynamic loads; 2 bearing rotor pull; 3 bearing engine inertial loads; 4 bearing transmission system inertial loads; 5 bearing fuel inertial loads; 6 bearing inertial forces, bending moments, and torques transmitted from the tail structure; 7 bearing inertial loads of each airborne equipment.

[0048] As Figure 1As shown in the figure, the integrated main body of the unmanned helicopter of the present invention includes an outer skin assembly of the main body, a main reduction platform 5, a fuel tank assembly, and a frame beam assembly of the main body, which are respectively formed; the frame beam assembly of the main body is connected inside the outer skin assembly of the main body, and the fuel tank assembly is connected between the outer skin assembly of the main body and the frame beam assembly of the main body; the main reduction platform 5 and the fuel tank assembly are arranged on the upper part of the outer skin assembly of the main body; the fuel tank assembly includes a left fuel tank skin unit 3 and a right fuel tank skin unit 4; the main reduction platform 5 is arranged between the top surface of the left fuel tank skin unit 3 and the top surface of the right fuel tank skin unit 4; the top surface of the fuel tank assembly, the main reduction platform 5 and the outer skin assembly of the main body together form the outer skin of the main body of the unmanned helicopter. A long straight barrel-shaped space is formed inside the outer skin of the main body of the unmanned helicopter, and an opening structure is provided at the frame at the lower rear side of the tail of the main body of the unmanned helicopter.

[0049] Specifically, the outer skin assembly of the main body includes a fairing 1, an upper body unit of the fuselage and a lower body unit of the fuselage. Among them, the upper body unit of the fuselage includes a front upper body 2 and a rear upper body 6; the lower body unit of the fuselage includes a front lower body 21 and a rear lower body 24.

[0050] Among them, the fairing 1 adopts a carbon fiber composite honeycomb sandwich structure, and the whole is in the shape of a box structure with side enclosures, upper and lower parts open. The outer shape of the fairing 1 has a streamline shape that conforms to aerodynamics, and the specific shape is obtained through hydrodynamic analysis and calculation; in the flight state, the fairing 1 can cooperate with the skins of the tail beam, tail wing, etc. to play a role in rectifying and reducing drag during flight.

[0051] As Figure 1 shown in the figure, the upper and lower parts of the fairing 1 respectively have stepped platforms with the front lower and the rear higher. The fairing 1 can be divided into multiple pieces for manufacturing and forming according to the stress level, section, function and processability, and finally assembled to form a complete fairing 1.

[0052] At the same time, since the fuel tank assembly, the frame beam assembly of the main body, etc. are integrally connected inside the fairing 1, the fairing 1 can bear the aerodynamic load together with structural components such as the fuel tank assembly and the frame beam assembly of the main body, and participate in the force transmission of the whole unmanned helicopter; that is, the load is transmitted to the fuselage frame beam in the form of shear force, torque, bending moment, etc.

[0053] As Figure 1 shown in the figure, preferably, a maintenance opening 26 is provided on the fairing 1, and through the maintenance opening 26, maintenance including but not limited to the engine can be carried out, so as to facilitate the maintenance work and is beneficial to improving the flight safety and service life of the unmanned helicopter.

[0054] As Figure 1 shown in the figure, the upper body unit of the fuselage is installed on the stepped platform of the upper part of the fairing 1.

[0055] Specifically, the front fuselage upper platform 2 is installed on the lower first step platform at the front upper part of the fairing 1, and the rear fuselage upper platform 6 is installed on the higher second step platform at the rear upper part of the fairing 1. Moreover, the rear fuselage upper platform 6 is installed at the rear part of the second step platform.

[0056] As Figure 7 shown, preferably, the front ventilation port frame 25 is installed at the front part of the front fuselage upper platform 2; the front ventilation port frame 25 communicates with the inside of the fairing 1 to form a front ventilation port.

[0057] The interior of the main body of the unmanned helicopter below the front fuselage upper platform 2 is the front equipment compartment, which mainly installs equipment such as avionics, electrical, navigation, and flight control of the unmanned helicopter.

[0058] The front ventilation port frame serves as a ventilation channel, providing an air intake channel for ventilation of the equipment compartment and the engine below the main reduction platform 5 and below the front part of the main body of the unmanned helicopter.

[0059] Preferably, the rear fuselage upper platform 6 follows the shape of the fairing 1 longitudinally in the main body of the unmanned helicopter. The interior of the main body of the unmanned helicopter below the rear fuselage upper platform 6 is the rear equipment compartment, which mainly installs the engine control equipment of the unmanned helicopter.

[0060] As Figure 3 shown, the fuselage lower platform unit is installed on the step platform at the lower part of the fairing 1.

[0061] Specifically, the front fuselage lower platform 21 is installed on the lower third step platform at the front lower part of the fairing 1, and the front fuselage lower platform 21 is installed at the front part of the third step platform; the front lower equipment compartment is located above the front fuselage lower platform 21, which is used to install navigation system equipment such as inertial navigation and altimeter without height, and an engine liquid cooling radiator is also installed in the front lower equipment compartment.

[0062] Specifically, the rear fuselage lower platform 24 is installed on the higher fourth step platform at the rear lower part of the fairing 1, and the middle part of the rear fuselage lower platform 24 is hollowed out for installing cooling system equipment such as an air-cooled radiator.

[0063] As Figure 5 shown, the left fuel tank skin unit 3 and the right fuel tank skin unit 4 are mirror symmetric parts of the main structure, both of which are L-shaped open box skin structures, and each includes a fuel tank box body part and a fuel tank flanging part; the bottom surfaces of the two fuel tank box body parts are arranged opposite to each other, and the fuel tank flanging parts are located on the outside for connecting with the outer skin assembly of the main body. In the state of being parked on the ground, the left fuel tank skin unit 3 and the right fuel tank skin unit 4 are in a position state where they are rotated 90° clockwise in the L shape, with the long side on the top and the short side in the front.

[0064] Specifically, the open box skin structure of the left fuel tank skin unit 3 includes a left fuel tank box body 31 and a left fuel tank turned-out edge part 32; the open box skin structure of the right fuel tank skin unit 4 includes a right fuel tank box body 41 and a right fuel tank turned-out edge part 42. In the overall forming state, the upper and front parts of the left fuel tank box body 31 and the right fuel tank box body 41 are part of the outer skin of the main body of the unmanned helicopter in this embodiment.

[0065] Specifically, the main reduction platform 5 is a C-shaped box section structure. After structural strength topology optimization design, the main reduction platform 5 is provided with main reduction platform stiffeners in the cross-sectional direction of the fuselage, and main reduction platform thickened parts are provided at local positions around the main reduction platform 5 for connecting with the surrounding structures through medium-temperature secondary bonding or room-temperature adhesive riveting to improve the structural efficiency of the main body of the unmanned helicopter.

[0066] The main reduction platform 5 is arranged between the upper edges of the bottoms of the left fuel tank box body 31 and the right fuel tank box body 41 and becomes part of the outer skin of the main body of the unmanned helicopter in this embodiment.

[0067] As Figure 6 shown, preferably, the main reduction platform 5 of this embodiment is an integrally machined part made of 7075 aviation aluminum alloy, on which a main reduction gear installation point 28 is designed. The engine of the unmanned helicopter is arranged in the middle of the fuselage at the position of the lower rotor main shaft of the main reduction platform 5.

[0068] The main reduction platform 5, as a part at the core position of the main body of the unmanned helicopter, provides an installation interface and support for the reduction gear of the transmission system. The main reduction platform 5 bears the inertial load of the reduction gear of the unmanned helicopter and transmits the rotor pull force, bending moment, and torque to the main body frame beam assembly of the main body of the unmanned helicopter.

[0069] The main reduction platform 5, the upper part of the bottom of the left fuel tank box body 31 and the right fuel tank box body 41 together form the front part of the second step of the fairing 1, which is continuously arranged with the upper part of the rear fuselage 6 located at the rear of the second step.

[0070] The upper edge of the fuel tank assembly is arranged between the upper part of the front fuselage 2 and the upper part of the rear fuselage 6; the lower edge of the fuel tank assembly is arranged between the lower part of the front fuselage 21 and the lower part of the rear fuselage 24. The front parts of the left fuel tank box body 31 and the right fuel tank box body 41 are connected to the first step and the second step of the fairing 1.

[0071] The left fuel tank skin unit 3 and the right fuel tank skin unit 4 are respectively hermetically riveted to the fairing 1 through the left fuel tank turned-out edge part 32 and the right fuel tank turned-out edge part 42 to form a closed fuel tank compartment, which becomes part of the main structure of the fuselage and participates in the overall aircraft load bearing.

[0072] As Figure 4As shown, the main body frame beam assembly includes a frame unit and a beam unit; the beam unit is arranged on the longitudinal section of the main body of the unmanned helicopter, and the frame unit is arranged on each transverse section of the main body of the unmanned helicopter.

[0073] like Figure 2 As shown, specifically, the beam unit includes a mirror-symmetrical front fuselage left beam 8 and a mirror-symmetrical front fuselage right beam 9 , and a mirror-symmetrical rear fuselage left beam 19 and a mirror-symmetrical rear fuselage right beam 20 .

[0074] The front fuselage left beam 8 and the front fuselage right beam 9 are the main load-bearing structures of the front fuselage, which are used to support and transmit the avionics equipment, mission loads, etc. installed in the front fuselage part of the unmanned helicopter, as well as the aerodynamic load.

[0075] The front fuselage left beam 8 and the front fuselage right beam 9, the skin of the front part of the air deflector 1 and the front fuselage upper platform 2 form a front ventilation duct, which can cooperate with the engine liquid cooling radiator installed in the front lower equipment compartment to provide a heat dissipation environment for the engine.

[0076] The rear fuselage left beam 19 and the rear fuselage right beam 20 are the main load-bearing components of the rear fuselage, and are mainly used to withstand the bending moment and shear force generated by the equipment installed in the rear fuselage of the unmanned helicopter and the tail beam.

[0077] Specifically, the frame unit includes a front fuselage connecting frame 12 , a middle fuselage front upper half connecting frame 13 , a middle fuselage rear connecting frame 16 and a tail beam docking frame 7 .

[0078] The front fuselage connection frame 12 is mainly used to maintain the structural shape of the unmanned helicopter, improve the anti-instability ability of the longitudinal components at the front of the fuselage, and form a closed box section together with the front fuselage left beam 8 and the front fuselage right beam 9, as well as the fairing 1 and the front fuselage upper platform 2 to bear the concentrated load generated by the mission load installed at the closed box section.

[0079] The upper half connecting frame 13 of the front part of the middle fuselage is used to form a closed frame with the reducer platform, the left fuel tank box body 31 and the right fuel tank box body 41 of the unmanned helicopter, etc., to participate in the force of the whole machine and balance the force and bending moment transmitted from both sides of the fuselage.

[0080] The middle fuselage rear connection frame 16 provides support for the main reduction platform 5 and the rear fulcrum of the landing gear of the unmanned helicopter, mainly bears and transmits vertical loads, and balances the forces and bending moments transmitted from both sides of the unmanned helicopter fuselage.

[0081] The tail beam docking frame 7 is in the shape of a C-shaped frame, providing an installation interface for the tail section structure. Specifically, the tail beam of the unmanned helicopter is connected to the integral unmanned helicopter main body of the present invention through the tail beam docking frame 7. Specifically, the tail beam docking frame 7 is horizontally arranged at the tail of the unmanned helicopter main body and riveted to the inner wall surface of the tail end of the unmanned helicopter main body on the outer periphery. The inner periphery of the tail beam docking frame 7 is provided with a tail beam docking plane 27, and the tail beam docking plane 27 is used to connect the tail beam of the unmanned helicopter. The tail beam docking frame 7 can integrate and transmit the inertial force, aerodynamic force, etc. of the unmanned helicopter tail section structure to the unmanned helicopter main body.

[0082] The main reduction platform 5, the fuel tank assembly and the main body frame beam assembly jointly support the outer skin assembly of the main body, forming an integral unmanned helicopter main body.

[0083] Preferably, the integral unmanned helicopter main body further includes a strengthening assembly, and the strengthening assembly includes a landing gear fulcrum strengthening frame unit, a fuel tank internal strengthening frame unit and a middle fuselage bottom strengthening unit.

[0084] As Figure 4 shown, specifically, the landing gear fulcrum strengthening frame unit includes a front landing gear fulcrum left strengthening frame 10 and a front landing gear fulcrum right strengthening frame 11, a rear landing gear fulcrum left strengthening member 17 and a rear landing gear fulcrum right strengthening member 18.

[0085] The front landing gear fulcrum left strengthening frame 10 and the front landing gear fulcrum right strengthening frame 11 are respectively located between the lower parts of the front fuselage left beam 8 and the front fuselage right beam 9 and the fairing 1, and are used to bear the front landing load of the landing gear and enhance the strength of the connected fairing 1 part.

[0086] The rear landing gear fulcrum left strengthening member 17 and the rear landing gear fulcrum right strengthening member 18 connect the rear part of the middle fuselage connecting frame 16 with the rear fuselage left beam 19 and the rear fuselage right beam 20 on both sides of the unmanned helicopter main body respectively, and the upper surfaces are respectively in direct or indirect contact with and not fixedly connected to the lower surfaces of the rear parts of the middle fuel tank skin boxes of the left fuel tank skin unit 3 and the right fuel tank skin unit 4. The rear landing gear fulcrum left strengthening member 17 and the rear landing gear fulcrum right strengthening member 18 are used to be integrated with the main body frame beam assembly, thereby enhancing the structural strength of the unmanned helicopter main body; at the same time, since the rear landing gear fulcrum left strengthening member 17 and the rear landing gear fulcrum right strengthening member 18 bear a relatively large rear landing load of the landing gear, therefore, the rear landing gear fulcrum left strengthening member 17 and the rear landing gear fulcrum right strengthening member 18 are not fixedly connected to the fuel tank skin box and the skin of the fairing 1; in this way, while the rear landing gear fulcrum left strengthening member 17 and the rear landing gear fulcrum right strengthening member 18 connect the main body frame beam assembly into a whole, it also avoids the damage of the landing load to the fuel tank and the skin of the fairing 1, and increases the strength and service life of the unmanned helicopter main body.

[0087] As Figure 4As shown in the figure, specifically, the internal strengthening frame unit of the fuel tank includes a left internal strengthening frame 14 of the fuel tank and a right internal strengthening frame 15 of the fuel tank. The left internal strengthening frame 14 of the fuel tank and the right internal strengthening frame 15 of the fuel tank respectively include a plurality of fuel tank strengthening sub-frames, which are respectively arranged in the fuel tank skin box body.

[0088] Taking the left internal strengthening frame 14 of the fuel tank as an example, preferably, the left internal strengthening frame 14 of the fuel tank in this embodiment includes a first fuel tank strengthening frame 141, a second fuel tank strengthening frame 142, a third fuel tank strengthening frame 143, and a fourth fuel tank strengthening frame 144 arranged in sequence from front to back. Central oil passing holes are provided on all 4 fuel tank strengthening sub-frames. On the one hand, it can improve the stiffness of the fuel tank. On the other hand, it can prevent excessive fuel oscillation and does not hinder the flow of fuel inside the fuel tank.

[0089] Preferably, at least one of the upper side and the lower side of each fuel tank strengthening frame is provided with a side oil passing hole; it can ensure that when the fuel quantity is small, regardless of the flight state of the unmanned helicopter, the fuel can still flow without being blocked by the fuel tank strengthening sub-frame.

[0090] The outer side of each fuel tank strengthening sub-frame is connected to the inner wall surface of the flow guide cover 1, and the other three peripheries are connected to the inner wall surface of the fuel tank skin box body, so as to effectively support the flow guide cover 1 while strengthening the strength of the fuel tank assembly.

[0091] Preferably, the fourth fuel tank strengthening frame 144 of this embodiment is located at the position of the rear connecting frame 16 of the middle fuselage of the integrated unmanned helicopter main body, so as to strengthen the structural integration strength of the fuel tank assembly.

[0092] The right internal strengthening frame 15 of the fuel tank has the same technical effect as above.

[0093] At the bottom of the middle fuselage, the flow guide cover 1 has no support. The present invention provides a middle fuselage bottom strengthening unit to support the weak link of the strength of the flow guide cover 1.

[0094] Such as Figure 3 As shown in the figure, specifically, the middle fuselage bottom strengthening unit includes a middle fuselage bottom left strengthening member 22 and a middle fuselage bottom right strengthening member 23, and the two are mirror-symmetrical structures with mirror-symmetrical installation positions.

[0095] Take the left reinforcing member 22 at the bottom of the middle fuselage as an example. The left reinforcing member 22 at the bottom of the middle fuselage is a bent plate structure, including a left rear upper plate, an inclined plate and a left front lower plate formed integrally. The rear end of the left rear upper plate is connected to the rear connecting frame 16 of the middle fuselage, and the upper surface of the left rear upper plate is connected to the outer surface of the rear part of the bottom of the left fuel tank box body 31. The front end of the left front lower plate is connected to the lower end of the short L side of the left fuel tank box body 31; on the integrated main body of the unmanned helicopter, the outer side surface of the left reinforcing member 22 at the bottom of the middle fuselage is shaped and connected to the fairing 1. Since the left reinforcing member 22 at the bottom of the middle fuselage is connected to the inner wall of the fairing 1 in the form of a broken line and is combined with the fuel tank assembly and the main body frame beam assembly, it effectively enhances the structural strength of the fairing 1 at the bottom of the middle fuselage. The strengthening unit at the bottom of the middle fuselage is used to maintain the structural shape of the main body of the unmanned helicopter, support the fairing 1, improve the load-bearing capacity of the fairing 1, and bear and transfer bending moment and axial load.

[0096] In the integrated main body of the unmanned helicopter of the present invention, the units and parts respectively included in the outer skin assembly of the main body, the main reduction platform 5, the fuel tank assembly, the main body beam and the frame assembly are all made of composite materials, and are connected by the connection form of medium-temperature secondary adhesive bonding or room-temperature adhesive riveting. The larger-area parts are all provided with weight-reducing holes. Among them, the medium temperature of the secondary adhesive bonding refers to about 125 °C.

[0097] Preferably, the weight-reducing holes provided in the larger-area parts, including the central oil-passing holes provided in the internal strengthening frame unit of the fuel tank, are all provided with flanging structures to increase the strength of the parts, which is beneficial to improving the structural strength of the entire main body of the unmanned helicopter. The weight-reducing holes provided in the larger-area parts also have the function of allowing air flow through and reducing air resistance.

[0098] The integrated main body of the unmanned helicopter of the present invention has a direct force transmission structure:

[0099] The main reduction platform 5 of the integrated main body of the unmanned helicopter bears the inertial loads transmitted from the rotor and the reducer of the unmanned helicopter, and transmits the rotor pull, bending moment and torque to the main body frame beam assembly.

[0100] The tail beam docking frame 7 and the tail beam docking plane 27 of the integrated main body of the unmanned helicopter provide installation interfaces for the tail section structure of the unmanned helicopter, and integrate and transmit the inertial force, aerodynamic force, etc. of the tail section structure to the main body of the unmanned helicopter. The C-shaped frame of the tail beam docking frame 7 can better transmit the torque of the tail section.

[0101] The fairing 1 and internal structures such as the fuel tank assembly and the main fuselage frame beam assembly are integrally joined together by medium-temperature secondary bonding or room-temperature adhesive riveting, enabling the fairing 1 to bear and balance, together with structural components such as the fuel tank assembly and the main fuselage frame beam assembly, the inertial loads of the engine, transmission, fuel system including the fuel tank assembly, various airborne equipment of the unmanned helicopter, as well as the inertial force, bending moment and torque transmitted from the tail section structure. The fairing 1 simultaneously transmits the loads it bears to the main fuselage frame beam assembly in the forms of shear force, torque, bending moment, etc. The main fuselage frame beam assembly is arranged at the layout position of the main mass blocks, and distributes and balances the concentrated loads along the transverse and longitudinal directions of the fuselage through the frames and beams respectively. The strengthening frames locally arranged on the main fuselage frame beam assembly are mainly used to maintain the structural shape and improve the anti-instability ability of the fuselage. The fairing 1, the main reduction platform 5, the fuel tank assembly and the main fuselage frame beam assembly jointly constitute the direct force transmission structure of the integrated unmanned helicopter. The integrated unmanned helicopter main fuselage of the present invention has an excellent air flow channel structure: at the front windward surface of the most front end of the integrated unmanned helicopter main fuselage, a front ventilation port frame 25 is provided as the air inlet of the whole machine's air intake duct, making the most of the forward flight air flow and being able to dissipate heat from the power cabin below the main reduction platform 5; during the flight of the unmanned helicopter, the air flow is introduced into the long straight barrel-shaped space inside the unmanned helicopter main fuselage through the front ventilation port frame 25, and the heat flow is dissipated until it exits from the opening of the rear lower side frame at the tail of the unmanned helicopter main fuselage. The front ventilation port frame 25, the long straight barrel-shaped space inside the unmanned helicopter main fuselage, and the opening of the rear lower side frame at the tail of the unmanned helicopter main fuselage form the air flow channel structure of the integrated unmanned helicopter main fuselage.

[0102] The inner skin of the fuel tank serves as the main structure of the heat dissipation channel, with a smooth surface transition to avoid air flow disorder.

[0103] The main structure of the integrated unmanned helicopter main fuselage of the present invention adopts an integrated structure design, with good processability and product consistency; parts such as the fairing 1, the fuel tank assembly, the main fuselage frame beam assembly and the main reduction platform 5 are all made of 7075 aviation aluminum alloy and fiber-reinforced composite materials, and among them, the fairing 1 adopts a carbon fiber composite material honeycomb sandwich structure, which is connected in the form of overall medium-temperature secondary bonding or room-temperature adhesive riveting. The forming process is simple and the material utilization rate is high, greatly reducing the number of parts and having a remarkable weight reduction effect. The weight of the whole machine is reduced by more than 20% compared with the truss structure.

[0104] The integrated unmanned helicopter main fuselage of the present invention adopts an integrated design of the fuel tank structure, which, while reducing the weight of the fuselage, wins space for the fuel carrying capacity on the aircraft and improves the weight efficiency of the unmanned helicopter.

[0105] The integrated unmanned helicopter main fuselage of the present invention has a simple structure, is easy to install, and has a high space utilization rate.

[0106] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art outside the technical scope disclosed by the present invention should be covered outside the protection scope of the present invention. At the same time, all devices equipped with this device to expand the application fields and produce compound technical effects fall within the protection scope of the method invention of the present invention.

Claims

1. An integrated main body of an unmanned helicopter, characterized in that, It includes the outer skin assembly of the main body, the main reduction platform (5), the fuel tank assembly and the frame beam assembly of the main body; The fuel tank assembly is arranged on the upper part of the frame beam assembly of the main body, and both the fuel tank assembly and the frame beam assembly of the main body are connected to the inner wall surface of the outer skin assembly of the main body; The fuel tank assembly includes a left fuel tank skin unit (3) and a right fuel tank skin unit (4); the main reduction platform (5) is arranged between the left fuel tank skin unit (3) and the right fuel tank skin unit (4); The outer skin assembly of the main body includes a fairing (1), an upper body unit of the fuselage and a lower body unit of the fuselage; The top surface of the fuel tank assembly, the main reduction platform (5) and the outer skin assembly of the main body jointly form the outer skin of the main body of the unmanned helicopter; The outer skin assembly of the main body, the main reduction platform (5), the fuel tank assembly and the frame beam assembly of the main body are respectively formed and integrally connected to form a direct force transmission structure.

2. The integrated unmanned helicopter main body according to claim 1, characterized in that The upper body unit of the fuselage includes a front upper body of the fuselage (2) and a rear upper body of the fuselage (6); the lower body unit of the fuselage includes a front lower body of the fuselage (21) and a rear lower body of the fuselage (24).

3. The integrated unmanned helicopter main body according to claim 2, wherein, The upper part of the main reduction platform (5) and the fuel tank assembly is arranged between the front upper body of the fuselage (2) and the rear upper body of the fuselage (6); the lower part of the fuel tank assembly is arranged between the front lower body of the fuselage (21) and the rear lower body of the fuselage (24).

4. The integrated main body of the unmanned helicopter according to any one of claims 1-3, characterized in that, The main body structures of the left fuel tank skin unit (3) and the right fuel tank skin unit (4) are mirror-symmetrical and are both open box skin structures.

5. The integrated unmanned helicopter main body according to claim 4, characterized in that Both the left fuel tank skin unit (3) and the right fuel tank skin unit (4) include a fuel tank box body part and a fuel tank flanging part, and the fuel tank flanging part is connected to the outer skin assembly of the main body.

6. The integrated unmanned helicopter main body according to claim 5, characterized in that, The frame beam assembly of the main body includes a frame unit and a beam unit; the beam unit is arranged on the longitudinal section of the main body of the unmanned helicopter, and the frame unit is arranged on the transverse section of the main body of the unmanned helicopter.

7. The integrated unmanned helicopter main body according to claim 6, wherein The beam unit includes a mirror-symmetrical front fuselage left beam (8) and a front fuselage right beam (9), and a mirror-symmetrical rear fuselage left beam (19) and a rear fuselage right beam (20).

8. The integrated unmanned helicopter main body according to claim 6, characterized in that, The frame unit includes a front fuselage connection frame (12), an upper half connection frame at the front part of the middle fuselage (13), a connection frame at the rear part of the middle fuselage (16) and a tail beam docking frame (7).

9. The integrated main fuselage of the unmanned helicopter according to any one of claims 1-3, 5-8, characterized in that The units and parts in the outer skin assembly of the main body, the main reduction platform (5), the fuel tank assembly and the frame beam assembly of the main body are all made of composite materials and are connected by medium-temperature secondary adhesive bonding or room-temperature adhesive riveting.

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