CN115743646A - Unmanned helicopter main frame body of integral type - Google Patents

Abstract

The invention relates to an integrated unmanned helicopter main body, belongs to the technical field of unmanned planes, and solves the technical problems that the unmanned helicopter main body is unreasonable in force transfer, and low in space utilization rate and weight efficiency. The unmanned helicopter main body comprises a main body outer skin assembly, a main reducer platform, an oil tank assembly and a main body frame beam assembly which are respectively formed and integrally connected; the oil tank assembly is arranged at the upper part of the main machine frame beam assembly, and the oil tank assembly and the main machine frame beam assembly are connected to the inner wall surface of the main machine outer skin assembly; the main reducing platform is arranged between the inner sides of the left oil tank skin unit and the right oil tank skin unit; the oil tank assembly, the main reducer platform and the main engine external skin assembly jointly form the main engine external skin of the unmanned helicopter. The unmanned helicopter main body and the oil tank are designed into an integrated structure, the product consistency is good, the force transmission route is direct, and the unmanned helicopter main body and the oil tank can bear and balance loads; space utilization and weight efficiency are improved.

Description

Unmanned helicopter main frame body of integral type

Technical Field

The invention relates to the technical field of unmanned helicopters, in particular to an integrated unmanned helicopter main body.

Background

The main body of the unmanned helicopter is generally formed by an external skin and an internal space truss, wherein the truss type body structure inside the unmanned helicopter is generally formed by welding stainless steel or titanium alloy rods. The full-aircraft load is axially transferred along the rod piece of the truss structure, and the outer skin of the unmanned helicopter does not participate in the skin structure of the main bearing force. The unmanned helicopter main body plays roles of shape maintenance, drag reduction and rectification.

The unmanned helicopter main body with the truss type inner structure has the characteristics of low cost and convenience for bearing concentrated loads; however, the bearing bending and torsion resistance of the bearing bending machine is poor, the utilization rate of the internal space of the machine body is low, and the structural weight efficiency is low; the truss structure adopts a welding connection process, has poor manufacturability, is easy to deform, and cannot ensure the consistency of products.

In addition, the oil tank of the unmanned helicopter is an important oil storage device in a fuel system, is generally formed by welding metal materials, is installed on the main body of the unmanned helicopter as an independent module, needs to occupy the internal space of a truss structure, and influences the internal space utilization rate of the main body and the fuel carrying capacity. In order to ensure that the oil tank is reliably connected with the main structure of the machine body, the oil tank and the machine body are connected by adopting a plurality of groups of bolts and binding bands, the connection is complex and a plurality of connecting structure weights are required to be paid out.

As the application range of the unmanned helicopter is favorable to be wide, the structure of the main body of the unmanned helicopter needs to be improved to solve the above problems.

Disclosure of Invention

In view of the foregoing analysis, the present invention aims to provide an integrated unmanned helicopter main body, so as to solve the problems of unreasonable stress on the unmanned helicopter main body, low space utilization rate, and low structural weight efficiency.

The invention is realized by the following technical scheme:

an integrated unmanned helicopter main body comprises a main body outer skin assembly, a main reducer platform, an oil tank assembly and a main body frame beam assembly; the oil tank assembly is arranged at the upper part of the main machine frame beam assembly, and the oil tank assembly and the main machine frame beam assembly are both connected to the inner wall surface of the main machine outer skin assembly; the oil tank assembly comprises a left oil tank skin unit and a right oil tank skin unit; the main reducing platform is arranged between the left oil tank skin unit and the right oil tank skin unit; the main machine body outer skin assembly, the main reducer platform, the oil tank assembly and the main machine body frame beam assembly are respectively formed and integrally connected.

Furthermore, the main machine body external skin assembly comprises a fairing, a machine body upper platform unit and a machine body lower platform unit.

Further, the fairing streamline shape is in accordance with aerodynamics and is obtained through fluid mechanics analysis calculation.

Further, the body upper unit comprises a front body upper table and a rear body upper table; the lower machine body unit comprises a front lower machine body and a rear lower machine body.

Furthermore, the upper parts of the main reducing platform and the oil tank assembly are arranged between the front machine body upper platform and the rear machine body upper platform; the lower part of the oil tank assembly is arranged between the front machine body lower platform and the rear machine body lower platform.

Furthermore, the main body structures of the left oil tank skin unit and the right oil tank skin unit are mirror images and are both of open box body skin structures.

Furthermore, the left oil tank skin unit and the right oil tank skin unit both comprise oil tank box body parts and oil tank flanging parts, and the oil tank flanging parts are connected with the main machine body outer skin assembly.

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

Furthermore, the beam unit comprises a front fuselage left beam and a front fuselage right beam which are in mirror symmetry, and a rear fuselage left beam and a rear fuselage right beam which are in mirror symmetry.

Furthermore, the frame unit comprises a front fuselage connecting frame, a middle fuselage front upper half connecting frame, a middle fuselage rear connecting frame and a tail beam butt-joint frame.

Further, the aircraft further comprises a reinforcing assembly, wherein the reinforcing assembly comprises a landing gear fulcrum reinforcing frame unit, an oil tank internal reinforcing frame unit and a middle aircraft body bottom reinforcing unit.

Furthermore, the undercarriage fulcrum reinforcing frame unit comprises an undercarriage front fulcrum left reinforcing frame, an undercarriage front fulcrum right reinforcing frame, an undercarriage rear fulcrum left reinforcing piece and an undercarriage rear fulcrum right reinforcing piece.

Furthermore, the undercarriage rear pivot left reinforcement and the undercarriage rear pivot right reinforcement are respectively arranged on two sides of the main body of the unmanned helicopter to connect the middle fuselage rear connecting frame with the rear fuselage left beam and the rear fuselage right beam, and the upper surfaces of the undercarriage rear pivot left reinforcement and the undercarriage rear pivot right reinforcement are respectively in direct or indirect contact with the lower surfaces of the rear parts of the oil tank skin box bodies in the left oil tank skin unit and the right oil tank skin unit.

Further, the oil tank internal reinforcing frame unit comprises a left oil tank internal reinforcing frame and a right oil tank internal reinforcing frame.

Further, the middle fuselage bottom reinforcing unit comprises a middle fuselage bottom left reinforcing piece and a middle fuselage bottom right reinforcing piece; the middle machine body bottom left reinforcing part and the middle machine body bottom right reinforcing part are of mirror symmetry structures, and installation positions are mirror symmetry.

Furthermore, units and parts in the main machine body outer skin assembly, the main reducer platform, the oil tank assembly and the main machine body beam frame assembly are all made of composite materials and are connected through medium-temperature secondary glue joint or normal-temperature glue rivet joint.

Furthermore, the main body of the integrated unmanned helicopter is provided with a direct force transmission structure, and the fairing 1, the main reducer platform 5, the oil tank assembly and the main body frame beam assembly jointly form the direct force transmission structure of the integrated unmanned helicopter.

Further, the integrated unmanned helicopter main body is provided with an airflow channel structure; the airflow channel structure comprises the front vent frame, a long straight barrel-shaped space inside the unmanned helicopter main body and an opening of the lower side frame behind the tail of the unmanned helicopter main body.

Compared with the prior art, the invention can realize at least one of the following beneficial effects:

1. the integrated unmanned helicopter main body structure uses composite materials, has high specific strength and specific stiffness, good fatigue resistance and strong designability, and is convenient for large-area integral molding; the unmanned helicopter has the advantages of good manufacturability, good product consistency and the like, and the weight of the fuselage structure of the unmanned helicopter can be effectively reduced.

2. The integrated unmanned helicopter main body is connected with the oil tank assembly and the main body outer skin assembly through the beam and the frame, the force transmission path is direct, and the integrated unmanned helicopter has good capacity of bearing concentrated load, bending moment and torque.

3. All parts made of composite materials of the integrated unmanned helicopter main body are connected through medium-temperature secondary glue joint or normal-temperature glue rivet joint, the number of parts of the helicopter body and the number of fasteners are effectively reduced, and the reliability and the maintainability of the helicopter body are improved.

4. The integrated unmanned helicopter main body comprises an oil tank structure which is designed integrally, and part of the structure of the oil tank is used as a part of the outer skin, so that space is gained for carrying fuel on the unmanned helicopter while the weight of the helicopter body is reduced, and the weight efficiency of the unmanned helicopter is improved.

5. The integrated unmanned helicopter main body has the advantages of simple structure, convenience in installation and high space utilization rate.

Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and drawings.

Drawings

The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.

Fig. 1 is a first structural diagram of a main body of the integrated unmanned helicopter of the present invention;

FIG. 2 is a schematic view of the remaining structure of the hidden forward fuselage upper deck and skin of the present invention;

FIG. 3 is a schematic view of the internal structure of the main body of the integrated unmanned helicopter of the present invention;

FIG. 4 is a schematic structural diagram of a main frame beam assembly according to the present invention;

FIG. 5 is a schematic structural diagram of left and right tank skin units of the present invention;

FIG. 6 is a schematic structural diagram of a main reduction platform according to the present invention;

fig. 7 is a schematic structural diagram of the main body of the integrated unmanned helicopter according to the second embodiment of the present invention.

Reference numerals are as follows:

1. a cowling; 2. a front machine body is arranged on the platform; 3. a left tank skin unit; 31. a left tank body; 32. the out-flanging part of the left oil tank; 4. a right tank skin unit; 41. a right tank box body; 42. the outer flanging part of the right oil tank; 5. a main subtraction platform; 6. the rear machine body is arranged on the platform; 7. a tail beam butt joint frame; 8. a front fuselage left spar; 9. a front fuselage right spar; 10. a left reinforcing frame of a front supporting point of the landing gear; 11. a right reinforcing frame of a front pivot of the landing gear; 12. a front body connecting frame; 13. the upper half connecting frame at the front part of the middle machine body; 14. a reinforcing frame inside the left oil tank; 141. a first tank reinforcing frame; 142. a second tank reinforcement frame; 143. a third tank reinforcement frame; 144. a fourth tank reinforcement frame; 15. a right oil tank inner reinforcing frame; 16. the rear part of the middle machine body is connected with the frame; 17. a landing gear rear pivot left stiffener; 18. a right reinforcing member of a rear pivot of the landing gear; 19. a rear fuselage left beam; 20. a rear fuselage right beam; 21. the front machine body is placed on the platform; 22. a middle fuselage bottom left stiffener; 23. a right reinforcement at the bottom of the middle fuselage; 24. the rear machine body is placed on the platform; 25. a front vent frame; 26. maintaining the mouth; 27. a tail beam butt joint plane; 28. and (5) installing a main reducer.

Detailed Description

The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form a part hereof, and which together with the embodiments of the invention serve to explain the principles of the invention and not to limit its scope.

In the embodiment, when the unmanned helicopter stops on the ground, the top and the bottom of the unmanned helicopter are upper and lower, and the head and the tail of the unmanned helicopter are front and rear.

The technical solution of the present invention is described in more detail below with reference to fig. 1 to 7:

the main body of the unmanned helicopter mainly provides an installation interface and support for mass modules such as an engine, a transmission, a rotor wing, fuel oil, a tail section structure, an undercarriage and airborne equipment, and maintains the appearance of the whole helicopter.

The main body of the unmanned helicopter is a main bearing structure of the unmanned helicopter, bears and balances the full-aircraft aerodynamic load and the loads transmitted by the mass blocks, and specifically comprises the following steps: 1, bearing pneumatic load; 2 bearing the tension of the rotor wing; 3 bearing the inertia load of the engine; 4 bearing the inertial load of the transmission system; 5, bearing the inertial load of the fuel oil; 6 bearing the inertia force, bending moment and torque transmitted by the tail section structure; 7 bear the inertial loads of the respective onboard equipment.

As shown in fig. 1, the main body of the integrated unmanned helicopter of the invention comprises a main body outer skin component, a main reducer platform 5, an oil tank component and a main body frame beam component which are respectively formed; the main machine body frame beam assembly is connected inside the main machine body outer skin assembly, and the oil tank assembly is connected between the main machine body outer skin assembly and the main machine body frame beam assembly; the main reducing platform 5 and the oil tank assembly are arranged on the upper part of the main engine body outer skin assembly; the oil tank assembly comprises a left oil tank skin unit 3 and a right oil tank skin unit 4; the main reducing platform 5 is arranged between the top surface of the left tank skin unit 3 and the top surface of the right tank skin unit 4; the top surface of the oil tank assembly, the main reducing platform 5 and the main engine body outer skin assembly form an outer skin of the main engine body of the unmanned helicopter together. A long straight barrel-shaped space is formed inside an outer skin of the unmanned helicopter main body, and an opening structure is arranged at a frame on the rear lower side of the tail of the unmanned helicopter main body.

Specifically, the main machine body external skin assembly comprises a fairing 1, a machine body upper platform unit and a machine body lower platform unit, wherein the machine body upper platform unit comprises a front machine body upper platform 2 and a rear machine body upper platform 6; the body mount unit includes a front body mount 21 and a rear body mount 24.

The fairing 1 adopts a carbon fiber composite material honeycomb sandwich structure, is integrally of a box body structure with side walls and an open upper part and a lower part, has a streamline shape conforming to aerodynamics in appearance, and is obtained by fluid mechanics analysis and calculation; in a flight state, the fairing 1 can be matched with skins of a tail beam, a tail wing and the like to play roles of rectification and drag reduction in the flight process.

As shown in fig. 1, the upper and lower portions of the cowl 1 have stepped portions each having a low front and a high rear. The fairing 1 can be divided into a plurality of blocks according to the stress level, the segment position, the function and the manufacturability, and the blocks are manufactured and molded and finally assembled to form the complete fairing 1.

Meanwhile, the oil tank assembly, the main body frame beam assembly and the like are integrally connected in the fairing 1, so that the fairing 1 can bear pneumatic load together with structural components such as the oil tank assembly, the main body frame beam assembly and the like to participate in the force transmission of the whole unmanned helicopter; that is, the load is transmitted to the body frame beam in the form of shear force, torque, bending moment, and the like.

As shown in fig. 1, preferably, the fairing 1 is provided with a maintenance opening 26, and the maintenance opening 26 can be used for engine maintenance, such that the maintenance work is facilitated, and the flight safety and the service life of the unmanned helicopter are improved.

As shown in fig. 1, a body mounting unit is mounted on a step platform at the upper portion of the cowl 1.

Specifically, a front fuselage upper deck 2 is mounted on a lower first step on the front upper portion of the cowl 1, a rear fuselage upper deck 6 is mounted on a higher second step on the rear upper portion of the cowl 1, and the rear fuselage upper deck 6 is mounted on the rear portion of the second step.

As shown in fig. 7, preferably, a front vent frame 25 is installed at the front of the front body upper deck 2; the front vent frame 25 is communicated with the inside of the cowl 1 to form a front vent.

The main body of the unmanned helicopter at the lower part of the upper platform 2 of the front body is provided with a front equipment cabin which is mainly used for installing avionics, electrical, navigation, flight control and other equipment of the unmanned helicopter.

The front vent frame is used as a ventilation channel and used for providing an air inlet channel for ventilation of an equipment cabin and an engine below the main platform 5 and the front part of the unmanned helicopter main body.

Preferably, the rear fuselage upper deck 6 follows the fairing 1 in the longitudinal direction of the main fuselage of the unmanned helicopter. The inside of the main body of the unmanned helicopter at the lower part of the upper platform 6 of the rear body is a rear equipment cabin which is mainly provided with engine control equipment of the unmanned helicopter.

As shown in fig. 3, a lower body landing unit is mounted on the step floor of the lower portion of the cowl 1.

Specifically, a front fuselage lower platform 21 is mounted on a lower third step platform at the front lower part of the fairing 1, and the front fuselage lower platform 21 is mounted at the front part of the third step platform; the lower front equipment cabin is arranged on the lower front body platform 21 and used for installing navigation system equipment such as inertial navigation equipment and a non-altimeter navigation equipment, and an engine liquid cooling radiator is further arranged in the lower front equipment cabin.

Specifically, a rear body lower platform 24 is installed on a higher fourth step platform at the rear lower part of the fairing 1, and the middle part of the rear body lower platform 24 is hollowed out and used for installing cooling system equipment such as an air cooling radiator.

As shown in fig. 5, the left tank skin unit 3 and the right tank skin unit 4 are mirror-symmetric main structure pieces, are both L-shaped open box body skin structures, and respectively comprise a tank box body part and a tank flanging part; the box bottoms of the 2 oil tank box body parts are arranged oppositely, and the oil tank flanging part is positioned on the outer side and is used for being connected with the external skin assembly of the main machine body. In the state of being stopped on the ground, the left tank skin unit 3 and the right tank skin unit 4 are in a position state where L is rotated 90 ° clockwise, the long side is on and the short side is on the front.

Specifically, the open box body skin structure of the left oil tank skin unit 3 comprises a left oil tank box body 31 and a left oil tank flanging part 32; the open box skin structure of the right tank skin unit 4 includes a right tank box 41 and a right tank outside flange 42. In the integrally formed state, the upper portions and the front portions of the left oil tank box body 31 and the right oil tank box body 41 are portions of the outer skin of the main body of the unmanned helicopter of the present embodiment.

Specifically, the main platform 5 that subtracts is C type box section structure, through structural strength topology optimization design, the main platform 5 that subtracts is provided with the main platform strengthening rib that subtracts on the cross section direction of fuselage, and subtracts the peripheral local position of platform 5 and be provided with the main platform thickening portion that subtracts at the main for splice through the medium temperature secondary or the normal atmospheric temperature is glued and is riveted connection peripheral structure, with the structural efficiency who improves the unmanned helicopter host computer body.

The main reducing platform 5 is arranged between the upper edges of the box bottoms of the left oil tank box body 31 and the right oil tank box body 41 and becomes a part of the outer skin of the unmanned helicopter main body.

As shown in fig. 6, the main reducer platform 5 of the present embodiment preferably adopts 7075 aviation aluminum alloy integral machining piece, and a main reducer mounting point 28 is designed on the main reducer platform. The engine of the unmanned helicopter is arranged in the middle of the helicopter body and is positioned at the position of a main shaft of a rotor wing at the lower part of the main reducing platform 5.

The main reducer platform 5 serves as a part of the core position of the main body of the unmanned helicopter and provides an installation interface and support for a speed reducer of a transmission system. The main reducing platform 5 bears the inertial load of the unmanned helicopter speed reducer and transmits the tension, bending moment and torque of a rotor wing to a main machine frame beam assembly of the unmanned helicopter main machine body.

The main reduction platform 5, the left oil tank box body 31 and the right oil tank box body 41 jointly form the front part of a second step platform of the fairing 1, and are continuously arranged with a rear machine body upper platform 6 positioned at the rear part of the second step platform.

The upper edge of the oil tank assembly is arranged between the front machine body upper platform 2 and the rear machine body upper platform 6; the lower rim of the tank assembly is disposed between the front fuselage lower deck 21 and the rear fuselage lower deck 24. The front parts of the left oil tank box body 31 and the right oil tank box body 41 are connected with the first step and the second step of the fairing 1.

The left oil tank skin unit 3 and the right oil tank skin unit 4 are respectively in sealing riveting with the fairing 1 through the left oil tank flanging part 32 and the right oil tank flanging part 42 to form a closed oil tank cabin which becomes a part of a main structure of a machine body and participates in full machine bearing.

As shown in fig. 4, 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 unmanned helicopter main body, and the frame unit is arranged on each transverse section of the unmanned helicopter main body.

As shown in fig. 2, in particular, the beam unit includes a front body left beam 8 and a front body right beam 9 which are mirror-symmetrical, and a rear body left beam 19 and a rear body right beam 20 which are mirror-symmetrical.

The front fuselage left beam 8 and the front fuselage right beam 9 are main bearing structures of the front fuselage and are used for supporting and transferring avionics equipment, task loads and the like and pneumatic loads which are arranged on the front fuselage part of the unmanned helicopter.

The front air duct is composed of a front fuselage left beam 8, a front fuselage right beam 9, a skin on the front part of the air guide sleeve 1 and the front fuselage upper platform 2, and can be matched with an engine liquid cooling radiator arranged in a front lower equipment cabin to provide a heat radiation environment for engine heat radiation.

The rear fuselage left beam 19 and the rear fuselage right beam 20 are main bearing members of the rear fuselage and mainly bear bending moment and shearing force generated by equipment and a tail beam which are arranged at the rear fuselage part of the unmanned helicopter.

Specifically, the frame unit comprises a front fuselage connection frame 12, a middle fuselage front upper half connection frame 13, a middle fuselage rear connection frame 16 and a tail boom butt-joint frame 7.

The front body connecting frame 12 is mainly used for maintaining the structural appearance of the unmanned helicopter and improving the instability resistance of a longitudinal member in the front of the helicopter, forms a closed box section together with the front body left beam 8, the front body right beam 9, the fairing 1 and the front body upper platform 2, and bears the concentrated load generated by the task load installed at the position of the closed box section.

The upper half connecting frame 13 on the front part of the middle fuselage is used for forming a closed frame with structures such as a speed reducer platform of the unmanned helicopter, a left oil tank box body 31, a right oil tank box body 41 and the like, participating in full-mechanical stress and balancing force and bending moment transmitted from two sides of the fuselage.

The middle fuselage rear connecting frame 16 provides support for the main damping platform 5 and the undercarriage rear pivot of the unmanned helicopter, mainly bears and transmits vertical load, and balances force and bending moment transmitted from two sides of the fuselage of the unmanned helicopter.

The tail beam butt-joint frame 7 is of a C-shaped frame structure and provides an installation interface for a tail section structure. Specifically, the tail boom of the unmanned helicopter is connected with the integrated unmanned helicopter main body through the tail boom butt joint frame 7. Specifically, the tail beam butt-joint frame 7 is transversely arranged at the tail of the unmanned helicopter main body, and the periphery of the tail beam butt-joint frame is riveted with the inner wall surface of the tail end of the unmanned helicopter main body. The inner periphery of the tail beam butt-joint frame 7 is provided with a tail beam butt-joint plane 27, and the tail beam butt-joint plane 27 is used for connecting the tail beam of the unmanned helicopter. The tail beam butt-joint frame 7 can integrate and transmit the inertia force, the aerodynamic force and the like of the tail section structure of the unmanned helicopter to the main body of the unmanned helicopter.

The main reducer platform 5, the oil tank assembly and the main machine frame beam assembly jointly support a main machine outer skin assembly to form an integrated unmanned helicopter main machine body.

Preferably, the integrated unmanned helicopter main body further comprises a reinforcing assembly, and the reinforcing assembly comprises a landing gear fulcrum reinforcing frame unit, an oil tank internal reinforcing frame unit and a middle fuselage bottom reinforcing unit.

As shown in fig. 4, in particular, the landing gear fulcrum reinforcing frame unit includes a landing gear forward fulcrum left reinforcing frame 10, a landing gear forward fulcrum right reinforcing frame 11, a landing gear rear fulcrum left reinforcing member 17, and a landing gear rear fulcrum right reinforcing member 18.

The landing gear front fulcrum left reinforcing frame 10 and the landing gear front fulcrum right reinforcing frame 11 are respectively and specifically located between the lower portions of the front body left beam 8 and the front body right beam 9 and the air guide sleeve 1, and are used for bearing landing load of the front portion of the landing gear and enhancing strength of the part, connected with the air guide sleeve 1.

The landing gear rear pivot left reinforcement 17 and the landing gear rear pivot right reinforcement 18 respectively connect the middle fuselage rear connecting frame 16 with the rear fuselage left beam 19 and the rear fuselage right beam 20 on two sides of the main fuselage of the unmanned helicopter, and the upper surfaces respectively directly or indirectly contact and are not fixedly connected with the lower surfaces of the rear parts of the oil tank skin box bodies in the left oil tank skin unit 3 and the right oil tank skin unit 4. The left reinforcing piece 17 of the rear supporting point of the undercarriage and the right reinforcing piece 18 of the rear supporting point of the undercarriage are used for integrating with a frame beam assembly of the main machine body, so that the structural strength of the main machine body of the unmanned helicopter is enhanced; meanwhile, the landing gear rear pivot left reinforcement 17 and the landing gear rear pivot right reinforcement 18 bear relatively large landing load at the rear part of the landing gear, so that the landing gear rear pivot left reinforcement 17 and the landing gear rear pivot right reinforcement 18 are not fixedly connected with the oil tank skin box body and the skin of the air guide sleeve 1; therefore, the landing gear rear pivot left reinforcing piece 17 and the landing gear rear pivot right reinforcing piece 18 connect the main machine body frame beam assembly into a whole, meanwhile, the damage of the landing load to the oil tank and the skin of the air guide sleeve 1 is avoided, and the strength and the service life of the main machine body of the unmanned helicopter are improved.

Specifically, as shown in fig. 4, the tank inside reinforcing frame unit includes a left tank inside reinforcing frame 14 and a right tank inside reinforcing frame 15. The left and right tank inner reinforcement frames 14 and 15 each include a plurality of tank reinforcement sub-frames therein, each disposed in a tank skin box.

Taking the left tank inner reinforcement frame 14 as an example, preferably, the left tank inner reinforcement frame 14 of the present embodiment includes a first tank reinforcement frame 141, a second tank reinforcement frame 142, a third tank reinforcement frame 143, and a fourth tank reinforcement frame 144, which are sequentially disposed from front to back. All be provided with the central oilhole of crossing on 4 oil tank reinforcing subframe, on the one hand can improve fuel tank rigidity, and on the other hand can prevent that the fuel from excessively shaking, can also not hinder the inside fuel flow of oil tank yet.

Preferably, each oil tank reinforcing frame is provided with a side oil passing hole at least on one of the upper side and the lower side; under the condition of less fuel, no matter the flight state of the unmanned helicopter, the fuel can still flow without being blocked by the reinforcing sub-frame of the fuel tank.

The outer side edge of each oil tank reinforcing sub-frame is connected with the inner wall surface of the air guide sleeve 1, and the inner wall surfaces of the skin box bodies of the oil tanks are connected with the other three peripheries of the oil tank reinforcing sub-frame, so that the air guide sleeve 1 is effectively supported while the strength of an oil tank assembly is enhanced.

Preferably, the fourth tank reinforcing frame 144 of the present embodiment is located at the position of the rear fuselage connecting frame 16 on the main body of the integrated unmanned helicopter, so as to reinforce the structural integration strength of the tank assembly.

The right tank inner reinforcing frame 15 has the same technical effects as above.

At the bottom of the midbody, the pod 1 is unsupported. The bottom reinforcing unit of the middle machine body is arranged to be used as a support for reinforcing the weak strength link of the air guide sleeve 1.

As shown in fig. 3, specifically, the middle fuselage bottom reinforcing unit includes a middle fuselage bottom left reinforcing member 22 and a middle fuselage bottom right reinforcing member 23, which are mirror-symmetrical structures and are mirror-symmetrical in installation position.

Take the bottom left reinforcement 22 of the middle fuselage as an example. The middle body bottom left reinforcement 22 is a bent plate structure, and comprises a left rear upper plate, an inclined plate and a left front lower plate which are formed in one step. The rear end of the left rear upper plate is connected with a middle machine body rear connecting frame 16, and the upper surface of the left rear upper plate is connected with the outside of the rear part of the box bottom of the left oil box body 31. The front end of the left front lower plate is connected with the lower end of the L short side of the left oil tank box body 31; in the integrated unmanned helicopter main body, the outer side surface of a left reinforcing piece 22 at the bottom of the main body is shaped and connected with the air guide sleeve 1. Because the left reinforcing member 22 at the bottom of the middle machine body is connected to the inner wall of the air guide sleeve 1 in a broken line form and is connected with the oil tank assembly and the main machine body frame beam assembly, the structural strength of the air guide sleeve 1 at the bottom of the middle machine body is enhanced powerfully. The middle fuselage bottom strengthening unit is used for maintaining the structural appearance of the main fuselage of the unmanned helicopter, supporting the fairing 1, improving the bearing capacity of the fairing 1, and bearing and transmitting bending moment and axial load.

In the integrated unmanned helicopter main body, units and parts respectively contained in a main body external skin assembly, a main damping platform 5, an oil tank assembly, a main body beam and a frame assembly which are respectively formed adopt composite materials and are connected in a medium-temperature secondary glue joint or normal-temperature glue riveting connection mode. Wherein the parts with larger area are provided with lightening holes. Wherein, the medium temperature of the secondary cementing refers to about 125 ℃.

Preferably, the parts with larger area are provided with lightening holes, the central oil passing holes are formed in the reinforcing frame unit in the oil tank, and the oil passing holes are all provided with flanging structures, so that the strength of the parts is increased, and the structural strength of the whole unmanned helicopter main body is beneficially improved. The part with a larger area is provided with lightening holes, and the function of allowing airflow to pass through and reducing air resistance is achieved.

The integrated unmanned helicopter main body provided by the invention has a direct force transmission structure:

the main reducer platform 5 of the main body of the integrated unmanned helicopter bears the inertial load transmitted by the rotor and the speed reducer of the unmanned helicopter and transmits the tension, the bending moment and the torque of the rotor to the frame and beam assembly of the main body.

The tail beam butt-joint frame 7 and the tail beam butt-joint plane 27 of the integrated unmanned helicopter main body provide a mounting interface for a tail section structure of the unmanned helicopter, and inertia force, aerodynamic force and the like of the tail section structure are integrated and transmitted to the unmanned helicopter main body. The tail beam is butted with a C-shaped frame of the frame 7, and can better transmit the torque of the tail section.

The fairing 1 and internal structures such as an oil tank assembly, a main machine body frame beam assembly and the like are integrally jointed through intermediate-temperature secondary connection or normal-temperature glue riveting, so that the fairing 1 can bear and balance an engine, transmission, a fuel system comprising the oil tank assembly, inertial loads of all airborne equipment and inertial force, bending moment and torque transmitted by a tail section structure of the unmanned helicopter together with structural components such as the oil tank assembly and the main machine body frame beam assembly. The fairing 1 simultaneously transfers the load to the main frame beam assembly in the form of shear, torque, bending moment, etc. The main machine body frame beam assembly is arranged at the arrangement position of the main mass block, and the concentrated load is dispersed and balanced respectively along the transverse direction and the longitudinal direction of the machine body through the frame and the beam. The reinforcing frame which is locally arranged on the frame beam component of the main machine body is mainly used for maintaining the structural appearance and improving the instability resistance of the machine body. The fairing 1, the main reducing platform 5, the oil tank assembly and the main machine frame beam assembly jointly form a direct force transmission structure of the integrated unmanned helicopter. The integrated unmanned helicopter main body has an excellent airflow channel structure: the windward side of the foremost end of the main body of the integrated unmanned helicopter is provided with a front vent frame 25 as an air inlet of an air inlet channel of the whole helicopter, so that the front flying airflow is utilized to the maximum extent, and the heat of a power cabin below a main reducing platform 5 can be dissipated; in the flight process of the unmanned helicopter, airflow is introduced into a long straight barrel-shaped space inside the unmanned helicopter main body through the front vent frame 25 until heat flows out from an opening of a lower side frame at the rear of the tail of the unmanned helicopter main body. The front vent frame 25, the long straight barrel-shaped space inside the unmanned helicopter main body and the opening of the lower side frame behind the tail of the unmanned helicopter main body form an integrated airflow channel structure of the unmanned helicopter main body.

The inner skin of the oil tank is used as the main structure of the heat dissipation channel, the surface transition is smooth, and the airflow disorder can be avoided.

The main structure of the integrated unmanned helicopter main body adopts an integrated structure design, and the manufacturability and the product consistency are good; parts such as the fairing 1, the oil tank assembly, the main machine body frame beam assembly, the main weight reducing platform 5 and the like all adopt 7075 aviation aluminum alloy and fiber reinforced composite materials, wherein the fairing 1 adopts a carbon fiber composite material honeycomb sandwich structure, is integrally connected in a medium-temperature secondary gluing or normal-temperature gluing riveting mode, is simple and convenient in forming process and high in material utilization rate, greatly reduces the number of parts, has an obvious weight reducing effect, and reduces the total weight by more than 20% compared with a truss structure.

The integrated unmanned helicopter main body adopts the integrated design of the fuel tank structure, so that space is gained for carrying fuel on the helicopter while the weight of the helicopter body is reduced, and the weight efficiency of the unmanned helicopter is improved.

The integrated unmanned helicopter main body has the advantages of simple structure, convenience in installation and high space utilization rate.

The above is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art without departing from the technical scope of the present invention are also encompassed by the present invention. Meanwhile, all the equipment carrying the device can expand the application field and generate composite technical effects, and the device belongs to the protection scope of the method.

Claims (10)

1. The integrated unmanned helicopter main body is characterized by comprising a main body outer skin assembly, a main reducer platform (5), an oil tank assembly and a main body frame beam assembly;

the oil tank assembly is arranged at the upper part of the main machine frame beam assembly, and the oil tank assembly and the main machine frame beam assembly are both connected to the inner wall surface of the main machine outer skin assembly;

the oil tank assembly comprises a left oil tank skin unit (3) and a right oil tank skin unit (4); the main reducing platform (5) is arranged between the left oil tank skin unit (3) and the right oil tank skin unit (4);

the main machine body outer skin assembly, the main reducer platform (5), the oil tank assembly and the main machine body frame beam assembly are respectively formed and integrally connected.

2. The main fuselage of the integrated unmanned helicopter of claim 1 characterized in that said main fuselage external skin assembly comprises a fairing (1), a fuselage upper deck unit and a fuselage lower deck unit.

3. The integrated unmanned helicopter main body according to claim 2, characterized in that said fuselage upper unit comprises a front fuselage upper (2) and a rear fuselage upper (6); the fuselage sill unit comprises a front fuselage sill (21) and a rear fuselage sill (24).

4. The unmanned helicopter main body of one piece according to claim 3, characterized in that the upper portion of said main step-down platform (5) and fuel tank assembly is disposed between said front fuselage upper deck (2) and rear fuselage upper deck (6); the lower part of the oil tank assembly is arranged between the front fuselage lower platform (21) and the rear fuselage lower platform (24).

5. The main fuselage of the integral unmanned helicopter of any of claims 1 to 4, characterized in that the main body structures of the left tank skin unit (3) and the right tank skin unit (4) are mirror images and are both open box skin structures.

6. The main fuselage of an integral unmanned helicopter of claim 5, characterized in that said left tank skin unit (3) and right tank skin unit (4) each comprise a tank box portion and a tank cuff portion, said tank cuff portion being connected to said main fuselage outer skin assembly.

7. The integrated unmanned helicopter main body of claim 6 wherein said main body frame beam assembly comprises a frame unit and a beam unit; the beam unit is arranged on the longitudinal section of the unmanned helicopter main body, and the frame unit is arranged on the transverse section of the unmanned helicopter main body.

8. The unmanned helicopter main body of one piece according to claim 7, characterized in that said beam elements comprise mirror symmetric front left and right fuselage beams (8, 9), mirror symmetric rear left and right fuselage beams (19, 20).

9. The integrated unmanned helicopter main body according to claim 7, characterized in that said frame unit comprises a front fuselage connection frame (12), a middle fuselage front upper half connection frame (13), a middle fuselage rear connection frame (16) and a tail boom docking frame (7).

10. The main body of the integrated unmanned helicopter of any of claims 1-4 and 6-9, wherein the units and parts of the main body outer skin assembly, the main reducer platform (5), the fuel tank assembly and the main body beam frame assembly are all made of composite materials and are connected by medium-temperature secondary glue or normal-temperature glue riveting.

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