A unmanned helicopter fuselage truss structure

Abstract

The present application relates to the technical fields of helicopter manufacturing, in particular to a unmanned helicopter fuselage truss structure, comprising: an engine truss, a first partition frame, a reducer truss and a second partition frame; the engine truss comprises a pair of first fixing points, second fixing points, third fixing points, fourth fixing points, and first mounting points, second mounting points, landing gear mounting points; the first partition frame and the second partition frame are connected through the reducer truss. The truss structure improves the stability of the helicopter engine and the reducer installation, stabilizes the center of gravity of the helicopter fuselage, maintains the fuselage structure strength, improves the load capacity of the fuselage, and meets the load flight requirements of the helicopter.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of helicopter manufacturing, in particular to a unmanned helicopter fuselage truss structure. BACKGROUND

[0002] As one of the most distinctive creations of aviation technology in the 20th century, helicopters greatly expand the application range of aircraft. Helicopters are typical dual-purpose military and civilian products, which can be widely used in transportation, patrol, tourism, rescue and other fields.

[0003] At present, in the manufacturing process of unmanned helicopters, the fuselage is prepared by composite materials, and the engine, reducer and other power transmission components are installed inside the fuselage. The structural strength of the fuselage determines the installation coefficient during flight, but the existing fuselage structure is not convenient for the installation of the engine and the reducer, which leads to poor fuselage stability, insufficient fuselage structural strength, and unstable center of gravity, and certain safety hazards during load flight. In view of this, we propose a unmanned helicopter fuselage truss structure. SUMMARY

[0004] The purpose of the present application is to provide a unmanned helicopter fuselage truss structure to solve the problems raised in the background art.

[0005] To achieve the above purpose, the present application provides the following technical scheme:

[0006] A unmanned helicopter fuselage truss structure, comprising: an engine truss, a first partition frame, a reducer truss and a second partition frame; the engine truss comprises a pair of first fixed points, second fixed points, third fixed points, fourth fixed points, and first mounting points, second mounting points, landing gear mounting points; wherein the pair of first fixed points, second fixed points, third fixed points, fourth fixed points are symmetrically fixed on the upper part, middle upper part, middle lower part and lower part of the front vertical surface of the first partition frame; the first mounting point is provided with a group, and the first mounting point and the first fixed point, second fixed point are connected and fixed by a support; the second mounting point is provided with two groups, and the second mounting point and the second fixed point, third fixed point, fourth fixed point are connected and fixed by a support; the landing gear mounting point and the fourth fixed point are connected and fixed by a support; the first partition frame and the second partition frame are connected by the reducer truss.

[0007] Preferably, the first fixed point and the second fixed point, the second fixed point and the third fixed point, the third fixed point and the fourth fixed point, the first mounting point and the second mounting point, and the second mounting point and the landing gear mounting point are connected and fixed by a support.

[0008] Preferably, the first mounting point and the two groups of second mounting points form an isosceles triangle.

[0009] Preferably, the first mounting point and the two groups of second mounting points form an isosceles triangle.

[0010] Preferably, the first mounting point and the two groups of second mounting points form an isosceles triangle.

[0011] Preferably, the first mounting point and the two groups of second mounting points form an isosceles triangle.

[0012] Preferably, the first mounting point and the two groups of second mounting points form an isosceles triangle.

[0013] Compared with the prior art, the unmanned helicopter fuselage truss structure has the beneficial effects that: the engine is mounted on the engine truss through bolts, the stability of engine installation is improved, and the helicopter landing gear is mounted through the support column, which is used for transmitting the gravity of the engine to the hub on the landing gear, the helicopter reducer is mounted on the reducer truss, the gravity center of the helicopter fuselage is stabilized, so that the truss structure cooperates with the engine truss, the reducer truss and the two groups of partition frames to maintain the structural strength of the fuselage, improve the load capacity of the fuselage, and meet the load flight requirements of the helicopter. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 is a schematic view of the overall structure of the present application;

[0015] Figure 2 is a schematic view of the overall structure of the present application;

[0016] In the figure:

[0017] 1. engine truss; 11. first fixed point; 12. second fixed point; 13. third fixed point; 14. fourth fixed point; 15. first mounting point; 16. second mounting point; 17. landing gear mounting point; 171. strut;

[0018] 2. first bulkhead; 21. first mounting window;

[0019] 3. reducer truss; 31. first frame; 32. first positioning point; 33. second positioning point; 34. third positioning point; 35. fourth positioning point; 36. second frame;

[0020] 4. second bulkhead; 41. second mounting window. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0022] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0023] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "setting" should be understood broadly, for example, it can be fixedly connected, set, or detachably connected, set, or integrally connected, set. For those skilled in the art, the specific meaning of the above terms in the present patent can be understood according to the specific circumstances.

[0024] In addition, the terms "first", "second", "third", "fourth" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second", "third", "fourth" can explicitly or implicitly include one or more features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise explicitly specified and limited.

[0025] Referring to Figure 1 and Figure 2 As shown in the technical scheme provided by the present application:

[0026] An unmanned helicopter fuselage truss structure, comprising: an engine truss 1, a first bulkhead 2, a reducer truss 3 and a second bulkhead 4; the engine truss 1 comprises a pair of first fixing points 11, second fixing points 12, third fixing points 13, fourth fixing points 14, and first mounting points 15, second mounting points 16 and landing gear mounting points 17; wherein the pair of first fixing points 11, second fixing points 11, third fixing points 13 and fourth fixing points 14 are symmetrically fixed on the upper, middle upper, middle lower and lower parts of the front vertical surface of the first bulkhead 2; the first mounting points 15 are provided in a group, and the first mounting points 15 are fixed by supports between the first fixing points 11 and the second fixing points 12; the second mounting points 16 are provided in two groups, and the second mounting points 16 are fixed by supports between the second fixing points 12, the third fixing points 13 and the fourth fixing points 14; the landing gear mounting points 17 are fixed by a support 171 between the fourth fixing points 14; the first bulkhead 2 and the second bulkhead 4 are connected by the reducer truss 3; the reducer truss 3 comprises a first frame 31, first positioning points 32, second positioning points 33, third positioning points 34, fourth positioning points 35 and a second frame 36; the four corners of the first frame 31 are fixed on the rear vertical surface of the first bulkhead 2, and the four corners of the second frame 36 are fixed on the front vertical surface of the second bulkhead 4; the first positioning points 32, the second positioning points 33 and the third positioning points 34 are arranged in a rectangle between the first bulkhead 2 and the second bulkhead 4, and the first positioning points 32 are fixed by an inclined support between the upper left corner of the first frame 31 and the upper left corner of the second frame 36; the second positioning points 33 are fixed by an inclined support between the upper right corner of the first frame 31 and the upper left and right corners of the second frame 36; the third positioning points 34 are fixed by an inclined support between the lower left and right corners of the first frame 31 and the lower left corner of the second frame 36; and the fourth positioning points 35 are fixed by an inclined support between the lower right corner of the first frame 31 and the lower right corner of the second frame 36.Therefore, through the truss structure, the first partition frame 2 and the second partition frame 4 can be installed in the fuselage by means of bonding with composite glue or threaded connection, the helicopter engine is installed through the engine truss 1, and the helicopter reducer is installed through the reducer truss 3. Specifically, the engine is installed on the first mounting point 15 and the second mounting point 16 through bolts. Since the first mounting point 15 and the second mounting point 16 are connected to the fixing point 14 on the first partition frame 2 through a plurality of groups of supports, the stability of the engine installation is improved, and the fourth fixing point 14 is installed on the helicopter landing gear through the support 171, for transmitting the gravity of the engine to the hub of the landing gear. Similarly, the reducer truss 3 between the first partition frame 2 and the second partition frame 4 installs the helicopter reducer through four positioning points, and the four positioning points connect the first partition frame 2 and the second partition frame 4 through a plurality of groups of inclined braces, so that the reducer is located between the two partition frames, and the gravity center of the helicopter fuselage is stable. In this way, the truss structure cooperates with the engine truss 1, the reducer truss 3 and the two groups of partition frames to maintain the structural strength of the fuselage, improve the load capacity of the fuselage, and meet the load flight requirements of the helicopter.

[0027] It is worth noting that the first fixing point 11 and the second fixing point 12, the second fixing point 12 and the third fixing point 13, the third fixing point 13 and the fourth fixing point 14, the first mounting point 15 and the second mounting point 16, and the second mounting point 16 and the landing gear mounting point 17 are connected and fixed through the supports. The plurality of groups of supports further improve the structural strength of the engine truss 1, and make the helicopter engine installation more stable and improve the safety factor of the helicopter during flight.

[0028] Further, the first mounting point 15 and the two groups of second mounting points 16 are arranged in an isosceles triangle. The triangular structure has good stability and is convenient for installing the helicopter engine.

[0029] In addition, the first fixing point 11, the second fixing point 12, the third fixing point 13, the fourth fixing point 14 and the first partition frame 2 are connected and fixed through bolts and nuts. The engine truss 1 can be installed on the first partition frame 2 through the four fixing points.

[0030] Specifically, the first partition frame 2 is provided with a first installation window 21, and the second partition frame 4 is provided with a second installation window 41. The transmission shaft between the helicopter engine and the reducer, and the transmission shaft between the reducer and the tail reducer are installed.

[0031] In addition, the four corners of the first frame 31 and the first partition frame 2, and the four corners of the second frame 36 and the second partition frame 4 are connected and fixed through the bolts and nuts. The first frame 31 and the second frame 36 of the reducer truss 3 are installed and fixed, and the reducer truss 3 is provided with a stress mounting point.

[0032] The unmanned helicopter fuselage truss structure of the embodiment is used, the first partition frame 2 and the second partition frame 4 are arranged to be installed in the fuselage by means of composite glue bonding or threaded connection, the helicopter engine is installed through the arranged engine truss 1, the helicopter reducer is installed through the arranged reducer truss 3, specifically, the engine is installed on the first mounting point 15 and the second mounting point 16 through bolts, since the first mounting point 15 and the second mounting point 16 are connected with the fixed point 14 on the first partition frame 2 through the arranged multiple groups of supports, the stability of the engine installation is improved, and the fourth fixed point 14 is installed with the helicopter landing gear through the arranged support 171, for transmitting the gravity of the engine to the hub on the landing gear, similarly, the reducer truss 3 between the first partition frame 2 and the second partition frame 4 is used to install the helicopter reducer through four positioning points, and the four positioning points are connected with the first partition frame 2 and the second partition frame 4 through multiple groups of inclined braces, so that the reducer is located between the two partition frames, the gravity center of the helicopter fuselage is stabilized, so that the truss structure cooperates with the engine truss 1, the reducer truss 3 and the two groups of partition frames, maintains the fuselage structure strength, improves the load capacity of the fuselage, and meets the load flight requirements of the helicopter.

[0033] The basic principles, main features and advantages of the present application are shown and described above. It should be understood by those skilled in the art that the present application is not limited by the above-mentioned embodiments, and the above-mentioned embodiments and descriptions in the specification are only preferred examples of the present application and are not intended to limit the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. An unmanned helicopter fuselage truss structure, characterized in that: include: An engine truss (1), a first bulkhead (2), a speed reducer truss (3) and a second bulkhead (4); The engine truss (1) includes a first fixing point (11), a second fixing point (12), a third fixing point (13), and a fourth fixing point (14) arranged in pairs, as well as a first mounting point (15), a second mounting point (16), and a landing gear mounting point (17); wherein the first fixing point (11), the second fixing point (12), the third fixing point (13), and the fourth fixing point (14) arranged in pairs are symmetrically fixed to the upper part, the middle upper part, the middle lower part, and the lower part of the front facade of the first bulkhead (2); a group of the first mounting point (15) is provided, and the first mounting point (15) is connected and fixed to the first fixing point (11) and the second fixing point (12) by a bracket; two groups of the second mounting point (16) are provided, and the second mounting point (16) is connected and fixed to the second fixing point (12), the third fixing point (13), and the fourth fixing point (14) by a bracket; the landing gear mounting point (17) is connected and fixed to the fourth fixing point (14) by a provided support (171); The first bulkhead (2) and the second bulkhead (4) are connected via the speed reducer truss (3); The reducer truss (3) includes a first frame (31), a first positioning point (32), a second positioning point (33), a third positioning point (34), a fourth positioning point (35), and a second frame (36); the four corners of the first frame (31) are fixed to the rear facade of the first bulkhead (2), and the four corners of the second frame (36) are fixed to the front facade of the second bulkhead (4); the first positioning point (32), the second positioning point (33), the third positioning point (34), and the fourth positioning point (35) are arranged in a rectangular shape between the first bulkhead (2) and the second bulkhead (4), and the first positioning point (32) and the first frame The upper left corner of the first frame (31) and the upper left corner of the second frame (36) are connected and fixed by a set diagonal brace; the second positioning point (33) and the upper right corner of the first frame (31), and the upper left corner and upper right corner of the second frame (36) are connected and fixed by a set diagonal brace; the third positioning point (34) and the lower left corner and lower right corner of the first frame (31), and the lower left corner of the second frame (36) are connected and fixed by a set diagonal brace; the fourth positioning point (35) and the lower right corner of the first frame (31), and the lower right corner of the second frame (36) are connected and fixed by a set diagonal brace; The first mounting point (15) and the two groups of the second mounting points (16) are arranged in an isosceles triangle.

2. The unmanned helicopter fuselage truss structure according to claim 1, characterized in that: The first fixing point (11) and the second fixing point (12), the second fixing point (12) and the third fixing point (13), the third fixing point (13) and the fourth fixing point (14), the first mounting point (15) and the second mounting point (16), and the second mounting point (16) and the landing gear mounting point (17) are all connected and fixed by means of a provided bracket.

3. The unmanned helicopter fuselage truss structure according to claim 1, characterized in that: The first fixing point (11), the second fixing point (12), the third fixing point (13), the fourth fixing point (14) and the first bulkhead (2) are fixed by bolts and nuts.

4. The unmanned helicopter fuselage truss structure according to claim 1, characterized in that: The first bulkhead (2) is provided with a first installation window (21), and the second bulkhead (4) is provided with a second installation window (41).

5. The unmanned helicopter fuselage truss structure according to claim 1, characterized in that: The four corners of the first frame (31) and the first bulkhead (2), and the four corners of the second frame (36) and the second bulkhead (4) are connected and fixed by provided bolts and nuts.

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