Small single-rotor unmanned helicopter and truss type structure thereof

Abstract

The utility model belongs to the technical field of aircraft structure design, and discloses a small single-rotor unmanned helicopter and a truss type structure thereof. The truss type structure comprises a main truss and a connecting piece. The main truss is formed by welding a plurality of steel pipes made of 304 stainless steel materials; the connecting pieces are of various types, are made of 304 stainless steel and are fixedly welded to the preset positions of the main truss correspondingly. The connecting piece is used for detachably installing corresponding equipment. The technical scheme disclosed by the utility model has the characteristics that the force transmission path is more direct, the equipment is more convenient to mount, dismount and maintain, the processing difficulty is low, the replaceability is strong and the like; the problems that according to a wall plate type structure of an existing small single-rotor unmanned helicopter, a force transmission path is not direct, the space for detecting and maintaining internal equipment is insufficient, replaceability and universality are poor, the helicopter body structure is prone to being damaged due to the fact that the local part of the helicopter body structure bears large loads, and the detection and maintenance cost is high are solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft structure design, and particularly relates to a small single-rotor unmanned helicopter and a truss structure thereof. Background Art

[0002] A single-rotor helicopter is a helicopter equipped with only one rotor and a tail rotor or other balancing device at the tail. It is the most technologically mature, largest in number, and most widely used helicopter. It has the advantages of simple structure, low maintenance difficulty, and long flight time. It can perform highly maneuverable actions such as vertical take-off and hovering.

[0003] Currently, the existing body structure design of small single-rotor unmanned helicopters relies heavily on a panel structure. This panel structure is usually composed of aluminum alloy panels and is manufactured through precision machining processes such as turning and milling. This design meets the structural requirements of unmanned helicopters to a certain extent, but it also has a series of problems that need to be solved, including:

[0004] 1) The force transmission path of the wall-plate structure is not direct enough: Due to the complex structure, the load needs to pass through multiple components and connection points during the transmission process. This not only increases the complexity of the structure, but may also lead to reduced force transmission efficiency, thereby affecting the flight performance and stability of the unmanned helicopter;

[0005] 2) The wall-panel structure has obvious deficiencies in the inspection and maintenance of internal equipment: Due to the compact structure and limited internal space, it is difficult for inspectors to conduct comprehensive and detailed inspections and maintenance of the equipment. This not only increases the difficulty of inspection and maintenance, but may also lead to equipment failure or damage due to the inability to discover and solve problems in a timely manner;

[0006] 3) The wall panel structure has poor replaceability and versatility: once a component fails or needs to be upgraded, it is often necessary to replace the entire wall panel or perform complex processing and modification, which not only increases maintenance costs but may also affect the overall performance of the unmanned helicopter due to component mismatch or insufficient processing accuracy;

[0007] 4) The panel structure is easily damaged due to large loads on a part of the body structure. Explanatoryally, during flight, the unmanned helicopter may be subjected to various external loads, such as wind and vibration. If the body structure is subjected to excessive loads, it may cause the panel to deform, crack, and other damage.

[0008] 5) The inspection and maintenance costs of the wall-panel structure are also relatively high. Explanation: the wall-panel structure is difficult to inspect and maintain, and has a long inspection and maintenance cycle, requiring a large amount of manpower and material resources. This not only increases operating costs, but may also cause malfunctions or accidents in the unmanned helicopter due to untimely or inadequate maintenance. Utility Model Content

[0009] The purpose of the present invention is to provide a small single-rotor unmanned helicopter and its truss structure to solve one or more of the above-mentioned technical problems. The truss structure for a small single-rotor unmanned helicopter disclosed in the present invention has the characteristics of a more direct force transmission path, easier installation and disassembly and maintenance of equipment, low processing difficulty, and strong interchangeability. It solves the problems of the wall plate structure of existing small single-rotor unmanned helicopters, such as an indirect force transmission path, insufficient space for testing and maintenance of internal equipment, poor interchangeability and versatility, easy damage due to localized heavy loads on the body structure, and high testing and maintenance costs.

[0010] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0011] In a first aspect, the present invention provides a truss structure for a small single-rotor unmanned helicopter, comprising: a main truss and a connecting member;

[0012] The main truss is welded from multiple 304 stainless steel pipes; wherein the multiple 304 stainless steel pipes include transverse steel pipes, longitudinal steel pipes and supporting steel pipes;

[0013] There are many types of connecting parts, made of 304 stainless steel, which are fixedly welded to the preset positions of the main truss respectively; wherein, the connecting parts are used for detachable installation of corresponding equipment.

[0014] A further improvement of the present invention is that:

[0015] The connecting pieces include: a first connecting piece, a second connecting piece, a fourth connecting piece, a fifth connecting piece, a sixth connecting piece, a seventh connecting piece, a ninth connecting piece, an eleventh connecting piece, a twelfth connecting piece, a thirteenth connecting piece, a fourteenth connecting piece, a fifteenth connecting piece, a sixteenth connecting piece, and a seventeenth connecting piece;

[0016] Among them, the first connecting member is used for the detachable installation of the cooling fan; the second connecting member is used for the detachable installation of the air intake filter; the fourth connecting member is used for the detachable installation of the landing gear; the fifth connecting member is used for the detachable installation of the engine; the sixth connecting member is used for the detachable installation of the generator; the seventh connecting member is used for the detachable installation of the flight control computer; the ninth connecting member is used for the detachable installation of the electrical control box; the eleventh connecting member is used for the detachable installation of the relay; the twelfth connecting member is used for the detachable installation of the tail boom; the thirteenth connecting member is used for the detachable installation of the power management module; the fourteenth connecting member is used for the detachable installation of the rectifier; the fifteenth connecting member is used for the detachable installation of the control system; the sixteenth connecting member is used for the detachable installation of the starter motor; and the seventeenth connecting member is used for the detachable installation of the reducer.

[0017] A further improvement of the present invention is that:

[0018] The first connecting member is arranged on the outside of the top end of the head of the main truss; the second connecting member is arranged on the outside of the front end of the head of the main truss; the fourth connecting member is arranged on the outside of the bottom end of the head and the outside of the bottom end of the tail of the main truss; the fifth connecting member and the sixth connecting member are both arranged on the inside of the bottom end of the middle part of the main truss; the seventh connecting member is arranged on the supporting steel pipe in the middle of the main truss; the ninth connecting member is arranged on the inside of the bottom end of the tail of the main truss; the eleventh connecting member is arranged on the inside of the top end of the tail of the main truss; the twelfth connecting member is arranged on the upper outside of the rear end of the tail of the main truss; the thirteenth connecting member and the fourteenth connecting member are both arranged on the outside of the top end of the tail of the main truss; the fifteenth connecting member is arranged on the inside of the top end of the middle part of the main truss; the sixteenth connecting member and the seventeenth connecting member are both arranged on the top end of the middle part of the main truss.

[0019] A further improvement of the present invention is that:

[0020] The connecting piece further comprises:

[0021] The third connecting piece is used for installing mission equipment.

[0022] A further improvement of the present invention is that:

[0023] The connecting piece further comprises:

[0024] The eighth connecting piece is used for installing the RTK airborne terminal.

[0025] A further improvement of the present invention is that:

[0026] The connecting piece further comprises:

[0027] The tenth connecting piece is used for installing the tail beam diagonal support rod.

[0028] A further improvement of the present invention is that:

[0029] Also included: engines and generators;

[0030] The engine is detachably mounted on the fifth connecting member, the generator is detachably mounted on the sixth connecting member, and the engine and the generator are connected via a tensioner and a synchronous belt.

[0031] A further improvement of the present invention is that:

[0032] Also includes: a starter motor;

[0033] The starter motor is detachably mounted on the sixteenth connecting member, and the engine is connected to the starter motor via gear transmission.

[0034] A further improvement of the present invention is that:

[0035] Also includes: speed reducer and steering system;

[0036] The reducer is detachably mounted on the seventeenth connecting member, and the operating system is detachably mounted on the fifteenth connecting member; the output shaft of the engine is connected to the synchronous pulley of the reducer, and the synchronous pulley of the reducer is connected to the operating system through a synchronous belt.

[0037] A second aspect of the present invention provides a small single-rotor unmanned helicopter, which adopts the truss structure described in any one of the first aspects of the present invention.

[0038] Compared with the prior art, the present invention has the following beneficial effects:

[0039] The utility model discloses a truss structure for a small single-rotor unmanned helicopter, which adopts a mature and reliable stainless steel welding process. The core advantage is that the force transmission path is more direct and efficient, ensuring rapid and accurate force transmission, thereby improving the stability and response speed of the overall structure; in addition, compared with the wall plate structure in the existing technical solution, the technical solution of the utility model adopts the technical means of the main truss and connecting parts. The main truss structure is extremely convenient in installation, disassembly and maintenance of equipment, and fully considers the needs of actual operation, so that users can easily get started when performing operations, greatly saving time and energy. At the same time, this structure also reduces the processing difficulty, making the manufacturing process smoother, helping to improve production efficiency and reduce costs; in addition, the corresponding equipment can be detachably installed through the connecting parts, with excellent replaceability. During the use of the drone, once a component fails or needs to be upgraded, it is only necessary to replace the corresponding component without the need for large-scale changes to the entire structure. This feature not only improves the maintainability of the drone, but also extends its service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below; obviously, the drawings described below are some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0041] Figure 1 This is a front view structural diagram of a truss structure of a small single-rotor unmanned helicopter in an embodiment of the present utility model;

[0042] Figure 2 This is a schematic diagram of the axial structure of a truss structure of a small single-rotor unmanned helicopter in an embodiment of the present utility model;

[0043] The explanation of the reference numerals in the figures is as follows:

[0044] 1. First connecting member; 2. Second connecting member; 3. Third connecting member; 4. Fourth connecting member; 5. Fifth connecting member; 6. Sixth connecting member; 7. Seventh connecting member; 8. Eighth connecting member; 9. Ninth connecting member; 10. Tenth connecting member; 11. Eleventh connecting member; 12. Twelfth connecting member; 13. Thirteenth connecting member; 14. Fourteenth connecting member; 15. Fifteenth connecting member; 16. Sixteenth connecting member; 17. Seventeenth connecting member. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention; it is obvious that the technical solutions of the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0046] All other embodiments obtained by persons of ordinary skill in the art based on the technical solutions disclosed in the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units that are not explicitly listed or that are inherent to these processes, methods, products, or apparatuses.

[0047] See also Figure 1 and Figure 2 The embodiment of the present invention provides a truss structure of a small single-rotor unmanned helicopter, comprising: a main truss and a connecting member; wherein,

[0048] The main truss is welded by multiple 304 stainless steel pipes; wherein the multiple 304 stainless steel pipes include transverse steel pipes, longitudinal steel pipes and support steel pipes; in the preferred technical solution, the main truss can be welded by laser welding; in a further exemplary technical solution, the main truss includes 4 transverse steel pipes, 7 longitudinal steel pipes and 8 vertical support steel pipes, such as Figure 2 As shown;

[0049] The main truss is provided with a variety of connectors for equipment installation in a fixed or detachable manner at a preset position, and the connectors are used for detachably installing corresponding equipment.

[0050] The truss structure for a small single-rotor unmanned helicopter disclosed in the embodiment of the present invention adopts a mature and reliable stainless steel welding process. Its core advantage is that the force transmission path is more direct and efficient, ensuring rapid and accurate force transmission, thereby improving the stability and response speed of the overall structure. In addition, compared with the wall plate structure in the existing technical solution, the technical solution of the embodiment of the present invention adopts the technical means of the main truss. The truss structure is extremely convenient in terms of installation, disassembly and maintenance of equipment. It fully considers the needs of actual operation, allowing users to easily get started when performing operations, greatly saving time and energy. At the same time, this structure also reduces the difficulty of processing, making the manufacturing process smoother, helping to improve production efficiency and reduce costs. The truss structure of the embodiment of the utility model also has excellent replaceability. During the use of the drone, once a component fails or needs to be upgraded, it only needs to replace the corresponding component without the need for large-scale changes to the entire structure. This feature not only improves the maintainability of the drone, but also extends its service life.

[0051] To further explain, regarding the material selection, although the density of stainless steel is relatively larger than that of aluminum alloy, the utility model fully utilizes the high strength limit characteristics of stainless steel by optimizing the structural design, which enables the structural size to be significantly reduced while maintaining the same load-bearing capacity; therefore, although a higher density material is used, the structural weight cost is almost zero. This innovative design not only ensures that the flight performance of the UAV is not affected, but also further improves its overall cost-effectiveness and market competitiveness.

[0052] In a specific embodiment of the present invention, the multiple connectors specifically include:

[0053] The first connecting member 1 is used for installing the cooling fan;

[0054] The second connecting piece 2 is used for installing the air intake filter;

[0055] The third connecting piece 3 is used for installing specific task equipment;

[0056] The fourth connecting member 4 is used for installing the landing gear;

[0057] The fifth connecting member 5 is used for installing the engine;

[0058] The sixth connecting member 6 is used for installing the generator;

[0059] The seventh connecting piece 7 is used for installing the flight control computer;

[0060] The eighth connecting member 8 is used for installing the RTK (Real Time Kinematic) airborne terminal;

[0061] The ninth connecting piece 9 is used for installing the electrical control box;

[0062] The tenth connecting member 10 is used for installing the tail beam diagonal brace;

[0063] The eleventh connecting piece 11 is used for installing the relay;

[0064] The twelfth connecting piece 12 is used for installing the tail beam;

[0065] A thirteenth connecting member 13 is used for installing a power management module;

[0066] A fourteenth connecting piece 14 is used for mounting the rectifier;

[0067] The fifteenth connecting piece 15 is used for installing the control system;

[0068] A sixteenth connecting member 16 is used for mounting the starter motor;

[0069] The seventeenth connecting piece 17 is used for installing the reducer.

[0070] See also Figure 1 and Figure 2 In a further preferred technical solution of the embodiment of the present utility model,

[0071] The first connecting member 1 may be arranged on the outside of the top end of the head of the main truss;

[0072] The second connecting member 2 may be arranged on the outside of the front end of the head of the main truss;

[0073] The fourth connecting member 4 may be provided on the outer side of the bottom end of the head portion and the outer side of the bottom end of the tail portion of the main truss;

[0074] The fifth connecting member 5 and the sixth connecting member 6 may be arranged on the inner side of the bottom end of the middle portion of the main truss;

[0075] The seventh connecting member 7 can be arranged on the supporting steel pipe in the middle of the main truss;

[0076] The ninth connecting member 9 may be provided on the inner side of the bottom end of the tail portion of the main truss;

[0077] The eleventh connecting member 11 may be provided on the inner side of the top end of the tail portion of the main truss;

[0078] The twelfth connecting member 12 may be provided at the upper outer portion of the rear end of the main truss;

[0079] The thirteenth connecting member 13 and the fourteenth connecting member 14 may be arranged on the outer side of the top end of the tail portion of the main truss;

[0080] The fifteenth connecting member 15 may be provided on the inner side of the top end of the middle portion of the main truss;

[0081] The sixteenth connecting member 16 and the seventeenth connecting member 17 may both be disposed at the top end of the middle portion of the main truss.

[0082] In a specific embodiment of the present invention, each connecting member is detachably fixedly connected to the installation device by bolts. The connecting member can be a fixed connecting plate provided with bolt mounting holes.

[0083] In an application embodiment of the present invention, the fifth connecting member 5 is equipped with an engine, which is connected to the generator installed on the sixth connecting member 6 through a tensioner and a synchronous belt, and is connected to the starter motor installed on the sixteenth connecting member 16 through a gear transmission. The output shaft is connected to the synchronous pulley of the main reducer installed on the seventeenth connecting member 17, and the synchronous pulley is connected to the control system installed on the fifteenth connecting member 15 through a synchronous belt, forming a complete power-transmission-control system.

[0084] In a specific embodiment of the present invention, the main truss structure and the connecting parts are both made of 304 stainless steel and are welded by laser welding. After the entire machine is installed, there is still a large space inside the machine body, which is conducive to the inspection, maintenance, and disassembly and replacement of the equipment. In addition, the truss structure is more direct in transmitting both aerodynamic loads and impact loads when landing, making the structural strength higher.

[0085] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be included in the scope of protection of the claims of the present invention.

Claims

1. A truss structure of a small single-rotor unmanned helicopter, characterized in that: include: Main trusses and connections; The main truss is welded from multiple 304 stainless steel pipes; wherein the multiple 304 stainless steel pipes include transverse steel pipes, longitudinal steel pipes and supporting steel pipes; There are many types of connecting parts, made of 304 stainless steel, which are fixedly welded to the preset positions of the main truss respectively; wherein, the connecting parts are used for detachable installation of corresponding equipment.

2. The truss structure of a small single-rotor unmanned helicopter according to claim 1, characterized in that: The connecting pieces include: a first connecting piece (1), a second connecting piece (2), a fourth connecting piece (4), a fifth connecting piece (5), a sixth connecting piece (6), a seventh connecting piece (7), a ninth connecting piece (9), an eleventh connecting piece (11), a twelfth connecting piece (12), a thirteenth connecting piece (13), a fourteenth connecting piece (14), a fifteenth connecting piece (15), a sixteenth connecting piece (16) and a seventeenth connecting piece (17); wherein the first connecting member (1) is used for the detachable installation of the cooling fan; the second connecting member (2) is used for the detachable installation of the air intake filter; the fourth connecting member (4) is used for the detachable installation of the landing gear; the fifth connecting member (5) is used for the detachable installation of the engine; the sixth connecting member (6) is used for the detachable installation of the generator; the seventh connecting member (7) is used for the detachable installation of the flight control computer; the ninth connecting member (9) is used for the detachable installation of the electrical control box; the eleventh connecting member (11) is used for the detachable installation of the relay; the twelfth connecting member (12) is used for the detachable installation of the tail beam; the thirteenth connecting member (13) is used for the detachable installation of the power management module; the fourteenth connecting member (14) is used for the detachable installation of the rectifier; the fifteenth connecting member (15) is used for the detachable installation of the control system; the sixteenth connecting member (16) is used for the detachable installation of the starter motor; and the seventeenth connecting member (17) is used for the detachable installation of the reducer.

3. The truss structure of a small single-rotor unmanned helicopter according to claim 2, characterized in that: The first connecting member (1) is arranged on the outside of the top end of the head of the main truss; the second connecting member (2) is arranged on the outside of the front end of the head of the main truss; the fourth connecting member (4) is arranged on the outside of the bottom end of the head and the outside of the bottom end of the tail of the main truss; the fifth connecting member (5) and the sixth connecting member (6) are both arranged on the inside of the bottom end of the middle part of the main truss; the seventh connecting member (7) is arranged on the supporting steel pipe in the middle part of the main truss; the ninth connecting member (9) is arranged on the bottom end of the tail of the main truss the inner side of the end; the eleventh connecting member (11) is arranged on the inner side of the tail top of the main truss; the twelfth connecting member (12) is arranged on the upper outer side of the rear end of the main truss; the thirteenth connecting member (13) and the fourteenth connecting member (14) are both arranged on the outer side of the tail top of the main truss; the fifteenth connecting member (15) is arranged on the inner side of the middle top of the main truss; the sixteenth connecting member (16) and the seventeenth connecting member (17) are both arranged on the middle top of the main truss.

4. The truss structure of a small single-rotor unmanned helicopter according to claim 2, characterized in that: The connecting piece further comprises: The third connecting piece (3) is used for installing the mission equipment.

5. The truss structure of a small single-rotor unmanned helicopter according to claim 2, characterized in that: The connecting piece further comprises: The eighth connecting piece (8) is used for installing the RTK airborne terminal.

6. The truss structure of a small single-rotor unmanned helicopter according to claim 2, characterized in that: The connecting piece further comprises: The tenth connecting piece (10) is used for installing the tail beam diagonal brace.

7. The truss structure of a small single-rotor unmanned helicopter according to claim 2, characterized in that: Also included: engines and generators; The engine is detachably mounted on the fifth connecting member (5), the generator is detachably mounted on the sixth connecting member (6), and the engine and the generator are connected via a tensioner and a synchronous belt.

8. The truss structure of a small single-rotor unmanned helicopter according to claim 7, characterized in that: Also includes: a starter motor; The starter motor is detachably mounted on the sixteenth connecting member (16), and the engine and the starter motor are connected via gear transmission.

9. The truss structure of a small single-rotor unmanned helicopter according to claim 7, characterized in that: Also includes: speed reducer and steering system; The reducer is detachably mounted on the seventeenth connecting member (17), and the operating system is detachably mounted on the fifteenth connecting member (15); the output shaft of the engine is connected to the synchronous pulley of the reducer, and the synchronous pulley of the reducer is connected to the operating system through a synchronous belt.

10. A small single-rotor unmanned helicopter, characterized in that: The truss structure according to any one of claims 1 to 9 is adopted.

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