Aircraft mooring cable anti-twist structure
By setting the first rigid section and the second rigid section on the aircraft and using carbon fiber rods to limit the position of the cables, the problem of the cables getting entangled in the propellers is solved, and safe and reliable flight control is achieved.
Patent Information
- Application Number
- CN202422543203.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-16
- Publication Date
- 2025-09-23
- Estimated Expiration
- 2034-10-16
AI Technical Summary
When the aircraft is tethered from top to bottom, the reserved cables can easily get tangled in the propellers, affecting flight safety.
The first rigid section and the second rigid section are used to limit the position of the reserved cable of the aircraft. The first rigid section is set outside the rotation range of the propeller, and the second rigid section is set above the first rigid section. The hardened section composed of carbon fiber rods is used to prevent the cable from being entangled in the propeller.
Ensure that the reserved cables do not enter the propeller's rotation range to avoid entanglement, ensure flight safety, and minimize interference with the flight control system.
Smart Images
Figure CN223371137U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of aircraft technology, and in particular to an anti-twisting structure for aircraft mooring cables. Background Art
[0002] When tethered from above, aircraft are susceptible to unexpected situations, such as wind disturbances. Considering the responsiveness of flight control, the tether cables should not be stretched straight, but rather require a certain length to accommodate dynamic adjustments. Therefore, ensuring that these cables do not become entangled in the propellers is a key design consideration for flight safety. Utility Model Content
[0003] (1) Technical problems to be solved
[0004] The present application provides an anti-twisting structure for aircraft tethered cables, which solves the problem of how to ensure that reserved cables will not be entangled in the propeller.
[0005] (2) Technical solution
[0006] The present application provides an anti-tangle structure for an aircraft tethered cable, comprising a first rigid section and a second rigid section; the first rigid section is flexibly connected to the aircraft fuselage and is arranged outside the rotation range of the aircraft propeller; the second rigid section is flexibly connected to the first rigid section and is arranged above the first rigid section; the first rigid section and the second rigid section are used to limit the position of the aircraft reserved cable in the air.
[0007] Furthermore, the first rigid section is flexibly connected to the center of the aircraft fuselage.
[0008] Furthermore, the first rigid section is arranged on a symmetric plane of the aircraft fuselage.
[0009] Furthermore, the length of the first rigid section is greater than the maximum distance between the connection between the first rigid section and the aircraft fuselage and the edge of the aircraft propeller protective cover.
[0010] Furthermore, the second rigid section includes a plurality of hardened sections, and two adjacent hardened sections are flexibly connected.
[0011] Furthermore, the first rigid section and the second rigid section are arranged on the same vertical plane.
[0012] Furthermore, the first rigid section and the second rigid section are both made of carbon fiber rods.
[0013] Furthermore, the first rigid section and the second rigid section are used to pass through the periphery of the aircraft reserved cable to limit the position of the aircraft reserved cable in the air.
[0014] Furthermore, the first rigid section and the second rigid section are used to be bonded to the outside of the aircraft reserved cable to limit the position of the aircraft reserved cable in the air.
[0015] (3) Beneficial effects
[0016] The above technical solution of this application has the following advantages:
[0017] The aircraft tethered cable anti-tangle structure provided in the present application limits the position of the aircraft's reserved cable in the air by using the first rigid section and the second rigid section, so that the position of the aircraft's reserved cable in the air can always be limited by the first rigid section and the second rigid section, and the first rigid section is arranged outside the rotation range of the aircraft's propeller, and the second rigid section is arranged above the first rigid section, so that the aircraft's reserved cable will never enter the rotation range of the aircraft's propeller, thereby ensuring that the reserved cable will not be entangled in the propeller. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the specific implementation methods or the description of the prior art. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.
[0019] Figure 1 Schematic diagram of the anti-twisting structure for aircraft tethering cables provided in this application.
[0020] Figure numerals: 1, first rigid section; 2, second rigid section; 21, hardened section; 3, fuselage; 4, propeller; 5, reserved cable. DETAILED DESCRIPTION
[0021] The following embodiments are used to illustrate the present invention, but are not intended to limit the scope of the present invention.
[0022] In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inside," "outside," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended only to facilitate the description of this application and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting this application. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0023] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.
[0024] References to "one embodiment" or "some embodiments" in this specification mean that a particular feature, structure, or characteristic described in conjunction with the embodiment is included in one or more embodiments of the present application. Thus, phrases such as "in one embodiment," "in some embodiments," "in other embodiments," and "in yet other embodiments" appearing in various places in this specification do not necessarily refer to the same embodiment, but rather mean "one or more but not all embodiments," unless otherwise specifically emphasized.
[0025] The following embodiments are used to illustrate the present invention, but are not intended to limit the scope of the present invention.
[0026] like Figure 1 As shown, an embodiment of the present application provides an anti-tangle structure for an aircraft tethered cable, comprising a first rigid section 1 and a second rigid section 2; the first rigid section 1 is flexibly connected to the aircraft fuselage 3 and is arranged outside the rotation range of the aircraft propeller 4; the second rigid section 2 is flexibly connected to the first rigid section 1 and is arranged above the first rigid section 1; the first rigid section 1 and the second rigid section 2 are used to limit the position of the aircraft reserved cable 5 in the air.
[0027] The reserved cable can be segmented and hardened into multiple rigid sections using appropriately rigid rods, such as carbon fiber rods. By controlling the length of each section, the reserved cable can be protected from kinking. The joints between the hardened sections remain flexible and unhardened, preventing the reserved cable from kinking while minimizing interference with the flight control system.
[0028] In this embodiment, the first rigid section 1 and the second rigid section 2 are used to limit the position of the aircraft reserved cable 5 in the air, so that the position of the aircraft reserved cable 5 in the air can always be limited by the first rigid section 1 and the second rigid section 2, and the first rigid section is arranged outside the rotation range of the aircraft propeller 4, and the second rigid section 2 is arranged above the first rigid section 1, so that the aircraft reserved cable 5 will never enter the rotation range of the aircraft propeller 4, thereby ensuring that the reserved cable will not be entangled in the propeller.
[0029] The first rigid section 1 is flexibly connected to the aircraft fuselage 3, and the second rigid section 2 is flexibly connected to the first rigid section 1, so that the first rigid section 1 and the second rigid section 2 can still be stretched as the reserved cable is stretched, thereby facilitating the top-down operation of the aircraft, while ensuring that the cables do not get tangled and minimizing interference with the flight control system.
[0030] In some embodiments, the first rigid section 1 is flexibly connected to the center of the aircraft fuselage 3 .
[0031] In some embodiments, the first rigid section 1 is disposed on a symmetric plane of the aircraft fuselage 3 .
[0032] In some embodiments, the length of the first rigid section 1 is greater than the maximum distance between the connection between the first rigid section 1 and the aircraft fuselage 3 and the edge of the protective cover of the aircraft propeller 4 .
[0033] In some embodiments, the second rigid section 2 includes a plurality of hardening sections 21 , and two adjacent hardening sections 21 are flexibly connected.
[0034] In some embodiments, the first rigid section 1 and the second rigid section 2 are arranged on the same vertical plane.
[0035] In some embodiments, the first rigid section 1 and the second rigid section 2 are both made of carbon fiber rods.
[0036] In some embodiments, the first rigid section 1 and the second rigid section 2 are used to pass through the outer periphery of the aircraft reserved cable 5 to limit the position of the aircraft reserved cable 5 in the air.
[0037] In some embodiments, the first rigid section 1 and the second rigid section 2 are used to be bonded to the outside of the aircraft reserved cable 5 to limit the position of the aircraft reserved cable 5 in the air.
[0038] In this embodiment, the method of hardening the reserved cable by the first rigid section and the second rigid section includes but is not limited to: passing the reserved cable through the carbon fiber rod; and bonding the reserved cable and the carbon fiber rod.
[0039] For aircraft without propeller guards, the structure of the connection between the first rigid section and the fuselage needs to be processed to limit the direction of this section, such as allowing it to rotate only on the symmetric plane of the fuselage to prevent twisting.
[0040] For aircraft with propeller protection covers, anti-twisting can be achieved by limiting the direction of the first rigid section, or by simply controlling the length of the first rigid section to be greater than the maximum distance between the connection between the first rigid section and the aircraft fuselage and the edge of the aircraft propeller protection cover.
[0041] The anti-tangle structure for aircraft tethered cables provided in an embodiment of the present application uses a first rigid section and a second rigid section to limit the position of the aircraft's reserved cable in the air, so that the position of the aircraft's reserved cable in the air can always be limited by the first rigid section and the second rigid section. The first rigid section is arranged outside the rotation range of the aircraft's propeller, and the second rigid section is arranged above the first rigid section, so that the aircraft's reserved cable will never enter the rotation range of the aircraft's propeller, thereby ensuring that the reserved cable will not be entangled in the propeller.
[0042] Those skilled in the art will clearly understand that, for the convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiments can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. In addition, the specific names of the functional units and modules are only for the purpose of distinguishing each other and are not used to limit the scope of protection of this application.
[0043] It should be noted that the various embodiments in this specification are described in a progressive manner. Reference can be made to the same or similar parts between the various embodiments. Each embodiment focuses on the differences from other embodiments. This application is not limited to the specific structures described above and shown in the figures. Furthermore, for the sake of brevity, detailed descriptions of known methods and technologies are omitted here.
[0044] The above-described embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present application, and should all be included in the scope of protection of the present application.
Claims
1. An anti-twisting structure for aircraft mooring cables, characterized in that: It includes a first rigid section and a second rigid section; the first rigid section is flexibly connected to the aircraft fuselage and is arranged outside the rotation range of the aircraft propeller; the second rigid section is flexibly connected to the first rigid section and is arranged above the first rigid section; the first rigid section and the second rigid section are used to limit the position of the aircraft reserved cable in the air.
2. The aircraft mooring cable anti-twisting structure according to claim 1, characterized in that: The first rigid section is flexibly connected to the center of the aircraft fuselage.
3. The aircraft mooring cable anti-twisting structure according to claim 1, characterized in that: The first rigid section is arranged on a symmetric plane of the aircraft fuselage.
4. The aircraft mooring cable anti-twisting structure according to claim 1, wherein: The length of the first rigid section is greater than the maximum distance between the connection between the first rigid section and the aircraft fuselage and the edge of the aircraft propeller protective cover.
5. The anti-twisting structure for aircraft mooring cables according to claim 1, wherein: The second rigid section includes a plurality of hardening sections, and two adjacent hardening sections are flexibly connected.
6. The aircraft mooring cable anti-twisting structure according to claim 1, wherein: The first rigid section and the second rigid section are arranged on the same vertical plane.
7. The aircraft mooring cable anti-twisting structure according to claim 1, wherein: The first rigid section and the second rigid section both use carbon fiber rods.
8. The aircraft mooring cable anti-twisting structure according to claim 1, wherein: The first rigid section and the second rigid section are used to pass through the outer periphery of the aircraft reserved cable to limit the position of the aircraft reserved cable in the air.
9. The aircraft mooring cable anti-twisting structure according to claim 1, wherein: The first rigid section and the second rigid section are used to be bonded to the outside of the aircraft reserved cable to limit the position of the aircraft reserved cable in the air.