Roof hanging device of aircraft

Abstract

The utility model provides an aircraft roof hanging device, including tensile cable subassembly, cardan joint subassembly, power supply communication conversion subassembly and aircraft roof adapter bracket subassembly, tensile cable subassembly includes support tube and support tube connecting piece, cardan joint subassembly both ends are connected with support tube connecting piece and power supply communication conversion subassembly respectively, and the support tube connecting piece is connected with the power supply communication conversion subassembly. The power supply communication conversion assembly is fixedly provided with a roof adapter bracket assembly, the roof adapter bracket assembly is provided with a hoop, the hoop is connected with an aircraft, and the tensile cable provides safety guarantee and / or power supply and communication for the aircraft through the tensile cable assembly, the universal joint assembly, the power supply communication conversion assembly and the roof adapter bracket assembly respectively. The aircraft top suspension device is applied to multi-degree-of-freedom, power supply and communication aircraft tests and other commercial applications, meets the requirements of flight control debugging such as unlimited endurance, pitching, rolling and yaw turning of an aircraft under different working conditions, ensures normal development of flight tests or flight experiences such as flight control debugging of the aircraft, and is safe and reliable.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, especially relates to a top hanging device of aircraft. BACKGROUND

[0002] The aircraft system comprises a flight platform, a related remote control station, a required command and control data link and other system components. The aircraft has strong control performance, is a kind of expensive and easily damaged equipment, and many advanced flight control algorithms are immature and unstable, which can easily lead to the damage of the flight aircraft during test flight, cause the equipment to be damaged, and result in the great economic loss of the related research participants. In addition, due to the defects of the flight control algorithm or the mistakes of the operator, the aircraft may lose control during test flight, which not only causes the damage of the aircraft itself, but also may endanger the personal safety of the test flight participants.

[0003] The existing aircrafts have irresistible factors during flight control test and commercial flight experience, which may cause the aircraft to be damaged. The common safeguard measures for the aircraft during flight control test are to use a hook rope or a single degree of freedom hanging mechanism, but these measures have great limitations for the attitude transformation of the aircraft. In addition, for the electric aircraft, there are problems such as the inconvenience of battery replacement or the time-consuming and laborious charging. Even if the power cable is connected to the aircraft for power supply by the hook rope or the single degree of freedom hanging mechanism, the power cable may be wound or twisted multiple times, which may cause the cable to break and lead to power interruption or even short circuit, thereby endangering the product and personal safety.

[0004] With the development of aircraft technology, the wide application of unmanned aerial vehicles, helicopters and other flight equipment puts forward higher requirements for the hanging device. In the prior art, the hanging device of the aircraft usually has the following problems: lack of universality, difficult to adapt to various types of aircraft. Complex structure, inconvenient operation, low efficiency. Insufficient safety measures may cause the aircraft to fall off or be damaged during the hanging process. UTILITY MODEL CONTENT

[0005] The utility model aims at providing a top hanging device of aircraft, which aims to solve the technical problems of the prior art, such as the great limitation of the attitude transformation of the aircraft caused by the cable, the inconvenience of battery replacement or the time-consuming and laborious charging of the electric aircraft, and the lack of universality and the difficulty in adapting to various types of aircraft.

[0006] In order to solve the above technical problems, the utility model adopts the technical scheme, provide a kind of aircraft's machine top hanging device, including tensile cable assembly, universal joint assembly, power supply communication conversion component and machine top switching support assembly, the tensile cable assembly includes support tube and support tube connecting piece, the universal joint assembly two ends are respectively connected with the support tube connecting piece and power supply communication conversion component, the power supply communication conversion component is fixed machine top switching support assembly, the machine top switching support assembly is equipped with fastener, the fastener is connected with aircraft, tensile cable is respectively passed through tensile cable assembly, universal joint assembly, power supply communication conversion component and machine top switching support assembly to provide security and / or power supply, communication for aircraft.

[0007] Further, the support tube connecting piece includes the support tube upper connecting piece and the support tube lower connecting piece, the support tube upper connecting piece is provided with a wire outlet hole, and the support tube connecting piece is provided with an open cable at the end and connected with the universal joint assembly.

[0008] Further, the support tube is provided with a protective cap at the end, and the wire outlet hole is provided with a wire protection ring.

[0009] Further, the universal joint assembly includes an upper fork arm, a cross shaft and a lower fork arm, the upper fork arm is provided with a universal joint connecting piece connected with the support tube connecting piece, the cross shaft is coupled with the upper fork arm and the lower fork arm to form a universal joint, and the other end of the lower fork arm is connected with the power supply communication conversion component.

[0010] Further, the upper fork arm is provided with an upper fork arm wire protection ring inside, the cross shaft is provided with a universal joint wire protection ring inside, the outer side of the cross shaft is provided with a cross shaft bushing, and the outer side of the cross shaft bushing is provided with a bearing bush.

[0011] Further, the power supply communication conversion component includes a limiting clamp, a bearing inner ring fixed shaft, a bearing, a bearing outer ring fixed cylinder and a conductive slip ring, the limiting clamp is connected with the universal joint assembly, the bearing is fixed by the bearing inner ring fixed shaft and the bearing outer ring fixed cylinder, and the conductive slip ring is connected with the tensile cable.

[0012] Further, the bearing is a double-row angular contact ball bearing, and the bearing inner ring fixed shaft is fixed in the double-row angular contact ball bearing.

[0013] Further, the conductive slip ring includes a rotor end wire, a conductive stator and a stator fixed seat, the rotor end wire is connected with the tensile cable, and the conductive stator is fixed on the stator fixed seat.

[0014] Further, the upper and lower ends of the bearing are respectively provided with a bearing inner ring shoulder and a bearing seat shoulder.

[0015] Further, the fastener comprises a fuselage fixing plate and a hoop, the fuselage fixing plate is fixed on the power supply communication conversion assembly, and the hoop is arranged around the fuselage fixing plate, and the hoop connects the top hanging device with the aircraft.

[0016] The aircraft top hanging device has the advantages that: the aircraft top hanging device comprises a tensile cable assembly, a universal joint assembly, a power supply communication conversion assembly and a top switching support assembly, the tensile cable provides safety guarantee and / or power supply and communication for the aircraft through the tensile cable assembly, the universal joint assembly, the power supply communication conversion assembly and the top switching support assembly, the aircraft top hanging device can realize multi-degree-of-freedom, power supply and communication aircraft test and other commercial application top hanging devices, meets different working conditions of the aircraft, unlimited endurance, pitch, roll and yaw turning and other flight control debugging, and ensures that the flight control debugging and other flight tests of the aircraft are normally carried out and safe and reliable. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical scheme in the embodiments of the utility model, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced below, and obviously, the drawings in the following description are only some embodiments of the utility model, and for those skilled in the art, other drawings can be obtained according to these drawings without creative labor.

[0018] Figure 1 It is a structural schematic view of the aircraft top hanging device of the utility model;

[0019] Figure 2 It is a tensile cable assembly schematic view of the aircraft top hanging device of the utility model;

[0020] Figure 3 It is a universal joint sectional schematic view of the aircraft top hanging device of the utility model;

[0021] Figure 4 It is a power supply communication conversion assembly schematic view of the aircraft top hanging device of the utility model;

[0022] Figure 5 It is a schematic view of the universal joint assembly and the power supply communication conversion assembly of the utility model after assembly;

[0023] Figure 6 It is a top switching support assembly schematic view of the aircraft top hanging device of the utility model;

[0024] Figure 7The utility model relates to a kind of aircraft's machine top hanging device usage state reference drawing.

[0025] Label explanation:

[0026] 10, tensile cable assembly;11, support tube;12, support tube upper connector;

[0027] 13, support tube lower connector;14, outlet hole;15, open cable;

[0028] 16, protective cap;17, wire protection ring;20, universal joint assembly;

[0029] 21, upper fork arm;22, upper fork arm wire protection ring;23, cross shaft;

[0030] 24, universal joint wire protection ring;25, cross shaft bushing;26, bearing bush;

[0031] 27, lower fork arm;28, through hole;29, connecting hole;

[0032] 30, power supply communication conversion assembly;31, limiting clamp;32, bearing inner ring fixed shaft;

[0033] 33, bearing inner ring shoulder;34, double-row angular contact ball bearing;35, bearing outer ring fixed cylinder;

[0034] 36, bearing seat shoulder;37, conductive slip ring;38, stator fixing seat

[0035] 40, machine top switching support assembly;41, fuselage fixed plate;42, clamp one;

[0036] 43, clamp two;44, clamp three;45, clamp four;

[0037] 50, tensile cable;60, aircraft. DETAILED DESCRIPTION

[0038] The embodiments of the utility model are described in detail below, examples of the embodiments are shown in the drawings, wherein the same or similar reference signs represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary, and are intended to explain the utility model, and cannot be understood as a limitation of the utility model.

[0039] In the description of this utility model, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0040] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0041] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0042] like Figures 1-7 As shown, this embodiment of the present invention provides a top-mounted device for an aircraft, including a tensile cable assembly 10, a universal joint assembly 20, a power supply and communication conversion assembly 30, and a top-mounted adapter bracket assembly 40. The tensile cable assembly 10 includes a support pipe 11 and a support pipe connector. The two ends of the universal joint assembly 20 are respectively connected to the support pipe connector and the power supply and communication conversion assembly 30. The top-mounted adapter bracket assembly 40 is fixed on the power supply and communication conversion assembly 30. The top-mounted adapter bracket assembly 40 is provided with fasteners, which are connected to the aircraft 60. The tensile cable 50 provides safety protection and / or power supply and communication for the aircraft 60 through the tensile cable assembly 10, the universal joint assembly 20, the power supply and communication conversion assembly 30, and the top-mounted adapter bracket assembly 40. The tensile cable can be a simple load-bearing rope, or it can be composed of a power supply cable and / or a communication cable. The power supply cable provides the required power and can be made of a metal material with good conductivity, such as a copper core or an aluminum core; the load-bearing rope provides tensile strength protection and can be made of a high-strength material, such as a steel wire rope or a fiber rope. Power cables and / or communication cables may be combined with the load-bearing rope or kept separate.

[0043] The top hanging device is connected with the tensile cable assembly 10 and the power supply communication conversion assembly through the universal joint assembly 20, and is connected with the aircraft. The universal joint assembly can realize multi-degree of freedom to meet the flight control debugging or flight experience of the aircraft pitching, rolling and yawing, etc. The aircraft flight control debugging or flight experience activity can be carried out normally and safely and reliably. The aircraft 60 can move smoothly and freely in different motion modes. When the aircraft continuously yaws, the flexible components such as cables do not wind. The connection component of the tensile cable and the aircraft has a certain strength, which can ensure that the aircraft is safe and limited in movement distance, speed and direction under the action of inertial force and impact force. The cable can also provide a power supply loop or signal transmission for the aircraft, realizing multi-degree of freedom safety protection, power supply and communication in one.

[0044] Please refer to Figure 2 The support pipe connecting piece includes a clamped support pipe upper connecting piece 12 and a support pipe lower connecting piece 13. The support pipe upper connecting piece is provided with a wire outlet hole 14. The support pipe connecting piece is provided with an open cable joint 15 connected with the universal joint assembly 20. The support pipe and the support pipe connecting piece have a certain rigidity, which ensures the safe distance between the aircraft 60 and the cable, thereby avoiding the safety hazard of winding the aircraft.

[0045] Please refer to Figure 2 The support pipe 11 is provided with a mouth cap 16 at the end, and the wire outlet hole 14 is provided with a wire protection ring 17. Specifically, the open cable joint 15 is installed and fixed at the joint of the support pipe connecting piece. The mouth cap 16 is sleeved on one end of the support pipe 11. The tensile cable 50 is passed through the support pipe 11 without the mouth cap 16 at one end. The support pipe upper connecting piece 13 and the tensile cable support rod lower connecting piece 13 are fixed and limited by a certain number of internal hexagonal cylindrical head screws, flat washers and self-locking nuts to fix the support pipe 11 and the open cable joint 15. The wire protection ring 17 is installed on the support rod upper connecting piece 12. The wire of the tensile cable 50 is passed out of the wire protection ring 17. The mouth cap and the wire protection ring are arranged to effectively protect the tensile cable and prevent the tensile cable from being worn.

[0046] Please refer to Figure 3 and Figure 5As shown, the universal joint assembly 20 includes an upper cross arm 21, a cross shaft 23, and a lower cross arm 27. The upper cross arm 21 is provided with a universal joint connector connected with a support tube connector. The cross shaft 23 is coupled with the upper cross arm 21 and the lower cross arm 23 to form a universal joint. The other end of the lower cross arm 27 is connected with the power supply communication conversion assembly 30. By using the universal joint assembly, the tensile cable is connected with the aircraft through the hanging device, and multiple degrees of freedom can be achieved to meet the flight control debugging or flight experience of the aircraft, such as pitching, rolling, and yawing, to ensure the normal development and safe and reliable operation of the flight control debugging or flight experience of the aircraft. Preferably, the upper cross arm 21 is provided with a connecting hole 29, and the open cable 15 is inserted into the connecting hole for fixation, which facilitates the connection of the tensile cable assembly and the universal joint assembly and facilitates assembly. The cross shaft 23 is provided with a through hole 28, and the tensile cable 50 passes through the through hole 28 to further prevent the tensile cable from winding.

[0047] Please refer to Figure 3 and Figure 5 As shown, the upper cross arm 21 is provided with an upper cross arm wire protection ring 22, the cross shaft 23 is provided with a universal joint wire protection ring 24, the outer side of the cross shaft is provided with a cross shaft bushing 25, and the outer side of the cross shaft bushing 25 is provided with a bearing bush 26. The wire protection ring is arranged to effectively protect the tensile cable and prevent the tensile cable from being worn.

[0048] Specifically, the cross shaft bushing 25 is interference press-fitted on the cross shaft 23, the flanged sliding bearing is installed on the press-fitted cross shaft bushing 25, the relevant parts are installed on the lower cross arm 27, the bearing bush 26 is fixed on the lower cross arm 27 by a certain number of hexagonal head screws and double-ear washers, the upper cross arm 21 and the bearing bush 26 are fixed with the cross shaft 23 by a certain number of hexagonal head screws and double-ear washers, and the upper cross arm wire protection ring 22 and the universal joint wire protection ring 24 are installed in the upper cross arm 21 and the cross shaft 23 of the universal joint, respectively. After ensuring the strength and rigidity requirements, the structure is simple and compact, the degree of freedom stroke is large, the work is stable and reliable, the service life is long, the cost is low, and the disassembly and assembly are convenient.

[0049] Please refer to Figure 4 , Figure 5 As shown, the power supply communication conversion assembly includes a limiting clamp 31, a bearing inner ring fixing shaft 32, a bearing, a bearing outer ring fixing cylinder 35, and a conductive slip ring 37. The limiting clamp 31 is connected with the universal joint assembly 20. The bearing is fixed by the bearing inner ring fixing shaft 32 and the bearing outer ring fixing cylinder 35. The conductive slip ring 37 is connected with the tensile cable 50.

[0050] Please refer to Figure 4As shown, the bearing is a double row angular contact ball bearing 34, and the bearing inner ring fixing shaft 32 is fixed to the double row angular contact ball bearing 34. Specifically, the double row angular contact ball bearing 34 is installed in the bearing outer ring fixing cylinder 35, and the bearing seat shoulder 36 is fixed in the bearing outer ring fixing cylinder 35 by a certain number of inner hexagonal cylindrical head screws, flat washers and spring washers. The bearing inner ring fixing shaft 32 is installed in the inner ring of the double row angular contact ball bearing 34, and the conductive slip ring 37 is fixed in the stator fixing seat 38 by a certain number of inner hexagonal cylindrical head screws, flat washers and self-locking nuts. The rotor end wire of the conductive slip ring 37 passes through the bearing inner ring fixing shaft 32, and the conductive slip ring 37 and the stator fixing seat 38 are fixed together with the bearing outer ring fixing cylinder 35 by a certain number of inner hexagonal cylindrical head screws, flat washers and self-locking nuts. Thus, the assembly of the power supply communication conversion assembly is completed. After ensuring certain strength and rigidity requirements, the structure is simple and compact, has large freedom travel, stable and reliable work, long service life, low cost and easy disassembly and assembly.

[0051] Please refer to Figure 4 As shown, the conductive slip ring 37 includes a rotor end wire, a conductive stator and a stator fixing seat 38, and the rotor end wire is connected with the tensile cable 50.

[0052] Please refer to Figure 4 As shown, the upper and lower ends of the bearing are respectively provided with a bearing inner ring shoulder 33 and a bearing seat shoulder 36.

[0053] Specifically, the universal joint assembly 20 and the power supply communication conversion assembly 30 are assembled and matched, the bearing inner ring shoulder 33 and the lower fork arm 27 of the universal joint assembly 20 are sleeved on the bearing inner ring fixing shaft 32, the rotor end wire of the conductive slip ring 37 passes through the lower fork arm 27, the cross shaft 23 and the upper fork arm 21 in sequence, and the limiting clamp 31 is used to connect and fix the universal joint assembly 20 and the power supply communication conversion assembly 30 by a certain number of inner hexagonal cylindrical head screws, flat washers and self-locking nuts. The rotor end wire of the conductive slip ring 37 is connected and fixed with the tensile cable 50, and the open cable joint 15 is fixed with the upper fork arm 21 by a certain number of outer hexagonal head bolts, nuts and limiting pins.

[0054] Please refer to Figure 6 , Figure 7As shown, the top-hanging adapter support assembly 40 includes a fuselage fixing plate 41 fixed to the power supply and communication conversion assembly 30 and a clamp around the fuselage fixing plate 41, and the clamp connects the top-hanging device with the aircraft 60. Specifically, the fuselage fixing plate 41 is fixed to the bearing outer ring fixing cylinder 35 by a certain number of inner hexagonal cylindrical head screws, flat washers and self-locking nuts, and then the fuselage fixing plate clamp is fixed to the fuselage fixing plate 41 and the aircraft top mounting position by a certain number of inner hexagonal cylindrical head screws, flat washers, spring washers and rivets. Preferably, the clamp one 42, the clamp two 43, the clamp three 44 and the clamp four 45 are arranged around the fuselage fixing plate, and the clamps are locked to be connected with the aircraft flexibly, not limited to the size of the aircraft fixing frame, and have strong universality and can be adapted to various types of aircraft.

[0055] In summary, the top-hanging device for the aircraft with multiple degrees of freedom, power supply and communication provided by the utility model can supply power and / or ensure safety for the aircraft through the tensile cable assembly, the universal joint assembly, the power supply and communication conversion assembly and the top-hanging adapter support assembly, can realize the top-hanging device for the aircraft with multiple degrees of freedom, power supply and communication, and other commercial applications, can meet the flight control debugging of the aircraft under different working conditions, unlimited endurance, pitch, roll and yaw, and can ensure the normal development and safe and reliable flight test of the aircraft flight control debugging. The top-hanging device for the aircraft provided by the utility model has the advantages of simple and compact structure design, large degree of freedom stroke, stable and reliable work, long service life, low cost, convenient disassembly and assembly, adaptability to various types of aircraft and the like after ensuring the strength and rigidity requirements.

[0056] The above only describes the embodiments of the utility model, and does not limit the patent range of the utility model, and any equivalent transformation or direct or indirect application in the related technical field based on the content of the utility model specification and drawings is also included in the patent protection range of the utility model.

Claims

1. An over-the-wing hanger apparatus for an aircraft, comprising: The application relates to a tension-resistant cable assembly, a universal joint assembly, a power supply and communication conversion assembly and a top-hanging adapter support assembly, wherein the tension-resistant cable assembly comprises a support pipe and a support pipe connector, the universal joint assembly is connected with the support pipe connector and the power supply and communication conversion assembly at two ends, the power supply and communication conversion assembly is fixed with the top-hanging adapter support assembly, the top-hanging adapter support assembly is provided with a fastener, the fastener is connected with an aircraft, and the tension-resistant cable provides safety guarantee and / or power supply and communication for the aircraft through the tension-resistant cable assembly, the universal joint assembly, the power supply and communication conversion assembly and the top-hanging adapter support assembly.

2. A device for stowing a suspended aircraft according to claim 1, characterised in that The support pipe connector comprises a clamped upper support pipe connector and a lower support pipe connector, the upper support pipe connector is provided with a wire outlet hole, and the lower end of the support pipe connector is provided with an open cable and connected with the universal joint assembly.

3. A device according to claim 2, wherein, The lower end of the support pipe is provided with a protective cap, and the wire outlet hole is provided with a wire protection ring.

4. The over-the-wing hanger apparatus of claim 1, wherein, The universal joint assembly comprises an upper fork arm, a cross shaft and a lower fork arm, the upper fork arm is provided with a universal joint connector connected with the support pipe connector, the cross shaft is coupled with the upper fork arm and the lower fork arm to form a universal joint, and the other end of the lower fork arm is connected with the power supply and communication conversion assembly.

5. A device according to claim 4, wherein the device is adapted to be mounted on the underside of the aircraft. The upper fork arm is internally provided with an upper fork arm wire protection ring, the cross shaft is internally provided with a universal joint wire protection ring, the outer side of the cross shaft is provided with a cross shaft bushing, and the outer side of the cross shaft bushing is provided with a bearing bush.

6. The over-the-wing hanger apparatus of claim 1, wherein, The power supply and communication conversion assembly comprises a limiting clamp, a bearing inner ring fixing shaft, a bearing, a bearing outer ring fixing cylinder and a conductive slip ring, the limiting clamp is connected with the universal joint assembly, the bearing is fixed by the bearing inner ring fixing shaft and the bearing outer ring fixing cylinder, and the conductive slip ring is connected with the tension-resistant cable.

7. A device according to claim 6, wherein the device is adapted to be mounted on the underside of the aircraft. The bearing is a double-row angular contact ball bearing, and the bearing inner ring fixing shaft is fixed in the double-row angular contact ball bearing.

8. A ceiling hanger apparatus for an aircraft as defined in claim 6, wherein, The conductive slip ring comprises a rotor end wire, a conductive stator and a stator fixing seat, the rotor end wire is connected with the tension-resistant cable, and the conductive stator is fixed on the stator fixing seat.

9. The over-the-wing hanger apparatus of claim 6, wherein, The upper and lower ends of the bearing are respectively provided with a bearing inner ring shoulder and a bearing seat shoulder.

10. The over-the-wing hanger apparatus of claim 1, wherein, The fastener comprises a fuselage fixing plate and a clamp, the fuselage fixing plate is fixed on the power supply and communication conversion assembly, the clamp is arranged around the fuselage fixing plate, and the clamp connects the top-hanging device with the aircraft.

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