Fire-fighting pod and aircraft

Abstract

The utility model discloses a fire-fighting pod and an aircraft, which belong to the technical field of aircrafts, the fire-fighting pod comprises a pod body and a connecting rod, the connecting rod is provided with a first connecting device used for connecting the top of the pod body and a second connecting device used for connecting an arm connector of the aircraft, the first connecting device is located in the middle of the connecting rod, and the second connecting device is located in the middle of the connecting rod. The second connecting device is located at the end of the connecting rod, in the flight process of the aircraft, the cabin body is hung below the aircraft fuselage through the connecting rod, the connecting rod bears force transmitted by the aircraft fuselage and the cabin body and deforms, the connecting rod provides buffering and damping for the cabin body, and the service life of the cabin body and all parts on the cabin body is prolonged.

Description

TECHNICAL FIELD

[0001] The utility model relates to an aircraft technical field especially, and relates to a fire-fighting pod and aircraft. BACKGROUND

[0002] In the field of unmanned aerial vehicle fire fighting, the fire-fighting unmanned aerial vehicle as a new type of efficient fire-fighting and rescue equipment is playing an increasingly important role. Among them, the fire-fighting unmanned aerial vehicle provided with a fire extinguishing bomb cabin can load and accurately drop the fire extinguishing bomb, effectively improving the fire extinguishing efficiency.

[0003] At present, the bomb cabin and the unmanned aerial vehicle body are generally connected in a rigid manner. Although this connection method ensures the stability of the structure to a certain extent, it has significant drawbacks in actual application. Due to the unmanned aerial vehicle, it is inevitable to be affected by factors such as airflow, flight attitude adjustment, and blade rotation vibration during flight, which causes the unmanned aerial vehicle to vibrate. The vibration of the body will be directly transmitted to the bomb cabin without any buffering.

[0004] Long-term strong vibration causes great damage to the internal structure of the bomb cabin. The various precision mechanical structures in the bomb cabin, such as the bomb launching device used for fixing and releasing the fire extinguishing bomb, are prone to loose and wear due to frequent vibration, which further reduces the reliability and stability of the entire structure and greatly shortens the service life of the internal structure of the bomb cabin. At the same time, the sensors installed on the outside of the bomb cabin, such as sensors for monitoring the state of the bomb cabin and positioning the target for launching, are also affected by vibration. The vibration interferes with the normal operation of the sensor, reduces the measurement accuracy, and accelerates the aging and damage of the internal electronic components of the sensor, greatly shortening the service life of the sensor. UTILITY MODEL CONTENTS

[0005] In order to overcome the shortcomings of the prior art, the purpose of the utility model is to provide a fire-fighting pod and an aircraft to solve the problem of reduced service life of the current fire-fighting unmanned aerial vehicle bomb cabin due to vibration.

[0006] The purpose of the utility model is achieved by the following technical solutions:

[0007] A fire-fighting pod, comprising a cabin body and a connecting rod;

[0008] The connecting rod is provided with a first connecting device and a second connecting device, the first connecting device is located in the middle part of the connecting rod, and the second connecting device is located in the end part of the connecting rod;

[0009] The first connecting device is connected to the top of the cabin body, and the second connecting device is used for connecting the arm connecting head of the multi-rotor aircraft.

[0010] Preferably, it further comprises a torsion-resistant arm, and the two ends of the torsion-resistant arm are respectively connected to the side surface of the cabin body and the connecting rod.

[0011] Preferably, the connection between the anti-torsion arm and the connecting rod and the first connecting device are respectively located on two sides of the second connecting device.

[0012] Preferably, the anti-torsion arm comprises a first anti-torsion connecting seat, a second anti-torsion connecting seat, a first connecting part and a second connecting part, the first anti-torsion connecting seat is connected to the connecting rod, and the second anti-torsion connecting seat is connected to the side of the cabin body.

[0013] The first connecting part is rotationally connected to the first anti-torsion connecting seat, the second connecting part is rotationally connected to the second anti-torsion connecting seat, and the first connecting part and the second connecting part are connected through threads.

[0014] Preferably, the first connecting device comprises a bushing, and a first hoop and a second hoop which are oppositely arranged and connected, the first hoop is detachably connected to the top of the cabin body, the first hoop and the second hoop are respectively located on two sides of the connecting rod, and the bushing is arranged between the first hoop and the connecting rod and / or between the second hoop and the connecting rod.

[0015] Preferably, the number of the connecting rods is two, and the two connecting rods are respectively located at two ends of the cabin body.

[0016] Preferably, each connecting rod corresponds to two anti-torsion arms, and the two anti-torsion arms are respectively located at two ends of the connecting rod and are respectively connected to two sides of the cabin body.

[0017] Preferably, the landing gear is further provided, and the third connecting device is arranged on the landing gear and is detachably connected to the bottom of the cabin body.

[0018] Preferably, the third connecting device comprises a connecting ball and a third hoop, the inner side of the third hoop is provided with a connecting groove, and the outer wall surface of the connecting ball is embedded in the connecting groove; the connecting ball is arranged on the landing gear, and the third hoop is detachably connected to the bottom of the cabin body.

[0019] In order to solve the same technical problem, the utility model further provides an aircraft which comprises the fire-fighting suspension cabin.

[0020] Compared with the prior art, the utility model has the beneficial effects that:

[0021] The connecting rod is provided with a first connecting device for connecting the top of the cabin body and a second connecting device for connecting the arm connecting head of the aircraft, the first connecting device is located in the middle of the connecting rod, and the second connecting device is located at the end of the connecting rod, in the process of flight of the aircraft, the cabin body is hung below the aircraft fuselage through the connecting rod, the connecting rod is deformed by the force transmitted by the aircraft fuselage and the cabin body, the connecting rod provides buffering and shock absorption for the cabin body, and the service life of the cabin body and various components thereon is improved. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a schematic view of the overall structure of the fire-fighting hanging cabin of the utility model;

[0023] Figure 2 It is a schematic view of the torsion-resistant arm of the fire-fighting hanging cabin of the utility model;

[0024] Figure 3 It is a schematic view of the first connecting device of the fire-fighting hanging cabin of the utility model;

[0025] Figure 4 It is an assembly schematic view of the first connecting device of the fire-fighting hanging cabin of the utility model;

[0026] Figure 5 It is a schematic view of the overall structure of the aircraft of the utility model;

[0027] Figure 6 It is a schematic view of the landing gear of the fire-fighting hanging cabin of the utility model;

[0028] Figure 7 It is a schematic view of the third connecting device of the fire-fighting hanging cabin of the utility model;

[0029] In the drawing: 10, cabin body; 20, connecting rod; 30, first connecting device; 31, first hoop; 32, second hoop; 33, bushing; 40, second connecting device; 50, torsion-resistant arm; 51, first torsion-resistant connecting seat; 52, second torsion-resistant connecting seat; 53, first connecting part; 54, second connecting part; 60, third connecting device; 61, connecting ball; 62, third hoop; 621, connecting groove; 70, landing gear; 80, fuselage; 81, arm connecting head. DETAILED DESCRIPTION

[0030] In order to facilitate the understanding of the present utility model, the present utility model will be described more fully below with reference to the related drawings. The preferred embodiments of the present utility model are shown in the drawings. However, the present utility model can be realized in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the understanding of the disclosure of the present utility model more thorough and comprehensive.

[0031] It should be noted that when an element is referred to as being "on" another element, it can be directly on the other element or intervening elements can also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements can also be present. As used herein the terms "vertical", "horizontal", "left", "right", and the like are merely used for the purpose of illustration and are not intended to be limiting.

[0032] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description herein is for describing particular embodiments only and is not intended to be limiting. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0033] Embodiment 1

[0034] In combination Figures 1 to 4 As shown in the drawings, the fire-fighting pod of the present application is shown schematically, comprising a pod body 10 and a connecting rod 20, wherein the pod body 10 is used for storing and launching fire extinguishing bombs, and the connecting rod 20 is preferably a rod member with a circular cross-section, wherein the hollow structure not only reduces the structural weight, but also enables the connecting rod 20 to have a certain deformation capacity.

[0035] As Figure 1 shown, the connecting rod 20 is provided with a first connecting device 30 and a second connecting device 40, the first connecting device 30 is located at the middle of the connecting rod 20, and the second connecting device 40 is located at the end of the connecting rod 20, the first connecting device 30 is connected to the top of the pod body 10, and the second connecting device 40 is used to connect the arm connecting head 81 of the multi-rotor aircraft, and the pod body 10 is hung below the aircraft fuselage 80 through the connecting rod 20. During the flight of the aircraft, the connecting rod 20 is subjected to the force transmitted by the aircraft fuselage 80 and the pod body 10, and the connecting rod 20 deforms under the action of external force, thereby providing the pod body 10 with buffering and shock absorption.

[0036] Specifically, as Figure 2The fire-fighting pod further comprises torsion resisting arms 50, both ends of the torsion resisting arms 50 being connected to the side of the pod body 10 and the connecting rod 20, the torsion resisting arms 50 and the first connecting device 30 being connected to the connecting rod 20, the torsion resisting arms 50 and the first connecting device 30 jointly resisting the torsion deformation of the connecting rod 20. Further, the connecting positions between the torsion resisting arms 50 and the connecting rod 20 and the first connecting device 30 are respectively located on both sides of the second connecting device 40, the connecting rod 20 serving as a connecting structure between the first connecting device 30 (connected to the pod body 10) and the second connecting device 40 (connected to the arm connecting head 81 of the aircraft), the connecting rod 20 being deformed in torsion during the force transmission, and the deformation being too large to cause the connecting rod 20 to fail and break, the torsion resisting arms 50 and the first connecting device 30 being respectively located on both sides of the second connecting device 40 to limit the torsion deformation of the connecting rod 20 between the torsion resisting arms 50 and the first connecting device 30, thereby improving the load bearing performance of the connecting rod 20.

[0037] In order to adjust the torsion resisting arms 50 to adapt to the connecting rods 20 with different torsion resisting requirements, the torsion resisting arms 50 comprise first and second torsion resisting connecting seats 51 and 52, first and second connecting portions 53 and 54. The first torsion resisting connecting seat 51 is connected to the connecting rod 20, and the second torsion resisting connecting seat 52 is connected to the side of the pod body 10. The first connecting portion 53 is rotatably connected to the first torsion resisting connecting seat 51, and the second connecting portion 54 is rotatably connected to the second torsion resisting connecting seat 52. The first and second connecting portions 53 and 54 are connected by threads, so that the first and / or second connecting portions 53 and 54 can be rotated to relatively rotate the first and second connecting portions 53 and 54, and then relatively move the first and second connecting portions 53 and 54. In this way, the distance between the first and second torsion resisting connecting seats 51 and 52 can be adjusted, so as to adjust the pre-tightening force applied by the pod body 10 to the end of the connecting rod 20, for resisting the torsion force applied to the connecting rod 20.

[0038] In the embodiment, the number of the connecting rods 20 is two, and the two connecting rods 20 are respectively located at the two ends of the pod body 10, which can improve the connection stability between the pod body 10 and the aircraft. Each connecting rod 20 corresponds to two torsion resisting arms 50, and the two torsion resisting arms 50 are respectively located at the two ends of the connecting rod 20 and are connected to the two sides of the pod body 10. The two torsion resisting arms 50 corresponding to each connecting rod 20 can provide the torsion resisting function for the two ends of the connecting rod 20. Furthermore, the torsion resisting arms 50 can actually bear a certain tension force, so that the torsion resisting arms 50 and the first connecting device 30 jointly connect the connecting rod 20.

[0039] Embodiment 2

[0040] In combination Figure 3 And Figure 4As shown, the difference between the embodiment and embodiment 1 is that the first connecting device 30 comprises a bushing 33, a first hoop 31 and a second hoop 32, the first hoop 31 and the second hoop 32 are preferably semi-ring structures, the first hoop 31 and the second hoop 32 are oppositely arranged and connected, the first hoop 31 is detachably connected to the top of the cabin body 10, and the first hoop 31 and the second hoop 32 are respectively located on both sides of the connecting rod 20. The bushing 33 is arranged between the first hoop 31 and the connecting rod 20, and / or the bushing 33 is arranged between the second hoop 32 and the connecting rod 20, the bushing 33 can tightly connect the first hoop 31 or the second hoop 32 with the connecting rod 20, and the arrangement of the first hoop 31 and the second hoop 32 enables the first connecting device 30 to be detachably connected to the connecting rod 20.

[0041] Embodiment 3

[0042] In combination Figures 5 to 7 As shown, the difference between the embodiment and embodiment 1 is that the fire-fighting nacelle further comprises a landing gear 70, the landing gear 70 is provided with a third connecting device 60, the third connecting device 60 is detachably connected to the bottom of the cabin body 10, and the bottom of the cabin body 10 is provided with the landing gear 70, which can make the integration of the whole aircraft higher.

[0043] Specifically, the third connecting device 60 comprises a connecting ball 61 and a third hoop 62, the inner side of the third hoop 62 is provided with a connecting groove 621, and the outer wall surface of the connecting ball 61 is embedded in the connecting groove 621. The connecting ball 61 can be made of rubber or plastic material, so as to have a certain elasticity, and the connecting ball 61 and the third hoop 62 can provide buffering.

[0044] In this embodiment, the connecting ball 61 is arranged on the landing gear 70, and the third hoop 62 is detachably connected to the bottom of the cabin body 10.

[0045] Embodiment 4

[0046] As Figure 5 , the embodiment discloses an aircraft, which comprises a fuselage 80 and a fire-fighting nacelle as described above, a plurality of arm connecting heads 81 are arranged on the fuselage 80, the arm connecting heads 81 are used for connecting arms of the aircraft, and the second connecting device 40 of the fire-fighting nacelle is connected to the arm connecting head 81 through existing fasteners such as bolts.

[0047] In summary, the connecting rod 20 is provided with the first connecting device 30 for connecting the top of the cabin body 10 and the second connecting device 40 for connecting the arm connecting head 81 of the aircraft, the first connecting device 30 is located in the middle of the connecting rod 20, and the second connecting device 40 is located at the end of the connecting rod 20, in the process of flight of the aircraft, the cabin body 10 is hung below the aircraft fuselage 80 through the connecting rod 20, the connecting rod 20 is deformed by the force transmitted from the aircraft fuselage 80 and the cabin body 10, the connecting rod 20 provides buffering and shock absorption for the cabin body 10, and the service life of the cabin body 10 and various components thereon is improved.

[0048] The above is only an embodiment of the present application, and does not limit the patent range of the present application, and any equivalent structure or equivalent process transformation obtained by using the content of the present application specification and drawings, or direct or indirect application in other related technical fields, are also included in the patent protection range of the present application.

Claims

1. A fire-fighting pod, characterized in that, Including the hull and connecting rods; The connecting rod is provided with a first connecting device and a second connecting device, the first connecting device being located in the middle of the connecting rod and the second connecting device being located at the end of the connecting rod; The first connecting device is connected to the top of the cabin, and the second connecting device is used to connect to the arm connector of the multirotor aircraft.

2. The fire-fighting pod according to claim 1, characterized in that, It also includes an anti-torsion arm, the two ends of which are respectively connected to the side of the cabin and the connecting rod.

3. The fire-fighting pod according to claim 2, characterized in that, The connection between the anti-torsion arm and the connecting rod and the first connecting device are respectively located on both sides of the second connecting device.

4. The fire-fighting pod according to claim 2, characterized in that, The anti-torsion arm includes a first anti-torsion connecting seat, a second anti-torsion connecting seat, a first connecting part, and a second connecting part. The first anti-torsion connecting seat is connected to the connecting rod, and the second anti-torsion connecting seat is connected to the side of the cabin. The first connecting part is rotatably connected to the first anti-torsion connecting seat, and the second connecting part is rotatably connected to the second anti-torsion connecting seat. The first connecting part and the second connecting part are connected by threads.

5. The fire-fighting pod according to claim 1, characterized in that, The first connecting device includes a bushing and a first clamp and a second clamp that are disposed opposite to and connected to each other. The first clamp is detachably connected to the top of the cabin. The first clamp and the second clamp are respectively located on both sides of the connecting rod. The bushing is provided between the first clamp and the connecting rod, and / or the bushing is provided between the second clamp and the connecting rod.

6. The fire-fighting pod according to claim 1, characterized in that, The number of connecting rods is two, and the two connecting rods are located at the two ends of the cabin respectively.

7. The fire-fighting pod according to any one of claims 2 to 4, characterized in that, Each connecting rod corresponds to two anti-torsion arms, which are located at both ends of the connecting rod and are connected to both sides of the cabin.

8. The fire-fighting pod according to claim 1, characterized in that, It also includes landing gear, on which a third connecting device is provided, which is detachably connected to the bottom of the cabin.

9. The fire-fighting pod according to claim 8, characterized in that, The third connecting device includes a connecting ball and a third clamp. The inner side of the third clamp is provided with a connecting groove, and the outer wall of the connecting ball is embedded in the connecting groove. The connecting ball is located on the landing gear, and the third clamp is detachably connected to the bottom of the cabin.

10. An aircraft, characterized in that, Including the fire-fighting pod as described in any one of claims 1 to 9.

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