Stabilizing mechanism for forced landing of rescue unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of rescue unmanned aerial vehicles, and particularly relates to a stabilizing mechanism for forced landing of a rescue unmanned aerial vehicle, the stabilizing mechanism for forced landing of the rescue unmanned aerial vehicle comprises a gas generator, a slow landing airbag and a stabilizing assembly, the slow landing airbag is fixedly connected and communicated with the gas outlet end of the gas generator; the stabilizing assembly comprises a six-way connector fixedly connected between the slow descending air bag and the air generator. According to the stabilizing mechanism for forced landing of the rescue unmanned aerial vehicle, all structures except the piston cylinder are installed in a hidden mode, so that the overall size of the rescue unmanned aerial vehicle can be reduced, the problem that an existing stabilizing mechanism for forced landing of the rescue unmanned aerial vehicle is large in occupied space is solved, and then the effect of reducing the operation burden of the rescue unmanned aerial vehicle is achieved; and meanwhile, the stabilizing assembly is elastically unfolded through redundant air flow generated when an existing slow descent air bag swells and slowly descends, the elastic contact area between the rescue unmanned aerial vehicle and the ground can be enlarged, and the impact force of forced landing of the rescue unmanned aerial vehicle is further reduced.

Description

TECHNICAL FIELD

[0001] The utility model belongs to rescue unmanned plane technical field, concretely relates to a kind of stabilizing mechanism for forced landing for rescue unmanned plane. BACKGROUND

[0002] Rescue unmanned plane refers to the unmanned plane equipment specially used for coping with emergency and emergency rescue, with the progress of science and technology, the application range of unmanned plane is more and more wide, such as for rescue, goods are transported to disaster area by unmanned plane, sometimes unmanned plane needs forced landing, which requires unmanned plane to have stabilizing mechanism.

[0003] For example, a new forced landing stabilizing device for unmanned plane (authorized publication number CN219295718U), the above-mentioned device improves the stability of unmanned plane forced landing by adopting stable ring belt and multiple support columns, however, to ensure that unmanned plane can be forced landing, large-size stable ring belt is needed to avoid the situation of unstable gravity center, however, the volume of support and stabilization assembly composed of large-size stable ring belt and vertically arranged support column is inevitably large, which still has the problem of increasing the operating load of unmanned plane. UTILITY MODEL CONTENT

[0004] The utility model aims at providing a kind of stabilizing mechanism for forced landing for rescue unmanned plane, which can optimize the occupied space on the basis of assisting rescue unmanned plane to stabilize forced landing, to achieve the purpose of reducing the influence on rescue unmanned plane operation.

[0005] The technical scheme adopted by the utility model is as follows:

[0006] A kind of stabilizing mechanism for forced landing for rescue unmanned plane, including gas generator, slow descent air bag and stabilizing assembly, the slow descent air bag is fixedly connected and communicated with the gas outlet end of gas generator;

[0007] In a preferred scheme, the stabilizing assembly includes a six-way connector fixedly connected between the slow descent air bag and the gas generator, the remaining four ends of the six-way connector are fixedly connected and communicated with gas pipes, the surface of the gas pipe is fixedly connected and communicated with a piston cylinder, the piston block is slidably connected inside the piston cylinder, the bottom of the piston block is fixedly connected with an elastic buffer column, and the bottom of the elastic buffer column is flush with the opening of the piston cylinder.

[0008] In a preferred scheme, the top of the piston block and the elastic buffer column is provided with a gas hole communicated with each other, and the opening of the lower gas hole is fixedly connected and communicated with a lateral stabilizing air bag.

[0009] In a preferred scheme, the surface of the elastic buffer column is provided with a mounting cavity communicated with the lower gas hole, the opening of the mounting cavity faces away from the gas generator, and one end of the lateral stabilizing air bag is fixedly connected inside the mounting cavity.

[0010] In a preferred scheme, the piston block and the top of the elastic buffer column are both provided with a guide groove in communication with each other, a guide rod is inserted into the lower guide groove, and the top of the guide rod penetrates the lower guide groove and the upper guide groove in sequence and is fixedly connected with the piston cylinder.

[0011] In a preferred scheme, the surface of the elastic buffer column is provided with a reserved cavity arranged above the mounting cavity, and the stabilizing assembly further comprises a positioning module, the positioning module comprises a positioning block slidingly connected to the inside of the reserved cavity, one end of the positioning block penetrates out of the reserved cavity and is in contact with the piston cylinder, the partial cross-sectional shape of the positioning block arranged outside the reserved cavity is an isosceles triangle, and a spring that is always in a compressed state is arranged between the positioning block and the reserved cavity.

[0012] In a preferred scheme, the cross-sectional shape of the reserved cavity is a lateral convex shape, and the maximum diameter of the positioning block arranged outside the reserved cavity is smaller than the maximum diameter of the positioning block arranged inside the reserved cavity.

[0013] In a preferred scheme, the other end of the positioning block is provided with a positioning groove, and one end of the spring penetrates into the inside of the positioning groove.

[0014] The technical effects achieved by the utility model are:

[0015] The rescue unmanned plane uses the forced landing stabilizing mechanism to hide and install the structures except the piston cylinder, which can reduce the overall volume of the rescue unmanned plane, solve the problem of the rescue unmanned plane that the existing forced landing stabilizing mechanism occupies a large space, and further achieve the effect of reducing the operation burden of the rescue unmanned plane, and the stabilizing assembly uses the excess airflow of the existing slow descent airbag inflation slow descent to elastically expand, which can expand the elastic contact area of the rescue unmanned plane and the ground, and further reduce the impact force of the rescue unmanned plane forced landing.

[0016] The positioning assembly can elastically lock the elastic buffer column in the inside of the piston cylinder when the elastic buffer column is not running, so as to reduce the purpose of increasing the flight resistance of the rescue unmanned plane due to the extension of the elastic buffer column out of the piston cylinder, and when the high-pressure airflow flows into the inside of the piston cylinder, the high-pressure airflow can easily push against the contracted positioning assembly, so as to ensure that the elastic buffer column can normally extend out of the piston cylinder, and after the elastic buffer column is moved in place, the positioning assembly can be reset and be in contact with the piston cylinder, so that the elastic buffer column runs more stably. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a connection schematic view of the overall structure of the utility model and the rescue unmanned plane;

[0018] Figure 2 is a structure schematic view of the overall structure of the utility model;

[0019] Figure 3 is the partial section view schematic diagram of the stabilizing assembly of the utility model;

[0020] Figure 4 is the partial explosion schematic diagram of the stabilizing assembly of the utility model.

[0021] In the drawings, the component list represented by each reference numeral is as follows:

[0022] 100, gas generator; 200, slow descent airbag; 300, stabilizing assembly; 310, six-way joint; 320, air pipe; 330, piston cylinder; 340, piston block; 341, air hole; 342, guide groove; 350, elastic buffer column; 351, mounting cavity; 352, reserved cavity; 360, lateral stabilizing airbag; 370, guide rod; 380, positioning module; 381, positioning block; 382, spring; 383, positioning groove. DETAILED DESCRIPTION

[0023] In order to make the above-mentioned purpose, features and advantages of the utility model more apparent, obvious and easy to understand, the specific embodiments of the utility model are described in detail below with reference to the drawings of the specification.

[0024] In the following description, a large number of specific details are set forth in order to fully understand the utility model, but the utility model can also be implemented in other ways different from those described herein, and those skilled in the art can make similar generalizations without departing from the connotation of the utility model, so the utility model is not limited by the specific embodiments disclosed below.

[0025] Secondly, "one embodiment" or "embodiment" referred to herein means that specific features, structures or characteristics can be included in at least one implementation of the utility model. "In a preferred embodiment" does not mean the same embodiment in different places in this specification, nor is it an embodiment that is separate or optional and mutually exclusive with other embodiments.

[0026] Thirdly, the utility model is described in detail in conjunction with the schematic diagram, and in the detailed description of the embodiments of the utility model, the cross-sectional view of the device structure is partially enlarged without general proportion for the convenience of description, and the schematic diagram is only an example, which should not limit the scope of protection of the utility model herein. In addition, three-dimensional spatial dimensions including length, width and depth should be included in actual production.

[0027] Embodiment 1

[0028] Please refer to the accompanying Figure 1 - Figure 4 As shown in the drawings, the first embodiment of the utility model provides a forced landing stabilizing mechanism for a rescue unmanned aerial vehicle,

[0029] In a preferred embodiment, please refer to Figure 1 , Figure 2 , Figure 3 and Figure 4 , a forced landing stabilizing mechanism for a rescue drone, comprising a gas generator 100, a slow-landing airbag 200 and a stabilizing assembly 300, the slow-landing airbag 200 is fixedly connected and communicated with the gas outlet end of the gas generator 100.

[0030] The top of the rescue drone needs to be designed in advance with a storage cavity for accommodating the gas generator 100, the slow-landing airbag 200, the six-way joint 310 and the gas pipe 320, then the gas generator 100 and the gas pipe 320 are fixed in the corresponding positions of the storage cavity respectively, and it is necessary to ensure that the slow-landing airbag 200 is in a compressed state at this time, then the four piston cylinders 330 are symmetrically distributed along the center line of the rescue drone at the bottom of the rescue drone, and the gas generator 100 needs to be matched and connected with the wireless controller in the rescue drone to ensure that the gas generator 100 can be remotely started;

[0031] When the rescue drone lands normally, the bottom of the piston cylinder 330 can act as a support leg of the rescue drone to support the rescue drone on the ground, without the need to separately install a support leg for the rescue drone.

[0032] The stabilizing assembly 300 comprises a six-way joint 310 fixedly connected between the slow-landing airbag 200 and the gas generator 100, the remaining four ends of the six-way joint 310 are fixedly connected and communicated with the gas pipes 320, the surfaces of the gas pipes 320 are fixedly connected and communicated with the piston cylinders 330, the interiors of the piston cylinders 330 are slidingly connected with the piston blocks 340, the bottoms of the piston blocks 340 are fixedly connected with the elastic buffer columns 350, the bottoms of the elastic buffer columns 350 are flush with the openings of the piston cylinders 330 at this time; the tops of the piston blocks 340 and the elastic buffer columns 350 are both provided with gas holes 341 communicated with each other, the openings of the lower gas holes 341 are fixedly connected and communicated with the lateral stabilizing airbags 360, which can increase the elastic contact area between the rescue drone and the ground, further reducing the impact force of forced landing; the surfaces of the elastic buffer columns 350 are provided with mounting cavities 351 communicated with the lower gas holes 341, the openings of the mounting cavities 351 are away from the gas generator 100, one end of the lateral stabilizing airbag 360 is fixedly connected to the interior of the mounting cavity 351, the tops of the piston blocks 340 and the elastic buffer columns 350 are both provided with guide grooves 342 communicated with each other, the interiors of the lower guide grooves 342 are inserted with guide rods 370, the tops of the guide rods 370 penetrate the lower guide grooves 342 and the upper guide grooves 342 in sequence and are fixedly connected with the piston cylinders 330, which can ensure that the lateral stabilizing airbag 360 always expands in the direction away from the axial line of the rescue drone, so as to reduce the effect of the lateral stabilizing airbag 360 damaging the rescue drone.

[0033] In this embodiment, in the process of high-speed airflow rushing into the piston cylinder 330, the high-speed airflow enters the lateral stabilizing airbag 360 along the air hole 341, at this time the lateral stabilizing airbag 360 expands rapidly along the mounting cavity 351 to the outside, which can increase the elastic contact area of the elastic buffer column 350 with the ground, further reducing the impact force of the rescue unmanned aerial vehicle forced landing.

[0034] Embodiment 2

[0035] Please refer to the accompanying Figure 3 and Figure 4 As shown in the second embodiment of the utility model, the embodiment provides a forced landing stabilizing mechanism for a rescue unmanned aerial vehicle, which comprises a positioning module 380, the surface of the elastic buffer column 350 is provided with a reserved cavity 352 arranged above the mounting cavity 351, the positioning module 380 comprises a positioning block 381 slidingly connected inside the reserved cavity 352, one end of the positioning block 381 penetrates out of the reserved cavity 352 and is in contact with the piston cylinder 330, the local cross-sectional shape of the positioning block 381 arranged outside the reserved cavity 352 is an isosceles triangle, and a spring 382 always in a compressed state is arranged between the positioning block 381 and the reserved cavity 352; the cross-sectional shape of the reserved cavity 352 is a lateral convex shape, and the maximum diameter of the positioning block 381 arranged outside the reserved cavity 352 is smaller than the maximum diameter of the positioning block 381 arranged inside the reserved cavity 352, which can avoid the positioning block 381 from completely coming out of the reserved cavity 352, so as to ensure that the positioning module 380 can be normally used; the other end of the positioning block 381 is provided with a positioning groove 383, and one end of the spring 382 penetrates into the inside of the positioning groove 383, which not only can limit the position of the spring 382, but also can reserve enough space for the spring 382 to stretch and contract, so as to ensure that the spring 382 can be normally used.

[0036] In this embodiment, in the process of the elastic buffer column 350 hiding inside the piston cylinder 330, the spring 382 presses the positioning block 381 against the inner wall of the piston cylinder 330, which prevents the elastic buffer column 350 from sliding to the outside of the piston cylinder 330, so as to reduce the resistance in the flight process of the rescue unmanned aerial vehicle, when the air inside the piston cylinder 330 pushes against the piston block 340, since the local cross-sectional shape of the positioning block 381 arranged outside the reserved cavity 352 is an isosceles triangle, which can ensure that when the air pressure reaches a preset value, the inner wall of the piston cylinder 330 can press the positioning block 381 back into the reserved cavity 352, so as to ensure that the elastic buffer column 350 can be used smoothly, and when the mounting cavity 351 completely moves to the outside of the piston cylinder 330, at this time the spring 382 can push the positioning block 381 more thoroughly to the outside of the reserved cavity 352, at this time the flat surface of the positioning block 381 is parallel to the bottom of the piston cylinder 330, which can prevent the elastic buffer column 350 from retracting into the piston cylinder 330 under a large impact, so as to ensure that the elastic buffer column 350 can effectively perform the buffering work.

[0037] The working principle of the utility model is: when the staff needs to control the emergency landing of the rescue unmanned plane, the staff only needs to control the gas generator 100 to produce gas quickly through the wireless controller, the gas generator 100 guides the gas into the six-way joint 310, the six-way joint 310 guides the gas into the four air pipes 320 and the slow descent air bag 200, the slow descent air bag 200 expands and moves out of the storage cavity to slow down the landing speed of the rescue unmanned plane, avoid the speed being too fast to generate too large impact force on the rescue unmanned plane, thereby improving the stability of the rescue unmanned plane when landing, at the same time, the air pipe 320 guides the gas into the piston cylinder 330, at this time, the air pressure in the piston cylinder 330 increases sharply, the piston block 340 is pushed downward under the action of the air pressure, part of the elastic buffer column 350 moves out of the piston cylinder 330 to ensure that the elastic buffer column 350 can be in contact with the ground first to absorb the impact force of the emergency landing, and since the stabilizing mechanism only has the piston cylinder 330 arranged outside the rescue unmanned plane, this can reduce the space occupied by the stabilizing mechanism outside the rescue unmanned plane.

[0038] It should be noted that the rescue unmanned plane, the wireless controller, the gas generator 100, the slow descent air bag 200, the six-way joint 310 and the lateral stabilizing air bag 360 in the above description are all relatively mature devices in the prior art, and the specific model can be selected according to actual needs, and the rescue unmanned plane, the wireless controller and the gas generator 100 are powered by the built-in power supply, which will not be described here.

[0039] The above is only the preferred embodiment of the utility model, and it should be pointed out that for ordinary skilled persons in the technical field, some improvements and refinements can be made without departing from the principle of the utility model, and these improvements and refinements should also be regarded as the protection range of the utility model. The structures, devices and operation methods not specifically described and explained in the utility model are implemented according to the conventional means in the field without special description and limitation.

Claims

1. A stabilizing mechanism for forced landing of a rescue drone, characterized by: It comprises a gas generator (100) and a descent control airbag (200), wherein the descent control airbag (200) is fixedly connected to and communicated with the gas outlet end of the gas generator (100); A stabilizing assembly (300) includes a six-way joint (310) fixedly connected between a descent airbag (200) and a gas generator (100); the other four ends of the six-way joint (310) are fixedly connected and communicated with an air pipe (320); the surface of the air pipe (320) is fixedly connected and communicated with a piston cylinder (330); the interior of the piston cylinder (330) is slidably connected to a piston block (340); the bottom of the piston block (340) is fixedly connected to an elastic buffer column (350); the bottom of the elastic buffer column (350) is flush with the opening of the piston cylinder (330).

2. The rescue drone forced landing stabilization mechanism according to claim 1, characterized in that: The piston block (340) and the elastic buffer column (350) are both provided with mutually communicating air holes (341) on their tops, and the openings of the air holes (341) below are fixedly connected and communicated with a lateral stabilizing air bag (360).

3. The stabilizing mechanism for forced landing of a rescue drone according to claim 2, characterized in that: The surface of the elastic buffer column (350) is provided with a mounting cavity (351) that is in communication with the air hole (341) below. The opening of the mounting cavity (351) faces away from the gas generator (100). One end of the lateral stabilizing airbag (360) is fixedly connected to the interior of the mounting cavity (351).

4. The rescue drone forced landing stabilization mechanism according to claim 1, characterized in that: The tops of the piston block (340) and the elastic buffer column (350) are both provided with mutually communicating guide grooves (342), the interior of the lower guide groove (342) is plugged with a guide rod (370), and the top of the guide rod (370) sequentially passes through the lower guide groove (342) and the upper guide groove (342) and is fixedly connected to the piston cylinder (330).

5. The rescue drone forced landing stabilization mechanism according to claim 1, characterized in that: The surface of the elastic buffer column (350) is provided with a reserved cavity (352) arranged above the installation cavity (351). The stabilizing assembly (300) further includes a positioning module (380). The positioning module (380) includes a positioning block (381) slidably connected to the inside of the reserved cavity (352). One end of the positioning block (381) passes through the reserved cavity (352) and contacts the piston cylinder (330). The local cross-section of the positioning block (381) arranged outside the reserved cavity (352) is an isosceles triangle. A spring (382) that is always in a compressed state is provided between the positioning block (381) and the reserved cavity (352).

6. The stabilizing mechanism for forced landing of a rescue drone according to claim 5, characterized in that: The cross-sectional shape of the reserved cavity (352) is a lateral convex shape, and the maximum diameter of the positioning block (381) arranged outside the reserved cavity (352) is smaller than the maximum diameter of the positioning block (381) arranged inside the reserved cavity (352).

7. The stabilizing mechanism for forced landing of a rescue drone according to claim 5, characterized in that: The other end of the positioning block (381) is provided with a positioning groove (383), and one end of the spring (382) passes through the interior of the positioning groove (383).

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