WO2019127565A1

WO2019127565A1 - Aircraft launcher

Info

Publication number: WO2019127565A1
Application number: PCT/CN2017/120386
Authority: WO
Inventors: 王凤太
Original assignee: 深圳市富斯科技有限公司
Priority date: 2017-12-30
Filing date: 2017-12-30
Publication date: 2019-07-04
Also published as: CN108513569A; CN108513569B

Abstract

Provided is an aircraft launcher, comprising a base (1) and a support frame (2) rotatably connected to the base (1), wherein the base (1) is used for placing an aircraft, the support frame (2) is rotated to support an end of the base (1) so that a certain angle is formed between the base (1) and the ground; and the support frame (2) comprises a support portion (22) arranged on one side of the base (1), and a positioning portion (21) arranged on the other side of the base (1) and connected to the support portion (22), with the positioning portion (21) being used for fixing the aircraft to the base (1), and the support portion (22) and the positioning portion (21) being in connection along a length direction of the support frame (2).

Description

Aircraft launcher

Technical field

The present disclosure relates to the field of aircraft launching device technology, and in particular to an aircraft launcher.

Background technique

Aircraft are widely used in the current society. The prospects for aerial photography, forest fire inspection, geological survey, high-voltage transmission line inspection, oil field pipeline inspection, highway management, emergency rescue and rescue are extremely broad.

At present, before the aircraft is maneuvered, it is placed on the ground. When taking off, the aircraft needs to fly a certain distance vertically from the ground before starting to fly back and forth, which takes a long time to take off. Alternatively, simply tilt the aircraft against a stone at an angle to the ground so that it can take off faster than the ground, but this method does not easily adjust the angle of the aircraft to the ground.

Summary of the invention

The present disclosure provides an aircraft launcher to address deficiencies in the related art.

The present disclosure provides an aircraft launcher comprising a base and a support frame rotatably coupled to the base, the base for placing an aircraft, the support frame being rotated to support one end of the base such that the base is grounded Certain angle

The support frame includes a support portion disposed on one side of the base, and a positioning portion disposed on the other side of the base and connected to the support portion, the positioning portion is configured to fix the aircraft in the a base, wherein the support portion and the positioning portion are connected along a length direction of the support frame.

Optionally, the support frame further includes a pivoting portion connecting the support portion and the positioning portion, and the pivoting portion is rotatably connected to the base.

Optionally, the base is provided with a receiving portion for receiving the support frame, and the receiving portion is formed in the base, and rotating the support frame can accommodate the support frame in the base.

Optionally, the base is provided with a fixing portion for fixing the support frame, and the support frame is provided with a matching portion that cooperates with the fixing portion, and when the support frame is received in the base, the support frame is The fixing portion is in contact with the fitting portion.

Optionally, one of the fixing portion and the engaging portion is a card slot, and the other is a buckle, and the fixing portion is engaged with the engaging portion.

Optionally, a first limiting portion is disposed at a position of the base adjacent to the positioning portion; and after the supporting frame is rotated to a preset angle, the first limiting portion may be in contact with the positioning portion. The support frame is prevented from continuing to rotate.

Optionally, one end of the base in the longitudinal direction is provided with a telescopic structure, and the telescopic structure can expand and contract along the length direction of the base.

Optionally, the base includes a receiving portion for receiving the telescopic structure, and the telescopic structure is slidable within the receiving portion.

Optionally, the receiving portion is a sliding slot formed in the base, and the telescopic structure is a U-shaped rod having a preset width.

Optionally, an end of the telescopic structure is provided with an elastic member, and the elastic member is disposed in the receiving portion.

Optionally, the telescopic structure is provided with a second limiting portion, and the supporting frame is provided with a nip portion that cooperates with the second limiting portion. When the telescopic structure is received in the receiving portion And the nip portion cooperates with the second limiting portion to fix the telescopic structure in the accommodating portion.

Optionally, the base is provided with a fixed card position, and the second limiting portion is movable to the fixed card position, and when the support frame is received in the base, the pressing portion is pressed The telescopic structure housed in the accommodating portion is fixed to the second limiting portion.

The technical solutions provided by the present disclosure may include the following beneficial effects:

The present disclosure can adjust the tilt angle of the base to meet the take-off requirements of the aircraft by rotating the connected support frame to the base. Rotating the support frame can easily adjust the angle between the aircraft and the ground, which changes the problem that the conventional launcher aircraft is difficult to adjust after being placed on the shelf.

DRAWINGS

1 is an exploded view of an aircraft launcher according to an embodiment of the present disclosure;

Figure 2 is a view of the first direction of the aircraft launcher of Figure 1;

Figure 3 is a view of the second direction of the aircraft launcher of Figure 1;

Figure 4 is a schematic view of the aircraft launcher mating with the aircraft.

Detailed ways

Exemplary embodiments will be described in detail herein, examples of which are illustrated in the accompanying drawings. The following description refers to the same or similar elements in the different figures unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. Instead, they are merely examples of devices and methods consistent with aspects of the present disclosure as detailed in the appended claims.

The terms used in the present disclosure are for the purpose of describing particular embodiments only, and are not intended to limit the disclosure. The singular forms "a", "the" and "the" It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

It should be understood that although the terms first, second, third, etc. may be used in the present disclosure to describe various information, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, the first information may also be referred to as second information without departing from the scope of the present disclosure. Similarly, the second information may also be referred to as first information. Depending on the context, the word "if" as used herein may be interpreted as "when" or "when" or "in response to a determination."

1 is an exploded view of an aircraft launcher according to an embodiment of the present disclosure; FIG. 2 is a first direction view of the aircraft launcher of FIG. 1; and FIG. 3 is a second direction view of the aircraft launcher of FIG. The first direction and the second direction are respectively a front side and a back side of the aircraft launcher. As shown in FIGS. 1 to 3, the aircraft launching frame includes a base 1 and a support frame 2, and the base 1 is rotatably coupled to the support frame 2. The base 1 is used for placing an aircraft, and the support frame 2 is rotated to support one end of the base 1 such that the base 1 is at an angle to the ground (for example, 30°-150°), and one end of the base 1 is One end of the support frame 2 is a fulcrum, and one end of the support frame 2 as a fulcrum is away from the base 1. The base 1 is composed of a plurality of rod-shaped cylinders and has a support area with a certain supporting area, and the area thereof may be slightly larger than the support area of the aircraft.

The support frame 2 includes a support portion 22, a positioning portion 21, and a pivot portion. The support portion 22 is disposed on the side of the base 1 , the positioning portion 21 is disposed on the other side of the base 1 and connected to the support portion 22 , and the support portion 22 and the positioning portion 21 are along The longitudinal direction of the support frame 2 is connected. The pivoting portion (not shown) is rotatably coupled to the base 1 , and the pivoting portion connects the support portion 22 and the positioning portion 21 .

In the present embodiment, the support frame 2 is composed of two columnar structures and a connecting rod connected between the two columnar structures. The pivoting portion is a through hole (formed on two columnar structures) disposed on the support frame 2, and correspondingly, the base 1 is also provided with a through hole 16 through which the rotating shaft passes through the two through holes. The support frame 2 is rotatably coupled to the base 1. The pivoting portion divides the two columnar structures into two parts, namely the support portion 22 and the positioning portion 21. Since the pivoting portion is located between the supporting portion 22 and the positioning portion 21, when the supporting frame 2 is rotated about the rotating shaft, the supporting portion 22 is opposite to the rotating direction of the positioning portion 21. Therefore, when the support frame 2 is rotated, the free end of the support portion 22 is away from the base 1, and the positioning portion 21 protrudes from the surface of the base 1, and the aircraft can be placed by the positioning portion 21 On the base 1 with a certain angle of inclination. The positioning portion 21 can fix the aircraft to the base 1, for example, the positioning portion 21 cooperates with a shelter of the aircraft to fix the aircraft, preventing the aircraft from sliding down on the base 1.

Referring to FIG. 1 to FIG. 4 , the base 1 is provided with a receiving portion 13 for receiving the support frame 2 , and the receiving portion 13 is formed in the base 1 , and rotating the support frame 2 can The support frame 2 is received in the base 1 . In an embodiment, the accommodating portion 13 is a strip-shaped slot, and is disposed adjacent to both sides of the base 1 respectively. The free end of the support portion 22 is rotated toward the base 1 , and when the plane of the support frame 2 coincides with the plane of the base 1 , the support frame 2 is received in the receiving portion 13 . This not only makes the structure of the aircraft launcher simple, but also fully utilizes the slot structure to reduce the volume of the aircraft launcher and is convenient to carry.

Further, the base 1 is provided with a fixing portion 14 for fixing the support frame 2, and the support frame 2 is provided with a fitting portion 23 that cooperates with the fixing portion 14, and the support frame 2 is received in the base In the case of the inside of the base 1, the fixing portion 14 is in contact with the engaging portion 23. In the embodiment of the present disclosure, the fixing portion 14 is a card slot disposed near the bottom end of the base 1; the engaging portion 23 is a buckle, disposed near the bottom end of the support frame 2 (located at the lower end of the support frame 2) On the support bar). When the carrier launching frame is to be accommodated, the support frame 2 is rotated, and when the support frame 2 is received in the receiving portion 13, the fixing portion 14 is engaged with the engaging portion 23, and the support frame is realized. 2 fixed. In use, the lower end of the support frame 2 and the lower end of the base 1 are directly separated from the engaged fixing portion 14 and the engaging portion 23. Of course, in other embodiments, the fixing portion 14 is a buckle, and the engaging portion 23 is a card slot.

A first limiting portion 12 is further disposed on the base 1 , and a position of the first limiting portion 12 on the base 1 is disposed adjacent to the positioning portion 21 . In the embodiment of the present disclosure, the first limiting portion 12 is disposed in the receiving portion 13 and located below the rotating shaft. After the support frame 2 is rotated to a preset angle, the first limiting portion 12 can be in contact with the positioning portion 21 to prevent the support frame 2 from continuing to rotate. The first limiting portion 12 includes a slot having a specific depth. The positioning portion 21 rotates from the plane of the base 1 until it contacts the first limiting portion 12, and the depth of the slot is The angle at which the positioning portion 21 is rotatable is related.

Further, at one end in the longitudinal direction of the base 1, a telescopic structure 3 is provided, and the telescopic structure 3 can be expanded and contracted along the longitudinal direction of the base 1. The telescopic structure 3 is arranged to increase the length of the aircraft launcher to accommodate different lengths of the aircraft 5 (see FIG. 4), and the effect of stable placement of different aircraft can be achieved. In an embodiment of the present disclosure, the telescopic structure 3 is a U-shaped bar having a preset width.

In order to simplify the structure, the telescopic structure 3 is expanded and contracted with respect to the base 1 , and the accommodating portion 11 is disposed on the base 1 , and the accommodating portion 11 can accommodate the telescopic structure 3 . The telescopic structure 3 is slidable within the accommodating portion 11. In the embodiment of the present disclosure, the accommodating portion 11 is a chute formed in the base 1 . Of course, it may also be a chute structure formed on the surface of the base 1.

The end of the telescopic structure 3 is provided with an elastic member 4, and the elastic member 4 is placed in the accommodating portion 11. In one embodiment, the telescopic structure 3 is slid into the accommodating portion 11 to compress the elastic member 4. When the telescopic structure 3 needs to be taken out, the elastic member 4 can assist in ejecting the telescopic structure 3. The elastic member 4 can be connected to the base 1 at one end and the telescopic structure 3 at the other end. In the present embodiment, the elastic member 4 is a spring.

The telescopic structure 3 is provided with a second limiting portion 12, and the supporting frame 2 is provided with a pressing portion 24 that cooperates with the second limiting portion 12. The second limiting portion 12 is a groove formed on the telescopic structure 3, and the pressing portion 24 is a connecting rod disposed on the support frame 2. When the telescopic structure 3 is received in the accommodating portion 11 and the telescopic structure 3 has the largest storage length, the connecting rod is engaged in the nip portion 24, and the nip portion 24 and the merging portion The two limiting portions 12 cooperate to fix the telescopic structure 3 in the receiving portion 11 .

The base 1 is provided with a fixed latching position 15 . The fixed latching position 15 is a strip-shaped slot formed on the base 1 , and the nip portion 24 can be received in the strip-shaped slot (the support frame 2 is received In the base 1). When the length of the telescopic structure 3 is received in the accommodating portion 11 , the second limiting portion 12 can be moved to the fixed latching portion 15 and exposed from the accommodating portion 13 . When the support frame 2 is received in the base 1 , the pressing portion 24 is pressed against the second limiting portion 12 to fix the telescopic structure 3 received in the receiving portion 11 . When the support frame 2 is rotated away from the receiving portion 13, the elastic member 4 can eject a part of the telescopic structure 3 from the receiving portion 11. The structure optimization of the aircraft launcher and the full utilization of the volume are realized.

The above description is only the preferred embodiment of the present disclosure, and is not intended to limit the disclosure, and any modifications, equivalents, improvements, etc., which are made within the spirit and principles of the present disclosure, should be included in the present disclosure. Within the scope of protection.

Claims

An aircraft launcher is characterized in that it comprises a base and a support frame rotatably connected with the base, the base is used for placing an aircraft, and the support frame is rotated to support one end of the base such that the base and the ground At a certain angle;

The support frame includes a support portion disposed on one side of the base, and a positioning portion disposed on the other side of the base and connected to the support portion, the positioning portion is configured to fix the aircraft in the a base, wherein the support portion and the positioning portion are connected along a length direction of the support frame.
The aircraft launcher according to claim 1, wherein the support frame further comprises a pivoting portion connecting the support portion and the positioning portion, the pivoting portion being rotatably coupled to the base.
The aircraft launcher according to claim 1, wherein the base is provided with a receiving portion for receiving the support frame, the receiving portion is formed in the base, and rotating the support frame can support the support The rack is received in the base.
The aircraft launcher according to claim 3, wherein the base is provided with a fixing portion for fixing the support frame, and the support frame is provided with a fitting portion for engaging with the fixing portion, When the support frame is received in the base, the fixing portion is in contact with the engaging portion.
The aircraft launcher according to claim 4, wherein one of the fixing portion and the engaging portion is a card slot, and the other is a buckle, and the fixing portion is engaged with the engaging portion. .
The aircraft launcher according to claim 1, wherein a position of the base near the positioning portion is provided with a first limiting portion; and after rotating the supporting frame to a preset angle, the first limit The seat portion is in contact with the positioning portion to prevent the support frame from continuing to rotate.
The aircraft launcher according to claim 1, wherein one end of the base in the longitudinal direction is provided with a telescopic structure, and the telescopic structure is expandable and contractible along the longitudinal direction of the base.
The aircraft launcher according to claim 7, wherein the base includes a receiving portion for receiving the telescopic structure, and the telescopic structure is slidable within the receiving portion.
The aircraft launcher according to claim 8, wherein the receiving portion is a chute formed in the base, and the telescopic structure is a U-shaped bar having a preset width.
The aircraft launcher according to claim 8, wherein the end of the telescopic structure is provided with an elastic member, and the elastic member is placed in the accommodating portion.
The aircraft launcher according to claim 8, wherein the telescopic structure is provided with a second limiting portion, and the supporting frame is provided with a nip portion that cooperates with the second limiting portion. When the telescopic structure is received in the accommodating portion, the nip portion cooperates with the second limiting portion to fix the telescopic structure in the accommodating portion.
The aircraft launcher according to claim 11, wherein the base is provided with a fixed card position, and the second limiting portion is movable to the fixed card position, and when the support frame is received in the The nip is pressed against the second limiting portion to fix the telescopic structure received in the accommodating portion.