CN110671211A - Large-corner automatic butt joint air source separating mechanism - Google Patents
Large-corner automatic butt joint air source separating mechanism Download PDFInfo
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- CN110671211A CN110671211A CN201910975769.8A CN201910975769A CN110671211A CN 110671211 A CN110671211 A CN 110671211A CN 201910975769 A CN201910975769 A CN 201910975769A CN 110671211 A CN110671211 A CN 110671211A
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- China
- Prior art keywords
- air source
- support
- launching
- butt joint
- separating mechanism
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
Abstract
The invention discloses an automatic large-corner butt joint air source separating mechanism which comprises an air source connecting nozzle supported on a launching frame through a support, wherein the support is rotatably connected with the launching frame, an air source pipeline is communicated with the air source connecting nozzle, the air source connecting nozzle is communicated with an air bottle through the air source pipeline, the support is rotatably connected with the launching frame, the tail end of the support is connected and driven through a driving structure, the driving structure is rotatably installed on the launching frame through a fixing seat, the output end of the driving structure is rotatably connected with the tail end of the support, and the air source connecting nozzle is driven by the support to form large-corner limiting rotation in the telescopic process of the driving structure. The invention can realize the movable control connection between the air source interface and the air source connector of the unmanned aerial vehicle, thereby leading the operating personnel to be far away from initiating explosive devices, effectively ensuring the personnel safety of a launching site, leading the whole mechanism to rotate at a large angle, providing enough safety distance for the unmanned aerial vehicle to move and improving the launching safety.
Description
Technical Field
The invention relates to the technical field of air source separation structures, in particular to a large-corner automatic butt joint air source separation mechanism.
Background
When the unmanned aerial vehicle using the turbojet engine as power is started, an air source is required to blow the engine, and an air source separating mechanism is generally required to separate an air source pipeline during launching. The prior gas source separating mechanism mainly comprises a manual gas source separating mechanism and a follow-up gas source separating mechanism.
The manual air source separation mechanism is simple in structure, butt joint is achieved in a manual mode before launching, and separation is achieved by manually removing the air source separation mechanism by an operator after the engine is started, so that the mode is simple to operate, and certain safety risk exists; the follow-up air source separating mechanism is fixedly installed, a manual mode is adopted for butt joint, separation is achieved along with movement of the unmanned aerial vehicle, the mode has strict requirements on the installation position, the movement track of the tail wing of the unmanned aerial vehicle needs to be avoided after separation, and the application range is small.
Disclosure of Invention
The invention aims to provide a large-corner automatic butt joint air source separating mechanism to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
the utility model provides an automatic butt joint air supply separating mechanism of big corner, includes the air supply faucet that supports on the launching cradle through the leg joint, support and launching cradle rotate to be connected, the intercommunication is provided with the air supply pipeline on the air supply faucet, the air supply faucet passes through air supply pipeline and gas cylinder and communicates mutually, support and launching cradle rotate to be connected and the end connects the transmission through drive structure, drive structure passes through the fixing base and rotates and install on the launching cradle, and drive structure's output and support end rotate to be connected, drive structure's flexible in-process drives the spacing formula rotation that the air supply faucet formed big corner through the support.
Further, the support comprises a rotating support which is rotatably connected to the launcher through a rotating base.
Furthermore, the rotating base is fixedly installed on the launching rack and is rotatably connected with the rotating support through a rotating pin.
Furthermore, the upper end of the rotating support is connected and assembled with the tail end of the air source connector, and the lower end of the rotating support is rotatably connected with the output end of the driving structure in a hinged mode.
Furthermore, the air source nozzle is in sliding fit with the upper end of the rotating support, and one end of the air source nozzle, which is far away from the rotating support, is elastically connected with the tail end of the rotating support through a compression spring.
Further, the drive structure includes electric putter and the flexible control system of drive electric putter operation, electric putter installs on the fixing base and rotates through the fixing base and connect in the launching cradle below, electric putter's the terminal and the runing rest of output rotate to be connected.
Furthermore, the control system comprises a power supply electrically connected with the electric push rod through an electromagnetic valve and a controller electrically connected with a control circuit of the electric push rod, and the controller controls the electromagnetic valve to be opened and closed through a relay connected with the power supply.
Compared with the prior art, the invention has the beneficial effects that: through control system's control, can realize controlling electric putter control and drive runing rest and rotate to can realize the swing control connection between unmanned aerial vehicle air source interface and the air supply connector, thereby let operating personnel keep away from the initiating explosive device like this, effectively guarantee the personnel's safety at the transmission scene, the large angle of rotation of whole mechanism provides sufficient safe distance for the unmanned aerial vehicle motion, has improved the transmission security.
Drawings
Fig. 1 is a schematic structural diagram of a large-angle automatic butt-joint air source separating mechanism.
Fig. 2 is a schematic view of a separating state structure of a large-angle automatic butt joint air source separating mechanism.
Fig. 3 is a circuit control diagram of a control system in a large-corner automatic butt joint air source separating mechanism.
In the figure: the device comprises a gas source connector 1, a compression spring 2, a gas source pipeline 3, a rotary support 4, a rotary base 5, an electric push rod 6, a fixed seat 7 and a launching frame 8.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
Referring to fig. 1-2, in the embodiment of the present invention, a large-corner automatic butt joint air source separation mechanism includes an air source nozzle 1 supported on a launcher 8 through a support, the support is rotatably connected to the launcher 8, an air source pipeline 3 is communicated with the air source nozzle 1, the air source nozzle 1 is communicated with an air bottle through the air source pipeline 3, the support is rotatably connected to the launcher 8, the end of the support is connected to a drive structure for transmission, the drive structure is rotatably mounted on the launcher 8 through a fixing base 7, and the output end of the drive structure is rotatably connected to the end of the support.
The support comprises a rotary support 4 which is rotatably connected onto a launching frame 8 through a rotary base 5, the rotary base 5 is fixedly mounted on the launching frame 8 and is rotatably connected with the rotary support 4 through a rotating pin, the upper end of the rotary support 4 is connected and assembled with the tail end of an air source connector 1, the air source connector 1 is in sliding fit with the upper end of the rotary support 4, the air source connector 1 is opposite to an air source interface of the unmanned aerial vehicle, and one end, far away from the rotary support 4, of the air source connector 1 is elastically connected with the tail end of the rotary support 4 through a spring, so that when the rotary support 4 rotates to enable the air source connector 1 and the air source interface of the unmanned aerial vehicle to be compressed and communicated, the air source connector 1 elastically compresses a compression spring 2, and elastically compresses the air source connector 1 and is connected with the air source interface of the unmanned aerial; the lower end of the rotating bracket 4 is rotatably connected with the output end of the driving structure in a hinged mode.
The drive structure includes electric putter 6 and the flexible control system of drive electric putter 6 operation, electric putter 6 is installed on fixing base 7 and is rotated through fixing base 7 and connect in the 8 below of launching cradle, electric putter 6's output is terminal to rotate with runing rest 4 and is connected, like this under control system's control, electric putter 6 drives runing rest 4 through flexible and rotates through rotating base 5 to the air supply connects mouth 1 compresses tightly at unmanned aerial vehicle air supply interface or breaks away from and the intercommunication of unmanned aerial vehicle air supply interface under runing rest 4's the drive, thereby let operating personnel keep away from the initiating explosive device, the personnel's safety at the transmission scene has effectively been guaranteed, whole mechanism's wide-angle is rotatory, provide sufficient safe distance for unmanned aerial vehicle motion, the transmission security has been improved.
Example 2
Referring to fig. 3, in the embodiment of the present invention, based on embodiment 1, the control system includes a power supply electrically connected to the electric push rod 6 through a solenoid valve, and a controller electrically connected to a control circuit of the electric push rod 6, where the controller controls to drive the solenoid valve to open and close through a relay connected to the power supply, so that when docking is performed, the electric push rod 6 extends out to push the rotary bracket 4 to rotate through the rotary base 5, so as to drive the air source nozzle 1 to be close to the air source port of the unmanned aerial vehicle, after docking is in place, the stroke of the electric push rod 6 reaches a preset limit, so as to send a feedback signal in place and feed the feedback signal back to the controller, the controller sends a control instruction, the relay drives the solenoid valve to power off the electric push rod 6 to stop operating, thereby completing automatic docking, and after power off, the electric push rod 6 in the prior art can be self-, and the gas source connector 1 is tightly pressed by the compression spring 2 to provide a butt joint pretightening force; when needing to separate, manual control electric putter 6 circular telegram and withdrawal to drive air supply faucet 1 and keep away from unmanned aerial vehicle air supply mouth, separate the feedback signal that targets in place through electric putter 6's stroke predetermined limit and send to the controller after targetting in place, thereby the controller sends the stop command, thereby drives the solenoid valve through the relay and cuts off the power supply stop motion to electric putter 6.
The working principle of the invention is as follows: when butt joint is carried out, the electric push rod 6 extends out, the rotary support 4 is pushed to rotate through the rotary base 5, so that the air source nozzle 1 is driven to be close to an air source port of the unmanned aerial vehicle, the stroke of the electric push rod 6 reaches preset limit after butt joint in place, a feedback signal in place is sent out and fed back to the controller, the controller sends out a control instruction, the relay drives the electromagnetic valve to cut off the power of the electric push rod 6 so as to stop acting, automatic butt joint is completed, the electric push rod 6 in the prior art can be self-locked after power is cut off, and the compression spring 2 compresses the reaction force of the air source nozzle 1 to provide butt joint preti; when needing to separate, manual control electric putter 6 circular telegram and withdrawal to drive air supply faucet 1 and keep away from unmanned aerial vehicle air supply mouth, separate the feedback signal that targets in place through electric putter 6's stroke predetermined limit and send to the controller after targetting in place, thereby the controller sends the stop command, thereby drives the solenoid valve through the relay and cuts off the power supply stop motion to electric putter 6.
The standard parts used in the invention can be purchased from the market, the special-shaped parts can be customized according to the description of the specification and the accompanying drawings, the specific connection mode of each part adopts conventional means such as bolts, rivets, welding and the like mature in the prior art, the machines, the parts and equipment adopt conventional models in the prior art, and the circuit connection adopts the conventional connection mode in the prior art, so that the detailed description is omitted.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. The utility model provides an automatic butt joint air supply separating mechanism of big corner, includes air supply connector (1) that supports on launching rack (8) through the leg joint, its characterized in that, support and launching rack (8) rotate the connection, the intercommunication is provided with air supply pipeline (3) on air supply connector (1), air supply connector (1) is through air supply pipeline (3) and gas cylinder intercommunication, support and launching rack (8) rotate to be connected and the end is connected the transmission through drive structure, drive structure passes through fixing base (7) and rotates and install on launching rack (8), and drive structure's output and support end rotate and connect, drive air supply connector (1) through the support drive the spacing formula rotation that forms big corner in the flexible in-process of drive structure.
2. The large-rotation-angle automatic butt joint air source separating mechanism is characterized in that the support comprises a rotating support (4) which is rotatably connected to the launching rack (8) through a rotating base (5).
3. The large-rotation-angle automatic butt joint air source separating mechanism is characterized in that the rotating base (5) is fixedly arranged on the launching frame (8) and is rotatably connected with the rotating support (4) through a rotating pin.
4. The large-rotation-angle automatic butt joint air source separating mechanism is characterized in that the upper end of the rotating support (4) is connected and assembled with the tail end of the air source connector (1), and the lower end of the rotating support (4) is rotatably connected with the output end of the driving structure in a hinged mode.
5. The large-rotation-angle automatic butt joint air source separating mechanism is characterized in that the air source nozzle (1) is in sliding fit with the upper end of the rotating support (4), and one end, far away from the rotating support (4), of the air source nozzle (1) is elastically connected with the tail end of the rotating support (4) through the compression spring (2).
6. The large-corner automatic butt joint air source separating mechanism according to claim 1, wherein the driving structure comprises an electric push rod (6) and a control system for driving the electric push rod (6) to extend and retract, the electric push rod (6) is mounted on a fixing seat (7) and is rotatably connected below the launching frame (8) through the fixing seat (7), and the tail end of the output end of the electric push rod (6) is rotatably connected with the rotating support (4).
7. The mechanism of claim 6, wherein the control system comprises a power supply electrically connected with the electric push rod (6) through a solenoid valve and a controller electrically connected with a control circuit of the electric push rod (6), and the controller controls the solenoid valve to be opened and closed through a relay connected with the power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910975769.8A CN110671211B (en) | 2019-10-15 | 2019-10-15 | Large-corner automatic butt joint air source separating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910975769.8A CN110671211B (en) | 2019-10-15 | 2019-10-15 | Large-corner automatic butt joint air source separating mechanism |
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| Publication Number | Publication Date |
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| CN110671211A true CN110671211A (en) | 2020-01-10 |
| CN110671211B CN110671211B (en) | 2021-07-13 |
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| CN201910975769.8A Active CN110671211B (en) | 2019-10-15 | 2019-10-15 | Large-corner automatic butt joint air source separating mechanism |
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| GB756056A (en) * | 1953-08-13 | 1956-08-29 | Ml Aviation Co Ltd | Improvements relating to rocket-propelled aircraft and the like |
| CN103723281A (en) * | 2013-12-31 | 2014-04-16 | 北京中宇新泰科技发展有限公司 | Folding wing unmanned aerial vehicle pneumatic launcher |
| CN106114891A (en) * | 2016-08-03 | 2016-11-16 | 南昌白龙马航空科技有限公司 | The pneumatic launching cradle of unmanned plane |
| WO2017037699A1 (en) * | 2015-09-01 | 2017-03-09 | Uvision Air Ltd | Launcher for unmanned aerial vehicles |
| CN106697317A (en) * | 2016-11-30 | 2017-05-24 | 深圳市优鹰科技有限公司 | Single-rail catapult frame of fixed-wing unmanned aerial vehicle |
| CN107097968A (en) * | 2017-05-03 | 2017-08-29 | 西安伺动科技有限公司 | A kind of pneumatic unmanned plane emitter |
| CN207191472U (en) * | 2017-09-12 | 2018-04-06 | 马鞍山市靓马航空科技有限公司 | A kind of adjustable support of gas-powered catapult |
| CN108190040A (en) * | 2017-12-20 | 2018-06-22 | 海鹰航空通用装备有限责任公司 | A kind of pneumatic launching cradle of universal small drone |
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2019
- 2019-10-15 CN CN201910975769.8A patent/CN110671211B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB756056A (en) * | 1953-08-13 | 1956-08-29 | Ml Aviation Co Ltd | Improvements relating to rocket-propelled aircraft and the like |
| CN103723281A (en) * | 2013-12-31 | 2014-04-16 | 北京中宇新泰科技发展有限公司 | Folding wing unmanned aerial vehicle pneumatic launcher |
| WO2017037699A1 (en) * | 2015-09-01 | 2017-03-09 | Uvision Air Ltd | Launcher for unmanned aerial vehicles |
| CN106114891A (en) * | 2016-08-03 | 2016-11-16 | 南昌白龙马航空科技有限公司 | The pneumatic launching cradle of unmanned plane |
| CN106697317A (en) * | 2016-11-30 | 2017-05-24 | 深圳市优鹰科技有限公司 | Single-rail catapult frame of fixed-wing unmanned aerial vehicle |
| CN107097968A (en) * | 2017-05-03 | 2017-08-29 | 西安伺动科技有限公司 | A kind of pneumatic unmanned plane emitter |
| CN207191472U (en) * | 2017-09-12 | 2018-04-06 | 马鞍山市靓马航空科技有限公司 | A kind of adjustable support of gas-powered catapult |
| CN108190040A (en) * | 2017-12-20 | 2018-06-22 | 海鹰航空通用装备有限责任公司 | A kind of pneumatic launching cradle of universal small drone |
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| CN110671211B (en) | 2021-07-13 |
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