CN205633092U - A block and hold mechanism for unmanned aerial vehicle transmission - Google Patents
A block and hold mechanism for unmanned aerial vehicle transmission Download PDFInfo
- Publication number
- CN205633092U CN205633092U CN201521135603.9U CN201521135603U CN205633092U CN 205633092 U CN205633092 U CN 205633092U CN 201521135603 U CN201521135603 U CN 201521135603U CN 205633092 U CN205633092 U CN 205633092U
- Authority
- CN
- China
- Prior art keywords
- wing
- support
- unmanned plane
- support arm
- unmanned aerial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Landscapes
- Forklifts And Lifting Vehicles (AREA)
Abstract
The utility model discloses a block and hold mechanism for unmanned aerial vehicle transmission, it includes U type support, the angle box is connected to four wings, four wings are hung a little and the wing connecting piece, U type support detachably install on launch vehicle, the support arm structure that sticked up its both sides is the same, low back two high spouts before the support arm top all has, four wings are connected the angle box and are fixed on the wing of unmanned aerial vehicle's both sides through two symmetries on the screw respectively, the wing is hung and a little is four support arms that the shape is the same, the wing is hung the one end that has a screw hole of point and can utilized the screw connection on the angle box is connected to the wing with the help of the wing connecting piece, the other end that the wing was hung a little is the cooperation the ladder type slider of spout, the mode short through former long back clamps four wings string point respectively in four spouts of U type support, can support unmanned aerial vehicle and prepare the transmission shape attitude. The utility model discloses a hanging the point and forming the guide rail with the support, guide effect when playing the clamping with the transmission makes unmanned aerial vehicle's transmission more smooth.
Description
Technical field
This utility model relates to a kind of catch mechanism launched for unmanned plane, and by the stepped support front and back there to be high low head as supporting guide, the hanging point being fixed on wing is dynamic guide rail, thus collectively constitutes the guide rail launched for unmanned plane.It is fixed with brake cable mechanism on supporting guide and plays spacing effect before transmission.This catch mechanism launched for unmanned plane is collectively constituted by guide rail and brake cable mechanism.
Background technology
In recent years, along with ocean is more and more significant in the aspect effect such as development of world commerce, economic boost and country, countries in the world start constantly to excavate and utilize abundant marine resources；Sovereignty consciousness in various countries' strengthens all the more simultaneously, and ocean strategy meaning in war is the most great, and thing followed sovereignty controversial issue constantly occurs and upgrades.Therefore country wants to realize exploitation marine resources, and the sovereignty that safeguard one's country are inviolable, and become the purposes such as military power, and one of them important step is the naval of Development of Morden.
The situation more sophisticated that Chinese Navy is faced, in order to tackle series of complex situation and current severe international-style, needs to improve naval's level of modernization as early as possible.This just requires that we constantly promote naval equipment, and in development, it is an important measure that being used in combination of unmanned plane and naval ship becomes.Along with constantly practice and the demand of future war, it is anticipated that Shipborne UAV will become the irreplaceable part of sea warfare, have bright prospects.
Shipborne UAV is it is generally required to perform the surface monitoring task and goal search mission of distance range near, middle, and supplements the own investigation ability of reconnaissance satellite and naval vessels.During long boat, SUAV quality is relatively big, and its discharger is used for pneumatic system launching cradle, and pneumatic means structure is complicated, needs to be equipped with huge pneumatic system regulator cubicle, not only to occupy bigger place, also to spend more man power and material.Ordinary construction launching cradle is more difficult to be installed without sled rear-mounted propeller unmanned plane.
Summary of the invention
This utility model predominantly solves above-mentioned series of problems, it is provided that a kind of bear constant weight for the clamping launched without sled rear-mounted propeller unmanned plane and supporting mechanism.
nullThe catch mechanism that this utility model is launched for unmanned plane includes U-shaped support、Four wing joint angle boxes、Four wing hanging points and wing connection，Described U-shaped support is removably mounted on car launcher，The support arm structure that its both sides are holded up is identical，The top of described support arm is all with two low early and high after chutes，Thus formed stepped，Four described wing joint angle boxes are fixed on the buttress brace of both sides wing of unmanned plane by screw two two symmetry respectively，Described wing hanging point is the support arm that four shapes are identical，But two length are the longest，Two length are slightly shorter，One end being threaded hole of described wing hanging point can utilize screw to be connected on described wing joint angle box by described wing connection，The other end of described wing hanging point is the ladder type slide block coordinating described chute，By four described wing hanging points are installed in four chutes of described U-shaped support respectively by the way of the front part is long and the back is short，Described unmanned plane can be supported on preparation emission state.
The most also include brake cable mechanism, it has the structure of bracing wire for connecting on flashboard, described flashboard is generally arcuate to turn shape plate, at its flex point, there is pin-and-hole, the bottom of the higher chute in the collateral arm rear portion of described U-shaped support can be arranged on by bearing pin in the way of freely rotatable, the one end of described flashboard has through hole, for connecting described brake cable, when described brake cable is fastened and is tightened up on described car launcher, the other end being installed on the support arm of both sides two described flashboards can be crimped on the described wing hanging point being installed on two chutes respectively.
Owing to pneumatic means structure is complicated, need personnel's design of specialty, operation, need a large amount of funds.Simultaneously because structure is complicated and it needs to be equipped with huge pneumatic system regulator cubicle, causes ejection mechanism not only floor space big, also accordingly increased a series of corollary equipment.This utility model only uses frame for movement to complete unmanned plane clamping and transmitting, largely reduces the floor space of launching cradle, has saved space.
For alleviating unmanned plane weight, preventing the winding problem of skid and recycling network, the unmanned plane majority carrying out net collision recovery does not install skid, thus causes part rear-mounted propeller not have lifting point without the unmanned plane of skid simultaneously.Hanging point is fixed with the angle box on wing buttress brace by this utility model by contiguous block, is formed on wing the hanging point being available for clamping.And be connected with aircraft hanging point by support, the part of joint forms a guide rail, adds the brake cable device being fixed on support, realizes guiding when launching and clamping effect.Thus solve the problem without sled unmanned plane clamping.Guide Rail Design is stepped to avoid colliding of rear hanging point and support.
Carry out the unmanned plane of medium and long distance investigation tasks, during small-sized long boat, multiplex petrol engine drives, and needing unmanned plane itself to have stronger flying power, this index will strengthen fuel carrying amount during unmanned plane during flying, thus the volume of the unmanned plane structure designed increases the most accordingly.For bearing unmanned plane weight, this utility model uses U-shaped support to connect aircraft and launching cradle car launcher.Support Design is U-shaped can to avoid rearmounted propeller simultaneously, thus completes the transmitting of rear-mounted propeller unmanned plane.
Being fixed on the car launcher of launching cradle by aircraft rack before transmitting again, during transmitting, by rubber band elastic force, dolly on launching cradle is delivered to peak, brake cable unclamps, and aircraft relies on the power of propeller offer and self inertia to launch away, completes to launch.
Accompanying drawing explanation
Fig. 1 is wing joint angle box schematic diagram.
Fig. 2 is wing connection schematic diagram.
Fig. 3 is wing hanging point schematic diagram.
Fig. 4 is brake cable component schematic diagram.
Fig. 5 is support schematic diagram.
Fig. 6 is that unmanned plane is in the schematic diagram launching readiness.
Detailed description of the invention
Below in conjunction with accompanying drawing, this utility model is described in detail.
As shown in drawings, the catch mechanism launched for unmanned plane of the present utility model includes U-shaped support 1, four wing hanging points 2 of 5, four wing joint angle boxes and wing connection 3, U-shaped support 5 is removably mounted on car launcher, the support arm structure that both sides are holded up is identical, its top is all with two low early and high after chutes, thus is formed stepped.Four wing joint angle boxes 1 are fixed on the buttress brace of both sides wing of unmanned plane by screw two two symmetry respectively, and wing hanging point 2 is the support arm that four shapes are identical, but two length are the longest, and two length are slightly shorter.One end being threaded hole of wing hanging point 2 can utilize screw to be connected on wing joint angle box 1 by wing connection 3, the other end of wing hanging point 2 is the ladder type slide block coordinating U-shaped support 5 top chute, by four wing hanging points 2 are installed in four chutes of U-shaped support by the way of the front part is long and the back is short, it is possible to unmanned plane to be supported on preparation emission state.
Flashboard 4 turns shape plate for generally arcuate, there are on flashboard 4 two through holes, through hole at its flex point is pin-and-hole, utilize this pin-and-hole that flashboard 4 can be arranged in the way of freely rotatable the bottom of the higher chute in the collateral arm rear portion of U-shaped support 5 by bearing pin, the through hole being positioned at one end of flashboard 4, for connecting brake cable, when brake cable is fastened and is tightened up on car launcher, the other end being installed on the support arm of both sides two flashboards 4 can be crimped on the wing hanging point 2 being installed on two chutes respectively.
The wing joint angle box 1 of Fig. 1 is connected with bolt by the wing connection 3 of Fig. 2 with Fig. 3 wing hanging point 2.And with rivet, nut and plate nut etc., angle box is fixed on wing buttress brace, using the trapezoidal portions on wing hanging point 2 as the part with dovetail groove stepped on slide block, with support as supporting chute guide rail, match formation sliding track mechanism by two parts.Before transmitting, unmanned vehicle engine starts, and pulls flashboard 4 by brake cable, withstands hanging point, limits aircraft and makes it immovable.During transmitting, along with launching cradle dolly forward, brake cable discharges, and brake cable loses tightening force, and flashboard 4 acts on hanging point the most effectively.Aircraft, along with dolly associated movement, keeps relative static conditions.Dolly arrives specific bit and postpones stopping, and due to inertia and the power of aircraft itself, aircraft keeps kinestate under guide rail guide effect, departs from launching cradle, it is achieved that launch.
U-shaped design high after using the front end due to U-shaped support 5, so be fixed on wing two short wing hanging points 2 can not encounter the anterior relatively low chute of U-shaped support 5 both sides support arm, the propeller of unmanned plane also can unimpededly be launched through U-shaped support 5 smoothly.
Chute on the support arm of U-shaped support 5 both sides plays the clamping to unmanned plane hanging point and fixation, and while launching, the guide rail that hanging point and support collectively constitute plays guide effect.
The brake cable mechanism installed on U-shaped support 5 acts on jointly with stair-stepping design, and the aircraft before launching is played position-limiting action.
Claims (2)
1. one kind for unmanned plane launch catch mechanism, it is characterised in that: include U-shaped support, four
Wing joint angle box, four wing hanging points and wing connection, described U-shaped support is removably mounted on to be sent out
Penetrating on car, the support arm structure that its both sides are holded up is identical, and the top of described support arm is all with low early and high after two
Chute, thus formed stepped, four described wing joint angle boxes are fixed on by screw two two symmetry respectively
On the buttress brace of the both sides wing of unmanned plane, described wing hanging point is the support arm that four shapes are identical, but two
Individual length is the longest, and two length are slightly shorter, and one end being threaded hole of described wing hanging point can be by described
Wing connection utilizes screw to be connected on described wing joint angle box, and the other end of described wing hanging point is for joining
Close the ladder type slide block of described chute, by four described wing hanging points are blocked dress respectively by the way of the front part is long and the back is short
In four chutes of described U-shaped support, it is possible to described unmanned plane is supported on preparation emission state.
2. the catch mechanism launched for unmanned plane as claimed in claim 1, it is characterised in that: also wrap
Including brake cable mechanism, it is to connect on flashboard that to have the structure of bracing wire, described flashboard be generally arcuate to turn shape plate,
At its flex point, there is pin-and-hole, it is possible in the way of freely rotatable, be arranged on the side of described U-shaped support by bearing pin
The bottom of the chute that support arm rear portion is higher, the one end of described flashboard has through hole, is used for connecting described brake cable,
When described brake cable is fastened and is tightened up on described car launcher, two the described flashboards being installed on the support arm of both sides
The other end can be crimped on the described wing hanging point being installed on two chutes respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521135603.9U CN205633092U (en) | 2015-12-31 | 2015-12-31 | A block and hold mechanism for unmanned aerial vehicle transmission |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521135603.9U CN205633092U (en) | 2015-12-31 | 2015-12-31 | A block and hold mechanism for unmanned aerial vehicle transmission |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205633092U true CN205633092U (en) | 2016-10-12 |
Family
ID=57078701
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521135603.9U Withdrawn - After Issue CN205633092U (en) | 2015-12-31 | 2015-12-31 | A block and hold mechanism for unmanned aerial vehicle transmission |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205633092U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105438495A (en) * | 2015-12-31 | 2016-03-30 | 航天神舟飞行器有限公司 | Clamping mechanism for launching unmanned aerial vehicle |
| CN106494636A (en) * | 2016-10-20 | 2017-03-15 | 北京华信宇航科技有限公司 | Trailed model vehicle launch system and its discharger |
| CN114013676A (en) * | 2022-01-10 | 2022-02-08 | 南充职业技术学院 | Unmanned aerial vehicle take-off cradle head for city planning and surveying |
-
2015
- 2015-12-31 CN CN201521135603.9U patent/CN205633092U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105438495A (en) * | 2015-12-31 | 2016-03-30 | 航天神舟飞行器有限公司 | Clamping mechanism for launching unmanned aerial vehicle |
| CN106494636A (en) * | 2016-10-20 | 2017-03-15 | 北京华信宇航科技有限公司 | Trailed model vehicle launch system and its discharger |
| CN106494636B (en) * | 2016-10-20 | 2019-01-15 | 北京华信宇航科技有限公司 | Trailed model vehicle launch system and its emitter |
| CN114013676A (en) * | 2022-01-10 | 2022-02-08 | 南充职业技术学院 | Unmanned aerial vehicle take-off cradle head for city planning and surveying |
| CN114013676B (en) * | 2022-01-10 | 2022-03-15 | 南充职业技术学院 | Unmanned aerial vehicle take-off cradle head for city planning and surveying |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8584985B2 (en) | Launch system | |
| CN205633092U (en) | A block and hold mechanism for unmanned aerial vehicle transmission | |
| US20140283728A1 (en) | Take-Off and Landing System for Carrier Aircraft on an Aircraft Carrier and the Method Thereof | |
| US10040549B2 (en) | Single use logistic glider | |
| JP6955279B2 (en) | Emergency vessel detention system and method | |
| CA2990606A1 (en) | Submersible vessel having retractable wing and keel assemblies | |
| CN207580097U (en) | A kind of automatic capture tail gliding style yawl draw off gear and double chute systems | |
| US20060081733A1 (en) | Pivotable pylon for external carriage of aircraft stores | |
| CN110386257A (en) | For vertical translation aircraft warship device and naval vessel | |
| US20200216147A1 (en) | Extended tow boat rope connector for water activities | |
| CN105667790A (en) | General layout of unmanned aerial vehicle capable of taking off with catapult assisted and being recovered by bumping net | |
| US5102145A (en) | Aerial gunnery target system | |
| CN202686721U (en) | Bow-and-crossbow type marine hawser apparatus | |
| CN106945807A (en) | A kind of unmanned air cushion platform without flight-deck aircraft carrier | |
| US8608111B2 (en) | Decoupling mechanism for a store | |
| CN105438495B (en) | Catch mechanism for unmanned plane transmitting | |
| CN108202876B (en) | Guarantor type unmanned aerial vehicle launches draw gear | |
| CN102951297A (en) | Method and device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection | |
| CN115709815A (en) | Portable unmanned aerial vehicle jettison device | |
| CN214138961U (en) | Air-drop war chariot buffer system disengaging device | |
| EP2119998A1 (en) | Launch system | |
| CN204021244U (en) | Waters runway military aircraft lifting gear | |
| US5732906A (en) | Nose landing gear assembly for a catapult launched airplane | |
| CN203231699U (en) | Gliding drone aircraft | |
| CN106586016B (en) | It is aerial to hang bullet system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161012 Effective date of abandoning: 20190301 |