CN203666998U - Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle - Google Patents
Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN203666998U CN203666998U CN201320769711.6U CN201320769711U CN203666998U CN 203666998 U CN203666998 U CN 203666998U CN 201320769711 U CN201320769711 U CN 201320769711U CN 203666998 U CN203666998 U CN 203666998U
- Authority
- CN
- China
- Prior art keywords
- parachuting
- catapulting
- unmanned aerial
- aerial vehicle
- supporting beam
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a catapulting and parachuting integrated type supporting beam of an unmanned aerial vehicle. The catapulting and parachuting integrated type supporting beam of the unmanned aerial vehicle comprises a body, and is characterized in that pipe inserting holes are formed in the two ends and the middle of the body respectively, protruding parts are arranged at the two ends of the body respectively, a protruding end of each protruding part is arc, a connecting hole is formed in the middle of each protruding part, a protruding part I is arranged at the lower portion of one end of the body, the protruding part I and the lower end of the body form an arc part I and an arc part II, and a plurality of hollowed-out holes are formed in the surface of the body. Even though a large number of hollowed-out holes are formed in the middle of the body, the catapulting and parachuting integrated type supporting beam of the unmanned aerial vehicle does not reduce the strength, and is more reasonable in overall structure. A front inserting pipe, a middle inserting pipe and a rear inserting pipe are connected together to form a load-bearing beam in the process of parachuting, so that the internal structure of a vehicle body is simplified and the weight of the vehicle body is reduced. Meanwhile, a catapulting device is designed on the support, so that the catapulting and parachuting integrated type supporting beam is achieved, and the structure of the vehicle body is further simplified.
Description
Technical field
The utility model belongs to aircraft manufacturing field, is specifically related to the loose integral type support beam that falls of a kind of unmanned aerial vehicle ejecting.
Background technology
Robot airplane is called for short " unmanned plane ", is the not manned aircraft that utilizes radio robot and the process controller of providing for oneself to handle.On machine, without driving compartment, but the equipment such as autopilot, process controller is installed.On ground, naval vessels or machine tool command and control station personnel by equipment such as radars, to its follow the tracks of, location, remote control, remote measurement and digital communication.Can under radio telecommand, as conventional airplane, take off or launch with booster rocket, also can take aerial input to by machine tool and fly.When recovery, the available mode automatic Landing the same with conventional airplane landing mission, also can reclaim with parachute or block by remote control.Can use repeatedly by repetitiousness.Be widely used in aerial reconnaissance, supervision, communication, antisubmarine, electro countermeasure etc.
When at present unmanned plane lands in parachuting mode, parachute is opened and can be produced vibration to body afterwards, can affect the land of aircraft.Meanwhile, also there is no to realize at present parachuting and launch the support beam into integral type.
Utility model content
The utility model object is to provide a kind of simple in structure, manufacture easy, the integral type support beam that parachuting function and ejecting function can be gathered together.
Scheme of the present utility model is as follows: a kind of unmanned aerial vehicle ejecting is loose falls integral type support beam, comprises body, and two ends and the middle part of body are provided with insertion hole, and body two ends are provided with protrusion, and jag is that orphan and middle part are provided with connecting bore; Bottom, body one end is provided with protrusion I, and protrusion I and this body lower end form orphan portion I, orphan portion II, and described body surface is provided with several hollow holes.Connecting bore is for connecting the dip rope of parachute, and bungee when orphan portion II is unmanned aerial vehicle ejecting is placed position, and orphan portion I can play certain position-limiting action to aircraft, sideslip while preventing from taking off.
Further, described body is made up of aluminum alloy materials.
The a large amount of hollow outs in the utility model middle part, not only do not reduce intensity and make on the contrary integral structure more rationalize; Bearing beam when intubate after in front is coupled together as parachuting, has reduced inner structure and the weight of fuselage; Also catapult-launching gear is designed on supporting simultaneously, realized parachuting and launched the support beam of integral type, reduced again airframe structure.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model is described further.
A kind of unmanned aerial vehicle ejecting is loose falls integral type support beam, comprises body 1, and two ends and the middle part of body are provided with insertion hole 2, and body two ends are provided with protrusion 3, and jag 4 is provided with connecting bore 5 for orphan and middle part; Body 1 bottom, one end is provided with protrusion I 6, and protrusion I 6 forms orphan portion I 7, orphan portion II 8 with this body lower end, and described body 1 surface is provided with several hollow holes 9.Connecting bore 5 is for connecting the dip rope of parachute, and bungee when orphan portion II 8 is unmanned aerial vehicle ejecting is placed position, and orphan portion I 7 can play certain position-limiting action to aircraft, sideslip while preventing from taking off.Described body 1 is made up of aluminum alloy materials.
The a large amount of hollow outs in the utility model middle part, not only do not reduce intensity and make on the contrary integral structure more rationalize; Bearing beam when intubate after in front is coupled together as parachuting, has reduced inner structure and the weight of fuselage; Also catapult-launching gear is designed on supporting simultaneously, realized parachuting and launched the support beam of integral type, reduced again airframe structure.
Although above the specific embodiment of the present utility model has been given to describe in detail and explanation; but what should indicate is; we can carry out various equivalences to above-mentioned embodiment according to conception of the present utility model and change and revise; when its function producing does not exceed spiritual that specification sheets contains yet, all should be within protection domain of the present utility model.
Claims (2)
1. unmanned aerial vehicle ejecting is loose falls an integral type support beam, comprises body, and two ends and the middle part of its feature noumenon are provided with insertion hole, and body two ends are provided with protrusion, and jag is that orphan and middle part are provided with connecting bore; Bottom, body one end is provided with protrusion I, and protrusion I and this body lower end form orphan portion I, orphan portion II, and described body surface is provided with several hollow holes.
2. a kind of unmanned aerial vehicle ejecting according to claim 1 is loose falls integral type support beam, and the body described in it is characterized in that is made up of aluminum alloy materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320769711.6U CN203666998U (en) | 2013-11-30 | 2013-11-30 | Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320769711.6U CN203666998U (en) | 2013-11-30 | 2013-11-30 | Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203666998U true CN203666998U (en) | 2014-06-25 |
Family
ID=50963318
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320769711.6U Expired - Fee Related CN203666998U (en) | 2013-11-30 | 2013-11-30 | Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203666998U (en) |
-
2013
- 2013-11-30 CN CN201320769711.6U patent/CN203666998U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102243228B1 (en) | Release and capture of a fixedwing aircraft | |
| CN102806990B (en) | Portable type mapping unmanned plane | |
| CN107792381B (en) | Unmanned aerial vehicle air-based towing net type recovery device and method | |
| CN102700713A (en) | Unmanned aerial vehicle with payload body | |
| CN104943864A (en) | Long-airborne-period combined stratosphere aircraft system scheme based on solar unmanned aerial vehicles | |
| CN104960657A (en) | Combined-separate stratospheric aircraft system scheme | |
| CN104483088A (en) | Wind tunnel multi-body separation free light test method of simulating residual engine thrust | |
| CN205221105U (en) | Solar energy VTOL fixed wing uavs | |
| CN204056287U (en) | A kind of autonomous flight is without active force unmanned plane | |
| CN202935570U (en) | Portable mapping unmanned aerial plane | |
| CN204916155U (en) | Multipurpose unmanned aerial vehicle | |
| CN205293058U (en) | Conveniently carry on fixed wing uavs of jumbo size loading device | |
| CN203666970U (en) | Driving connecting structure for aileron of unmanned aerial vehicle | |
| CN203666998U (en) | Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle | |
| CN104192295B (en) | A kind of autonomous flight is without active force unmanned plane and flying method thereof | |
| CN203958603U (en) | A kind of aerial survey unmanned plane | |
| CN203486130U (en) | Camera cabin at bottom of unmanned aerial vehicle | |
| CN206954510U (en) | It is a kind of can VTOL fixed-wing unmanned plane | |
| CN106347677B (en) | A kind of unmanned machine parachute | |
| CN211178156U (en) | Unmanned drone | |
| CN204916213U (en) | Unmanned aerial vehicle starts jettison device | |
| CN203497168U (en) | Front camera bin of unmanned plane | |
| CN203497173U (en) | Single-interceptor tail wing of unmanned plane | |
| CN107150806A (en) | It is a kind of can VTOL fixed-wing unmanned plane | |
| CN203727648U (en) | Unmanned annunciator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: ANHUI TIANLU AVIAT TECHNOLOGY CO., LTD. Free format text: FORMER NAME: HUAIBEI TIANLU AVIAT TECHNOLOGY CO., LTD. |
|
| CP01 | Change in the name or title of a patent holder |
Address after: 235000, F industrial building, Longhu Industrial Park, Huaibei Economic Development Zone, Anhui Province, No. 3, building 1-2 Patentee after: Anhui's aviation Polytron Technologies Inc Address before: 235000, F industrial building, Longhu Industrial Park, Huaibei Economic Development Zone, Anhui Province, No. 3, building 1-2 Patentee before: Huaibei City Tian Lu Aerotech Inc. |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle Effective date of registration: 20160329 Granted publication date: 20140625 Pledgee: Huaibei City Development Zone Hongfu Construction Development Co. Ltd. Pledgor: Anhui's aviation Polytron Technologies Inc Registration number: 2016340000013 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20170512 Granted publication date: 20140625 Pledgee: Huaibei City Development Zone Hongfu Construction Development Co. Ltd. Pledgor: Anhui's aviation Polytron Technologies Inc Registration number: 2016340000013 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Catapulting and parachuting integrated type supporting beam of unmanned aerial vehicle Effective date of registration: 20170522 Granted publication date: 20140625 Pledgee: Huaibei City Development Zone Hongfu Construction Development Co. Ltd. Pledgor: Anhui's aviation Polytron Technologies Inc Registration number: 2017340000063 |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140625 Termination date: 20201130 |