CN202414170U - Pull type accurate parachuting device for unmanned aerial vehicle - Google Patents
Pull type accurate parachuting device for unmanned aerial vehicle Download PDFInfo
- Publication number
- CN202414170U CN202414170U CN2011205172665U CN201120517266U CN202414170U CN 202414170 U CN202414170 U CN 202414170U CN 2011205172665 U CN2011205172665 U CN 2011205172665U CN 201120517266 U CN201120517266 U CN 201120517266U CN 202414170 U CN202414170 U CN 202414170U
- Authority
- CN
- China
- Prior art keywords
- parachuting
- unmanned plane
- ground
- aerial vehicle
- 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.)
- Expired - Lifetime
Links
Images
Abstract
The utility model discloses a pull type accurate parachuting device for an unmanned aerial vehicle. The pull type accurate parachuting device comprises a similar target sensitivity projectile, a ground irradiator and a pull winch. A parachute, the unmanned aerial vehicle and the similar target sensitivity projectile are sequentially connected. The ground irradiator and the pull winch are respectively arranged at the destination. According to the pull type accurate parachuting device, the similar target sensitivity projectile is hanged on the unmanned aerial vehicle; and after the ground irradiator leads an explosive column to burst, eject and shuttle accurately to a predetermined landing point, a pull rope is used for pulling the unmanned aerial vehicle in parachuting of the parachute to land on the predetermined landing point. The pull type accurate parachuting device can ensure the accuracy of parachuting, recovering and pointing the unmanned aerial vehicle.
Description
Technical field
The utility model relates to telecontrol engineering, is applicable to unmanned plane emission recovery, specifically relates to the accurate parachuting apparatus and method of a kind of towed unmanned plane.
Background technology
Unmanned plane reclaims the landing type and generally is divided into: the downhill race of unmanned plane runway, hit that net reclaims, several kinds of aerial helicopter recovery, parachuting recovery etc.Wherein parachuting is recovered in has appreciiable use in China's unmanned plane.When unmanned plane during flying was overhead to predetermined level point, parachute was opened.Unmanned plane parachute traction down slowly land in predetermined level point on every side in the certain limit.As shown in Figure 1, present parachuting is reclaimed stationing accuracy and generally can only be reached about 50m.
Common parachuting precision is lower; Its major cause is: 1) because parachute-opening constantly must be after aero-engine shuts down several seconds: engine off fixes on before the predetermined level point constantly; After stopping, aircraft rely on inertia to continue flight forward, parachute-opening after several seconds approximately.So parachute-opening point just can not accurately be accomplished directly over predetermined parachute-opening point; 2) after the parachute-opening, the aircraft freedom of entry descends slowly and lightly the stage, because the influence of factor such as wind speed, aircraft produces drift in the horizontal surface more or less in this stage, hundreds of rice at most, tens meters at least.
Summary of the invention
The purpose of the utility model is, a kind of parachuting landing gear and landing concept thereof are provided, and makes unmanned function realize that high precision lands.
To above-mentioned purpose; The utility model is taked following technical scheme; The accurate parachuting device of towed unmanned plane comprises: type last quick bullet, ground irradiator and towing capstan is characterized in that; Parachute, unmanned plane, a type last quick bullet connect successively, and ground irradiator and towing capstan are installed in target ground respectively.
In the internal weapon bays of said type of last quick bullet; Be equipped with and fly shuttle, hauling rope and blast powder column, fly shuttle and be connected towards the below of the last quick bullet body of class and with hauling rope, the traction cheese is loaded on internal weapon bays upper-deck cabin body; The blast powder column is installed on cabin body under the internal weapon bays; Infrared senstive device is fixedly installed in outside the internal weapon bays, and rotating blade is connected the upper end of the last quick bullet of rotating shaft type of being connected in through Connection Block with rotating shaft.
Parachute connects unmanned plane; The quick bullet in carry class end, unmanned plane below; The ground irradiator is through transmitting to the explosion of infrared senstive device guiding blast powder column; Launch out and fly to fly shuttle bonded assembly hauling rope through ground-surface towing capstan again and draw after shuttle accurately arrives predetermined level point, make with the traction of parachute bonded assembly unmanned plane and drop to predetermined level point.
The utility model has the advantages that; Utilize present existing mature technology and equipment; The last quick bullet of carry one kind on unmanned plane, the ground irradiator of ground increase by one cover infrared beam transmitter is after a guiding type last quick bullet explosion is launched and flown the predetermined level point of the accurate arrival of shuttle; The unmanned plane that re-uses in the hauling rope traction parachuting drops on the predetermined level point, accomplishes the high precision parachuting of unmanned plane and lands.This method can guarantee that unmanned aircraft parachute descent reclaims stationing accuracy in 5 meters.
Description of drawings
Fig. 1 is the unmanned plane landing scheme drawing of prior art.
Fig. 2 is the unmanned plane landing scheme drawing of the utility model.
Fig. 3 is the structural representation of the utility model.
Among the figure: 1, type last quick bullet, 11, fly shuttle, 12, infrared senstive device, 13, hauling rope, 14, the blast powder column, 15, Connection Block, 16, rotating shaft.17, rotating blade, 2, unmanned plane, 3, parachute, 4, ground irradiator, 5, towing capstan.
The specific embodiment
Combine accompanying drawing and embodiment that the utility model is described further at present; Referring to Fig. 2 and Fig. 3; The accurate parachuting device of towed unmanned plane; Comprise: type last quick bullet 1, ground irradiator 4 and towing capstan 5, parachute 3, unmanned plane 2, a type last quick bullet 1 connect successively, and ground irradiator 4 and towing capstan 5 are with being installed in target respectively.In the internal weapon bays of said type of last quick bullet 1; Be equipped with and fly shuttle 11, hauling rope 13 and blast powder column 14, fly shuttle 11 and be connected towards the below of type last quick bullet 1 body and with hauling rope 13, hauling rope 13 dishes are loaded on internal weapon bays upper-deck cabin body; Blast powder column 14 is installed on cabin body under the internal weapon bays; Infrared senstive device 12 is fixedly installed in outside the internal weapon bays, and rotating blade 17 is connected the upper end of the last quick bullet 1 of rotating shaft 16 types of being connected in through Connection Block 15 with rotating shaft 16.
Embodiment:The last quick bullet 1 of class is installed in the ventral the inside near unmanned plane 2 barycenter.After unmanned plane 2 parking parachute-openings, a type last quick bullet 1 falls and hangs on fuselage with hanging rope in ventral.When descending after unmanned plane 2 parachute-openings, type last quick bullet 1 produces rotation under rotating blade 17 drives.
After unmanned plane 2 parking parachute-openings; 1 pair of ground of the last quick bullet of class is searched for, and passes through the signal of infrared senstive device 12 reception ground irradiators 4 emissions, behind the aligning level point; Ignite 14 explosions of blast powder column and start and fly the predetermined level point of shuttle 11 directives, make to fly shuttle 11 and drop on the predetermined level point.Fly shuttle 11 rear portion tractions one hauling rope 13, hauling rope 13 is with in dish strand form or the last quick internal weapon bays of folded form type of being placed in, and hauling rope 13 is received strand through the towing capstan 5 that ground is provided with.The unmanned plane 2 that makes hauling rope 13 link lands in predetermined level point.
Fly shuttle 11 and drop on after the object point, unmanned plane 2 also aloft descends slowly and lightly with certain descending speed.Hauling rope 13 tightens up with proper speed/angle of traction, and traction unmanned plane 2 lands to the object point position.Unmanned plane 2 is with certain speed free-falling downwards, and hauling rope 13 draws at side-lower simultaneously.Final unmanned plane 2 accurately drops on the predetermined level point.
Claims (2)
1. the accurate parachuting device of towed unmanned plane; Comprise: type last quick bullet (1), ground irradiator (4) and towing capstan (5); It is characterized in that; Parachute (3), unmanned plane (2), a type last quick bullet (1) connect successively, and ground irradiator (4) and towing capstan (5) are installed in target ground respectively.
2. the accurate parachuting device of towed unmanned plane according to claim 1; It is characterized in that, in the internal weapon bays of said type of last quick bullet (1), be equipped with and fly shuttle (11), hauling rope (13) and blast powder column (14); Flying shuttle (11) is connected towards type below of last quick bullet (1) body and with hauling rope (13); Hauling rope (13) dish is loaded on internal weapon bays upper-deck cabin body, and blast powder column (14) is installed on cabin body under the internal weapon bays, and infrared senstive device (12) is fixedly installed in outside the internal weapon bays; Rotating blade (17) is connected the upper end of the last quick bullet of rotating shaft (16) type of being connected in (1) through Connection Block (15) with rotating shaft (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205172665U CN202414170U (en) | 2011-12-13 | 2011-12-13 | Pull type accurate parachuting device for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205172665U CN202414170U (en) | 2011-12-13 | 2011-12-13 | Pull type accurate parachuting device for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202414170U true CN202414170U (en) | 2012-09-05 |
Family
ID=46738957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205172665U Expired - Lifetime CN202414170U (en) | 2011-12-13 | 2011-12-13 | Pull type accurate parachuting device for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202414170U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530255A (en) * | 2011-12-13 | 2012-07-04 | 江西洪都航空工业集团有限责任公司 | Accurate parachute landing device for traction type unmanned plane and method |
-
2011
- 2011-12-13 CN CN2011205172665U patent/CN202414170U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530255A (en) * | 2011-12-13 | 2012-07-04 | 江西洪都航空工业集团有限责任公司 | Accurate parachute landing device for traction type unmanned plane and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102530255A (en) | Accurate parachute landing device for traction type unmanned plane and method | |
| US10133272B2 (en) | Methods and apparatus to deploy and recover a fixed wing unmanned aerial vehicle via a non-fixed wing aircraft | |
| CN108146639B (en) | High-speed parachute landing system and method for recycling small and medium unmanned aerial vehicle and ejection parachute | |
| CN107792381B (en) | Unmanned aerial vehicle air-based towing net type recovery device and method | |
| CN107738750B (en) | Aerial towline towing target system-based unmanned aerial vehicle air-based accurate recovery device and method | |
| CN109229409B (en) | Cluster type unmanned aerial vehicle aerial rapid transmitting system | |
| CN101988813A (en) | Launching system and launching apparatus | |
| CN106379552B (en) | Small drone folding and unfolding method based on captive balloon | |
| CN103043214A (en) | Folding type unmanned plane | |
| CN102520727B (en) | Reconnaissance system with unmanned plane | |
| CN107792371A (en) | A kind of unmanned plane space base rapid fire apparatus and method for system of being towed target based on aviation trailing cable | |
| Honda et al. | D-SEND project for low sonic boom design technology | |
| CN205345355U (en) | Portable unmanned aerial vehicle transmitter | |
| CN103112591A (en) | Multipurpose pneumatic type launch airborne landing flight training device | |
| CN206007850U (en) | Air-to-surface missile fire extinguisher | |
| CN110553550A (en) | anti-unmanned aerial vehicle net catches device in air | |
| CN105292472A (en) | Multi-purpose flexible-wing unmanned aerial vehicle | |
| CN202414170U (en) | Pull type accurate parachuting device for unmanned aerial vehicle | |
| US5137193A (en) | Covert air-to-ground cargo recovery system | |
| CN106945807A (en) | A kind of unmanned air cushion platform without flight-deck aircraft carrier | |
| CN104943866A (en) | Airborne training launching device | |
| WO2016079747A1 (en) | Delivery of intelligence gathering devices | |
| US2390677A (en) | Catapult device for autonomous aerial torpedoes | |
| CN204514195U (en) | A kind of high-performance cruise formula target missile | |
| CN202453736U (en) | Unmanned aerial vehicle reconnaissance system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120905 |