CN102700713A - Unmanned aerial vehicle with payload body - Google Patents
Unmanned aerial vehicle with payload body Download PDFInfo
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- CN102700713A CN102700713A CN2012102105723A CN201210210572A CN102700713A CN 102700713 A CN102700713 A CN 102700713A CN 2012102105723 A CN2012102105723 A CN 2012102105723A CN 201210210572 A CN201210210572 A CN 201210210572A CN 102700713 A CN102700713 A CN 102700713A
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Abstract
The invention discloses an unmanned aerial vehicle with a payload body and aims to solve the technical problems that the conventional unmanned aerial vehicle has an integral structure provided with a manned aircraft and is large in overall dimension, heavy in takeoff weight, complex in structure and high in cost and the like. The unmanned aerial vehicle with the payload body comprises a body, wings and empennages, wherein electronic equipment, a flight control system, a missile load launch control device and an engine are arranged on the body; and the body consists of a compound launcher mounted with payloads and the payloads, namely the body consists of a main body which has a cross section shaped like a Chinese character 'pin' or shaped like the Chinese character 'pin' in an inverted mode and payloads which are borne below the symmetrical body shaped like the Chinese character 'pin' through a mount device. The invention has the advantages that the unmanned aerial vehicle with the payload body has the characteristics of miniaturization, portability, practicality, effectiveness and the like. By adoption of the design of the unique body shaped like the Chinese character 'pin', the traditional design idea that the aircraft main body is separated from the payload is changed, a weapon payload serves as a main body and is integrally fused with the body, namely a missile launching device and a missile body serve as the body of the unmanned aerial vehicle, so that the payload ratio of the unmanned aerial vehicle is maximized, and the unmanned aerial vehicle with the payload body is a unique unmanned aerial vehicle which can realize aerial carrier mounted airdrop and take off from the ground.
Description
Technical field:
The present invention relates to a kind of robot airplane, relate in particular to a kind of capacity weight fuselage unmanned plane.Belong to the design of space flight and aviation equipment, manufacturing field.Can be used for aerial or ground strike, execution investigation tasks etc.; Also can be used as agricultural, civilian unmanned plane, like pesticide spraying, rainmaking, communication, information acquisition etc.
Background technology:
21 century is the century of unmanned plane, and the appearance of unmanned plane influences aspect of social life.
The unmanned plane platform is the reconnaissance version unmanned plane mostly at present, and it is the most advanced with the U.S. to examine the unmanned plane of beating one.But be to take off in ground mostly, carry out aerial reconnaissance or hit task over the ground.The present dozen one unmanned plane of examining exists take-off weight big; Volume is big, the span is long.Unmanned plane flat-bed forward position research at present more is people's aircraft is arranged; Such as four generation machine design concepts such as high stealthy, high cruising speed, agility and information fusion indiscriminately imitate on the unmanned plane; Institute's design-calculated unmanned plane have stealthy external form, in bury weapon, multisensor, special-purpose remaining data link etc.; This advanced person's unmanned plane overall dimensions and weight and have man-machine quite, its development technical risk is big, cost is high.Although various countries put into high gear to develop at present, present this unmanned battle platform is not also equipped.
Summary of the invention:
The present invention is in order to solve present unmanned plane owing to the integral structure of continuing to use people's aircraft; And the oad that exists is big, take-off weight big, complex structure, cost high-technology problem; A kind of capacity weight fuselage unmanned plane is provided; Capacity weight fuselage unmanned plane, it comprises fuselage, wing, empennage; Electronic machine, flight control system, guided missile load are housed on said fuselage send out control device and driving engine; Said fuselage is made up of the compound launcher and the capacity weight of carry capacity weight jointly, promptly is the main body of isosceles triangle or the layout of falling the isosceles triangle by cross-sectional plane and the capacity weight that under the symmetrical body of isosceles triangle, carries through the carry device constitutes jointly.
Characteristics of the present invention and beneficial effect: be a kind of small-sized, light, practical, actv. unmanned plane that has.This unmanned plane adopts unique isosceles triangle fuselage designs; Having changed traditional elder generation is that main body is carried out airplane design with the aircraft; The carry weapon is as the design philosophy of capacity weight; Change into weapon load and be the main body, the means of delivery of weapon load as body, as guided missile launcher and guided missile bomb body as unmanned aerial vehicle body.Make payload ratio reach maximum unmanned plane.But this unmanned plane also is unique year machine carry of can realizing drops again the unmanned plane that takes off in ground.Its characteristics are in particular in:
(1) the present invention adopts the isosceles triangle fuselage and at the right and left of article word machine body capacity weight carry device is set; This machine of making becomes the high unmanned attack plane that can carry bullet of present payload ratio, is one through capacity weight with load and unmanned aerial vehicle body group, has not only realized unique " isosceles triangle " fuselage appearance of unmanned plane; And because the topology layout of fuselage article word; Make structure become compact more, simple, reduced the volume and weight of complete machine, reduced manufacturing cost simultaneously.
(2) this unmanned plane can be realized assembling fast and disassembling because volume is little and adopt the design of modularization modular construction;
(3) because this unmanned plane adopts through capacity weight is the structure design of one, can realize load air-to-air missile and air-to-ground guided missile to load and unmanned aerial vehicle body group, and the realization carry and the use of attacking gondola over the ground, make it to become a kind of attack unmanned plane.
(4) air-drop type capacity weight fuselage unmanned plane; Can realize carrying the air-drop of machine long distance; Unmanned plane is attacked near target, after constituting the attack condition again; Thereby the weapon that has reached maximum range increases journey, makes the very near guided missile of range can attack the outer target of hundreds of kilometer, promotes weapon power and fighting efficiency.
(5) casement capacity weight fuselage unmanned plane can realize that ground takes off, and indication is closed with the enemy according to the chain data target, and constituting launches a guided missile after the attack condition attacks, and gives an encore after the attack.Thereby become the attack unmanned plane of sky; Type realizes hitting over the ground or scouting through installing video component additional over the ground.
Description of drawings:
Fig. 1 structural representation of the present invention
Fig. 2 is the Facad structure scheme drawing of Fig. 1
Fig. 3 is that the another kind of Fig. 1 is implemented state (fuselage of falling the isosceles triangle) structural representation
Fig. 4 is the Facad structure scheme drawing of Fig. 3
Fig. 5 is another enforcement state static structure scheme drawing (folding wing) of Fig. 3
Fig. 6 is the dynamic structure scheme drawing of Fig. 5
Fig. 7 is the Facad structure scheme drawing of Fig. 5
Fig. 8 is the plan structure scheme drawing of Fig. 5
Fig. 9 is the local enlarged diagram of the fuselage of Fig. 7
Figure 10 is the engine installation scheme drawing
Figure 11 is that wing connects scheme drawing
Figure 12 is the folded wing structural representation
Figure 13 is the folding fin structural representation
The implication of each mark in the accompanying drawing:
1---fuselage (isosceles triangle or the isosceles triangle that falls)
2---wing (or folding wing);
3---carry device;
4--empennage (or collapsible empennage);
The 5---driving engine;
6---capacity weight (like guided missile);
7---folds wing-bow;
8---unmanned plane hanger.
The specific embodiment:
Referring to Fig. 1-Figure 13, capacity weight fuselage unmanned plane, it comprises fuselage 1, wing 2, empennage 4; Electronic machine, flight control system, guided missile load are housed on said fuselage 1 send out control device and driving engine 5; Said fuselage 1 is made up of the compound launcher and the capacity weight 6 of carry capacity weight 6 jointly, promptly is the main body of isosceles triangle or the layout of falling the isosceles triangle by cross-sectional plane and the capacity weight 6 that under the symmetrical body of isosceles triangle, carries through carry device 3 constitutes jointly.Wherein:
The said wing of isosceles triangle or the fuselage of falling the isosceles triangle is made up of left and right two parts, and the folding wing-bow 7 that struts/lock with the band that is fixed on waist flexibly connects, and forms the folding wing, and said empennage 4 adopts collapsible empennage;
Said driving engine 1 is contained between the left and right sides body of isosceles triangle, is positioned at the body below;
On the fuselage that said driving engine 1 is carried on the back between the left and right sides body that is contained in down isosceles triangle;
The each several part of above-mentioned unmanned plane adopts the design of modularization modular construction.
Referring to Fig. 1-Fig. 2, capacity weight fuselage unmanned plane, this unmanned plane body each several part adopt the design of modularization modular construction, and it comprises fuselage, wing, vee tail; Electronic machine, flight control system and turbojet engine are housed on said fuselage; Said fuselage 1 is the main body that isosceles triangle arranges and the capacity weight 6 that under the symmetrical body of isosceles triangle, carries through carry device 3 constitutes jointly by cross-sectional plane.Referring to Fig. 7, said carry device 3 is made up of the T font slideway of the fixed structure with lock under the symmetrical body that is fixed on isosceles triangle; Referring to Figure 10, turbojet engine is lifted under the fuselage through mounting guide rail, and fixes through locking mechanism and fuselage; Said electronic machine and flight control system by index biography/figure biography equipment, mission computer, weapon feedway are formed are contained in the isosceles triangle fuselage and are positioned on the fuselage of centre portion.Said wing also can be designed to folding, and this machine is suitable for as the unmanned attack plane of air-drop type.
When the carry machine tool flew through this unmanned aerial vehicle body hanger 8 carry bands, the unmanned plane wing-folding was loaded with compound extension bullet of guided missile and isosceles triangle fuselage and becomes one on the capacity weight carry device 3 of the right and left setting of isosceles triangle fuselage 1; The carry machine tool provides target of attack location information and velocity information through the chain data receive-transmit system to unmanned plane, makes unmanned plane realize interception flight; After unmanned plane enters into the missile homer investigative range, the release of carry machine tool control unmanned plane missile homer, search target, missile homer detect and blip steady after, the unmanned plane target of attack of independently launching a guided missile.After the MISSILE LAUNCHING, unmanned plane changes course back under the control of independent flight control system, realizes airport or highway landing nearby.Because air-drop type capacity weight fuselage unmanned plane is near target, attacks after the formation attack condition again, and has realized that the weapon of maximum range increases journey, makes the very near guided missile of range can attack the outer target of 100-200 kilometer.
Be that capacity weight fuselage unmanned plane is attacked example below
Isosceles triangle/fuselage of falling the isosceles triangle is the integrated design of having merged airframe and capacity weight body, is the feedway that mounts of capacity weight, is again the fuselage of unmanned plane; Wing is plugged on the unmanned aerial vehicle body both sides; Vee tail becomes miter angle to be fixed in article word machine body both sides.Turbojet engine is lifted under the fuselage through the engine installation guide rail; Preceding of tricycle landing gear under the isosceles triangle fuselage, led in the driving engine both sides; Under fixed installation of capacity weight carry device and the isosceles triangle fuselage.Autonomous flight control device and chain data receive-transmit system and weapon calculate with jettison system and are installed in the isosceles triangle fuselage.
Fly the machine that carries by extension and carry effective load machine body unmanned plane to the battlefield, hang and fly to carry machine perception battle field information, after the discovery combat, send capacity weight fuselage unmanned plane preparation instruction, the unmanned plane navigationsystem is carried out the engine-bed aligning, sets up communication through the chain data receive-transmit system; Extension flies to carry the autopilot that machine bookbinding mission planning information is given capacity weight fuselage unmanned plane.After constituting the attack condition, hang and fly to carry machine input capacity weight fuselage unmanned plane, engine ignition, capacity weight fuselage unmanned plane independently opens wing, realizes autonomous flight.The capacity weight fuselage is according to chain data target information correction flight path; When arriving target proximity; Start guided missile and prepare, missile homer is set up the region of search according to the target position information that chain data transmits, behind the target seeker blip steady; Passback is given and is carried machine blip steady, the target of attack of launching a guided missile simultaneously.
Referring to Fig. 3-Fig. 4, the said fuselage of capacity weight fuselage unmanned plane is the main body of the layout of falling the isosceles triangle and the capacity weight 6 that under the symmetrical body of isosceles triangle, carries through carry device 3 constitutes jointly by three sliver transvers sections.On the fuselage that said turbojet engine 1 is carried on the back between the left and right sides body that is contained in down isosceles triangle.Said wing is designed to folding, and its structure is referring to Figure 11-Figure 12, and left and right sides wing is through pegging graft and the connection of bolt mechanism; Through strutting/the realization wing-folding/expansion of lock support mechanism; Collapsible empennage upspring along with the expansion of wing (, becoming plumbness) by horizontality referring to Figure 13.This fuselage is because the article of employing word is more suitable for the installation of alighting gear installation and photodetection load.
When hitting aerial target; Through the chain data system is that the task system of unmanned plane provides target of attack location information and velocity information, and unmanned plane is realized interception flight, after entering into the missile homer investigative range; By the release of ground station control unmanned plane missile homer; Search target, missile homer detect and blip steady after, unmanned plane is through the task system control target of attack of independently launching a guided missile.After the MISSILE LAUNCHING, unmanned plane changes course back over to, realizes airport or highway landing nearby.
Referring to Fig. 5-Fig. 9, said wing is designed to folding.This machine is suitable for as the capacity weight fuselage unmanned plane that hits terrain object.
Referring to Fig. 5, when unmanned plane remained static before place in operation, left and right sides wing closed up, and was consistent with body;
Referring to Fig. 6, Figure 13, when unmanned plane wing expansion in the left and right sides after place in operation takes off, empennage 4 is upspring in the groove of fuselage relevant position; Get into state of flight.
When hitting terrain object; Ground station at first binds navigation route, and unmanned plane is pressed navigation route flight, and the camera that fuselage carried when approaching target point was overhead is through chain data system passback perception outdoor scene image; Ground station is through the image recognition target, and the control unmanned plane is realized target is hit.
Capacity weight fuselage unmanned plane is attacked example:
Capacity weight fuselage unmanned plane, the ground car launcher launches emission, when hitting aerial target; Through target of attack location information and the velocity information that the chain data system gives unmanned plane, unmanned plane is realized interception flight, after entering into TY-90 missile homer investigative range; The release of ground station control unmanned plane missile homer; Search target, missile homer detect and blip steady after, the unmanned plane target of attack of independently launching a guided missile.After the MISSILE LAUNCHING, unmanned plane changes course back over to, realizes airport or highway landing nearby.When hitting terrain object, ground station at first binds the air route, and unmanned plane is by air route flight, and camera was through chain data system passback perception outdoor scene image when approaching target point was overhead, and ground station is through the image recognition target, and the control unmanned plane is realized target is hit.
Other are with embodiment 1.
The present invention is applicable to civilian unmanned plane too, realizes through disposing different loads and control system.As realize spraying insecticide through this unmanned plane, rainmaking etc.
Claims (6)
1. capacity weight fuselage unmanned plane, it comprises fuselage (1), wing (2), empennage (4); Electronic machine, flight control system, guided missile load are housed on said fuselage (1) send out control device and driving engine (5); It is characterized in that: said fuselage (1) is by the compound launcher and the common formation of capacity weight (6) of carry capacity weight (6), the common formation of capacity weight (6) that promptly is the main body of isosceles triangle or the layout of falling the isosceles triangle by cross-sectional plane and under the symmetrical body of isosceles triangle, carries through carry device (3).
2. capacity weight fuselage unmanned plane according to claim 1; It is characterized in that: the said wing of isosceles triangle or the fuselage of falling the isosceles triangle is made up of left and right two parts; And the folding wing-bow (7) that struts/lock with the band that is fixed on waist flexibly connects, and forms the folding wing.
3. capacity weight fuselage unmanned plane according to claim 2 is characterized in that: said empennage (4) adopts collapsible empennage.
4. capacity weight fuselage unmanned plane according to claim 1 is characterized in that: said driving engine (1) is contained between the left and right sides body of isosceles triangle, is positioned at the body below.
5. capacity weight fuselage unmanned plane according to claim 1 is characterized in that: said driving engine (1) is carried on the back on the fuselage between the left and right sides body that is contained in down isosceles triangle.
6. according to the capacity weight fuselage unmanned plane described in any among the claim 1-5, it is characterized in that: the each several part of unmanned plane all adopts the design of modularization modular construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102105723A CN102700713A (en) | 2012-06-25 | 2012-06-25 | Unmanned aerial vehicle with payload body |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102105723A CN102700713A (en) | 2012-06-25 | 2012-06-25 | Unmanned aerial vehicle with payload body |
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| CN102700713A true CN102700713A (en) | 2012-10-03 |
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| CN2012102105723A Pending CN102700713A (en) | 2012-06-25 | 2012-06-25 | Unmanned aerial vehicle with payload body |
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Cited By (19)
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| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN104309806A (en) * | 2014-10-08 | 2015-01-28 | 中国航空工业集团公司西安飞机设计研究所 | Cruise missile carrier vehicle |
| CN105157488A (en) * | 2015-09-21 | 2015-12-16 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle-based guided missile attack route planning method |
| CN105882988A (en) * | 2014-12-31 | 2016-08-24 | 航天神舟飞行器有限公司 | Quick dismounting and mounting design scheme for load and body of small unmanned aerial vehicle |
| CN106643292A (en) * | 2017-01-06 | 2017-05-10 | 南京壹诺为航空科技有限公司 | Small unmanned aerial vehicle load launching device |
| WO2017131823A3 (en) * | 2015-09-16 | 2017-09-14 | Christopher Wilkinson | Space combat drone |
| CN107310729A (en) * | 2016-03-11 | 2017-11-03 | 甘丽霞 | A kind of wing |
| CN107472534A (en) * | 2016-02-25 | 2017-12-15 | 陈国栋 | Flying Camera head can freely convert take photo by plane unmanned plane and its method for work of shooting angle |
| CN107554794A (en) * | 2016-01-20 | 2018-01-09 | 陈国栋 | Spray insecticide or the unmanned plane and its method of work of chemical fertilizer |
| CN107672780A (en) * | 2017-11-08 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | A kind of load configuration structure of the dynamic unmanned plane of oil |
| CN107870628A (en) * | 2016-09-27 | 2018-04-03 | 北京理工大学 | A kind of depopulated helicopter ground control system and its control method |
| CN107870631A (en) * | 2016-09-27 | 2018-04-03 | 北京理工大学 | A kind of unmanned helicopter-mounted system and its control method |
| CN107878739A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | A kind of depopulated helicopter control system and its control method |
| CN107885230A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | Depopulated helicopter control system and its control method with laser guided weapon |
| CN108482679A (en) * | 2018-03-19 | 2018-09-04 | 成都飞机工业（集团）有限责任公司 | Towed bird system that is a kind of while lifting two frame unmanned planes |
| CN109649647A (en) * | 2017-10-11 | 2019-04-19 | Wing航空有限责任公司 | The modularization fuselage of unmanned vehicle |
| CN110294127A (en) * | 2019-08-02 | 2019-10-01 | 北京通用航空江西直升机有限公司 | Novel examine of one kind beats integrated unmanned helicopter body abdomen weapon drop in beam |
| CN110597287A (en) * | 2019-09-29 | 2019-12-20 | 中电莱斯信息系统有限公司 | Multi-functional portable unmanned aerial vehicle ground satellite station |
| CN113443145A (en) * | 2021-05-31 | 2021-09-28 | 中航(成都)无人机系统股份有限公司 | Military unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR704078A (en) * | 1929-10-08 | 1931-05-11 | Bleriot Aeronautique | Improvements to monoplane airplanes with two fuselages intended to receive passengers or cargo |
| US2072029A (en) * | 1935-02-16 | 1937-02-23 | William F Crowe | Aeroplane construction |
| GB1209290A (en) * | 1970-06-01 | 1970-10-21 | Arthur Paul Pedrick | Improvements in the design, structure, and safety of large aircraft |
| EP1167183A2 (en) * | 2000-06-29 | 2002-01-02 | The Boeing Company | Blended wing and multiple-body airplane configuration |
| GB2377683A (en) * | 2001-07-20 | 2003-01-22 | Bae Systems Plc | Composite of unmanned aerial vehicles |
| CN202754145U (en) * | 2012-06-25 | 2013-02-27 | 沈阳申蓝航空科技有限公司 | Unmanned aerial vehicle with effective load fuselage |
-
2012
- 2012-06-25 CN CN2012102105723A patent/CN102700713A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR704078A (en) * | 1929-10-08 | 1931-05-11 | Bleriot Aeronautique | Improvements to monoplane airplanes with two fuselages intended to receive passengers or cargo |
| US2072029A (en) * | 1935-02-16 | 1937-02-23 | William F Crowe | Aeroplane construction |
| GB1209290A (en) * | 1970-06-01 | 1970-10-21 | Arthur Paul Pedrick | Improvements in the design, structure, and safety of large aircraft |
| EP1167183A2 (en) * | 2000-06-29 | 2002-01-02 | The Boeing Company | Blended wing and multiple-body airplane configuration |
| GB2377683A (en) * | 2001-07-20 | 2003-01-22 | Bae Systems Plc | Composite of unmanned aerial vehicles |
| CN202754145U (en) * | 2012-06-25 | 2013-02-27 | 沈阳申蓝航空科技有限公司 | Unmanned aerial vehicle with effective load fuselage |
Cited By (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN104309806A (en) * | 2014-10-08 | 2015-01-28 | 中国航空工业集团公司西安飞机设计研究所 | Cruise missile carrier vehicle |
| CN105882988A (en) * | 2014-12-31 | 2016-08-24 | 航天神舟飞行器有限公司 | Quick dismounting and mounting design scheme for load and body of small unmanned aerial vehicle |
| WO2017131823A3 (en) * | 2015-09-16 | 2017-09-14 | Christopher Wilkinson | Space combat drone |
| CN105157488A (en) * | 2015-09-21 | 2015-12-16 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle-based guided missile attack route planning method |
| CN107554794A (en) * | 2016-01-20 | 2018-01-09 | 陈国栋 | Spray insecticide or the unmanned plane and its method of work of chemical fertilizer |
| CN107554795A (en) * | 2016-01-20 | 2018-01-09 | 陈国栋 | Spray insecticide or chemical fertilizer, improvement afforestation unmanned plane and its method of work |
| CN107685859B (en) * | 2016-02-25 | 2020-11-03 | 南京启缘星信息科技有限公司 | Aerial photography unmanned aerial vehicle with moving camera capable of freely changing shooting angle |
| CN107472534A (en) * | 2016-02-25 | 2017-12-15 | 陈国栋 | Flying Camera head can freely convert take photo by plane unmanned plane and its method for work of shooting angle |
| CN107685859A (en) * | 2016-02-25 | 2018-02-13 | 陈国栋 | Flying Camera head can freely convert the unmanned plane of taking photo by plane of shooting angle |
| CN107310729A (en) * | 2016-03-11 | 2017-11-03 | 甘丽霞 | A kind of wing |
| CN107870628B (en) * | 2016-09-27 | 2021-03-19 | 北京理工大学 | Ground control system of unmanned helicopter and control method thereof |
| CN107870628A (en) * | 2016-09-27 | 2018-04-03 | 北京理工大学 | A kind of depopulated helicopter ground control system and its control method |
| CN107870631A (en) * | 2016-09-27 | 2018-04-03 | 北京理工大学 | A kind of unmanned helicopter-mounted system and its control method |
| CN107885230B (en) * | 2016-09-29 | 2021-01-05 | 北京理工大学 | Unmanned helicopter control system with laser guided weapon and control method thereof |
| CN107878739A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | A kind of depopulated helicopter control system and its control method |
| CN107885230A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | Depopulated helicopter control system and its control method with laser guided weapon |
| CN107878739B (en) * | 2016-09-29 | 2020-12-22 | 北京理工大学 | Unmanned helicopter control system and control method thereof |
| CN106643292A (en) * | 2017-01-06 | 2017-05-10 | 南京壹诺为航空科技有限公司 | Small unmanned aerial vehicle load launching device |
| CN106643292B (en) * | 2017-01-06 | 2018-11-16 | 南京壹诺为航空科技有限公司 | A kind of small drone load emitter |
| CN109649647A (en) * | 2017-10-11 | 2019-04-19 | Wing航空有限责任公司 | The modularization fuselage of unmanned vehicle |
| CN107672780A (en) * | 2017-11-08 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | A kind of load configuration structure of the dynamic unmanned plane of oil |
| CN107672780B (en) * | 2017-11-08 | 2023-11-07 | 沈阳旋飞航空技术有限公司 | Load configuration structure of oil-driven unmanned aerial vehicle |
| CN108482679A (en) * | 2018-03-19 | 2018-09-04 | 成都飞机工业（集团）有限责任公司 | Towed bird system that is a kind of while lifting two frame unmanned planes |
| CN108482679B (en) * | 2018-03-19 | 2023-09-29 | 成都飞机工业（集团）有限责任公司 | Nacelle system for hoisting two unmanned aerial vehicles simultaneously |
| CN110294127A (en) * | 2019-08-02 | 2019-10-01 | 北京通用航空江西直升机有限公司 | Novel examine of one kind beats integrated unmanned helicopter body abdomen weapon drop in beam |
| CN110597287A (en) * | 2019-09-29 | 2019-12-20 | 中电莱斯信息系统有限公司 | Multi-functional portable unmanned aerial vehicle ground satellite station |
| CN113443145A (en) * | 2021-05-31 | 2021-09-28 | 中航(成都)无人机系统股份有限公司 | Military unmanned aerial vehicle |
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