CN102923296A - Modularized unmanned aerial vehicle - Google Patents

Modularized unmanned aerial vehicle Download PDF

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Publication number
CN102923296A
CN102923296A CN2012104658976A CN201210465897A CN102923296A CN 102923296 A CN102923296 A CN 102923296A CN 2012104658976 A CN2012104658976 A CN 2012104658976A CN 201210465897 A CN201210465897 A CN 201210465897A CN 102923296 A CN102923296 A CN 102923296A
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China
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module
wing
fuselage
face
modularized unmanned
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CN2012104658976A
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方力
盛慧
李梓衡
陈晓静
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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Priority to CN2012104658976A priority Critical patent/CN102923296A/en
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Abstract

The invention discloses a modularized unmanned aerial vehicle. More specifically, the invention relates to a modularized unmanned aerial vehicle which comprises a plurality of modules, and the arrangement mode and the loading capacity can be changed through the reloading and combination of different modules. According to the modularized unmanned aerial vehicle, an auxiliary wing module and a rectifying module can be added according to demands, and the modules can be rapidly assembled, dismantled and changed. A power module of the modularized unmanned aerial vehicle is structurally connected with a vehicle body module through a rapid dismantling joint; and the connection between the power and the system is realized through a power transmission component and the vehicle body module; the power module is optionally installed at the front part of the vehicle body module or installed at the rear part of the vehicle body module, or one power module is respectively installed at the front part and the rear part; a main wing module is composed of wings and a central wing box; the central wing box is butted and locked with the wings through a wing connecting component, and the assembling and dismantling are accomplished rapidly; and the main wing module and the auxiliary wing module can be both rapidly assembled and dismantled with the vehicle body module through a wing body connecting component.

Description

A kind of Modularized unmanned machine
Technical field
The invention discloses a kind of Modularized unmanned machine.More particularly, the present invention relates to a kind ofly be formed by a plurality of modules changing the outfit and make up the Modularized unmanned machine that can change its distribution form and delelivered payload capability by disparate modules.
Background technology
At military domain and the civil areas such as anti-riot place is prominent, exploration mapping such as battle reconnaissance, gun layings, unmanned plane is being brought into play the effect that becomes more and more important.From the design angle of unmanned plane, main design has two kinds at present: 1) Integration Design and 2) modular design.The advantage of Integration Design is with strong points, and the characteristics of unmanned plane and performance are outstanding.The advantage of modular design then is strong adaptability, and is easy to maintenance.For example task system is designed to a module, can carries out different tasks by changing the outfit; If some modules break down, then can carry out quick-replaceable, do not affect the execution of task.From the development tendency of unmanned plane, modular design is following main direction.
Disclosed Modularized multifunctional unmanned aerial vehicle is by arranging one or more module bay in the ZL200920008551.7 utility model patent at engine room inside, the midget plant of finishing a certain independent function is installed in the module bay, realize the conversion of unmanned plane task ability by changing module bay, simplify maintenance operation.Application number is that the application for a patent for invention of 201110095531.X discloses a kind of Modular quick-splicing type unmanned aerial vehicle, comprises left main wing module, hatchcover module, vertical module, fuselage module, umbrella cabin module and right main wing module.Each module all adopts the latching system connection each other, can realize that quick the replenishing of modular manufacturing, minimum volume packing, consumable accessory of UAV Components reaches installation etc.Be unmanned plane according to the design of modularization thinking although above-mentioned patent documentation is disclosed, all have a great deficiency: the unmanned aerial vehicle platform configuration is unique, i.e. the distribution form of unmanned plane, and the internal body volume all immobilizes.Although such design can change by the mode of the task module that changes the outfit the mission mode of unmanned plane, but because distribution form is unique, the internal capacity of unmanned plane, capacity weight all can't further improve, can only compatible task module less than design maximum capacity weight and design maximum effective volume, bad adaptability.
Based on this, need a kind of Modularized unmanned machine of design, can be by replacing or the combination of intermodule, change this unmanned plane distribution form, improve its delelivered payload capability.
Summary of the invention
The Modularized unmanned machine that the objective of the invention is to propose that a kind of comformability is good, internal capacity and capacity weight can improve further all.
Technical solution of the present invention is, the Modularized unmanned machine comprises fuselage module, power plant module, main wing module, have a front fuselage face and back body face on the fuselage module, arrange respectively at least one buckle and latchplate and power transmitting assembly on front fuselage face and the back body face, the buckle and latchplate that power plant module is connected with power transmitting assembly on the back body face by the buckle and latchplate on the front fuselage face is connected with the fuselage module with power transmitting assembly; The main wing module is connected with the fuselage module by being installed in fuselage upper surface on the fuselage module or the wing body coupling assembling on the fuselage lower surface; Be designed with at least one mission module and at least one equipment compartment in the fuselage module; The main wing module is comprised of wing and central wing box, the central wing box docks and locking by the wing coupling assembling with wing, be furnished with another wing body coupling assembling on the central wing box, the main wing module is docked with wing body coupling assembling on being installed in the fuselage module by the wing body coupling assembling that is installed on the central wing box.
Power plant module and rectification module are installed respectively or a power plant module is installed respectively on front fuselage face and back body face on the described front fuselage face that is installed in the fuselage module and the back body face.
The hole, installation site that described fuselage module is furnished with wing body coupling assembling in upper surface or the fuselage lower surface of fuselage, wing body coupling assembling is along fuselage axis to the conversion installation site.
The form of described wing is designed to the straight wing, swept wing, buzzard-type wing or connecting wing form according to the needs of design and task, and arranges necessary control rudder face thereon.
Described fuselage module is provided for installing the wing body coupling assembling of auxiliary wing module in upper surface or the fuselage lower surface of fuselage, and the component count of the auxiliary wing module of quantity basis of wing body coupling assembling is determined.
The front fuselage face of described fuselage module or back body face join by buckle and latchplate and the power transmitting assembly that is arranged on front fuselage face and the back body face with another and the identical fuselage module of aforementioned fuselage module.
When the form of described wing is connecting wing, two central wing boxes are set on the main wing module, when the Modularized unmanned machine is a fuselage module, two central wing boxes are arranged on the fuselage upper surface and fuselage lower surface of fuselage module, when the Modularized unmanned machine was two fuselage modules, two central wing boxes joined with a rear fuselage module of previous fuselage module respectively.
The advantage that the present invention has and beneficial effect: the invention provides a kind of Modularized unmanned machine.This Modularized unmanned machine can increase auxiliary wing module and rectification module as required. and each intermodule can be realized fast assembling-disassembling and replacing.The power plant module of Modularized unmanned machine is connected with fuselage module implementation structure by buckle and latchplate, realizes that by power transmitting assembly and fuselage module power is connected with system.Selectable power plant module can be installed in the front portion of fuselage module, perhaps is installed in the rear portion of fuselage module, and perhaps front and back are respectively installed one.The main wing module is comprised of wing and central wing box.The central wing box docks and locks by the wing coupling assembling with wing, and can finish fast assembling-disassembling.Main wing module, auxiliary wing module all can be by the fast assembling-disassembling of wing body coupling assembling realization with the fuselage module.Wing body coupling assembling can be arranged in a plurality of positions of the upper and lower end face of fuselage module.The Modularized unmanned machine can change and regulate the position of main wing module, auxiliary wing module etc., and then changes distribution form.Be designed with at least one mission module and at least one equipment compartment in the fuselage module.Mission module is used for installing mission payload, and equipment compartment is used for the required tele-control system of installation module unmanned plane, flight control system, Power Component etc.Two or more fuselage modules can make up by buckle and latchplate.
Modularized unmanned machine disclosed in this invention can be by intermodule replacing or combination, change this unmanned plane distribution form, improve its delelivered payload capability.
Description of drawings
Fig. 1 is the decomposition module schematic diagram according to the Modularized unmanned machine 10 of one of them enforcement sample of the present invention.
Fig. 2 be shown in Figure 1 according to of the present invention one of them implement the assembling schematic diagram of the Modularized unmanned machine 10 of sample.
Fig. 3 is the assembling schematic diagram of implementing according to another preferred the Modularized unmanned machine 10 of sample.
Fig. 4 is the assembling schematic diagram of implementing according to another preferred the Modularized unmanned machine 10 of sample.
Fig. 5 is the assembling schematic diagram of implementing according to another preferred the Modularized unmanned machine 10 of sample.
The specific embodiment
By describe in detail and wherein accompanying drawing can fully understand the present invention;
Fig. 1 is the decomposition module schematic diagram according to the Modularized unmanned machine 10 of one of them enforcement sample of the present invention.This Modularized unmanned machine 10 adopts airscrew engine as power, mainly is comprised of fuselage module 100, power plant module 20, main wing module 30, rectification module 50, auxiliary wing module 62 and task module 70.
Power plant module 20 is comprised of screw propeller assembly 22, driving engine 24 and driving engine mount pad 26.In this enforcement sample, driving engine 24 is an electrical motor.Selectable driving engine 24 can also select to meet the combustion engine of unmanned plane designing requirement or the engine type of other types.Screw propeller assembly 22 drives pulling force or the thrust that produces 10 flights of driver module unmanned plane by driving engine 24.Driving engine 24 is fixedly mounted on the driving engine mount pad 26.Comprise simultaneously buckle and latchplate 28 on the driving engine mount pad 26.Power plant module 20 and fuselage module 100 can realize that fast speedes install fixing and separate by buckle and latchplate 28.In this enforcement sample, be furnished with power transmitting assembly 92 on the driving engine mount pad 26.Concrete, driving engine 24 is electrical motor in this enforcements sample, is arranged in the equipment compartment 114 in the fuselage module 100 for driving engine 24 provides the power-supply system of the energy, and the radical function of power transmitting assembly 92 comprises that delivery of electrical energy and engine control signal transmit.If change driving engine 24 into combustion engine, then the radical function of power transmitting assembly 92 comprises fuel delivery and engine control signal transmission.In the connection procedure of power plant module 20 and fuselage module 100, need to finish the connection that buckle and latchplate 28 is connected with power transmitting assembly.The selectable Power Component that the energy is provided for driving engine 24 such as battery or fuel tank, also can be designed to the part of power plant module 20.But consider that safety reaches the impact on Modularized unmanned machine 10 centers of gravity, the Power Component of the energy is provided for driving engine 24, such as battery or fuel tank, should pay the utmost attention in the equipment compartment 114 that is arranged in the fuselage module 100.
Main wing module 30 is comprised of wing 32 and central wing box 56.Wing 32 can be designed to the forms such as the straight wing, swept wing or buzzard-type wing according to the needs of design and task, and arranges necessary control rudder face thereon.Central wing box 56 docks and locks by wing coupling assembling 54 with wing 32, and can finish fast assembling-disassembling.Also be furnished with simultaneously wing body coupling assembling 40 on the central wing box 56, and realize the fast assembling-disassembling of main wing module 30 and fuselage module 100 by wing body coupling assembling 40.Be furnished with equally wing body coupling assembling 40 on the auxiliary wing module 62, and realize fast assembling-disassembling with fuselage module 100 in an identical manner.Difference is that main wing module 30 is different from the installation site of auxiliary wing module 62.In this enforcement sample, auxiliary wing module 62 has adopted conventional horizontal tail to add the design of vertical fin.Selectable auxiliary wing module 62 can be designed to " T " tail layout, " V " tail layout or other forms that meets design requirement.
Fuselage module 100 has a front fuselage face 102 of having arranged at least one buckle and latchplate 28 and power transmitting assembly 92, has arranged equally the back body face 104 of at least one buckle and latchplate 28 and power transmitting assembly 92.In this enforcement sample, power plant module 20 is connected with power transmitting assembly by the buckle and latchplate 28 that is arranged in front fuselage face 102 and is connected with fuselage module 100; Fairing 50 is connected with fuselage module 100 by the buckle and latchplate 28 that is arranged in back body face 104.Selectable power plant module 20 can also be connected with power transmitting assembly by the buckle and latchplate 28 that is arranged in back body face 104 and be connected with fuselage module 100; 50 of fairings are connected with fuselage module 100 by the buckle and latchplate 28 that is arranged in front fuselage face 102, realize the Variable Designing Of of the propulsion mode of Modularized unmanned machine 10 with this.Fuselage module 100 has the fuselage upper surface 106 that wing body coupling assembling 40 can be installed and the fuselage lower surface 108 that wing body coupling assembling 40 can be installed equally simultaneously.Be furnished with the installation site of a plurality of wing body coupling assemblings 40 in fuselage upper surface 106 and fuselage lower surface 108.Change by wing body coupling assembling 40 positions can change main wing module 30 and auxiliary wing module 62 installation sites, to improve Modularized unmanned machine 10 for the comformability of the mission payload 70 of Different Weight.Be designed with at least one mission module 112 and at least one equipment compartment 114 in the fuselage module 100.Mission module 112 is used for installing mission payload 70, and equipment compartment 114 is used for the required tele-control system of installation module unmanned plane 10, flight control system, Power Component etc.The principle of design of equipment compartment 114 should be followed the inner space that a) takes full advantage of fuselage module 100, b) effectively controls center-of-gravity position, c) reasonable arrangement system layout scheme, the complexity of reduction system.
Fig. 2 be shown in Figure 1 according to of the present invention one of them implement the assembling schematic diagram of the Modularized unmanned machine 10 of sample.
Fig. 3 is the assembling schematic diagram of implementing according to another preferred the Modularized unmanned machine 10 of sample.Implement in the sample at this, the auxiliary wing module 62 of Modularized unmanned machine 10 is comprised of canard assembly 62a and vertical fin assembly 62b.The installation site of main wing module 30 moves to fuselage lower surface 108 by fuselage upper surface 106.This enforcement sample has been showed according to the present invention, by the exchange of module, can realize the change of Modularized unmanned machine 10 distribution forms, namely is converted to canard configuration by normal arrangement shown in Figure 2.
Fig. 4 is the assembling schematic diagram of implementing according to another preferred the Modularized unmanned machine 10 of sample.This enforcement sample and enforcement sample shown in Figure 3 are similarly canard configuration.By changing the exchange of power plant module 20 and fairing 50 installation sites, change simultaneously screw propeller assembly 22, can realize that the type of drive of Modularized unmanned machine 10 is by drawing in to the conversion that advances.
Fig. 5 is the assembling schematic diagram of implementing according to another preferred the Modularized unmanned machine 10 of sample.Implement in the sample at this, two fuselage modules 100 have been combined into a larger fuselage module by buckle and latchplate 28 and power transmitting assembly 92, the arrangement space of larger equipment compartment 114 also is provided for Modularized unmanned machine 10, has the more important thing is the delelivered payload capability of the mission payload 70 that can provide stronger.Simultaneously, by main wing module 30 is replaced by the Lian Yi design by the wing design of routine, can provide larger lifting area, satisfy the higher load-carrying capacity requirement that 70 pairs of Modularized unmanned machines of mission payload 10 of increasing propose.In this enforcement sample, only adopted a power plant module 20.It is selectable when single power plant module 20 can't satisfy Modularized unmanned machine 10 for the requiring of thrust, the fairing 50 of afterbody can be replaced with the power plant module 20 that adopts pusher propeller, namely adopting one in front and one in back, two power plant modules 20 satisfy Modularized unmanned machine 10 for the requirement of thrust.
Although invention has been described according to various specific enforcement samples, one skilled in the art would recognize that and in the marrow of claims and scope, to improve the present invention.

Claims (7)

1. Modularized unmanned machine, it is characterized in that, this Modularized unmanned machine comprises fuselage module (100), power plant module (20), main wing module (30), have a front fuselage face (102) and back body face (104) on the fuselage module (100), arrange respectively at least one buckle and latchplate (28) and power transmitting assembly (92) on front fuselage face (102) and the back body face (104), power plant module (20) is connected 92 by the buckle and latchplate (28) on the front fuselage face (102) with power transmitting assembly) or back body face (104) on buckle and latchplate (28) be connected 92 with power transmitting assembly) be connected with fuselage module (100); The main wing module is connected with fuselage module (100) by fuselage upper surface (106) or the wing body coupling assembling (40) on fuselage lower surface (108) that is installed on the fuselage module (100); Be designed with at least one mission module (112) and at least one equipment compartment (114) in the fuselage module (100); Main wing module (30) is comprised of wing (32) and central wing box (56), central wing box (56) docks and locking by wing coupling assembling (54) with wing (32), be furnished with another wing body coupling assembling (40) on the central wing box (56), main wing module (30) is docked with wing body coupling assembling (40) on being installed in fuselage module (100) by the wing body coupling assembling (40) that is installed on the central wing box (56).
2. a kind of Modularized unmanned machine according to claim 1, it is characterized in that, power plant module (20) and rectification module (50) are installed respectively or on front fuselage face (102) and back body face (104), a power plant module (20) are installed respectively on the described front fuselage face (102) that is installed in fuselage module (100) and the back body face (104).
3. a kind of Modularized unmanned machine according to claim 1, it is characterized in that, the mounting hole that described fuselage module (100) is furnished with wing body coupling assembling (40) in upper surface (106) or fuselage lower surface (108) of fuselage, wing body coupling assembling (40) is along fuselage axis to the conversion installation site.
4. a kind of Modularized unmanned machine according to claim 1 is characterized in that, the form of described wing (32) is designed to the straight wing, swept wing, buzzard-type wing or connecting wing form according to the needs of design and task, and arranges necessary control rudder face thereon.
5. a kind of Modularized unmanned machine according to claim 1, it is characterized in that, described fuselage module (100) is provided for installing the wing body coupling assembling (40) of auxiliary wing module (62) in upper surface (106) or fuselage lower surface (108) of fuselage, and the component count of the auxiliary wing module of the quantity basis of wing body coupling assembling (40) (62) is determined.
6. a kind of Modularized unmanned machine according to claim 1, it is characterized in that, the front fuselage face (102) of described fuselage module (100) or back body face (104) join by buckle and latchplate (28) and the power transmitting assembly (92) that is arranged on front fuselage face (102) and the back body face (104) with another and the identical fuselage module of aforementioned fuselage module (100) (100).
7. according to claim 1 or 6 described a kind of Modularized unmanned machines, it is characterized in that, when the form of described wing (32) is connecting wing, two central wing boxes (56) are set on the main wing module (30), when the Modularized unmanned machine is a fuselage module (100), two central wing boxes (56) are arranged on the fuselage upper surface (106) and fuselage lower surface (108) of fuselage module (100), when the Modularized unmanned machine was two fuselage modules (100), two central wing boxes (56) joined with a rear fuselage module (100) of previous fuselage module (100) respectively.
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Cited By (21)

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CN103318401A (en) * 2013-06-06 2013-09-25 哈尔滨工程大学 Magnesium-lithium ultra-light alloy unmanned aerial vehicle
CN105235904A (en) * 2015-10-29 2016-01-13 北京航天科颐技术有限公司 Connecting device of drone aircraft and splicing-type drone aircraft
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
CN106005365A (en) * 2016-08-06 2016-10-12 北京耐威智能科技有限公司 Built-in connecting assembly, external connecting assembly, connecting device, wing and airplane
CN106114816A (en) * 2016-07-23 2016-11-16 北京耐威智能科技有限公司 A kind of wing attachment means, wing and aircraft
CN106143886A (en) * 2015-03-25 2016-11-23 北京天翼合创科技发展有限公司 One can be disintegrated formula multi-rotor aerocraft
EP3162705A1 (en) * 2015-10-30 2017-05-03 Ewatt Technology Co., Ltd. Hand-launched unmanned aerial vehicle
CN107600414A (en) * 2017-09-11 2018-01-19 珠海天晴航空航天科技有限公司 A kind of unmanned plane that can be taken off and quickly be assembled without instrument in case
CN108791868A (en) * 2018-07-31 2018-11-13 刘浩然 A kind of new transport unmanned plane of safety and stability
CN108820204A (en) * 2018-08-02 2018-11-16 中国科学院工程热物理研究所 Modularization supersonic speed unmanned plane
CN109178293A (en) * 2018-10-31 2019-01-11 长光卫星技术有限公司 A kind of unmanned plane modularization wing
CN109515706A (en) * 2018-12-03 2019-03-26 成都纵横大鹏无人机科技有限公司 A kind of Modularized unmanned machine
CN109562834A (en) * 2016-07-29 2019-04-02 泗川航空航天工业制造有限公司 Reconfigurable modular assembly type unmanned vehicle
CN109665101A (en) * 2019-01-07 2019-04-23 浙江自贸区协同科技有限公司 A kind of modularization head
CN109689497A (en) * 2016-09-12 2019-04-26 以色列宇航工业有限公司 Modularization carrier systems
CN110718133A (en) * 2019-10-19 2020-01-21 中国人民解放军空军工程大学 Multifunctional airplane teaching model and manufacturing method thereof
CN110963018A (en) * 2019-12-19 2020-04-07 清华大学 Modularized unmanned helicopter facing configuration and task system
CN113682475A (en) * 2021-08-27 2021-11-23 沈阳无距科技有限公司 Modularization unmanned aerial vehicle
CN114889802A (en) * 2022-04-22 2022-08-12 中国航空工业集团公司沈阳飞机设计研究所 Isomorphism modularization aircraft based on general fuselage
WO2023220447A3 (en) * 2022-05-13 2024-02-15 Firestorm Labs, Inc. Mission-adaptable aerial vehicle and methods for in-field assembly and use
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CN103318401A (en) * 2013-06-06 2013-09-25 哈尔滨工程大学 Magnesium-lithium ultra-light alloy unmanned aerial 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
CN106143886B (en) * 2015-03-25 2018-11-06 北京天翼合创科技发展有限公司 One kind can disintegrate formula multi-rotor aerocraft
CN106143886A (en) * 2015-03-25 2016-11-23 北京天翼合创科技发展有限公司 One can be disintegrated formula multi-rotor aerocraft
CN105235904A (en) * 2015-10-29 2016-01-13 北京航天科颐技术有限公司 Connecting device of drone aircraft and splicing-type drone aircraft
CN105235904B (en) * 2015-10-29 2017-03-08 北京航天科颐技术有限公司 A kind of attachment means of target drone and spliced target drone
EP3162705A1 (en) * 2015-10-30 2017-05-03 Ewatt Technology Co., Ltd. Hand-launched unmanned aerial vehicle
CN106114816A (en) * 2016-07-23 2016-11-16 北京耐威智能科技有限公司 A kind of wing attachment means, wing and aircraft
CN106114816B (en) * 2016-07-23 2018-06-15 北京耐威智能科技有限公司 A kind of wing attachment device, wing and aircraft
CN109562834A (en) * 2016-07-29 2019-04-02 泗川航空航天工业制造有限公司 Reconfigurable modular assembly type unmanned vehicle
CN106005365A (en) * 2016-08-06 2016-10-12 北京耐威智能科技有限公司 Built-in connecting assembly, external connecting assembly, connecting device, wing and airplane
CN109689497A (en) * 2016-09-12 2019-04-26 以色列宇航工业有限公司 Modularization carrier systems
US11603197B2 (en) 2016-09-12 2023-03-14 Israel Aerospace Industries Ltd. Modular vehicle system
CN107600414A (en) * 2017-09-11 2018-01-19 珠海天晴航空航天科技有限公司 A kind of unmanned plane that can be taken off and quickly be assembled without instrument in case
CN107600414B (en) * 2017-09-11 2024-03-15 珠海天晴航空航天科技有限公司 Unmanned aerial vehicle capable of taking off in box and rapidly assembling without tools
CN108791868A (en) * 2018-07-31 2018-11-13 刘浩然 A kind of new transport unmanned plane of safety and stability
CN108820204A (en) * 2018-08-02 2018-11-16 中国科学院工程热物理研究所 Modularization supersonic speed unmanned plane
CN109178293A (en) * 2018-10-31 2019-01-11 长光卫星技术有限公司 A kind of unmanned plane modularization wing
CN109515706A (en) * 2018-12-03 2019-03-26 成都纵横大鹏无人机科技有限公司 A kind of Modularized unmanned machine
CN109665101A (en) * 2019-01-07 2019-04-23 浙江自贸区协同科技有限公司 A kind of modularization head
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Application publication date: 20130213