CN109823525A - A kind of separate assembling aircraft - Google Patents
A kind of separate assembling aircraft Download PDFInfo
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- CN109823525A CN109823525A CN201910217771.9A CN201910217771A CN109823525A CN 109823525 A CN109823525 A CN 109823525A CN 201910217771 A CN201910217771 A CN 201910217771A CN 109823525 A CN109823525 A CN 109823525A
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- split type
- unit
- aircraft
- separate assembling
- payload
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Abstract
The invention discloses a kind of separate assembling aircraft, the aircraft is without fixed main body, including at least two split type units, and split type unit is by connecting and composing the state of flight of aircraft with payload；The split type unit includes unit skeleton and is arranged in the intraskeletal power supply of unit, Aerial Electronic Equipment and power device, split type unit passes through Aerial Electronic Equipment each other and carries out wireless communication networking, control split type unit posture in flight course, the payload is with can provide any form of rigid connection point；Separate assembling aircraft provided by the invention has the characteristics that split type, flexible controllable, modular combination, without bulky structural fuselage, it is relatively simple, installation, practicability and expansibility are preferable, whole controllable, can give full play to the advantage of split type aircraft.
Description
Technical field
The present invention relates to aviation aircraft field, a kind of split type, modularization is related in particular to, can composite configuration's flight
Device can be widely used for dual-use field.
Background technique
Aviation aircraft has become research hotspot at present, with the maturation of technology and the reduction of cost, is widely used in boat
The every field such as bat, agricultural, fire, natural calamity early warning, play an important role.However, conventional aircraft or unmanned plane one
As all use fuselage and load-bearing frame, cause architecture quality larger, complete machine electrical system is complicated, and since package size limits
So that aircraft applications range is limited, expansibility, maintenanceability are poor.
To solve the above problems, research and development are split type, modularization, knockdown course of new aircraft are only ways, have very
Big theory and realistic meaning.The design of existing some split type aircraft not yet solves the above problems, such as disclosed patent
The important avionics component of unmanned vehicle is fixed in independently installed control box in CN201510041217.1, components point
Area is placed, but still has integral body, electrical system complexity, using limited dimension, and it is split type to belong to simple single component.And it is another
Kind of similar combination aircraft (CN201710645425.1) is related at least two unmanned planes that can independently fly, focused on combination and
Seperated two states, still without achieve the purpose that ideal split type, modularization, can composite configuration.
Summary of the invention
It, should without bulky structural fuselage it is an object of the invention to propose a kind of separate assembling Flight Vehicle Design
Design, which is combined by load ontology with split type unit, realizes that complete machine is efficiently flown, and payload accounting greatly improves；
Another object of the present invention is to propose a kind of separate assembling aircraft layout of split type unit flexible combination, can be with
It is required according to the size of load, weight, installation interface etc., the split type unit installation number of flexible setting and placement position；
Another object of the present invention is to propose a kind of split type unit module, has unit skeleton, power device, battery and boat
Electric equipment is based on modularization and fold design, and expansibility, maintenanceability are preferable.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of separate assembling aircraft, the aircraft is without fixed main body, including at least two split type units, split type unit
By the state of flight for connecting and composing aircraft with payload；
The split type unit includes unit skeleton and setting in the intraskeletal power supply of unit, Aerial Electronic Equipment and power device, is divided
Body formula unit passes through Aerial Electronic Equipment each other and carries out wireless communication networking, controls split type unit posture in flight course,
The payload be with can provide rigid connection point any form.
In the above-mentioned technical solutions, the unit skeleton is long-armed shape, is divided into leading portion, middle section and back segment, power device is set
It sets in front end, Aerial Electronic Equipment and power supply setting are in middle section, and back segment with payload for connecting.
In the above-mentioned technical solutions, the leading portion, middle section, back segment are separated from each other, and three passes through connection between any two
Part is connected as an entirety.
In the above-mentioned technical solutions, the power device includes firm banking, motor and propeller, firm banking and unit
The leading portion of skeleton connects, and motor is fixed on the fixed base, and propeller is installed vertically on motor output shaft.
In the above-mentioned technical solutions, load connector is provided between back segment and payload.
In the above-mentioned technical solutions, foldable between the load connector and unit skeleton, there are two states: static
When to be folded inward, state of flight is expansion outward.
It in the above-mentioned technical solutions, can be according to the size and weight of payload, the split type unit number of flexible setting
With placement position, an integral combined aircraft is formed.
In the above-mentioned technical solutions, the split type unit is symmetrically distributed on the outside of payload, forms more rotor flyings
Device.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
1, separate assembling aircraft provided by the invention has the characteristics that split type, flexible controllable, modular combination, does not have
Bulky structural fuselage, relatively simple, installation, practicability and expansibility are preferable, whole controllable, can give full play to fission
The advantage of formula aircraft；
2, the separate assembling aircraft layout of split type unit flexible combination provided by the invention, interface is easy, not by effective
Load limitation can be required according to the size of load, weight, installation interface etc., the split type unit installation number of flexible setting with
Placement position, payload accounting greatly improve；
3, split type assembled unit provided by the invention, using modularized design, aircraft body architecture quality is greatly lowered,
Combination multiplicity, can combine with existing vehicle, cargo, equipment etc., also have efficient transportation function, be unfolded when flight
The unit, is collapsed or is folded when arriving at the destination, and is had a wide range of application.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 is the split type cell schematics of the present invention；
Fig. 2 is a kind of schematic diagram of separate assembling aircraft of the present invention；
In figure, 1, unit skeleton, 11 be leading portion, and 12 be middle section, and 13 be back segment；2, power device, 21 be firm banking, and 22 be electricity
Machine, 23 be propeller；3, battery；4, Aerial Electronic Equipment；5, load connecting interface；6, payload.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification (including any accessory claim, abstract and attached drawing), except non-specifically chatting
It states, can be replaced by other alternative features that are equivalent or have similar purpose.That is, unless specifically stated, each feature is only
It is an example in a series of equivalent or similar characteristics.
As shown in Figure 1 to Figure 2, the present invention has unit skeleton 1, power device 2, battery 3, Aerial Electronic Equipment 4, load connection
Interface 5 and payload 6；The split type unit includes unit skeleton 1, power device 2, battery 3, Aerial Electronic Equipment 4 and carries
Lotus connecting interface 5, unit skeleton 1 provide the reliable installation of power device 2, battery 3 and Aerial Electronic Equipment 4, are connected by load
Interface 5 and payload 6 are connected；The unit skeleton 1 includes leading portion 11, middle section 12 and back segment 13, and the power device 2 connects
On leading portion 11, the battery 3 is located in middle section 12 with Aerial Electronic Equipment 4, and the load connecting interface 5 is connected with rear end 13, preceding
An integral unit skeleton 1 is connected by screw between section 11, middle section 12 and back segment 13；The power device 2 includes fixing
Pedestal 21, motor 22 and propeller 23, firm banking 21 are connect with unit skeleton 1, and motor 22 is fixed on firm banking 21, spiral shell
Rotation paddle 23 is installed vertically on 22 output shaft of motor；The battery 3 can require to be configured with load condition according to flight；Institute
State Aerial Electronic Equipment 4 include electric machine controller, sensor, for each split type unit communication wireless communication module and it is some must
Connector is wanted, is placed in Aerial Electronic Equipment box；5 side of load connecting interface is connected with unit skeleton 1, the other side and effectively load
Lotus 6 connects, and interface is adaptable, can design fold mechanism here, and when flying use, split type unit is just unfolded, and effectively reduces
The volume that split type unit occupies.
Embodiment one
On the basis of above-mentioned, payload can directly serve as fuselage, and split type unit is distributed by connector fixed symmetrical
In connection framework surrounding.As shown in Fig. 2, being combined into multi-rotor aerocraft, more multi-load is carried.Unit skeleton uses aviation aluminum
Make, battery is lithium battery, and Aerial Electronic Equipment includes electric machine controller, for the bluetooth module of each split type unit communication and necessary
The sensors such as position, speed, complete machine flight control can be set to open source and fly in control or load；Load connecting interface can flexibly be set
Meter, is matched or is customized according to the size and weight of payload, can also adjust installation site and setting angle, it is ensured that full
Sufficient complete machine flight requires.
Embodiment two
On the basis of above-mentioned, payload can be directly load mounted, cargo etc., and split type unit does not need to connect
Frame can be directly symmetrically distributed on the outside of payload, also shown in FIG. 2, be combined into multi-rotor aerocraft.It is set by avionics
For upper wireless device, adaptively adjusted between each split type unit by avionics control system, so that each split type list
Dynamic balancing is mutually realized between member, adjusts installation site and setting angle, it is ensured that is met complete machine flight and is required.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (8)
1. a kind of separate assembling aircraft, it is characterised in that the aircraft is without fixed main body, including at least two split type lists
Member, split type unit is by connecting and composing the state of flight of aircraft with payload；
The split type unit includes unit skeleton and setting in the intraskeletal power supply of unit, Aerial Electronic Equipment and power device, is divided
Body formula unit passes through Aerial Electronic Equipment each other and carries out wireless communication networking, controls split type unit posture in flight course,
The payload be with can provide rigid connection point any form.
2. a kind of separate assembling aircraft according to claim 1, it is characterised in that the unit skeleton is long-armed shape,
It is divided into leading portion, middle section and back segment, power device setting is in front end, and in middle section, back segment is used for and has for Aerial Electronic Equipment and power supply setting
Imitate load connection.
3. a kind of separate assembling aircraft according to claim 2, it is characterised in that the leading portion, middle section, back segment are
It is separated from each other, three passes through connector between any two and is connected as an entirety.
4. a kind of separate assembling aircraft according to claim 1 or 2, it is characterised in that the power device includes solid
Determine pedestal, motor and propeller, firm banking is connect with the leading portion of unit skeleton, and motor is fixed on the fixed base, propeller
It is installed vertically on motor output shaft.
5. a kind of separate assembling aircraft according to claim 2, it is characterised in that set between back segment and payload
It is equipped with load connector.
6. a kind of separate assembling aircraft according to claim 5, it is characterised in that the load connector and unit
Foldable between skeleton, have two states: to be folded inward when static, state of flight is expansion outward.
7. a kind of separate assembling aircraft according to claim 1, it is characterised in that can be according to the big of payload
Small and weight, the split type unit number of flexible setting and placement position form an integral combined aircraft.
8. a kind of separate assembling aircraft according to claim 7, it is characterised in that the split type unit symmetrically divides
Cloth forms multi-rotor aerocraft on the outside of payload.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910217771.9A CN109823525A (en) | 2019-03-21 | 2019-03-21 | A kind of separate assembling aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910217771.9A CN109823525A (en) | 2019-03-21 | 2019-03-21 | A kind of separate assembling aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109823525A true CN109823525A (en) | 2019-05-31 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910217771.9A Pending CN109823525A (en) | 2019-03-21 | 2019-03-21 | A kind of separate assembling aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112362289A (en) * | 2021-01-13 | 2021-02-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft split test method and device, computer equipment and readable storage medium |
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| EP3162708A1 (en) * | 2015-10-30 | 2017-05-03 | BAE Systems PLC | Air vehicle and method and apparatus for control thereof |
| CN107226209A (en) * | 2017-06-05 | 2017-10-03 | 歌尔科技有限公司 | A kind of unmanned plane unit and a kind of Combined unmanned machine |
| CN107985577A (en) * | 2017-12-07 | 2018-05-04 | 宁波隆翔环保科技有限公司 | A kind of safe unmanned plane |
| CN207550503U (en) * | 2017-12-15 | 2018-06-29 | 江苏航丰智控无人机有限公司 | Lightweight unmanned plane and cluster cooperative system |
| CN108928469A (en) * | 2018-06-26 | 2018-12-04 | 西华大学 | A kind of modularized combination type multi-rotor unmanned aerial vehicle |
| CN208393616U (en) * | 2018-05-17 | 2019-01-18 | 北京大工科技有限公司 | A kind of standby battery device and unmanned plane of unmanned plane |
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2019
- 2019-03-21 CN CN201910217771.9A patent/CN109823525A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3162708A1 (en) * | 2015-10-30 | 2017-05-03 | BAE Systems PLC | Air vehicle and method and apparatus for control thereof |
| CN107226209A (en) * | 2017-06-05 | 2017-10-03 | 歌尔科技有限公司 | A kind of unmanned plane unit and a kind of Combined unmanned machine |
| CN107985577A (en) * | 2017-12-07 | 2018-05-04 | 宁波隆翔环保科技有限公司 | A kind of safe unmanned plane |
| CN207550503U (en) * | 2017-12-15 | 2018-06-29 | 江苏航丰智控无人机有限公司 | Lightweight unmanned plane and cluster cooperative system |
| CN208393616U (en) * | 2018-05-17 | 2019-01-18 | 北京大工科技有限公司 | A kind of standby battery device and unmanned plane of unmanned plane |
| CN108928469A (en) * | 2018-06-26 | 2018-12-04 | 西华大学 | A kind of modularized combination type multi-rotor unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112362289A (en) * | 2021-01-13 | 2021-02-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft split test method and device, computer equipment and readable storage medium |
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Application publication date: 20190531 |
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