CN207809790U - A kind of unmanned logistics transportation machine of binary - Google Patents
A kind of unmanned logistics transportation machine of binary Download PDFInfo
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- CN207809790U CN207809790U CN201721746806.0U CN201721746806U CN207809790U CN 207809790 U CN207809790 U CN 207809790U CN 201721746806 U CN201721746806 U CN 201721746806U CN 207809790 U CN207809790 U CN 207809790U
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Abstract
A kind of unmanned logistics transportation machine of binary, including wing, fuselage, cargo hold, propeller, nose-gear, main landing gear, empennage and engine.The utility model is using the unmanned design of twin-fuselage configuration：Each fuselage itself is symmetrical, and two fuselages are completely the same；Wing uses high mounted wing, empennage to be laid out for diesis；Two fore-bodies install a turbo oar engine respectively, and the propeller of front is driven to generate pulling force；Undercarriage be lorry formula arrangement, left and right fuselage respectively arrangement one group before, main landing gear；Container-type cargo hold through pneumatic rectification design is hung in the middle part of inner wing.The utility model pneumatic efficiency is high, architecture quality is small, voyage is big, is easy to ensure, air transportation efficiency can be effectively improved, improve logistics timeliness, there is great application value in military transport, civilian logistics field, be a kind of efficient aircraft for expanding air transportation theory, mode and range significantly.
Description
Technical field
The utility model is related to a kind of unmanned logistics transportation machines of binary, belong to field of flight vehicle design.
Background technology
During carrying out cargo transport, mainly by the way of land transportation, sea-freight and air transport.According to different shippings
The combined factors such as amount, time, cost choose suitable Shipping Method.
The advantage of air transportation is embodied in high value, high added value and high timeliness.Its shortcomings that is freight rate than high, carrying capacity
Limited etc., certain advantage is it is also obvious that travelling speed is fast, spatial extent is big.With the explosive growth of logistic industry, logistics fortune
Defeated accuracy and timeliness require to greatly improve, and air transportation also becomes more and more important, and especially some are important urgent
Part needs to be sent on time in client's hand.
It according to new air transportation demand, on the one hand requires cargo aircraft carrying capacity big, needs solution aircraft effective
Load and engine, the matching problem of aerodynamic arrangement, use novel pneumatic layout and General Arrangement Scheme to improve aircraft
Carrying capacity.On the other hand it requires shipping efficient, needs to reduce time cost and economic cost.Current someone's airfreighter
Buying, O＆M it is costly, sortie of taking off and landing is limited, and can not be transported to four or five line cities or more remote place, causes
The timeliness of logistics is not satisfactory.
It for novel cargo aircraft, needs to meet safety, high timeliness, high conevying efficiency, need thus a kind of new
Type binary unmanned transporter solves the above problems, and is competent at the task of branch line large cargo transport.
Utility model content
The technology of the utility model solves the problems, such as：Overcome the deficiencies in the prior art proposes a kind of unmanned fortune of novel binary
Defeated machine, it is safe and reliable, it is flexible and efficient, cargo dead-weight and voyage can be improved, and branch line freight transport task can be completed.
The technical solution of the utility model is：
A kind of unmanned logistics transportation machine of binary, including wing, fuselage, cargo hold, propeller, nose-gear, main landing gear, tail
The wing and engine；
The unmanned transporter of binary uses twin-fuselage configuration, and two fuselages are symmetrical, and inside is equipped with airborne equipment；Empennage
It is laid out using cross empennage, is connected to afterbody, ensure pitching course-stability；Wing is high mounted wing form, is connected to fuselage
Top；Two engines are separately mounted to the head of two fuselages；Two fuselages respectively arrange one group of nose-gear and main landing gear, goods
Cabin is hung in the middle part of wing, is located between two fuselages.
Every group of empennage includes two horizontal tails and two vertical fins, constitutes cross empennage layout.
The wing includes inner wing and outer wing, and two fuselage both sides are outer wing, and the part between outer wing is inner wing, length
Respectively 9m, 8m..
Fuselage includes forebody, four part of middle fuselage, rear body and tail supporting rod, length be respectively 1.5m, 2.5m, 2.5m,
3.5m。
Main landing gear, nose-gear are column support type；Main landing gear is mounted in middle fuselage, is received forward；Nose-gear is installed
It in forebody, receives backward, wing is mounted on middle fuselage top.
Engine uses turbo oar engine, single engine power to be not less than 250kw.
Unmanned plane parameter is as follows:
Nose-gear, main landing gear design parameter are as follows：
, wherein
Preceding main wheel track refers to distance of the nosewheel contact point to main-gear touchdown point；
Main wheel track refers to the distance between two main-gear touchdown points；
Main landing gear height refers to vertical range of the main landing gear earth point to fuselage lower surface；
The maximum compressibility that compressed shape journey refers to main landing gear is led；
Empennage grazing angle refers to the angle between connecting line and horizontal plane between main landing gear earth point and vertical fin minimum point；
Front-wheel to centroidal distance refers to horizontal distance of the nose-gear wheel earth point to center of gravity；
Main wheel to centroidal distance refers to horizontal distance of the main landing gear wheel earth point to center of gravity；
Wing tip grazing angle refers between main landing gear earth point and wing wingtip minimum point between connecting line and horizontal plane
Angle；
Main wheel carrying ratio refers to the ratio that the weight that two main landing gears are born when aircraft is shut down accounts for aircraft gross weight amount.
The advantageous effect of the utility model compared with prior art is：
(1) the utility model proposes the independent cargo hold module of similar container, cargo in conventional cargo aircraft is breached
Loading, Transportation Model, convenient for handling so that logistics working efficiency improve.
(2) it is laid out using binary aircraft in the technical solution of the utility model, the load of outer wing root can be effectively reduced,
Reduce construction weight, allows to further increase wing aspect ratio, improve pneumatic efficiency, increase voyage, additionally it is possible to ensure cargo hold
Installation, binary aircraft layout can be good at the hanging transport for meeting whole container-type cargo hold.
(3) aircraft uses unmanned pattern, improves safety, reduces the cost of exploitation, buying, operation maintenance.
(4) twin fuselage have symmetrical consistency, therefore all components including fuselage can carry out repair and replacement, carry
Height ensures efficiency.
Description of the drawings
Fig. 1 is the structural schematic diagram of the unmanned transporter of the utility model binary；
Fig. 2 is side view；
Fig. 3 is the front view of cargo hold；
Fig. 4 is airframe structure schematic diagram.
Specific implementation mode
Specific embodiment of the present utility model is further described in detail below in conjunction with the accompanying drawings.
New air transportation needs to meet safety, high timeliness, high conevying efficiency, and the high value and height of air transportation
Added value needs to compress operation expense to embody.The utility model proposes a kind of novel unmanned transporters of binary, have
High flight efficiency improves voyage, increases cargo dead-weight, additionally it is possible to improve conevying efficiency and timeliness, reduce operation expense.
As shown in Figure 1, 2, 3, the utility model proposes a kind of unmanned logistics transportation machine of binary, including wing 1, fuselage 2,
Cargo hold 5, propeller 6, nose-gear 7, main landing gear 8, empennage and engine；
The unmanned transporter of binary use twin-fuselage configuration, two fuselages 2 are symmetrical, inside be equipped with airborne equipment, two
A fuselage is identical, to meet the versatility that fuselage repair is replaced；Empennage is laid out using cross empennage, and every group of empennage includes two
A horizontal tail 3 and two vertical fins 4 constitute cross empennage, are connected to 2 tail portion of fuselage, ensure pitching course-stability；Wing 1 is great Zhan
String than high mounted wing form, be connected to 2 top of fuselage；Two engines are separately mounted to the head of two fuselages 2；Undercarriage is four
Trolley type arrangement is taken turns, two fuselages respectively hang at 1 middle part of wing by one group of nose-gear 7 of arrangement and one group of main landing gear 8, cargo hold 5,
Between two fuselages 2, close to position of centre of gravity, be conducive to match gentle control, be easy to ensure the stability of aircraft.
Cargo is put into inside big container in advance on ground, only by replace container come replace repeat dress,
Large batch of bulk goods is unloaded, the aircraft floor residence time is shortened；Streamlined correction of the flank shape is carried out to cargo hold shape, to reduce gas in-flight
Dynamic resistance.Using fork truck come carry and hoist, switching beam suspension arrangement carries out cargo hold carry.Cargo hold using tail portion hatch door on to
Lower opening.
It can ensure that the installation of cargo hold, the interference of fuselage and cargo hold are unlikely to too big again between two fuselages, resistance will not be bright
It is aobvious to increase.Wing 1 includes inner wing and outer wing, and two fuselage both sides are outer wing, and the part between outer wing is inner wing, length difference
For 9m, 8m..
As shown in figure 4, fuselage 2 includes forebody 21,24 4 part of middle fuselage 22, rear body 23 and tail supporting rod, length point
It Wei not 1.5m, 2.5m, 2.5m, 3.5m.Considering functional while initial breakdown interface, structure parting surface is facilitated to be detached with technique
Sharing for the consistent and reinforcement structure in face, advantageously reduces overall weight.
Main landing gear 8, nose-gear 7 are column support type；Main landing gear 8 is mounted in middle fuselage 22, is received forward；Nose-gear
7 are mounted in forebody 21, receive backward, and wing 1 is mounted on 22 top of middle fuselage.
Composite material semi-monocoque and beam type mixed structure is respectively adopted in the main structure of fuselage and cargo hold, and wing and empennage are adopted
With front and back two-beam type layout structure.
The engine that the utility model uses uses turbo oar engine, single engine power to be not less than 250kw.Engine
Body be mounted on forebody 21 within, propeller be arranged on forebody head.
Unmanned plane specific example parameter provided by the utility model is as follows:
Because twin-fuselage configuration allows to use larger aspect ratio, therefore the lift resistance ratio that cruises is larger, can reach 20 or more.
The characteristics of engine can be used whirlpool paddle -9 or PT-6A, engine be：Oil consumption rate is low；Flying height height, speed
Soon.
Using double bicycle type single-wheel layouts, design parameter is as follows for nose-gear 7, main landing gear 8：
Preceding main wheel track refers to distance of the nosewheel contact point to main-gear touchdown point；
Main wheel track refers to the distance between two main-gear touchdown points；
Main landing gear height refers to vertical range of the main landing gear earth point to fuselage lower surface；
The maximum compressibility that compressed shape journey refers to main landing gear is led；
Empennage grazing angle refers to the angle between connecting line and horizontal plane between main landing gear earth point and vertical fin minimum point；
Front-wheel to centroidal distance refers to horizontal distance of the nose-gear wheel earth point to center of gravity；
Main wheel to centroidal distance refers to horizontal distance of the main landing gear wheel earth point to center of gravity；
Wing tip grazing angle refers between main landing gear earth point and wing wingtip minimum point between connecting line and horizontal plane
Angle；
Main wheel carrying ratio refers to the ratio that the weight that two main landing gears are born when aircraft is shut down accounts for aircraft gross weight amount.
The unmanned transporter of novel binary in the present embodiment can reach following technology after calculating and emulating
Index：
Claims (8)
1. a kind of unmanned logistics transportation machine of binary, it is characterised in that：Including wing (1), fuselage (2), cargo hold (5), propeller
(6), nose-gear (7), main landing gear (8), empennage and engine；
The unmanned transporter of binary uses twin-fuselage configuration, and two fuselages (2) are symmetrical, and inside is equipped with airborne equipment；Empennage
It is laid out using cross empennage, is connected to fuselage (2) tail portion, ensure pitching course-stability；Wing (1) is high mounted wing form, connection
On fuselage (2) top；Two engines are separately mounted to the head of two fuselages (2)；Two fuselages respectively arrange one group of nose-gear
(7) it is located between two fuselages (2) in the middle part of wing (1) with main landing gear (8), cargo hold (5) hanging.
2. the unmanned logistics transportation machine of a kind of binary according to claim 1, it is characterised in that：Every group of empennage includes two flat
Tail (3) and two vertical fins (4) constitute cross empennage layout.
3. the unmanned logistics transportation machine of a kind of binary according to claim 1, it is characterised in that：The wing (1) includes interior
The wing and outer wing, two fuselage (2) both sides are outer wing, and the part between outer wing is inner wing, and length is respectively 9m, 8m.
4. the unmanned logistics transportation machine of a kind of binary according to claim 1, it is characterised in that：Fuselage (2) includes forebody
(21), (24) four part of middle fuselage (22), rear body (23) and tail supporting rod, length is respectively 1.5m, 2.5m, 2.5m, 3.5m.
5. the unmanned logistics transportation machine of a kind of binary according to claim 4, it is characterised in that：Main landing gear (8) preceding rises and falls
Frame (7) is column support type；Main landing gear (8) is mounted in middle fuselage (22), is received forward；Nose-gear (7) is mounted on forebody
(21) it in, receives backward, wing (1) is mounted on middle fuselage (22) top.
6. the unmanned logistics transportation machine of a kind of binary according to claim 1, it is characterised in that：Engine is started using whirlpool paddle
Machine, single engine power are not less than 250kw.
7. according to a kind of unmanned logistics transportation machine of binary of claim 1~6 any one of them, it is characterised in that：Unmanned plane is joined
Number is as follows:
Span 26m, overall length 10.6m containing propeller hub, total high 3.38m, wing area 30m2, 226.67 kg/m of wing load2, center carry sky
Between wide 9m, cargo hold volume 12m3, cruise lift coefficient 0.9, and cruise lift resistance ratio 20.7, aspect ratio 22.53.
8. according to a kind of unmanned logistics transportation machine of binary of claim 1~6 any one of them, it is characterised in that：Nose-gear
(7), main landing gear (8) design parameter is as follows：
Preceding main wheel track 2550mm, main wheel track 7070mm, main landing gear height 720mm have led compression travel 84mm, empennage grazing angle
12.72 °, front-wheel to centroidal distance 2170mm, main wheel to centroidal distance 380mm, hanging object road clearance 458mm, wing tip wiping ground
11.60 ° of angle, main wheel carry ratio 85%；
Wherein,
Preceding main wheel track refers to distance of the nosewheel contact point to main-gear touchdown point；
Main wheel track refers to the distance between two main-gear touchdown points；
Main landing gear height refers to vertical range of the main landing gear earth point to fuselage lower surface；
The maximum compressibility that compressed shape journey refers to main landing gear is led；
Empennage grazing angle refers to the angle between connecting line and horizontal plane between main landing gear earth point and vertical fin minimum point；
Front-wheel to centroidal distance refers to horizontal distance of the nose-gear wheel earth point to center of gravity；
Main wheel to centroidal distance refers to horizontal distance of the main landing gear wheel earth point to center of gravity；
Wing tip grazing angle refers to the angle between connecting line and horizontal plane between main landing gear earth point and wing wingtip minimum point；
Main wheel carrying ratio refers to the ratio that the weight that two main landing gears are born when aircraft is shut down accounts for aircraft gross weight amount.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201721746806.0U CN207809790U (en) | 2017-12-14 | 2017-12-14 | A kind of unmanned logistics transportation machine of binary |
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| CN201721746806.0U CN207809790U (en) | 2017-12-14 | 2017-12-14 | A kind of unmanned logistics transportation machine of binary |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108058830A (en) * | 2017-12-14 | 2018-05-22 | 彩虹无人机科技有限公司 | A kind of unmanned logistics transportation machine of binary |
| CN109263855A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | A kind of super large aspect ratio aerodynamic configuration of aircraft using the rear edge support wing |
| CN109263856A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN113335517A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Double-fuselage tandem rotor wing composite wing aircraft layout |
-
2017
- 2017-12-14 CN CN201721746806.0U patent/CN207809790U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108058830A (en) * | 2017-12-14 | 2018-05-22 | 彩虹无人机科技有限公司 | A kind of unmanned logistics transportation machine of binary |
| CN109263855A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | A kind of super large aspect ratio aerodynamic configuration of aircraft using the rear edge support wing |
| CN109263856A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement |
| CN109263856B (en) * | 2018-09-28 | 2020-07-03 | 北京航空航天大学 | Pneumatic layout of multipurpose carrier aircraft with large aspect ratio support wings and double aircraft bodies |
| CN109263855B (en) * | 2018-09-28 | 2020-12-29 | 北京航空航天大学 | Pneumatic layout of ultra-large aspect ratio aircraft adopting trailing edge supporting wings |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN113335517A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Double-fuselage tandem rotor wing composite wing aircraft layout |
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