CN206679269U - A kind of double hair unmanned planes - Google Patents
A kind of double hair unmanned planes Download PDFInfo
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- CN206679269U CN206679269U CN201720275185.6U CN201720275185U CN206679269U CN 206679269 U CN206679269 U CN 206679269U CN 201720275185 U CN201720275185 U CN 201720275185U CN 206679269 U CN206679269 U CN 206679269U
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- shoe
- horizontal tail
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- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses a kind of double hair unmanned planes, it is intended to can increase unmanned plane take-off weight lifting aircraft task ability, and can increase power and power supply remaining improve aircraft safety.The technical solution adopted in the utility model is such：Including fuselage, wing, 2 wing gondolas, 2 secondary propellers, 2 shoes, 2 secondary vertical fins, 1 secondary horizontal tail；Wing is overlapped on back；2 wing gondolas are lifted on the lower section of wing respectively, and are located at the both sides of fuselage respectively；2 secondary propellers positioned at the front end of 2 wing gondolas, are connected on the engine being arranged in wing gondola by rotating shaft respectively；2 shoes are located at 2 wing gondola rears respectively, are connected with wing gondola rear end；2 secondary vertical fins are located at 2 shoe rears respectively, are connected with shoe；The left and right ends of the horizontal tail are connected with 2 secondary vertical fins respectively.
Description
Technical field
It the utility model is related to a kind of unmanned plane layout, particularly a kind of bimotored unmanned plane.
Background technology
Development of UAV is very fast in recent years, especially with predator's series unmanned plane, pterosaur unmanned plane, the nothing of rainbow 4
Man-machine and heron unmanned plane is deep by various countries user favor for the long endurance unmanned aircraft of representative.These unmanned plane endurances are long, speed is low,
Can a variety of reconnaissance equipments of carry and weapon, perform scouting, monitoring, on a surface target attack etc. task, be well suited for be used for anti-terrorism make
A variety of the army and the people's applications such as war, border patrol, disaster surveillance, Meteorological Services.
The presently disclosed long endurance unmanned aircraft using propeller power (including piston screw oar power and whirlpool oar power)
Separate unit engine is mostly used, and is all in afterbody, using pusher propeller, to avoid spiral by engine arrangement
Oar blocks light path or the electromagnetism wave path that the work of the task devices such as the photoelectric nacelle below fuselage is sent when being in head.But
The take-off weight of this kind of unmanned plane using separate unit engine is big without being easy to do because being limited by engine power；Meanwhile engine
It is difficult that safety returns to landing that aircraft will be made to run out of steam after scram, and power supply capacity can also be affected.
Utility model content
Goal of the invention of the present utility model is：For above-mentioned problem, there is provided a kind of unmanned plane layout, Ji Nengzeng
Unmanned plane take-off weight is added to lift aircraft task ability, and can increase power and power supply remaining improve aircraft safety.
The technical solution adopted in the utility model is such：Including fuselage, wing, 2 wing gondolas, 2 secondary propellers,
2 shoes, 2 secondary vertical fins, 1 secondary horizontal tail；
The length of wing is not less than 12 meters, and aspect ratio is not less than 10, and wing is overlapped on back；
2 wing gondolas are lifted on the lower section of wing respectively, and are located at the both sides of fuselage respectively；Wing gondola leading edge protrudes
Before the leading edge of a wing；
Positioned at the front end of 2 wing gondolas, the hair being arranged in wing gondola is connected to by rotating shaft respectively for 2 secondary propellers
In motivation；
2 shoes are located at 2 wing gondola rears respectively, are connected with wing gondola rear end；
2 secondary vertical fins are located at 2 shoe rears respectively, are connected with shoe；
The left and right ends of the horizontal tail are connected with 2 secondary vertical fins respectively.
Further, fore-and-aft distance of a quarter chord length point away from head of machine wing root chord for fuselage length 50%~
60%.
Further, the span distance of the wing gondola centre-to-centre spacing fuselage plane of symmetry is the 15%~35% of the length of wing half.
Further, inner surface of the end face of the left and right ends of horizontal tail respectively with left and right vertical fin upper end is connected, or horizontal tail
Upper surface of the lower surface respectively with left and right vertical fin of left and right ends be connected, or the end face of the left and right ends of horizontal tail passes through respectively
Changeover portion with corner is connected with the upper surface of left and right vertical fin.
Further, the middle part upper position of vertical fin is connected to the rear of shoe, and the root of vertical fin is protruded under shoe, or
The root of person's vertical fin is connected to the rear of shoe, and the root of vertical fin is not protruded under shoe.
Further, nose-gear is located on forebody, and main landing gear is located on the wing gondola of left and right.
In summary, by adopting the above-described technical solution, the beneficial effects of the utility model are：
1st, the propeller of unmanned plane of the present utility model is located at the wing gondola front end of fuselage both sides, thus will not block machine
The light path or electromagnetism wave path that the work of the task devices such as the photoelectric nacelle below body is sent.
2nd, the utility model is provided with two slave wing gondolas, is respectively provided with two sets of engines and two propellers, have than
The bigger take-off weight of separate unit same-handed oar power, while increase power and power supply remaining.
3rd, main landing gear can be arranged on the wing gondola of left and right sides, so that the airframe structure of unmanned plane and space
It is more complete, be advantageous to dress and hang large-scale task device.
4th, wing, gondola, vertical fin, horizontal tail connect to form closed frame, increase integral rigidity, improve structural stability；Subtract
The aeroeleastic deformation in few course, lifts course stability.
Brief description of the drawings
Fig. 1 is the utility model unmanned plane overall structure diagram；
Fig. 2 is that the utility model critical piece connects relative position schematic diagram；
Fig. 3 is the utility model horizontal tail and the schematic diagram of vertical fin connected mode 1；
Fig. 4 is the utility model horizontal tail and the schematic diagram of vertical fin connected mode 2；
Fig. 5 is the utility model horizontal tail and vertical fin connected mode 3 and shoe and the schematic diagram of vertical fin connected mode 1；
Fig. 6 is the utility model shoe and the schematic diagram of vertical fin connected mode 2.
Marked in figure：1 is fuselage；2 be wing；3 be wing gondola；4 be propeller；5 be shoe；6 be vertical fin；7 be flat
Tail；8 be nose-gear；9 be main landing gear；10 be changeover portion；21 be aileron；22 be wing flap；61 be rudder；71 be lifting
Rudder.
Embodiment
Below in conjunction with the accompanying drawings, the utility model is described in detail.
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining
The utility model, it is not used to limit the utility model.
Fig. 1 is laid out the schematic diagram of a basic embodiment, including 2,2 fuselage 1, wing machines for the utility model unmanned plane
Wing gondola 3,2 secondary 4,2 shoes 5 of propeller, 2 secondary vertical fins 6,1 secondary horizontal tail 7.Wing 2 is overlapped on the top of fuselage 1, the exhibition of wing
Long to be equal to or more than 12 meters, aspect ratio is equal to or more than 10.Aspect ratio is defined as the ratio between wing span and mean geometric chord, commonly uses
Below equation represents：
AR=l/b=l2/S；
Here l is wingspan length, and b is geometric chord of airfoil, and S is wing area.Therefore it can also state as the span (wing
Length) square divided by wing area.
2 wing gondolas 3 are lifted on the lower section of wing 2 respectively, positioned at the both sides of fuselage.The leading edge of wing gondola 3 protrudes from
Before the leading edge of wing 2, the trailing edge of gondola 3 is protruded from after the trailing edge of wing 2.
Positioned at the front end of 2 gondolas 3, the engine being arranged in gondola 3 is connected to by rotating shaft respectively for 2 secondary propellers 4
On.
2 shoes 5 are located at 2 rears of gondola 3 respectively, are connected with the rear end of gondola 3.
2 secondary vertical fins 6 are located at 2 rears of shoe 5 respectively, are connected with shoe 5.
Between 2 secondary vertical fins 6, the left and right ends of horizontal tail 7 are connected 1 secondary horizontal tail 7 with 2 secondary vertical fins 6 respectively.
Wing 2 is divided into port wing and starboard wing again from the angle of aerodynamic arrangement, and 2 wing gondolas 3 divide for left and right part, left machine
Wing gondola is identical with starboard wing gondola theory profile or symmetrical on the full machine plane of symmetry, and only local form is because of equipment peace
Dress, protrusion and blow vent etc. are it is possible that different.
2 shoes 5 divide for left and right part, left shoe it is identical with right shoe theory profile or on full machine plane of symmetry or so pair
Claim, only local form is because equipment installation, protrusion and blow vent etc. are it is possible that different.
2 secondary vertical fins 6 divide for left and right part, left secondary vertical fin it is identical with right secondary vertical fin theory profile or on full machine plane of symmetry or so
Symmetrically, only local form is because equipment installation, protrusion and blow vent etc. are it is possible that different.
Fuselage 1 has accommodation space, and the inside is disposed with avionic device, electrical equipment, fuel tank etc., can also carry nothing
The task device that man-machine needs carry, retractable nose-gear 8 is arranged in forebody.Wing gondola then mainly start by arrangement
The parts such as machine, propeller, retractable main landing gear 9.Main landing gear is not arranged on fuselage, so that the fuselage of unmanned plane
Structure and space are more complete, are advantageous to dress and hang large-scale task device.
The aileron 21 for roll guidance is disposed with wing 2, can further arrange wing flap 22, for increasing during landing
Lift.
The rudder 61 for directional control is disposed with vertical fin 6；The liter for pitch control is disposed with horizontal tail 7
Rudder 71 drops.
Fig. 2 is that the utility model critical piece connects relative position schematic diagram, it is preferred that a quarter string of machine wing root chord
(root chord length is wing theory flat shape and the chord length of plane of symmetry intersection to long point, and a quarter chord length point of machine wing root chord exists
On root string, the distance away from root string leading edge is 1/4) the fore-and-aft distance X away from head of root chord length1/4For fuselage length Lf50%~
60%；The span distance Y of the wing gondola centre-to-centre spacing fuselage plane of symmetry is the 15%~35% of the length l/2 of wing half.
The relative position relation that the left and right ends of horizontal tail 7 are connected with the 2 secondary upper ends of vertical fin 6 respectively includes but is not limited to following
It is several：
The lower surface of the left and right ends of horizontal tail 7 is connected with the upper surface of left and right vertical fin 6, as shown in Figure 3；Or
The end face of horizontal tail 7 or so is connected with the inner surface of left and right vertical fin upper end, as shown in Figure 4；Or
It is connected respectively with the upper surface of vertical fin 6 and the end face of horizontal tail 7 by the changeover portion 10 with corner, as shown in Figure 5.
The connected mode of the vertical fin 6 and shoe 5 includes but is not limited to following several：
The middle part upper position of vertical fin 6 is connected to the afterbody of shoe 5, and the root of vertical fin 6 is protruded under shoe 5, such as Fig. 5 institutes
Show；Or
The root of vertical fin 6 is connected to the afterbody of shoe 5, and the root of vertical fin 6 is not protruded under shoe 5, as shown in Figure 6.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
All any modification, equivalent and improvement made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (9)
1. a kind of double hair unmanned planes, it is characterised in that including fuselage, wing, 2 wing gondolas, 2 secondary propellers, 2 shoes, 2
Secondary vertical fin, 1 secondary horizontal tail；
The length of wing is not less than 12 meters, and aspect ratio is not less than 10, and wing is overlapped on back；
2 wing gondolas are lifted on the lower section of wing respectively, and are located at the both sides of fuselage respectively；Wing gondola leading edge protrudes from machine
Before nose of wing；
Positioned at the front end of 2 wing gondolas, the engine being arranged in wing gondola is connected to by rotating shaft respectively for 2 secondary propellers
On；
2 shoes are located at 2 wing gondola rears respectively, are connected with wing gondola rear end；
2 secondary vertical fins are located at 2 shoe rears respectively, are connected with shoe；
The left and right ends of the horizontal tail are connected with 2 secondary vertical fins respectively.
A kind of double 2. hair unmanned planes according to claim 1, it is characterised in that a quarter chord length point of machine wing root chord away from
The fore-and-aft distance of head is the 50% ~ 60% of fuselage length.
3. a kind of double hair unmanned planes according to claim 1 or 2, it is characterised in that wing gondola centre-to-centre spacing fuselage is symmetrical
The span distance in face is the 15% ~ 35% of the length of wing half.
A kind of 4. double hair unmanned planes according to claim 1 or 2, it is characterised in that the end face of the left and right ends of horizontal tail point
Inner surface not with left and right vertical fin upper end is connected, or the lower surface upper end with left and right vertical fin respectively of the left and right ends of horizontal tail
Face is connected, or the end face of the left and right ends of horizontal tail is connected by the changeover portion with corner with the upper surface of left and right vertical fin respectively.
A kind of 5. double hair unmanned planes according to claim 1 or 2, it is characterised in that the middle part upper position connection of vertical fin
To the rear of shoe, the root of vertical fin is protruded under shoe, or the root of vertical fin is connected to the rear of shoe, the root of vertical fin
Portion is not protruded under shoe.
6. a kind of double hair unmanned planes according to claim 1 or 2, it is characterised in that nose-gear is located on forebody, main
Undercarriage is located on the wing gondola of left and right.
A kind of double 7. hair unmanned planes according to claim 3, it is characterised in that the end face of the left and right ends of horizontal tail respectively with
The inner surface connection of left and right vertical fin upper end, or the lower surface of the left and right ends of horizontal tail connect with the upper surface of left and right vertical fin respectively
Connect, or the end face of the left and right ends of horizontal tail is connected by the changeover portion with corner with the upper surface of left and right vertical fin respectively.
8. a kind of double hair unmanned planes according to claim 3, it is characterised in that the middle part upper position of vertical fin is connected to tail
The rear of support, the root of vertical fin are protruded under shoe, or the root of vertical fin is connected to the rear of shoe, and the root of vertical fin is not
Protrude under shoe.
9. a kind of double hair unmanned planes according to claim 3, it is characterised in that nose-gear is located on forebody, leads
Fall frame to be located on the wing gondola of left and right.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720275185.6U CN206679269U (en) | 2017-03-21 | 2017-03-21 | A kind of double hair unmanned planes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720275185.6U CN206679269U (en) | 2017-03-21 | 2017-03-21 | A kind of double hair unmanned planes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206679269U true CN206679269U (en) | 2017-11-28 |
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ID=60390001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720275185.6U Active CN206679269U (en) | 2017-03-21 | 2017-03-21 | A kind of double hair unmanned planes |
Country Status (1)
| Country | Link |
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| CN (1) | CN206679269U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110228581A (en) * | 2019-06-06 | 2019-09-13 | 天峋创新（北京）科技有限公司 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
-
2017
- 2017-03-21 CN CN201720275185.6U patent/CN206679269U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110203373B (en) * | 2019-05-24 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Structure is dismantled to unmanned aerial vehicle tail of hanging down |
| CN110228581A (en) * | 2019-06-06 | 2019-09-13 | 天峋创新（北京）科技有限公司 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Overall aerodynamic layout and short-distance taking-off and landing method of double-engine unmanned aerial vehicle Effective date of registration: 20191227 Granted publication date: 20171128 Pledgee: Agricultural Bank of China Co.,Ltd. Chengdu Tianfu New Area Branch Pledgor: SICHUAN TENGDUN TECHNOLOGY Co.,Ltd. Registration number: Y2019510000082 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20231026 Granted publication date: 20171128 Pledgee: Agricultural Bank of China Co.,Ltd. Chengdu Tianfu New Area Branch Pledgor: SICHUAN TENGDUN TECHNOLOGY Co.,Ltd. Registration number: Y2019510000082 |