CN110228581A - A kind of high speed Bi-Tail-Boom Layout unmanned plane - Google Patents
A kind of high speed Bi-Tail-Boom Layout unmanned plane Download PDFInfo
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- CN110228581A CN110228581A CN201910492368.7A CN201910492368A CN110228581A CN 110228581 A CN110228581 A CN 110228581A CN 201910492368 A CN201910492368 A CN 201910492368A CN 110228581 A CN110228581 A CN 110228581A
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- tail
- wing
- vertical fin
- supporting rod
- fuselage
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- 238000013461 design Methods 0.000 claims abstract description 6
- 230000007704 transition Effects 0.000 claims abstract description 4
- 239000000446 fuel Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 238000013016 damping Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 238000000748 compression moulding Methods 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 238000012545 processing Methods 0.000 claims description 2
- 230000007812 deficiency Effects 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 241000272194 Ciconiiformes Species 0.000 description 1
- 239000006173 Good's buffer Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000002283 diesel fuel Substances 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention discloses a kind of high speed Bi-Tail-Boom Layout unmanned plane, and fuselage interior is from front to back by being divided into equipment compartment, Bunker and piggyback pod.Fuselage arranged beneath tricycle landing gear.Wing is installed in fuselage two sides, is connected with the end of main beam on fuselage.Tail supporting rod is separately installed with below the wing of two sides；Tail supporting rod end is equipped with vertical fin, and design has integral structure horizontal tail between vertical fin.Rectification transition is carried out between above-mentioned fuselage and wing, wing and shoe, tail supporting rod and vertical fin and vertical fin and horizontal tail；And pass through Quick-release pin axis connection between wing and girder, tail supporting rod and wing and vertical fin and tail supporting rod.There are 6 independent rudder faces simultaneously, separately design in outside, two vertical fin rears and horizontal tail rear in two wings.Assembly and disassembly rapid and convenient of the present invention；It is combined manipulation by 6 independent rudder faces and winged control module, the redundancy of steerable system is increased, improves flight course reliability, solve the deficiency of Bi-Tail-Boom Layout unmanned plane takeoff and landing performance difference.
Description
Technical field
The invention belongs to fixed wing aircraft design field in aviation aircraft, be related to a kind of high speed Bi-Tail-Boom Layout without
It is man-machine.
Background technique
Bi-Tail-Boom Layout refers to that empennage is mounted on two from the shoe that fuselage stretches out.Relative to normal configuration's aircraft,
Bi-Tail-Boom Layout is a kind of unconventional aerodynamic arrangement in airplane design, and there are many feature, such as common pushers for twin-boom aircraft
Engine is easily installed photoelectronic reconnaissance equipment, will not cause to cover to equipment；Dynamical system is located in the middle part of full machine, operating mass unloden
The advantages that concentration, flight control is good, in some application fields, have to mission payload ability and endurance voyage higher and higher
It is required that Bi-Tail-Boom Layout unmanned plane provides a solution.The unmanned plane packet of the double shoe formula layouts of the use being currently known
Patrol's unmanned plane of Switzerland, the shadow unmanned plane in the U.S., penguin unmanned plane, black Jack's unmanned plane etc. are included, absolutely proves double tails
Support layout unmanned plane is greatly paid close attention to by countries in the world, and will obtain bigger development in future.
Although Bi-Tail-Boom Layout unmanned plane has the advantages that numerous protrusions, but also have corresponding insufficient and limitation, needs
Pointedly solve:
A) unmanned plane requires lifting capacity strong, needs to reduce housing construction weight as far as possible, improves structure space utilization rate；
B) unmanned plane requires to carry out the operation flight of longer endurance and voyage, needs faster flying speed, lesser flies
Row resistance and higher lift resistance ratio；
C) Bi-Tail-Boom Layout unmanned plane carries out long endurance flight, needs to reduce engine oil consumption rate, equips airborne microminiature
Generator；
D) Bi-Tail-Boom Layout unmanned plane shoe is longer, takes off and is easy to rub ground when landing.
Summary of the invention
To overcome above-mentioned unfavorable factor, the present invention carries out reasonable master-plan and aircraft gas to Bi-Tail-Boom Layout unmanned plane
Dynamic profile optimization, proposes a kind of high speed Bi-Tail-Boom Layout unmanned plane.
High speed Bi-Tail-Boom Layout unmanned plane of the present invention, including fuselage, wing, shoe, horizontal tail, vertical fin and undercarriage.
Wherein, fuselage is divided into equipment compartment, Bunker and piggyback pod by partition from front to back.It is loaded inside equipment compartment and flies control
Module, power module, mission payload and Qian Qi steering mechanism；Conformal soft tank is loaded in fuel compartment；It is equipped in piggyback pod
ECU controls box and turbojet.
Fuselage arranged beneath tricycle landing gear.Fuselage two sides are installed by port wing and starboard wing respectively；Port wing and the right side
Airfoil root is connected by quick-release coupling with the end of main beam on fuselage；Port wing and starboard wing rear arrange outside rudder face and interior
Side rudder face.
Left tail supporting rod and right tail supporting rod are separately installed with below port wing and starboard wing.Left tail supporting rod and right tail supporting rod front
Pass through two Quick-release pin axis connections between the lower section in the middle part of port wing and starboard wing respectively.Part after left tail supporting rod and right tail supporting rod
Left vertical fin and right vertical fin are not installed, left vertical fin and right vertical fin root are respectively between left tail supporting rod and right tail supporting rod rear portion by fast
Unload pin shaft connection.Horizontal tail is provided between left vertical fin and right vertical fin；Left vertical fin, right vertical fin and horizontal tail rear are respectively provided with control vane
Face.
It is carried out between above-mentioned fuselage and wing, wing and shoe, tail supporting rod and vertical fin and vertical fin and horizontal tail rectified
It crosses.
The present invention has the advantages that
1, a kind of high speed Bi-Tail-Boom Layout unmanned plane of the present invention, maximum flying speed is more than 400km/h, suitable for quickly supporting
Up to target area, emergency disposal is carried out；
2, a kind of high speed Bi-Tail-Boom Layout unmanned plane of the present invention, each component use quick-release connector, guarantee the group of unmanned plane
Assembly and disassembly being capable of rapid and convenient；
3, a kind of high speed Bi-Tail-Boom Layout unmanned plane of the present invention, shares 8 independent rudder faces, flies control module and is combined behaviour
It is vertical, the redundancy of steerable system is increased, the reliability of flight course is improved, and solves Bi-Tail-Boom Layout unmanned plane takeoff and landing performance
The deficiency of difference；
4, a kind of high speed Bi-Tail-Boom Layout unmanned plane of the present invention, fuselage-wing, wing-shoe, shoe-vertical fin and vertical fin
Rectification transition is carried out between horizontal tail, reduces the interference drag of each component of body in flight course.
Detailed description of the invention
Fig. 1 is overall structure of the present invention；
Fig. 2 is overall structure top view of the present invention；
Fig. 3 is landing gear structure schematic diagram in the present invention；
Fig. 4 is the rectification design schematic diagram in the present invention between wing and fuselage.
In figure:
1- fuselage 2- wing 3- tail supporting rod
4- horizontal tail 5- vertical fin 6- undercarriage
101- nose shell 102- fuselage main body 103- equipment compartment
104- Bunker 105- piggyback pod 106-ECU controls box
107- turbojet 108- nose-gear 109- main landing gear
Rudder face on the outside of 110- port wing 111- starboard wing 112-
The left tail supporting rod of rudder face 114- girder 115- on the inside of 113-
The left right vertical fin of vertical fin 118- of the right tail supporting rod 117- of 116-
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
High speed Bi-Tail-Boom Layout unmanned plane of the present invention, including fuselage 1, wing 2, shoe 3, horizontal tail 4, vertical fin 5 and undercarriage
6。
As shown in Fig. 2, fuselage 1 includes 102 two parts of nose shell 101 and fuselage main body, nose shell 101 is taper, installation
In 102 front end of fuselage main body, rectified action is played, while inside can be used to charging appliance.Fuselage main body 102 carries out profile optimization and sets
Meter makes whole streamlined, the flight resistance of reduction fuselage 1 while improving internal loading space.
Equipment compartment 103, Bunker 104 and piggyback pod 105 are divided by partition from front to back in fuselage main body 102；Wherein,
The winged control module of loading, power module, mission payload (photoelectric nacelle, phased-array radar etc.) and preceding turn inside equipment compartment 103
To mechanism；Fly control module to be connected with power module by power cable, is the power supply of full machine equipment by power module；While and task
It is connected between load by cable, flies control module and be used to execute aerial mission resolving, maintain aircraft normal flight.Equipment compartment 103 has
There are equipment hatchcover 103a, equipment hatchcover 103a also to be manufactured by composite material, guarantees good appearance curved surface and formed precision.Fuel
Conformal soft tank 104a is loaded in cabin 104, for installing fuel.ECU control box 106 is installed in piggyback pod 105 and turbine sprays
Gas engine 107.ECU control box 106 is mainly used for status monitoring and the control of turbojet 107, including engine
The parameters such as revolving speed, temperature, distributive value are connected by cable with turbojet 107, and transmission ECU control box 106 is to turbine
The condition monitoring data of the control instruction and turbojet 107 of jet engine 107 itself.Turbojet
107 spray combustion gas backward, provide forward thrust, maximum thrust 296N for unmanned plane, and can be applicable in kerosene/diesel oil etc. and is more
Plant astatki, warship demand in satisfaction.Above-mentioned ECU control box 106 is connect with winged control module by cable, is transmitted and is flown control module
The two-way signal data between ECU control box.
As shown in figure 3,102 arranged beneath tricycle landing gear 6 of fuselage main body, including nose-gear 108 and master rise and fall
Frame 109, nose-gear 108 are designed as the articulated landing gear with spring damping, are installed on 102 front of fuselage main body；It leads
The carbon fiber composite structure part that frame 109 is compression molding is fallen, damping can be carried out by the flexible deformation of itself, it is light-weight,
Good buffer effect is installed below 102 middle and back of fuselage main body.
102 middle and back two sides of fuselage main body are installed by port wing 110 and starboard wing 111 respectively；Port wing 110 and starboard wing
111 roots are connected by quick-release coupling with 114 end of girder in fuselage main body, realize port wing 110 and starboard wing 111 just
Prompt quick assembly or disassembly.To improve the stalling characteristics of unmanned plane, improving flight quality, port wing 110 and starboard wing 111 are set
In respect of negative geometric twist.
The wing tip of port wing 110 and starboard wing 111 has carried out round and smooth processing, and reduction port wing 110 is lured with starboard wing 111
Lead resistance.Meanwhile as shown in figure 4, the join domain 119 between fuselage 102 and port wing 110 and starboard wing 111 carry out rectification set
Meter, reduces the interference drag of fuselage main body 102 and port wing 110 and starboard wing 111, and the inside for improving fuselage main body 102 holds
Product increases fuel oil volume.
Port wing 110 and 111 rear of starboard wing arrangement outside rudder face 112 and inside rudder face 113.Wherein, outside rudder face
112 are used as aileron in flight course, provide roll guidance；Inside rudder face 113 is used as flaperon, can assist in flight course
Outside rudder face 112 carries out roll guidance, in the takeoff and landing stage, can be used as wing flap or flap, improve Bi-Tail-Boom Layout without
Man-machine low-speed condition.
Left tail supporting rod 115 and right tail supporting rod 116 are separately installed with below port wing 110 and starboard wing 111.Left tail supporting rod
115 and 116 front of right tail supporting rod connected between port wing 110 and the lower section at the middle part of starboard wing 111 by two quick-release pin shafts respectively
It connects.Left tail supporting rod 115 is separately installed with left vertical fin 117 and right vertical fin 118 with right 116 rear portion of tail supporting rod, and left vertical fin 117 hangs down with the right side
118 root of tail passes through Quick-release pin axis connection between 116 rear portion of left tail supporting rod 115 and right tail supporting rod respectively.Left vertical fin 117 hangs down with the right side
It is provided with horizontal tail 4 between tail 118, it is integrally formed between three, the construction weight of empennage is reduced to greatest extent.Left vertical fin 117, the right side are hung down
Tail 118 and 4 rear of horizontal tail are respectively provided with primary control surface, and wherein the elevator at 4 rear portion of horizontal tail provides full machine pitch control, left vertical fin
117 provide directional control with the rudder at right 118 rear portion of vertical fin.It above-mentioned wing 2 and shoe 3, tail supporting rod 3 and vertical fin 5 and hangs down
Rectification transition is carried out between tail 5 and horizontal tail 4, reduces the interference drag of each component of body in flight course.
Claims (4)
1. a kind of high speed Bi-Tail-Boom Layout unmanned plane, including fuselage, wing, shoe, horizontal tail, vertical fin and undercarriage；Its feature exists
In:
Fuselage is divided into equipment compartment, Bunker and piggyback pod by partition from front to back；It is loaded inside equipment compartment and flies control module, power supply
Module, mission payload and Qian Qi steering mechanism；Conformal soft tank is loaded in fuel compartment；ECU control box is installed in piggyback pod
With turbojet；
Fuselage arranged beneath tricycle landing gear；Fuselage two sides are installed by port wing and starboard wing respectively；Port wing and starboard wing
Root is connected by quick-release coupling with the end of main beam on fuselage；Port wing and starboard wing rear arrangement outside rudder face and in-rudder
Face；
Left tail supporting rod and right tail supporting rod are separately installed with below port wing and starboard wing；Left tail supporting rod and right tail supporting rod front are distinguished
Pass through two Quick-release pin axis connections between the lower section in the middle part of port wing and starboard wing；Left tail supporting rod is pacified respectively with right tail supporting rod rear portion
Equipped with left vertical fin and right vertical fin, left vertical fin and right vertical fin root pass through Quick-release pin between left tail supporting rod and right tail supporting rod rear portion respectively
Axis connection；Horizontal tail is provided between left vertical fin and right vertical fin；Left vertical fin, right vertical fin and horizontal tail rear are respectively provided with primary control surface；
Rectification transition is carried out between above-mentioned fuselage and wing, wing and shoe, tail supporting rod and vertical fin and vertical fin and horizontal tail.
2. a kind of high speed Bi-Tail-Boom Layout unmanned plane as described in claim 1, it is characterised in that: bikini undercarriage includes preceding rises
Fall frame and main landing gear；Nose-gear is designed as the articulated landing gear with spring damping；Main landing gear is compression molding
Carbon fiber composite structure part.
3. a kind of high speed Bi-Tail-Boom Layout unmanned plane as described in claim 1, it is characterised in that: port wing and starboard wing design have
Negative geometric twist.
4. a kind of high speed Bi-Tail-Boom Layout unmanned plane as described in claim 1, it is characterised in that: the wing tip of port wing and starboard wing
Round and smooth processing is carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910492368.7A CN110228581A (en) | 2019-06-06 | 2019-06-06 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910492368.7A CN110228581A (en) | 2019-06-06 | 2019-06-06 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN110228581A true CN110228581A (en) | 2019-09-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910492368.7A Pending CN110228581A (en) | 2019-06-06 | 2019-06-06 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607000A (en) * | 2020-12-23 | 2021-04-06 | 武汉量宇智能科技有限公司 | Aircraft control surface control mechanism |
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