CN108275273A - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
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- CN108275273A CN108275273A CN201810190385.0A CN201810190385A CN108275273A CN 108275273 A CN108275273 A CN 108275273A CN 201810190385 A CN201810190385 A CN 201810190385A CN 108275273 A CN108275273 A CN 108275273A
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- unmanned plane
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- 239000007921 spray Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 7
- 230000005611 electricity Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000005265 energy consumption Methods 0.000 description 2
- 210000000515 tooth Anatomy 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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Abstract
The present invention relates to air vehicle technique fields, more particularly to a kind of unmanned plane of civilian low speed, it includes fuselage, the both sides of fuselage are respectively equipped with wing, engine is equipped in fuselage, afterbody is equipped with engine jet pipe, engine jet pipe is connect with engine, the head upper end of the fuselage or/and lower end are equipped with air admission hole, and wherein at least one air admission hole is equipped with air-inlet cover, air-inlet cover is flexibly connected with fuselage, fuselage is equipped with the control unit for driving the movable driving device of air-inlet cover and for controlling the driving device, the front end of fuselage is equipped with pitot, pitot, engine is electrically connected with control unit.Invention is by being arranged movable air-inlet cover, so that unmanned plane, in flight course, the size of practical adjustment air inlet, optimizes the resistance and lift and thrust that it is subject to as needed, so that resistance minimum is to extend continuation of the journey, next, which is additionally provided with wind motor, can further extend continuation of the journey.
Description
Technical field
The present invention relates to air vehicle technique field more particularly to a kind of unmanned planes of civilian low speed.
Background technology
With the development of aeronautical technology, the application of unmanned plane is more and more extensive, has had express company to test nobody at present
Machine carries out package dispensing, also has using unmanned plane camera shooting etc.；Since the load of unmanned plane increases, energy consumption is opposite to be increased, therefore nothing
The man-machine requirement to cruising ability is relatively high, and unmanned plane carries out resistance adjustment windward or when contrary wind, cannot being directed to wind speed, causes
Energy consumption is larger, causes cruising ability weak.
Invention content
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to provide a kind of unmanned plane of cruising ability length.
The both sides of a kind of unmanned plane, including fuselage, fuselage are respectively equipped with wing, and engine, afterbody are equipped in fuselage
Equipped with engine jet pipe, engine jet pipe is connect with engine, and the head upper end of the fuselage or/and lower end are equipped with air admission hole,
And wherein at least one air admission hole is equipped with air-inlet cover, air-inlet cover is flexibly connected with fuselage, and fuselage is equipped with for driving air inlet
The movable driving device of lid and the control unit for controlling the driving device, the front end of fuselage are equipped with pitot, pitot,
Engine is electrically connected with control unit.
Further, the fuselage is equipped with the matched guide groove in tail portion with air-inlet cover, and the driving device is rudder
Machine, servo driving are connected with pivoted arm, and pivoted arm is connect by connecting rod with air-inlet cover, wherein the both ends of connecting rod respectively with pivoted arm, into
Gas port lid is hinged.
Further, the opening area of air admission hole is S1, and the flight resistance that air admission hole is brought is：F1=K1×S1×V2；Its
In, K1 is proportionality coefficient, and V is air speed, i.e. speed of the unmanned plane machine relative to air；Unmanned plane during flying resistance：L2=0.5(ρV2
C2S), C2Indicate resistance coefficient；ρ indicates that atmospheric density, S indicate unmanned plane surface area； S1=L2/（KV-K1V2）, wherein K is
Normal proportionality coefficient.
Further, inlet channel is additionally provided in fuselage, inlet channel is equipped at least one air inlet by-path section and a master
Channel section, air admission hole are the entrance of air inlet by-path section, and the outlet of main channel section is correspondingly arranged with jet engine；The main channel
It is provided with the wind-driven generator for being connected with accumulator.
Further, the main channel section is set there are one side opening, and side opening is connected with side road, and side is set in road
There are wind-driven generator, the outlet in side road to be connected to engine jet pipe；The side opening flexible connection is useful for adjusting main channel
The switching door of section and side road air inflow, switching door are connected with switching driving device, and switching driving device is electrically connected with control unit
It connects.
Further, the rear end of the wing is equipped with wing flap, and wing flap is flexibly connected with wing, and fuselage is connected with for driving wing
The wing flap of overturning drives switching mechanism；The wing flap driving switching mechanism includes the shaft being connect with wing flap, and shaft is connected with rudder
Machine, steering engine are electrically connected with control unit.
Further, the rear end of the wing is additionally provided with aileron, and aileron is located on the outside of wing flap, and aileron connects with wing activity
It connects；The aileron is connected with auxiliary spindle, and the shaft is equipped with through-hole, and one end of auxiliary spindle is connect across through-hole with steering engine.
Further, the both sides of afterbody are respectively equipped with spoiler.
Further, the leading edge of a wing is smoothly connected with 1 leading edge of fuselage by circular arc, wherein maximum leading edge sweep is
45.26 °, minimum leading edge sweep is 27.18 °, and trailing edge angle of sweep is 10 °~12 °.
Further, the wing flap includes main wing flap and flaperon, and the main wing flap includes main casing, the rear end of main casing
Opening, flaperon include sub-shell, and main casing is stretched into the front end of sub-shell by opening, and the shaft in main casing is connected with main cone
Shape gear, is fixed with bearing block in main casing, and bearing block is connected with transmission shaft by bearing, the front end of transmission shaft be connected with it is main
The rear end of the secondary angular wheel of angular wheel engagement, transmission shaft is equipped with screw thread and is threadedly coupled with sub-shell.
Preferably, fuselage is provided with switch, and the switching-driving device for driving switch to be moved relative to fuselage,
Switching-driving device is electrically connected with control unit, and steering engine is drivingly connected with shaft, auxiliary spindle respectively by switch, the switching
Device includes intermediate propeller shaft, and the steering engine is equipped with output shaft, and output shaft is connected with A driving gears and B driving gears, shaft connection
There are A driven gears, auxiliary spindle to be connected with B driven gears, the intermediate propeller shaft is connected with two groups of intermediate gears, one group of center tooth
Wheel includes A+ intermediate gears and A- intermediate gears, and another group of intermediate gear includes B+ intermediate gears and B- intermediate gears；Wherein, A
Driving gear is engaged by one group of intermediate gear with A driven gears, B driving gears by another group of intermediate gear with
B driven gears engage, and A+ intermediate gears are disposed adjacent with B+ intermediate gears；When steering engine only controls shaft rotation, switch phase
Fuselage is moved, A driving gears are connect by A- intermediate gears with A driven gears, when steering engine only controls auxiliary spindle rotation, are cut
Parallel operation is moved relative to fuselage, and B driving gears are connect by B- intermediate gears with B driven gears, when servos control shaft and pair
When shaft rotates, switch is moved relative to fuselage, and A driving gears are connect by A+ intermediate gears with A driven gears, B driving tooths
Wheel is connect by B+ intermediate gears with B driven gears.
Advantageous effect of the invention：Invention is by being arranged movable air-inlet cover so that unmanned plane in flight course, according to
The size for needing practical adjustment air inlet optimizes resistance and lift and thrust that it is subject to so that resistance minimum is to extend
Continuation of the journey, next, which is additionally provided with wind motor, can further extend continuation of the journey.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram of the present embodiment.
Fig. 2 is the schematic diagram at another visual angle of Fig. 1.
Fig. 3 is the driving structure schematic diagram of air-inlet cover；
Fig. 4 is gas channel distribution schematic diagram.
The driving structure schematic diagram of Fig. 5 wing flaps and aileron.
Fig. 6 is the structural schematic diagram of wing flap.
Fig. 7 is the structural schematic diagram of servo driving wing flap, aileron.
Reference numeral includes：
1 --- fuselage；2 --- wing；3 --- wing flap；4 --- aileron；5 --- spoiler；6 --- engine jet pipe；7——
Air-inlet cover；8 --- connecting rod；9 --- pivoted arm；10 --- steering engine；11 --- air admission hole；12 --- air inlet by-path section；13——
Switch door；14 --- main channel section；15 --- engine；17 --- side opening；18 --- side road；19 --- wind-power electricity generation
Machine；20 --- shaft；21 --- auxiliary spindle；22 --- pitot；31 --- main wing flap；32 --- flaperon；33 --- main cone
Shape gear；34 --- transmission shaft；35 --- secondary angular wheel；23 --- A driven gears；24 --- B driven gears；101——
Intermediate propeller shaft；102 --- B- intermediate gears；103 --- B+ intermediate gears；104 --- A+ intermediate gears；105 --- in A-
Between gear；25 --- B driving gears；26 --- A driving gears.
Specific implementation mode
Invention is described in detail below in conjunction with attached drawing.As shown in Figures 1 to 5.
Embodiment 1：The both sides of a kind of unmanned plane, including fuselage 1, fuselage 1 are respectively equipped with wing 2, are equipped with and start in fuselage 1
Machine 15,1 tail portion of fuselage are equipped with engine jet pipe 6, and engine jet pipe 6 is connect with engine 15, the head upper end of the fuselage 1
Or/and lower end is equipped with air admission hole 11, and wherein at least one air admission hole 11 is equipped with air-inlet cover 7, air-inlet cover 7 is lived with fuselage 1
Dynamic connection, fuselage 1 are equipped with the control list for driving 7 movable driving device of air-inlet cover and for controlling the driving device
The front end of member, fuselage 1 is equipped with pitot 22, and pitot 22, engine 15 are electrically connected with control unit.
In the technical program, the promotion of unmanned plane is passed through using engine 15 in the prior art such as jet engine
Rearward jet is to obtain power；The size of power is controlled unit control.Unmanned plane in flight course, air drag at
To restrict the biggest factor of unmanned plane continuation of the journey, the engine 15 of unmanned plane needs that air drag is overcome to do work, in order to reduce flight
Air drag in the process, unmanned plane majorities many at present is by the Characteristic Design to wing 2, as the activity of wing flap 3 is set
It sets.And the unmanned plane of the technical program overcomes the technology prejudice, using the change to 11 size of air admission hole, to adjust in-flight
Air drag, reducing cost and enforcement difficulty reduces, it is easy to accomplish.Secondly, air-inlet cover 7 and driving device can adopt
With the prior art, such as air-inlet cover 7 is driven to move linearly along air admission hole 11 by worm and gear by servo motor.
Further, the fuselage 1 is equipped with the matched guide groove in tail portion with air-inlet cover 7, and the driving device is
Steering engine 10, the drive connection of steering engine 10 have pivoted arm 9, pivoted arm 9 to be connect with air-inlet cover 7 by connecting rod 8, wherein the both ends of connecting rod 8 point
It is not hinged with pivoted arm 9, air-inlet cover 7.
Rocking handle rotation is driven by steering engine 10, and connecting rod 8 is driven to move forward and backward, connecting rod drives air-inlet cover 7 is front and back to move
It is dynamic, to complete the air inlet rea adjusting to air inlet.
Further, the opening area of air admission hole 11 is S1, and the flight resistance that air admission hole 11 is brought is：F1=K1×S1×
V2；Wherein, K1 is proportionality coefficient, and V is air speed, i.e. speed of the unmanned plane machine relative to air；Unmanned plane during flying resistance：L2=0.5
(ρV2 C2S), C2Indicate resistance coefficient；ρ indicates that atmospheric density, S indicate unmanned plane surface area； S1=L2/（KV-K1V2）, wherein
K is normal proportionality coefficient.
It is since the flight thrust and air inflow of unmanned plane are proportional, i.e., proportional with 11 opening area of air admission hole, air speed.It is logical
After crossing setting air-inlet cover 7, the opening area of air admission hole 11 can be adjusted, when air inlet open area minimum, unmanned plane
Flight thrust it is minimum, therefore longer continuation of the journey can be obtained.Air inlet open area can be adjusted according to wind speed, and wind speed can be with
It is measured by pitot 22.
Further, inlet channel is additionally provided in fuselage 1, inlet channel is equipped at least one air inlet by-path section 12 and one
Main channel section 14, air admission hole 11 are the entrance of air inlet by-path section 12, and the outlet of main channel section 14 is corresponding with jet engine 15 to be set
It sets；The main channel is provided with the wind-driven generator 19 for being connected with accumulator.
After wind-driven generator 19 is set in main channel, the wind-force with air speed can be applied to generate electricity, save energy,
Further improve cruising ability.In specific setting, fuselage 1 is provided with rechargable power supplies, and wind motor is to chargeable electricity
Source is charged, and rechargable power supplies are to power supplies such as steering engine, engine, processors.
Further, the main channel section 14 is set there are one side opening 17, and side opening 17 is connected with side road 18, other
Wind-driven generator 19 is equipped in side line 18, the outlet in side road 18 is connected to engine jet pipe 6；The side opening 17 is flexibly connected
It is useful for adjusting the switching door 13 of main channel section 14 and 18 air inflow of side road, switching door 13 is connected with switching driving device, cuts
Driving device is changed to be electrically connected with control unit.
Side road 18 and wind-driven generator 19 are set, inlet guide can be gone to generate electricity.Such as：It, can in descent
To reduce the power of jet engine, while the amount that air enters jet engine and generator is adjusted by switching door 13.
Unmanned plane needs to reduce lift resistance ratio, improves resistance in landing.And in landing, engine continuous reduces power, the need of air
The amount of asking persistently reduces, but needs higher drag；At this time can air admission hole 11 completely open, increase the resistance of landing and sliding, simultaneously will
Air is introduced into side road 18, while absorbing wind energy, extends continuation of the journey.
Further, the rear end of the wing 2 is equipped with wing flap 3, and wing flap 3 is flexibly connected with wing 2, and fuselage 1 is connected with for driving
The wing flap 3 that the motivation wing 2 is overturn drives switching mechanism；It includes the shaft being connect with wing flap 3 that the wing flap 3, which drives switching mechanism, is turned
Axis connection has steering engine 10, steering engine 10 to be electrically connected with control unit.
Wing flap 3 is for lift, the resistance during adjusting unmanned plane during flying；When aircraft is when taking off, wing flap 3 is to the back lower place
Deviation angle is smaller, primarily serves the effect for increasing lift, can accelerate to take off；When aircraft is in landing, wing flap 3 is backward
Lower section offset angle it is larger, can make aircraft lift and resistance simultaneously increase, in favor of reduction landing speed.
Further, the rear end of the wing 2 is additionally provided with aileron 4, and aileron 4 is located at 3 outside of wing flap, and aileron 4 is lived with wing 2
Dynamic connection；The aileron 4 is connected with auxiliary spindle 21, and the shaft 20 is equipped with through-hole, and one end of auxiliary spindle 21 passes through through-hole and rudder
Machine 10 connects.
Steering engine 10 can drive aileron 4, wing flap 3 to rotate simultaneously.In specific setting, steering engine 10 is equipped with output shaft, output shaft
It is drivingly connected respectively with shaft 20, auxiliary spindle 21 by transmission mechanism；Transmission mechanism can be gear drive, belt transmission
Mechanism.
Further, the both sides of 1 tail portion of fuselage are respectively equipped with spoiler 5.
In specific setting, spoiler 5 is flexibly connected with fuselage 1, can be used for adjusting the balance of fuselage 1 and wind turbine falls
When, increase aerodynamic drag.
Further, 2 leading edge of wing is smoothly connected with 11 leading edge of fuselage by circular arc, wherein maximum leading edge sweep is
45.26 °, minimum leading edge sweep is 27.18 °, and 2 trailing sweep of wing is 10 °~12 °.
In specific setting up procedure, 2 trailing edge angle of wing is 10.37 °.The aerofoil profile of wing 2 uses the s aerofoil profiles of EH series, makes
Obtaining Center of Pressure will not be moved forward and backward, and provide stable longitudinal moment, do not have horizontal tail offer so as to improve Flying-wing's unmanned plane
Problem caused by nose-up pitching moment, in 2 aerofoil profile of wing according to the present invention, mainly EH 2,0-12 aerofoil profiles.Aileron 4 is inclined
Corner is 25 °~30 °.
Embodiment 2：Referring to Fig. 6；Difference from Example 1 is：3 wing flap includes main wing flap 31 and flaperon
32, the main wing flap 31 includes main casing, and the open rearward end of main casing, flaperon 32 includes sub-shell, and the front end of sub-shell is logical
It crosses opening and stretches into main casing, the shaft 20 in main casing is connected with main angular wheel 33, and bearing block, bearing are fixed in main casing
Seat is connected with transmission shaft 34 by bearing, and the front end of transmission shaft 34 is connected with the secondary angular wheel engaged with main angular wheel 33
35, the rear end of transmission shaft 34 is equipped with screw thread and is threadedly coupled with sub-shell.Shaft 20 can be turn for driving wing flap to overturn
Axis, or additional setting is used only for driving flaperon 32 and stretches.
Unmanned plane provides lift or resistance in flight course, by wing, and current wing area substantially constant, that is, opens up
String is than fixing；In order to change lift or resistance, flap configurations are used substantially, and lift or resistance are adjusted by changing the angle of wing flap
Power, but since wing flap accounts for the small volume of entire wing, this change is still than relatively limited.The technical program overcomes technology inclined
See, the flap configurations that can be changed using area, that is, use aspect ratio unfixed wing, changes nothing by adjusting aspect ratio
Man-machine lift, resistance；The size of aspect ratio has apparent influence to In-Flight Performance.When aspect ratio increases, wing lures
Leading resistance can reduce, and so as to improve the mobility of aircraft and increase subsonic speed voyage, but wave resistance will increase, so that can shadow
The supersonic flight performance for ringing aircraft, so subsonic aircraft generally selects high aspect ratio wing；And supersonic fighterplane opens up string
Than being typically chosen 2.0~4.0.Such as big voyage, low mobility aircraft --- B-52 bomber aspect ratios are 6.5, U-2 reconnaissance plane exhibitions
String is than 10.6, global hawk unmanned plane aspect ratio 25；Small voyage, highly maneuverable aircraft --- J-8 aspect ratios 2, Su-27 aspect ratios
3.5, F-117 aspect ratios 1.65.
Big aspect ratio can be used when taking off, landing in unmanned plane, and small aspect ratio is used in flight course.Favorably
In raising unmanned plane performance.When adjusting aspect ratio, the extension elongation of flaperon 32 is adjusted, countershaft is such as adjusted by electricity
It is controlled, makes its rotation；Shaft drives transmission shaft 34 to rotate by two angular wheels, and transmission shaft 34 is silk with flaperon 32
Stem nut connection structure, when transmission shaft 34 rotates, flaperon 32 is moved forward and backward along transmission shaft 34.Transmission shaft 34 can be in front and back sets
It sets, it also can be angularly disposed.
Preferably, referring to Fig. 7, fuselage 1 is provided with switch, and the switching for driving switch to be moved relative to fuselage
Driving mechanism, switching-driving device are electrically connected with control unit, and steering engine is connected with shaft, auxiliary spindle driving respectively by switch
It connects, the switch includes intermediate propeller shaft 101, and the steering engine is equipped with output shaft, and output shaft is connected with A driving gears 26 and B
Driving gear 25, shaft are connected with A driven gears 23, and auxiliary spindle is connected with B driven gears 24, and the intermediate propeller shaft 101 connects
Two groups of intermediate gears are connected to, one group of intermediate gear includes A+ intermediate gears 104 and A- intermediate gears 105, another group of intermediate gear
Including B+ intermediate gears 103 and B- intermediate gears 102；Wherein, A driving gears 26 are driven by one group of intermediate gear and A
Gear 23 engages, and B driving gears 25 are engaged by another group of intermediate gear with B driven gears 24, A+ intermediate gears 104 and
B+ intermediate gears 103 are disposed adjacent；When steering engine only controls shaft rotation, switch is moved relative to fuselage, and A driving gears 26 are logical
A- intermediate gears 105 are crossed to connect with A driven gears 23, when steering engine only controls auxiliary spindle rotation, switch is moved relative to fuselage,
B driving gears 25 are connect by B- intermediate gears 102 with B driven gears 24, when servos control shaft and auxiliary spindle rotation,
Switch is moved relative to fuselage, and A driving gears 26 are connect by A+ intermediate gears 104 with A driven gears 23, B driving gears 25
It is connect with B driven gears 24 by B+ intermediate gears 103.
In specific setting, switch is fixed on a sliding block, and fuselage is equipped with and the matched sliding slot of sliding block, and sliding block
It is threaded with lead screw, lead screw is connect with servo motor；Servo motor is electrically connected with control unit；The intermediate propeller shaft of switch
101 can be fixed on by bearing on sliding block, among A- intermediate gears 105, A+ intermediate gears 104, B+ intermediate gears 103 and B-
Gear 102 is in turn secured on intermediate propeller shaft 101, and the spacing of adjacent two intermediate gears is unequal, due to 3 spacing
It differs, therefore when adjusting switch position, it, can be as needed when wing flap and the flank rotation of control unmanned plane may be implemented
It is controlled, can also be separately controlled；And load can be effectively reduced by a servos control simultaneously.Shaft 20 is hollow, auxiliary spindle
21 pass through shaft 20；Effectively save space.
The above content is only the preferred embodiment invented, for those of ordinary skill in the art, the thought of foundation invention,
There will be changes in the specific implementation manner and application range, and the content of the present specification should not be construed as the limitation to invention.
Claims (10)
1. the both sides of a kind of unmanned plane, including fuselage, fuselage are respectively equipped with wing, it is equipped with engine in fuselage, afterbody is set
There are engine jet pipe, engine jet pipe to be connect with engine, the head upper end of the fuselage or/and lower end are equipped with air admission hole,
It is characterized in that：Wherein at least one air admission hole is equipped with air-inlet cover, and air-inlet cover is flexibly connected with fuselage, and fuselage is equipped with for driving
The front end of the dynamic movable driving device of air-inlet cover and the control unit for controlling the driving device, fuselage is equipped with pitot,
Pitot, engine are electrically connected with control unit.
2. unmanned plane according to claim 1, it is characterised in that：The fuselage is equipped with and is matched with the tail portion of air-inlet cover
Guide groove, the driving device is steering engine, and servo driving is connected with pivoted arm, and pivoted arm is connect by connecting rod with air-inlet cover,
In, the both ends of connecting rod are hinged with pivoted arm, air-inlet cover respectively.
3. unmanned plane according to claim 1, it is characterised in that：The opening area of air admission hole is S1, what air admission hole was brought
Flight resistance is：F1=K1×S1×V2；Wherein, K1 is proportionality coefficient, and V is air speed, i.e. speed of the unmanned plane machine relative to air
Degree；Unmanned plane during flying resistance：L2=0.5(ρV2 C2S), C2Indicate resistance coefficient；ρ indicates that atmospheric density, S indicate unmanned plane table
Area； S1=L2/（KV-K1V2）, wherein K is normal proportionality coefficient.
4. unmanned plane according to claim 1, it is characterised in that：Inlet channel is additionally provided in fuselage, inlet channel is equipped with
At least one air inlet by-path section and a main channel section, air admission hole are the entrance of air inlet by-path section, the outlet and spray of main channel section
Gas engine is correspondingly arranged；The main channel is provided with the wind-driven generator for being connected with accumulator.
5. unmanned plane according to claim 4, it is characterised in that：Main channel section sets that there are one side opening, sides
Opening is connected with side road, is equipped with wind-driven generator in side road, the outlet in side road is connected to engine jet pipe；It opens the side
Mouth flexible connection is useful for adjusting the switching door of main channel section and side road air inflow, and switching door is connected with switching driving device,
Switching driving device is electrically connected with control unit.
6. unmanned plane according to claim 1, it is characterised in that：The rear end of the wing is equipped with wing flap, wing flap and wing
Flexible connection, the wing flap that fuselage is connected with for driving wing to overturn drive switching mechanism；The wing flap drives switching mechanism packet
The shaft being connect with wing flap is included, shaft is connected with steering engine, and steering engine is electrically connected with control unit.
7. unmanned plane according to claim 6, it is characterised in that：The rear end of the wing is additionally provided with aileron, and aileron is located at
On the outside of wing flap, aileron is flexibly connected with wing；The aileron is connected with auxiliary spindle, and the shaft is equipped with through-hole, and the one of auxiliary spindle
End is connect across through-hole with steering engine.
8. unmanned plane according to claim 1, it is characterised in that：The leading edge of a wing is smoothly connected with 1 leading edge of fuselage by circular arc
Connect, wherein maximum leading edge sweep be 45.26 °, minimum leading edge sweep be 27.18 °, trailing edge angle of sweep be 10 °~
12°。
9. unmanned plane according to claim 1, it is characterised in that：The wing flap includes main wing flap and flaperon, the master
Wing flap includes main casing, and the open rearward end of main casing, flaperon includes sub-shell, and main casing is stretched into the front end of sub-shell by opening
Body, the shaft in main casing are connected with main angular wheel, bearing block are fixed in main casing, bearing block is connected with biography by bearing
Moving axis, the front end of transmission shaft are connected with the secondary angular wheel engaged with main angular wheel, the rear end of transmission shaft be equipped with screw thread and with
Sub-shell is threadedly coupled.
10. unmanned plane according to claim 7, it is characterised in that：Fuselage is provided with switch, and for driving switching
The switching-driving device that device is moved relative to fuselage, switching-driving device are electrically connected with control unit, and steering engine is distinguished by switch
It is drivingly connected with shaft, auxiliary spindle, the switch includes intermediate propeller shaft, and the steering engine is equipped with output shaft, exports axis connection
There are A driving gears and B driving gears, shaft to be connected with A driven gears, auxiliary spindle is connected with B driven gears, the intermediate transmission
It includes A+ intermediate gears and A- intermediate gears, another group of intermediate gear packet that axis connection, which has two groups of intermediate gears, one group of intermediate gear,
Include B+ intermediate gears and B- intermediate gears；Wherein, A driving gears are engaged by one group of intermediate gear with A driven gears, B
Driving gear is engaged by another group of intermediate gear with B driven gears, and A+ intermediate gears are disposed adjacent with B+ intermediate gears；
When steering engine only controls shaft rotation, switch is moved relative to fuselage, and A driving gears pass through A- intermediate gears and A driven gears
Connection, when steering engine only controls auxiliary spindle rotation, switch is moved with respect to fuselage, B driving gears by B- intermediate gears and B from
Moving gear connects, and when servos control shaft and auxiliary spindle rotation, switch is moved relative to fuselage, and A driving gears pass through A+
Intermediate gear is connect with A driven gears, and B driving gears are connect by B+ intermediate gears with B driven gears.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810190385.0A CN108275273B (en) | 2018-03-08 | 2018-03-08 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810190385.0A CN108275273B (en) | 2018-03-08 | 2018-03-08 | Unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108275273A true CN108275273A (en) | 2018-07-13 |
| CN108275273B CN108275273B (en) | 2024-04-02 |
Family
ID=62809306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810190385.0A Active CN108275273B (en) | 2018-03-08 | 2018-03-08 | Unmanned plane |
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Cited By (1)
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| Publication number | Publication date |
|---|---|
| CN108275273B (en) | 2024-04-02 |
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