CN108263604A - A kind of semi-ring rotor aircraft - Google Patents
A kind of semi-ring rotor aircraft Download PDFInfo
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- CN108263604A CN108263604A CN201810085500.8A CN201810085500A CN108263604A CN 108263604 A CN108263604 A CN 108263604A CN 201810085500 A CN201810085500 A CN 201810085500A CN 108263604 A CN108263604 A CN 108263604A
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- 238000004080 punching Methods 0.000 claims description 3
- 239000000446 fuel Substances 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 230000007423 decrease Effects 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 241000566150 Pandion haliaetus Species 0.000 description 1
- 241000607479 Yersinia pestis Species 0.000 description 1
- 239000003905 agrochemical Substances 0.000 description 1
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- 239000002917 insecticide Substances 0.000 description 1
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- 230000035939 shock Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention discloses a kind of semi-ring rotor aircraft, including propeller, fuselage and the semi-ring wing being connect with fuselage, the propeller controls flight attitude by controller, the semi-ring wing is mounted on fuselage both sides, the propeller is installed on by rotating device correspondence above the semi-ring wing, the controller controls propeller angle by rotating device, so as to control flight attitude, Flight Vehicle Structure provided by the invention is simple, the lift that the semi-ring wing generates is far longer than the lift of helicopter wing, it is big that this aircraft is provided simultaneously with loading capacity, flying speed is fast, voyage is remote, noise is small, the features such as low energy consumption, present invention eliminates traditional ailerons, empennage, structure is simpler, posture is more flexible, improve operational efficiency.
Description
Technical field
The present invention relates to a kind of aircraft, and in particular to a kind of semi-ring rotor aircraft.
Background technology
Aircraft is that one kind can be in endoatmosphere or exoatmosphere space（Space）The instrument of flight, aircraft mainly wrap
Include rotor class and fixed-wing class, common such as helicopter and fixed wing aircraft and multi-rotor aerocraft.
Helicopter because can VTOL, to landing condition, especially runway requirement is very low, thus is answered extensively
With, such as sightseeing tour, fire rescue, first aid at sea, anti-smuggling drug law enforcement, fire-fighting, transit commercial, medical rescue, communication and spray
Spill each department that agricultural chemical insecticide eliminates the national economy such as pest, detection resource.But helicopter shortcoming is it is also obvious that for example
Loading capacity is small, and practical ceiling is low, and particularly speed is low, thus also limits its use scope.
Fixed wing aircraft occurs earlier than helicopter, and because its loading capacity is big, cruising ability is strong, and practical ceiling is high, and safety is relaxed
The series of advantages such as suitable and be largely used in the fields such as transport, observation, military affairs, but its is expensive, airport requirements height etc. is lacked
Point is also apparent from.
Multi-rotor aerocraft is a kind of aircraft occurred in recent years, be mostly quadrotor, six rotors or eight rotors nobody fly
Row device, with compact, convenient, the simple in structure, good mechanical stability of manipulation, the very high feature of of low cost, cost performance, but because
Its loading capacity is smaller, and airborne period is short, therefore is used in a small number of fields such as toy, model plane, agricultural.
Also occurred a kind of channel wing in aviation history（Half ring wing）Aircraft possesses a kind of appearance
For semi-circular, annular wing half is equivalent to, the wing for the aircraft both sides that are placed in, this wing possesses good lift, short distance
Clearly, but for various reasons, there is no large-scale promotion uses for the aircraft of this semi-ring wing wing for landing advantage.
Recently as the rise of U.S. V22 osprey tiltrotors, each state all strengthen tiltrotor research,
V22 had not only had the ability of pure helicopter VTOL and hovering, but also there is the high speed cruise flight of fixed wing aircraft
Ability, advantage be suitable it will be evident that still V22 the shortcomings that it is also quite apparent, complicated, maintenance cost is high, and wing load is high, hangs down
It has more than needed and is short of power during straight landing, lead to Frequent Troubles.
Invention content
For the deficiency of all kinds of aircraft of background technology, the present invention has researched and developed a kind of simple in structure, and wing load is low, moves
Power it is abundant can be with vertical short landing semi-ring rotor aircraft.
The technical solution of the present invention：
A kind of semi-ring rotor aircraft passes through controller including propeller, fuselage and the semi-ring wing being connect with fuselage, the propeller
Control flight attitude, it is characterised in that：The semi-ring wing is mounted on fuselage both sides, and the propeller is corresponded to by rotating device pacifies
Loaded on above the semi-ring wing, the controller controls propeller angle by rotating device, so as to control flight attitude.
The rotating device slewing area is 0 to 180 degree.
The controller includes shaft coupling, deceleration group and deceleration group mounting base, and shaft coupling is connect with rotating device, and is passed through
Deceleration group is mounted in deceleration group mounting base.
The propeller is piston aviation engine, gas-turbine unit or punching engine.
The rotating device is the shaft of hollow structure, and promising propeller is set to provide the oil circuit or electricity of power in shaft
Road, one section of connection propeller, other end connection fuselage fuel cell or power supply.
The semi-ring wing has four sets, is symmetrically mounted on fuselage both sides.
The propeller is piston aviation engine, and airscrew diameter is more than semi-ring wing width.
Beneficial effects of the present invention：
The present invention is had the following advantages that by the way that the semi-ring wing and the impeller design that can be adjusted the angle are combined：
1. speed is fast, helicopter by the shock stall of rotor advancing blade and the separation of retreating blade air-flow because being limited, limit speed
Spend low, and when this aircraft puts down winged is identical with tandem fixed-wing, and flying speed is faster；
2. noise is small, tiltrotor during cruise in a manner of Fixed Wing AirVehicle because generally being flown, therefore noise compares helicopter
It is much smaller；
3. voyage is remote, tiltrotor during cruise in a manner of Fixed Wing AirVehicle because generally being flown, therefore voyage compares helicopter
It is much farther away；
4. loading capacity is big, compare helicopter and v22, and more rotors have more actuating units, can provide the lift of bigger,
Therefore loading capacity bigger；
5. low energy consumption, for the present invention in cruising flight, the lift that the semi-ring wing generates is far longer than the lift of helicopter wing, and revolves
Wing rotating speed is relatively low, so energy consumption is lower than helicopter；
6. posture is flexible, traditional aileron, empennage are eliminated, the theory of gesture stability and novel multi-rotor aerocraft is similar
Seemingly, complete gesture stability circuit is formed by differential control, structure is simpler, and posture is more flexible, reduces windage, improves
Operational efficiency.
Description of the drawings
Fig. 1:Principle schematic diagram of the present invention.
Fig. 2:Controller architecture principle schematic of the present invention.
Fig. 3:Principle schematic diagram when rotating device of the present invention is 0 °.
Fig. 4:Principle schematic diagram when rotating device of the present invention is 90 °.
Fig. 5:Principle schematic diagram when rotating device of the present invention is 180 °.
Fig. 6:Flying vehicles control principle schematic of the present invention.
Fig. 7:Flying vehicles control circuit diagram of the present invention.
Wherein：Rotating device, the 3 semi-ring wings, 3- after rotating device, 2-2 before 1 fuselage, 2 rotating devices, 2-1
The semi-ring wing, 4 propellers, 4-1 behind the semi-ring wing, the left back semi-ring wings of 3-3, the 3-4 right sides before the 1 left front semi-ring wing, the 3-2 right sides
Behind the right forward propeller of left front propeller, 4-2, the left back propellers of 4-3, the 4-4 right sides before propeller, 5 shaft couplings, 5-1
After shaft coupling, 5-2 after shaft coupling, 6 deceleration groups, 6-1 front reduction gears group, 6-2 before deceleration group, 7 deceleration group mounting bases, 7-1
10 pilot controller of deceleration group mounting base 8 transmitter, 9 receiver, 11 fixed-wing flies to control after deceleration group mounting base, 7-2
Module rotor more than 12 flies to control 13 angular transducer of module, 14 8 tunnel linkage single pole double throw analog switch.
Specific embodiment
The present invention is described further with reference to the accompanying drawings and examples：
As shown in Fig. 1 to 7, a kind of semi-ring rotor aircraft is described including propeller 4, fuselage 1 and the semi-ring wing 3 being connect with fuselage
Propeller 4 controls flight attitude by controller, and the semi-ring wing 3 is mounted on 1 both sides of fuselage, and the propeller 4 passes through rotation
The correspondence of device 2 is installed on 3 top of the semi-ring wing, and 2 slewing area of rotating device is 0 to 180 degree, during the rotating device 2 is
The shaft of hollow structure, energy are supplied to propeller 4 by the oil circuit or circuit that are set in shaft, and the controller passes through rotating dress
2 control propeller, 4 angle is put, so as to control flight attitude, the controller includes shaft coupling 5, deceleration group 6 and the installation of deceleration group
Seat 7, shaft coupling 5 is connect with rotating device 2, and passes through deceleration group 6 in deceleration group mounting base 7.
The semi-ring wing 3 is equipped with four sets, is symmetrically mounted on 1 both sides of fuselage.
The propeller 4 is piston aviation engine, gas-turbine unit or punching engine, and propeller 4 is lives
During plug aero-engine, 3 width of the semi-ring wing is less than piston aviation engine airscrew diameter.
When rotating device is 0 °, aircraft flies control pattern for fixed-wing, and when rotating device is 90 °, aircraft is more rotations
The wing flies control pattern.
The present invention controls the state of flight of aircraft by control system, and control system includes transmitter 8, receiver 9, auxiliary
Help controller 10,13 and 8 tunnel of angular transducer linkage single pole double throw analog switch 14, the pilot controller 10,9 and of receiver
Angular transducer 13 is located inside fuselage 1, and the transmitter 8 is located at ground, the transmitter 8 and receiver 9 by 2.4G without
Wire module communicates, and control operational order sends receiver 9 to by transmitter 8, and the receiver 9 flies to control module with fixed-wing
11st, more rotors, which fly to control module 12, connects, and more rotors, which fly to control module 12 and pass through 8 tunnels, to link the logical of single pole double throw analog switch 14
Road is connect with propeller 4, and the fixed-wing flies control module 11 and connect with 8 tunnels linkage single pole double throw analog switch 12, the auxiliary
Controller 11 is connect respectively with 8 tunnels linkage single pole double throw analog switch 14, angular transducer 13, deceleration group 6, receiver 9, described
Angular transducer 13 is connect with deceleration group 6.
The manual operation instruction of aircraft driver switchs to wireless analog signals by transmitter 8, and receiver 9 connects
It receives analog signals and is converted to pwm signals and more rotors are transmitted to by signal wire fly to control module 12, fixed-wing and fly to control 11 and of module
Pilot controller, pilot controller 10 according to 9 signal of receiver, the channel selecting of 8 road single pole double throw analogs switch 14 of control and
The control of deceleration group 6, angular rate signal are transferred to pilot controller 13, and pilot controller 10 determines 8 according to the angle of setting
Road single pole double throw analog switchs 14 channel selectings, so as to complete the switching that more rotors fly control pattern and fixed-wing flies control pattern.
Such as：When taking off vertically, the default setting is more rotors to fly control pattern, flies 8 throttle of hand push transmitter and exports long-range mould
Analog quantity signal, receiver 9 become pwm signal after receiving analog signals, and two-way flies to control while be connected to the increased signal of throttle,
Because acquiescence flies control pattern in more rotors, only more rotors fly control output control signal and access to propeller 4, propeller 4
According to winged control instruction works, winged control is set as posture from steady, and aircraft vertical takes off.But fly hand and dial offline mode switching push button
When, for signal by transmitter 8 to receiver 9 to pilot controller 10, pilot controller 10 is connected to adjustment deceleration group 6 after signal,
The angle of inclination of propeller 4 starts to change, and still flying control module 12 by more rotor modes at this time controls posture, for no other reason than that pulling force
The variation aircraft of angle flies before starting, and more rotors fly to control the adjusting throttle holding present level of module 12, and angular transducer 13 is negative
Duty detection angle change, when angle reaches setting value, 8 road single pole double throw analog switch 14 of the control of pilot controller 10 is cut
Channel is changed, fixed-wing pattern flies the control signal access propeller 4 of control, and aircraft is according to fixed-wing mode flight at this time.
Embodiment 1：It takes off
First, sliding race pattern
It is taken off on runway using undercarriage, 2 angle of rotating device is located at 0 ° of position at this time, and propeller 4 generates backward
Thrust, when the semi-ring wing 3 is equipped with four sets of 2 row, control front row propeller（4-1、4-2）Power be more than heel row propeller（4-3、
4-4）Power, the corresponding front row semi-ring wing（3-1、3-2）The lift of generation is more than the heel row semi-ring wing（3-3、3-4）Lift,
So as to produce a nose-up pitching moment, aircraft is liftoff, as vehicle flight speeds gradually rise, adjusts front-seat propeller
（4-1、4-2）Power be less than heel row propeller（4-3、4-4）Power, the corresponding front row semi-ring wing（3-1、3-2）It generates
Lift is less than the heel row semi-ring wing（3-3、3-4）Lift, so as to produce a nose-down pitching moment, by the posture leveling of aircraft,
Hence into flat winged state.
When the semi-ring wing 3 is equipped with 1 row 2, the power that propeller 4 generates gradually increases, the liter that the corresponding semi-ring wing 3 generates
Power also gradually increases, and when lift increases to greater than the gravity of fuselage, aircraft is liftoff to take off, in the air by adjusting propeller 4
2 degree of power and rotating dress angle setting adjust flight attitude.
2nd, short takeoff
2 angle of rotating device is adjusted by controller, usually between 0 ° to 90 °, the thrust that propeller 4 generates at this time is after tiltedly
Lower section, thrust can be decomposed into backward, the power of downward both direction, aircraft is sliding forwards to be run, when upward power and the semi-ring wing 3
When the sum of lift of generation is more than aircraft weight, aircraft is liftoff to take off, this 2 angle of pattern rotating device is sliding closer to 90 °
Row distance is shorter.
3rd, it takes off vertically
2 angle of rotating device is adjusted by controller, rotating device 2 is in 90 ° of positions at this time, and the thrust that propeller 4 generates is hung down
Vertical pulling rises fuselage, when thrust is more than aircraft weight, aircraft takeoff.
Embodiment 2：Aerial statue
First, it hovers
2 angle of rotating device is adjusted by controller, rotating device 2 is in 90 ° of positions at this time, and the thrust that propeller 4 generates is hung down
Straight downward, when controlling thrust identical with aircraft weight, aircraft is in floating state.
2nd, aerial somersault
When hovering posture, by increasing propeller on the left of aircraft（4-1、4-3）Thrust, while reduce right-side propellers（4-
2、4-4）Thrust, it is on the contrary then generate to the left because the differential force of aircraft both sides generates a yawing to the right to aircraft
Yawing, can also front and rear somersaults.
3rd, normal flight
Identical with takeoff, 2 angle of rotating device of aircraft is located at 0 ° of position, and propeller 4 generates thrust backward, at this time
Aircraft is in flat winged state, regulates the speed by adjusting 4 power size of aircraft propellers.
4th, it flies at low speed
1. identical with normal flight pattern, realized by reducing by 4 power of propeller, because 3 lift of the semi-ring wing it is big the characteristics of, at this time
Aircraft can keep relatively low speed；
2. by controller adjust 2 angle of rotating device, usually between 0 ° to 90 °, then by control 4 thrust of propeller come
Realize the low-speed operations of aircraft.
5th, inverted flight
2 angle of rotating device is adjusted by controller, usually between 90 ° to 180 °, the thrust that propeller 4 generates at this time is to oblique
Front, thrust can be decomposed into the power of both direction back, up, then realize aircraft by controlling 4 thrust of propeller
It flies backward.
Embodiment 3：Landing
First, vertical landing
By adjusting 2 angle of rotating device, rotating device 2 is in 90 ° of positions at this time, the thrust that propeller 4 generates vertically downward,
By reducing thrust, thrust is made gradually to be less than aircraft weight, realizes aircraft vertical landing.
2nd, short distance lands
2 angle of rotating device is adjusted by controller, usually between 0 ° to 90 °, the thrust that propeller 4 generates at this time is after tiltedly
Side, thrust can be decomposed into forward, the power of upward both direction, then continuously decrease 4 thrust of propeller, realize aircraft short distance
It lands.
3rd, it is sliding to run landing
2 angle of rotating device is located at 0 ° of position at this time, and propeller 4 generates thrust backward, continuously decreases the power of propeller 4,
The lift of the semi-ring wing is also gradually reduced, and when lift is less than fuselage gravity, aircraft is begun to decline, and undercarriage is opened, after landing
Propeller is closed, is run using undercarriage is sliding on runway, speed is continuously decreased until stopping.
Except above-described embodiment, this aircraft can also be by controlling propeller power and inclination angle to realize other many attitudes.
To sum up, the present invention accomplishes the end in view.
Claims (7)
1. a kind of semi-ring rotor aircraft passes through control including propeller, fuselage and the semi-ring wing being connect with fuselage, the propeller
Device controls flight attitude, it is characterised in that：The semi-ring wing is mounted on fuselage both sides, and the propeller is corresponded to by rotating device
It is installed on above the semi-ring wing, the aircraft further includes controller, and propeller angle is controlled by rotating device, winged so as to control
Row posture.
2. semi-ring rotor aircraft as described in claim 1, it is characterised in that：The rotating device slewing area is 0 to 180
Degree.
3. semi-ring rotor aircraft as described in claim 1, it is characterised in that：The controller include shaft coupling, deceleration group and
Deceleration group mounting base, shaft coupling are connect with rotating device, and pass through deceleration group in deceleration group mounting base.
4. semi-ring rotor aircraft as described in claim 1, it is characterised in that：The propeller is piston aviation engine,
Gas-turbine unit or punching engine.
5. semi-ring rotor aircraft as claimed in claim 1 or 2, it is characterised in that：The rotating device turns for hollow structure
Axis sets in shaft promising propeller to provide the oil circuit or circuit of power, one section of connection propeller, other end connection fuselage fuel cell
Or power supply.
6. semi-ring rotor aircraft as claimed in claim 1 or 2, it is characterised in that：The semi-ring wing is equipped with four sets, is symmetrically installed
In fuselage both sides.
7. semi-ring rotor aircraft as claimed in claim 4, it is characterised in that：The propeller is piston aviation engine,
Its airscrew diameter is more than semi-ring wing width.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810085500.8A CN108263604A (en) | 2018-01-29 | 2018-01-29 | A kind of semi-ring rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810085500.8A CN108263604A (en) | 2018-01-29 | 2018-01-29 | A kind of semi-ring rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108263604A true CN108263604A (en) | 2018-07-10 |
Family
ID=62776962
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810085500.8A Withdrawn CN108263604A (en) | 2018-01-29 | 2018-01-29 | A kind of semi-ring rotor aircraft |
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| Country | Link |
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| CN (1) | CN108263604A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109335004A (en) * | 2018-11-30 | 2019-02-15 | 福建星图智控科技有限公司 | A kind of miniature drone configuring hybrid power |
-
2018
- 2018-01-29 CN CN201810085500.8A patent/CN108263604A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109335004A (en) * | 2018-11-30 | 2019-02-15 | 福建星图智控科技有限公司 | A kind of miniature drone configuring hybrid power |
| CN109335004B (en) * | 2018-11-30 | 2024-04-26 | 福建星图智控科技有限公司 | Micro unmanned aerial vehicle equipped with hybrid power |
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Application publication date: 20180710 |