CN110254700A - The flight control method of aircraft and the flight system of application this method - Google Patents
The flight control method of aircraft and the flight system of application this method Download PDFInfo
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- CN110254700A CN110254700A CN201910518654.6A CN201910518654A CN110254700A CN 110254700 A CN110254700 A CN 110254700A CN 201910518654 A CN201910518654 A CN 201910518654A CN 110254700 A CN110254700 A CN 110254700A
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- Prior art keywords
- aircraft
- mounting
- propeller
- ring
- mounting ring
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- 238000000034 method Methods 0.000 title claims abstract description 13
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 8
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000010899 nucleation Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000009331 sowing Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of flight control method of aircraft and the flight systems of application this method, it applies in aircraft field, its key points of the technical solution are that: including the mounting rod being set at the top of aircraft and the mounting ring being connected on mounting rod, mounting ring is equipped with driving device；Driving device: including several mounting plates being slidably connected in mounting ring, mounting plate is equipped with first motor, propeller is connected on the output end of first motor, tooth form runway is equipped on the inside of mounting ring, mounting plate is equipped with the second motor, is connected with the tooth of running being meshed with tooth form runway on the output end of the second motor；Have when having the technical effect that the damage of one of propeller, remaining propeller still can provide the lifting force of balance to aircraft, avoid because the propeller shape of normal work at lifting force it is uneven due to lead to the possibility of the unbalance crash of aircraft.
Description
Technical field
The present invention relates to aircraft field, in particular to the flight control method of a kind of aircraft and application this method
Flight system.
Background technique
Aircraft be by mankind's manufacture, can fly away from ground, space flight and controlled by people in endoatmosphere or big
The instrument flying object of the gas-bearing formation external space (space) flight.
Notification number is that the Chinese patent of CN206710862U discloses a kind of agricultural sowing unmanned plane based on GPS,
Including unmanned plane and seeding apparatus, unmanned plane includes unmanned body, the rotor that is fixed on the machine body, motor and is arranged in body
Under undercarriage, which is characterized in that seeding apparatus is located in unmanned plane body, and seeding apparatus includes seed granary, feed pipe, vertical
Defeated kind of conduit, switch valve, horizontal flow device, seed counter, sowing nozzle, microprocessor and power supply, microprocessor are connected with ground
Manage location information acquisition device and wireless communication device.
But as long as the one of damage of the rotor of this unmanned plane or stopping working, just to the lifting force of unmanned plane
Unevenly, thus entire unmanned plane all can be unbalance and from falling in the air, cause unmanned plane to be damaged.
Summary of the invention
The object of the present invention is to provide a kind of flight control methods of aircraft, its advantage is that: one of propeller damage
Bad when, still can provide the lifting force of balance to aircraft, avoid propeller shape because of normal work at lifting force it is uneven
Possibility that is even and leading to the unbalance crash of aircraft.
Above-mentioned technical purpose of the invention has the technical scheme that a kind of flight control of aircraft
Method comprising the steps of: step 1: n propeller, n >=3, between two adjacent propellers are set on board the aircraft
Angle is set as 360 °/n；Step 2: it if one of propeller stops working, adjusts between the propeller that remaining is worked normally
Angle, at this time the angle between the propeller of two neighboring normal work be set as 360 °/(n-1).
Through the above technical solutions, angle when all propellers work normally, between two adjacent propellers
It is set as 360 °/n, therefore the lifting force of balance can be provided to aircraft；When one of propeller is because of failure or other originals
When cause stops working, remaining propeller worked normally meeting adjust automatically respective positions, until two neighboring normal work
Angle between propeller be set as 360 °/(n-1), the propeller of all normal works can provide aircraft flat again at this time
The lifting force of weighing apparatus, avoid because the propeller shape of normal work at lifting force it is uneven due to lead to the unbalance crash of aircraft can
Can, improve the flight safety of aircraft.
The present invention is further arranged to: further including step 3: if wherein m propeller stops working, it is normal to adjust remaining
Angle between the propeller of work, the angle between the propeller of two neighboring normal work is set as 360 °/(n- at this time
M).
Through the above technical solutions, when wherein m propeller stops working because of failure or other reasons, remaining normal work
The propeller meeting adjust automatically respective positions of work, until the angle between the propeller of two neighboring normal work is set as
360 °/(n-m), the propeller of all normal works can provide the lifting force of balance to aircraft again at this time, avoid because normal
The propeller shape of work at lifting force it is uneven and lead to the possibility of the unbalance crash of aircraft, improve the flight peace of aircraft
Quan Xing.
It is a further object to provide a kind of flight systems of aircraft, including the peace being set at the top of aircraft
Dress bar and the mounting ring being connected on mounting rod, the mounting ring are equipped with driving device；Driving device: including being slidably connected
Several mounting plates in mounting ring, the mounting plate are equipped with first motor, are connected on the output end of the first motor
Propeller, the mounting ring inside are equipped with tooth form runway, and the mounting plate is equipped with the second motor, the output of second motor
The tooth of running being meshed with tooth form runway is connected on end.
Through the above technical solutions, operator controls first motor work, at this time each spiral when aircraft needs to circle in the air
Paddle rotation, forms upward lifting force and drives aircraft flight；When one of propeller stops working, each second electricity
Machine work, tooth of running at this time is run on tooth form runway, so that drive installation plate is run in mounting ring, when each normal work
Propeller be moved to designated position, i.e., when the angle between the propeller of two neighboring normal work is identical, each propeller
The lifting force of balance can be formed again, to drive aircraft flight, crashed to prevent aircraft because of lifting force imbalance.
The present invention is further arranged to: the mounting rod and mounting ring are coaxially disposed, if passing through involvement on the mounting rod
Extension bar is connected on the inner sidewall of mounting ring.
Through the above technical solutions, connecting rod can reinforce the connective stability between mounting rod and mounting ring, and have
Conducive to the circularity for keeping mounting ring, the possibility of mounting ring stress deformation is reduced, to be conducive to propeller accurately with mounting rod axis
Line is center line etc. point distribution, promotes the balanced capacity of aircraft.
The present invention is further arranged to: the mounting plate is equipped with balancing pole, the one end of the balancing pole far from mounting plate
Equipped with lantern ring, the lantern ring is arranged on the securing lever.
Through the above technical solutions, mounting plate is connected by balancing pole with mounting rod, and balancing pole passes through lantern ring and installation
Rod set connects, so that mounting plate can be rotated around the central axes of mounting rod always when moving, improves the rotation essence of mounting plate
Degree, and balancing pole can play a supporting role to mounting plate, be deformed and block after reducing the use of mounting plate long-time
Possibility extremely in mounting ring improves the relative stability between mounting plate and mounting ring.
The present invention is further arranged to: the locating rod peripherally offers annular groove, and the lantern ring is set in annular groove.
Through the above technical solutions, lantern ring rotates in annular groove, annular groove can play a position-limiting action to lantern ring at this time,
So that lantern ring and balancing pole can be more accurate around the rotation of the central axes of mounting rod.
The present invention is further arranged to: the two sides up and down of the mounting ring are equipped with one group of driving device.
Through the above technical solutions, to the lifting dynamics of aircraft when two groups of driving devices can increase propeller rotational,
And when wherein one group of driving device stops working because of failure, another group of driving device still can keep aircraft just
Often flight reduces the possibility that aircraft crashes.
The present invention is further arranged to: the outer peripheral edge of the mounting ring is recessed inwardly to form limiting slot, the mounting plate
Inner wall is matched with limiting slot.
Through the above technical solutions, limiting slot can cooperate with mounting plate, and at this time since limiting slot is recessed inwardly, peace
Loading board is equivalent to be interlocked with mounting ring, so as to reduce the possibility that mounting plate and mounting ring are separated.
In conclusion the invention has the following advantages:
1, when one of propeller stops working because of failure or other reasons, remaining propeller worked normally can be adjusted automatically
Whole respective positions, to provide the lifting force of balance to aircraft, avoid propeller shape because of normal work at lifting force not
The possibility for uniformly leading to the unbalance crash of aircraft, improves the flight safety of aircraft；
2, to the lifting dynamics of aircraft when two groups of driving devices can increase propeller rotational, and ought wherein one group of driving dress
It sets when stopping working because of failure, another group of driving device still can keep the normal flight of aircraft, reduce aircraft pendant
The possibility ruined.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the present embodiment.
Fig. 2 is the structural schematic diagram that the present embodiment is used to embody tooth of running.
Fig. 3 is the structural schematic diagram that the present embodiment is used to embody annular groove and lantern ring.
Appended drawing reference: 1, mounting rod；2, mounting ring；3, driving device；31, mounting plate；32, first motor；33, spiral
Paddle；34, tooth form runway；35, the second motor；36, it runs tooth；4, connecting rod；5, balancing pole；6, lantern ring；7, annular groove；8, it limits
Slot.
Specific embodiment
Below in conjunction with attached drawing, invention is further described in detail.
Embodiment: the flight system of aircraft, such as Fig. 1, including mounting rod 1 and the coaxial sleeve being set at the top of aircraft
The mounting ring 2 being located on mounting rod 1, fixed there are four connecting rod 4 on mounting rod 1, the one end of connecting rod 4 far from mounting rod 1 is equal
It is fixed on the inner sidewall of mounting ring 2, equal point of four connecting rods 4 is arranged on mounting rod 1, thus uniform and stable by mounting ring
2 and mounting rod 1 connect.
Such as Fig. 1, the outer peripheral edge of mounting ring 2 is recessed inwardly to form the limiting slot 8 of V-arrangement, and the two sides up and down of mounting ring 2 are equipped with
One group of driving device 3, driving device 3 include three mounting plates 31, first motor 32 and the spiral being slidably connected in mounting ring 2
Paddle 33, mounting plate 31 is Z-shape to be connected in mounting ring 2 and matches with limiting slot 8, at this time since limiting slot 8 is recessed inwardly, because
This mounting plate 31 is equivalent to be interlocked with mounting ring 2, so as to reduce the possibility that mounting plate 31 and mounting ring 2 are separated, and
And mounting plate 31 can slide in mounting ring 2.First motor 32 is installed in the one end of mounting plate 31 far from mounting rod 1, spiral
Paddle 33 is connected on the output end of first motor 32, when first motor 32 works, propeller 33 can be driven to rotate, thus to flying
Row device generates a lifting force.
Such as Fig. 1 and Fig. 2, mounting plate 31 is fixedly connected with the second motor 35 close to one end of mounting rod 1, the second motor 35
Output end extends to the inside of mounting ring 2, tooth 36 of running, the inner sidewall of mounting ring 2 are connected on the output end of the second motor 35
It is equipped with tooth form runway 34, tooth 36 is run and tooth form runway 34 is meshed, therefore when the second motor 35 works, can be driven entire
Mounting plate 31 is slided along mounting ring 2, and by the driving of each second motor 35, each propeller 33 can be flexibly distributed
The lifting force of relative equilibrium is provided on each point of mounting ring 2, and then to aircraft.
Such as Fig. 1 and Fig. 3, be designed with a balancing pole 5 on each mounting plate 31, balancing pole 5 be obliquely installed and with mounting rod 1
Between form three-legged structure, balancing pole 5 is installed with lantern ring 6 far from one end of mounting plate 31, and the both ends of positioning ring offer one
Group annular groove 7, there are three every group of annular groove 7 is set, the lantern ring 6 on three balancing poles 5 in upper and lower two groups of driving devices 3 is respectively sleeved at
In two groups of three annular grooves 7, annular groove 7 can form a limit to lantern ring 6 at this time, and balancing pole 5 then can be to mounting plate 31
Play a supporting role, thus mounting plate 31 in mounting ring 2 when moving, can be always around the central axes of mounting rod 1
Rotation, to improve the rotation precision of mounting plate 31.
Working principle: mounting ring 2 is divided into several Along ents, the present embodiment is set as 12 Along ents, initially
When state, one group of three propeller 33 being located above are successively set on first, the 5th and the 9th point, and underlying one
Three propellers 33 of group are then successively set on third, the 7th and the 11st point, and each 33 equal part of propeller is distributed at this time
In mounting ring 2, and the angle between every group of adjacent two propeller 33 is 120 °.When work, propeller 33 can be with single group work
Make, double can also organize work, the lifting force of a balance can be played to aircraft.
When 33 single group of propeller works, if one of propeller 33 damages or stops working, such as on first point
Propeller 33 damages, at this time can be there are two types of operation scheme:
One, the second motor 35 works, this is organized remaining two propellers 33 and is respectively driven to the 4th and the tenth point, this
When two neighboring normal work propeller 33 between angle be 180 °, still maintain respectively, therefore still can be to flight
Device plays the lifting force of a balance, to guarantee the normal flight of aircraft, reduces the possibility of the unbalance crash of aircraft.
Two, the second motor 35 works, by another group of idle one of propeller 33 driving to first point simultaneously
Work, to carry out cover to the propeller 33 of damage, the angle between the propeller 33 of two neighboring normal work is at this time
It 120 °, still maintains respectively, therefore still can play the lifting force of a balance to aircraft, to guarantee the normal of aircraft
Flight reduces the possibility of the unbalance crash of aircraft.
When 33 pairs of group work of propeller, if one of propeller 33 damages or stops working, such as on first point
Propeller 33 damages, at this time can be there are two types of operation scheme:
One, the propeller 33 on the 7th point stops working, at this time on third, the five, the 9th and the 11st point
Propeller 33 is respectively moved on the four, the seven, the tenth and first point, adjacent in the propeller 33 of four normal works at this time
Angle between two propellers 33 is 90 °, can play the lifting force of a balance, to aircraft still to guarantee aircraft
Normal flight, reduce the unbalance crash of aircraft possibility.
Two, five remaining propellers 33 worked normally are mobile simultaneously, and are located on five Along ents of mounting ring 2,
The angle in the propeller 33 of five normal works between two neighboring propeller 33 is 72 ° at this time, still can be to aircraft
The lifting force of a balance is played, to guarantee the normal flight of aircraft, reduces the possibility of the unbalance crash of aircraft.
This specific embodiment is only explanation of the invention, is not limitation of the present invention, those skilled in the art
Member can according to need the modification that not creative contribution is made to the present embodiment after reading this specification, but as long as at this
All by the protection of Patent Law in the scope of the claims of invention.
Claims (8)
1. a kind of flight control method of aircraft, it is characterised in that comprise the steps of:
Step 1: being arranged n propeller, n >=3 on board the aircraft, the angle between two adjacent propellers be set as 360 °/
n；
Step 2: if one of propeller stops working, the angle between the propeller of remaining normal work, this phase are adjusted
Angle between the propellers of adjacent two normal works be set as 360 °/(n-1).
2. the flight control method of aircraft according to claim 1, which is characterized in that further include step 3: if wherein m
A propeller stops working, and adjusts the angle between the propeller of remaining normal work, at this time the spiral shell of two neighboring normal work
Rotation paddle between angle be set as 360 °/(n-m).
3. a kind of flight system of aircraft, it is characterised in that: including the mounting rod (1) being set at the top of aircraft and connection
Mounting ring (2) on mounting rod (1), the mounting ring (2) are equipped with driving device (3)；
Driving device (3): it including several mounting plates (31) being slidably connected on mounting ring (2), is set on the mounting plate (31)
Have first motor (32), be connected with propeller (33) on the output end of the first motor (32), is set on the inside of the mounting ring (2)
Have tooth form runway (34), the mounting plate (31) is equipped with the second motor (35), connects on the output end of second motor (35)
It is connected to the tooth of running (36) being meshed with tooth form runway (34).
4. the flight system of aircraft according to claim 3, it is characterised in that: the mounting rod (1) and mounting ring (2)
It is coaxially disposed, is connected on the inner sidewall of mounting ring (2) on the mounting rod (1) by several connecting rods (4).
5. the flight system of aircraft according to claim 4, it is characterised in that: the mounting plate (31) is equipped with balance
Bar (5), the balancing pole (5) are equipped with lantern ring (6) far from the one end of mounting plate (31), and the lantern ring (6) is arranged on the securing lever.
6. the flight system of aircraft according to claim 5, it is characterised in that: the locating rod peripherally offers ring
Slot (7), the lantern ring (6) are set in annular groove (7).
7. the flight system of aircraft according to claim 3, it is characterised in that: the two sides up and down of the mounting ring (2)
It is equipped with one group of driving device (3).
8. the flight system of aircraft according to claim 7, it is characterised in that: the outer peripheral edge of the mounting ring (2) to
Sunken inside forms limiting slot (8), and the inner wall of the mounting plate (31) is matched with limiting slot (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910518654.6A CN110254700A (en) | 2019-06-15 | 2019-06-15 | The flight control method of aircraft and the flight system of application this method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910518654.6A CN110254700A (en) | 2019-06-15 | 2019-06-15 | The flight control method of aircraft and the flight system of application this method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110254700A true CN110254700A (en) | 2019-09-20 |
Family
ID=67918528
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910518654.6A Pending CN110254700A (en) | 2019-06-15 | 2019-06-15 | The flight control method of aircraft and the flight system of application this method |
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| CN (1) | CN110254700A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108814404A (en) * | 2018-09-17 | 2018-11-16 | 江苏师范大学 | A kind of unmanned plane formula high-altitude glass-cleaning machine device people |
| CN109094778A (en) * | 2018-07-24 | 2018-12-28 | 王迅 | A kind of unmanned plane formula Succor plain stage |
| CN210793623U (en) * | 2019-06-15 | 2020-06-19 | 安徽芳奎环境治理研究所有限公司 | Flight system of aircraft |
-
2019
- 2019-06-15 CN CN201910518654.6A patent/CN110254700A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109094778A (en) * | 2018-07-24 | 2018-12-28 | 王迅 | A kind of unmanned plane formula Succor plain stage |
| CN108814404A (en) * | 2018-09-17 | 2018-11-16 | 江苏师范大学 | A kind of unmanned plane formula high-altitude glass-cleaning machine device people |
| CN210793623U (en) * | 2019-06-15 | 2020-06-19 | 安徽芳奎环境治理研究所有限公司 | Flight system of aircraft |
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