CN206502021U - Efficient multi-rotor aerocraft - Google Patents
Efficient multi-rotor aerocraft Download PDFInfo
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- CN206502021U CN206502021U CN201720026192.2U CN201720026192U CN206502021U CN 206502021 U CN206502021 U CN 206502021U CN 201720026192 U CN201720026192 U CN 201720026192U CN 206502021 U CN206502021 U CN 206502021U
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- rotor
- power
- posture
- signal
- rotor motor
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Abstract
The utility model proposes a kind of efficient multi-rotor aerocraft, power and the rotor of control posture will be controlled individually to set.Power rotor is only responsible for flight altitude control, is slowly run acquisition higher efficiency using large scale rotor.Posture rotor is responsible for comprehensive gesture stability, using the more flexible power saving of the quick speed change of small size rotor.The beneficial effects of the utility model are：Above measure can be kept for longer cruising time with less electricity, realize the efficient flight of multi-rotor aerocraft.
Description
Technical field
The utility model is related to multi-rotor aerocraft technical field, more particularly to a kind of efficient multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft is a kind of simple in construction, aircraft that manipulation is flexible, flight attitude is stable.Typically it common are
The variety classeses such as four axles, six axles, eight axles.Have benefited from micro electronmechanical in recent years, sensor technology development, multi-rotor aerocraft is wide
It is general to be applied to the fields such as model plane, aerial photographing platform.
By taking most common X-type layout four-axle aircraft as an example, multi-rotor aerocraft control method is generally：Winged control sends height
Control signal, all rotors synchronously increase and decrease rotating speed, and winged control sends Heading control signal, increased respectively in cornerwise two groups of rotors
Turn reducing speed, winged control sends pitching, control of sideward roll signal, and two adjacent groups rotor increases and decreases rotating speed respectively.
Multi-rotor aerocraft provides power by battery.Wherein, sensor, processor, motor etc. are required for battery to power,
The motor power consumption for being especially to provide power is maximum.Current battery state-of-art is confined to, the use of battery is many of power
Rotor craft universal cruising time is short, load capacity is small, and which greatly limits the performance of multi-rotor aerocraft and application
Field.To solve the shortcoming that multi-rotor aerocraft cruising time is short, people consider thousand and one way to improve multi-rotor aerocraft
Cruising time, for example：Using engine fuel as power, balloon utilizes fuel cell etc. as auxiliary power.But these sides
Case suffers from such-and-such shortcoming.For example, fuel engines scheme has one in terms of vibrations, noise, response speed, security
Determine defect.Fuel cell technology is still immature, and balloon auxiliary power build is huge, larger by wind effect.
In general rotor size is big and higher with flight efficiency during relatively low rotation speed operation, but the quick rotating speed that changes relatively is stranded
Difficulty, flexibility is defective.Otherwise rotor size is small and flight efficiency is relatively low when being run with higher rotation speed, but flexibility is higher.Mesh
Preceding battery power multi-rotor aerocraft, rotor typically use onesize size, it is impossible to take into account the efficient of large scale rotor with
The advantage of small size rotor flexibility.
Multi-rotor aerocraft is to keep the various flight attitudes of aircraft by constantly quickly adjusting each rotor rotating speed, is frequently become
Speed can increase electric quantity consumption reduction cruising time, if rotor can with constant speed rotate or as far as possible reduce speed change frequency and
Amplitude can effectively reduce energy consumption, extend cruising time.
The content of the invention
It is provided with a kind of efficient multi-rotor aerocraft, including rotor mechanism, undercarriage, cabin, cabin and flies control case, battery
Group, load cabin, it is characterised in that：
The rotor mechanism includes power rotor, power rotor motor, power rotor support, posture rotor, posture rotor
Motor, posture rotor support,
Power rotor is driven by power rotor motor direct connection or slowed down and links, and quantity is two or more even numbers,
Each two is one group and is symmetrically vertically arranged to power rotor support two ends relative to aircraft vertical axis and each two is one
The positive oar and anti-oar of identical size is respectively adopted in group；
Posture rotor is driven by posture rotor motor direct connection, and quantity is four or more even number, and each two is one
Group is symmetrical relative to aircraft vertical axis and with using the positive oar of identical size or with the anti-oar of identical size is used, and owns
The positive oar quantity of posture rotor and anti-oar quantity are equal, and multigroup intersects and be not on same straight line；
The product of power rotor area and lift coefficient is more than posture rotor, and power rotor motor peak power is more than posture
Rotor motor peak power；
Power rotor motor with electricity adjust signal be connected, electricity adjust be connected with remote controller receiver signal, remote controller receiver and
Remote control wireless signal is connected, and remote control only transmits height control signal or power rotor motor to power rotor motor and adjusted with electricity
Signal is connected, and electricity is adjusted to be connected with flying control case signal, is flown control case and is only transmitted height control signal to power rotor motor；
Posture rotor motor adjusts signal to be connected with electricity, and electricity is adjusted to be connected with flying control case signal, flies control case to posture rotor motor
Transmit height, course, roll, pitch control signal.
Further, power rotor slows down the mode linked by power rotor motor including passing through train of reduction gears or deceleration
Belt pulley set, which is slowed down, to link.
Further, power rotor motor KV values are less than posture rotor motor KV values.
Further, power rotor is using oar paddle type at a slow speed.
Compared with prior art, efficient multi-rotor aerocraft of the present utility model has the characteristics that and advantage：
1st, efficient multi-rotor aerocraft of the present utility model, has functionally distinguished the power rotor for providing power and adjustment
The posture rotor of posture.Brought to design efficient multi-rotor aerocraft than the larger free degree.Traditional multi-rotor aerocraft respectively revolves
Wing function phase is same, had not only undertaken power function has but also undertaken posture function, be limited when from rotor size and rotor motor power compared with
It is many.The utility model realizes power and adjustment posture function by what power function and posture functional areas separately can more optimize.It is dynamic
Power rotor motor is because of a constant speed drive or is only involved in highly controlling to be not involved in course, pitching, roll pose adjustment, and its rotating speed becomes
Change frequency and amplitude is greatly reduced, more high-tensile strength effect can be obtained using the method for the big oar of low speed, save electricity extension cruising time.
Similarly, the posture rotor of adjustment posture then can be by miniaturization, to realize the effect of more flexible more power saving.
2nd, efficient multi-rotor aerocraft of the present utility model, power rotor motor KV values are relatively low to be conducive to obtaining more preferable torsion
Square performance drives larger-size rotor, obtains higher power effect.Posture rotor motor KV values are higher, and speed change is quick, is conducive to
Obtain more preferable flexibility.
3rd, efficient multi-rotor aerocraft of the present utility model, power rotor is using oar paddle type at a slow speed.Oar is in the slow-speed of revolution at a slow speed
It is lower that larger pulling force can be achieved, greater efficiency can have been given play to.This kind of propeller outside area is larger also more abundant, and blade root is thinner.
Be conducive to obtaining more high-tensile strength effect at the low rotational speed using oar at a slow speed, save power consumption, extend cruising time.
It is read in conjunction with the figure after embodiment of the present utility model, will becomes more with advantage the characteristics of the utility model
Plus it is clear.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the accompanying drawing used required in description of the prior art is briefly described, it should be apparent that, drawings in the following description are these
Some embodiments of utility model, for those of ordinary skill in the art, on the premise of not paying creative work, also
Other accompanying drawings can be obtained according to these accompanying drawings.
Fig. 1 is a kind of stereogram of efficient multi-rotor aerocraft of six axles of the utility model embodiment 1；
Fig. 2:For a kind of schematic diagram of efficient multi-rotor aerocraft of eight axles of the utility model embodiment 2；
Wherein,
1st, power rotor, 2, power rotor motor, 3, posture rotor support, 4, posture rotor, 5, posture rotor motor,
6th, cabin, 61, fly control case, 62, battery pack, 63, load cabin, 7, undercarriage, 8, power rotor support.
Embodiment
The utility model is described in detail with reference to the accompanying drawings and detailed description.
As shown in figure 1, the present embodiment 1 provides a kind of efficient multi-rotor aerocraft, assembly connection has cabin on undercarriage 7
6.It is provided with inside cabin 6 and flies control case 61, battery pack 62, load cabin 63.Connection dynamic rotor support 8 is installed in cabin 6, moved
Connection power rotation is installed in the vertically-mounted dynamic rotor motor 2 in the two ends of power rotor support 8, the rotary shaft of power rotor motor 2
The wing 1.Power rotor quantity is 2 and the positive oar of size identical and anti-oar is respectively adopted there is provided can be cancelled out each other during pulling force in the same direction
Moment of torsion effect to fuselage.Installed in cabin 6 and be connected with posture rotor support 3,3 outer ends of posture rotor support are vertically-mounted appearance
Connection posture rotor 4 is installed in state rotor motor 5, the rotary shaft of posture rotor motor 5.The quantity of posture rotor is 4, two-by-two
Relative flight device vertical central axis line is symmetrically distributed in fuselage surrounding, and the positive oar of size identical and anti-oar, same diagonal is respectively adopted
Posture rotor paddle type is consistent.Battery pack 62 is electrically connected with flying control case 61 through wire.Power rotor motor 2, posture rotor motor 5 are passed through
The electricity for flying to install in control case 61 adjusts electrical connection.Power rotor motor 2, posture rotor motor 5 are adjusted with flying the winged control in control case through electricity
Signal is connected.
The major impetus of efficient multi-rotor aerocraft is provided by power rotor 1.The dimensioned area of power rotor 1 is revolved more than posture
The wing 4, the peak power of power rotor motor 2 is more than the peak power of posture rotor 5.The rotor of large-size compared with low velocity to rotate
Be conducive to obtaining higher flight efficiency.When the timing of aircraft load constant, power rotor 1 provides a definite value pulling force and is equal to flight
Device gross weight, the gravity of aircraft is overcome as major impetus, is not involved in aircraft, pitching, roll, course pose adjustment.Fly
Row device height, pitching, roll, course flight attitude are responsible for by four posture rotors 4.Power rotor is not involved in course, pitching, horizontal stroke
The control of posture is rolled, the amplitude and frequency of rotation speed change are substantially reduced in flight course, have saved electric power.The chi of posture rotor 4
Very little area is smaller, from low-power machine, the flexible power saving of speed change.Four control attitude of flight vehicle of posture rotor 4 of the present embodiment
Control logic is identical with traditional four-axle aircraft, substantially reduces and flies control development difficulty.
Illustrate specific control method below：
First, take off：
Step 1：Remote control wirelessly sends takeoff order to winged control case 61.
Step 2：Fly control case 61 and send constant speed rotating signal to power rotor motor 2.Power rotor motor 2 produces one and determined
It is worth lift.This lift is preferably exactly equal to aircraft gravity.
Step 3：Fly control case 61 and send pose adjustment order, including height, course, pitching, roll to posture rotor motor 5
Pose adjustment signal.
Step 4：Aircraft takeoff is simultaneously raised to specified altitude assignment.
2nd, hover
Step 1：Remote control sends hovering signal to winged control case 61.
Step 2：The constant speed rotating signal that winged control case 61 is sent to power rotor motor 2 remains unchanged, and flies appearance in control case 61
State sensor senses floating state, and status signal is sent to processor, signal is after flying control processor and handling, to posture rotor
Motor 5 sends height, course, pitching, the holding hovering of roll pose adjustment signal.
3rd, fly
Step 1：Remote control sends flight signal to winged control case 61, and flight signal includes forward-reverse, and course rotation, side is winged
It is traversing.
Step 2：The constant speed rotating signal that winged control case 61 is sent to power rotor motor 2 remains unchanged.Fly control case 61 to appearance
State rotor motor 5 sends Pitch signal and realizes forward-reverse；Course signal is sent, course spinfunction is realized in aircraft spin；
Send roll signal aircraft and realize horizontal winged sideward sliding function.
4th, land
Step 1：Remote control sends landing order to winged control case 61.
Step 2:Fly control case 61 and send reduction altitude signal to power rotor motor 2, the rotational deceleration of power rotor motor 2,
The lift of generation is less than aircraft gravity.Fly control case 61 and send control height, roll, pitching, heading device to posture rotor motor 5
Number.Aircraft declines low clearance in the control of self gravitation and posture rotor motor 5 and realizes landing.
Fig. 2：For a kind of schematic diagram of efficient multi-rotor aerocraft of eight axles of the utility model embodiment 2.Wherein four A rotations
The wing is power rotor 1, and specification is APC companies 14*47, power motor model 4008.Four B rotors are posture rotor 4, and specification is
APC companies 11*47, posture rotor motor model 4004.
In order to further verify advantage of the present utility model and high efficiency, spy carries out cruising time contrast experiment.This experiment
Contrasting two model machines is respectively：Model machine 1 is traditional eight axles multi-rotor aerocraft, and model machine 2, which is that the axle of the utility model eight efficiently more, to be revolved
Rotor aircraft.
Table 1：Cruising time data comparison table
Experimental prototype uses same specification battery, and take-off weight is identical.Traditional eight axle aircraft are using eight identical sizes
The motor of 12*45 specifications propeller and same size.Four power rotor chis of the efficient multi-rotor aerocraft of the axle of the utility model eight
Very little area is larger, and four rotor motor power are larger, is only responsible for control aircraft altitude.It is high that posture rotor is responsible for flight
Degree.Course, pitching, roll gesture stability.It is can be seen that by the data of table 1 in same specification battery, same take-off weight, this practicality
New and effective multi-rotor aerocraft effectively extends cruising time 50%, further demonstrates validity of the present utility model and superior
Property.
Certainly, described above is not that, to limitation of the present utility model, the utility model is also not limited to the example above,
The variations, modifications, additions or substitutions that those skilled in the art are made in essential scope of the present utility model, also should
Belong to protection domain of the present utility model.
Claims (4)
- Fly control case, battery 1. being provided with a kind of efficient multi-rotor aerocraft, including rotor mechanism, undercarriage, cabin, cabin Group, load cabin, it is characterised in that：The rotor mechanism include power rotor, power rotor motor, power rotor support, posture rotor, posture rotor motor, Posture rotor support,Power rotor is driven by power rotor motor direct connection or slowed down and links, and quantity is two or more even numbers, every two It is individual to be one group and be symmetrically vertically arranged to power rotor support two ends relative to aircraft vertical axis and each two is a component Not Cai Yong identical size positive oar and anti-oar；Posture rotor is driven by posture rotor motor direct connection, and quantity is four or more even number, and each two is one group of phase For aircraft vertical axis it is symmetrical and with using the positive oar of identical size or with use the anti-oar of identical size, all postures The positive oar quantity of rotor and anti-oar quantity are equal, and multigroup intersects and be not on same straight line；Power rotor area is more than posture rotor with lift coefficient product, and power rotor motor peak power is more than posture rotor electricity Machine peak power；Power rotor motor adjusts signal to be connected with electricity, and electricity is adjusted and is connected with remote controller receiver signal, remote controller receiver and remote control Device wireless signal is connected, and remote control only transmits height control signal or power rotor motor to power rotor motor and electricity adjusts signal Connection, electricity is adjusted to be connected with flying control case signal, is flown control case and is only transmitted height control signal to power rotor motor；Posture rotor motor adjusts signal to be connected with electricity, and electricity is adjusted to be connected with flying control case signal, is flown control case and is transmitted to posture rotor motor Highly, course, roll, pitch control signal.
- 2. efficient multi-rotor aerocraft according to claim 1, it is characterised in that：The power rotor is by power rotor electricity Machine slows down the mode linked including by train of reduction gears or the deceleration linkage of deceleration belt pulley group.
- 3. efficient multi-rotor aerocraft according to claim 1, it is characterised in that：Power rotor motor KV values are less than posture Rotor motor KV values.
- 4. efficient multi-rotor aerocraft according to claim 1, it is characterised in that：Power rotor is using oar paddle type at a slow speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720026192.2U CN206502021U (en) | 2017-01-11 | 2017-01-11 | Efficient multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720026192.2U CN206502021U (en) | 2017-01-11 | 2017-01-11 | Efficient multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206502021U true CN206502021U (en) | 2017-09-19 |
Family
ID=59839324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720026192.2U Expired - Fee Related CN206502021U (en) | 2017-01-11 | 2017-01-11 | Efficient multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206502021U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542093A (en) * | 2017-01-11 | 2017-03-29 | 刘海涛 | Efficient multi-rotor aerocraft |
-
2017
- 2017-01-11 CN CN201720026192.2U patent/CN206502021U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542093A (en) * | 2017-01-11 | 2017-03-29 | 刘海涛 | Efficient multi-rotor aerocraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170919 Termination date: 20180111 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |