CN109131834A - Wing formula aircraft - Google Patents
Wing formula aircraft Download PDFInfo
- Publication number
- CN109131834A CN109131834A CN201810804828.0A CN201810804828A CN109131834A CN 109131834 A CN109131834 A CN 109131834A CN 201810804828 A CN201810804828 A CN 201810804828A CN 109131834 A CN109131834 A CN 109131834A
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- CN
- China
- Prior art keywords
- wing
- electromagnet
- adjustment mechanism
- flight attitude
- formula aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 43
- 230000007717 exclusion Effects 0.000 claims abstract description 3
- 230000013011 mating Effects 0.000 claims abstract description 3
- 210000001367 artery Anatomy 0.000 claims 1
- 210000003462 vein Anatomy 0.000 claims 1
- 230000009286 beneficial effect Effects 0.000 description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- BGPVFRJUHWVFKM-UHFFFAOYSA-N N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] Chemical compound N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] BGPVFRJUHWVFKM-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000012271 agricultural production Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 230000005294 ferromagnetic effect Effects 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to flight instruments technical fields, more particularly to a kind of wing formula aircraft, wing formula aircraft includes body and wing, flight attitude adjustment mechanism is equipped between body and wing, the flight attitude adjustment mechanism includes electromagnet and elasticity reset device, and the electromagnet is set on body, it is connected with pulse generating unit, Hu Xi mechanism or exclusion mechanism are formed between corresponding wing, the elasticity reset device is set between wing and body, mating with electromagnet.Aircraft in the present invention is able to solve the problem of flight attitude adjustment mechanism complexity in the prior art.
Description
Technical field
The present invention relates to flight instruments technical fields, and in particular to a kind of wing formula aircraft.
Background technique
In traditional aircraft, it is general using it is pneumatic, surge, the flight attitude adjustment mechanism of the forms such as electronic is come to winged
The wing of row device is controlled, and is controlled to realize the movement of aircraft.By taking electronic flight attitude adjustment mechanism as an example,
Including motor, deceleration mechanism, angle measurement mechanism and control circuit etc., under the action of control circuit, motor exports dynamic outward
Power, and later rotate a part of wing or wing by deceleration mechanism, angle measurement mechanism is right during aircraft flight
Its movement angle measures, and makes the wing of aircraft according to the requirement campaign of control system.
But with the continuous improvement of technical requirements, these flight attitude adjustment mechanisms are since structure is complicated, volume weight
The reason of bigger than normal and processing and debugging difficulty and be difficult to aircraft that be suitable for some low dispensing costs, small-sized.
Summary of the invention
The purpose of the present invention is to provide a kind of wing formula aircraft, are able to solve the flight attitude of aircraft in the prior art
The problem of adjustment mechanism complexity.
To achieve the above object, the wing formula aircraft in the present invention adopts the following technical scheme that
Wing formula aircraft, including body and wing are equipped with flight attitude adjustment mechanism, the flight attitude between body and wing
Adjustment mechanism includes electromagnet and elasticity reset device, and the electromagnet is set on body, is connected with pulse generating unit, and right
Hu Xi mechanism or exclusion mechanism are formed between the wing answered, the elasticity reset device is set between wing and body, with electromagnetism
Iron is mating.
The beneficial effect is that: attracted by electromagnet or repels wing so that wing generates corresponding movement, structure
Simply, the components used are less, and the control system and driving circuit that are controlled to electromagnet also being capable of integrated installations
In the body of small-sized wing formula aircraft, elasticity reset device, elastic reset are additionally provided in flight attitude adjustment mechanism
Device can will generate an elastic force opposite with the electromagnetic force that electromagnet generates for wing, and electromagnet will drive wing
Movement is made jointly so that wing be made to be in moment of elasticity provided by the electromagnetic torque and elasticity reset device of electromagnet offer
With stable adjustment can be carried out to the movement of wing, and while two torque during wing formula aircraft flight
Effect can guarantee that wing is in after the adjustment on stable position again, not need to introduce other components in aircraft, from
And the flight attitude adjustment mechanism of aircraft is simplified, keep the structure of flight attitude adjustment mechanism simpler.
Further, the airfoil root be fixedly installed it is vertically extending pull arm, pull arm and flight by described
The electromagnet and elasticity reset device of attitude-adjusting system cooperate.
The beneficial effect is that: it is provided on wing and pulls arm to be formed and be cooperated with electromagnet, structure is simple, pulls arm
Length and shape can according to need to be designed, overall structure is laid out convenient for technical staff.
Further, described one end far from wing where it for pulling arm extends to the flight attitude adjustment mechanism
Between electromagnet and elasticity reset device.
The beneficial effect is that: electromagnet and elasticity reset device are separately positioned on to the front and rear sides for pulling arm, formed
A force structure drawn is inhaled to arm one is pulled, has active force pulling arm two sides, avoids and occur pulling arm unilateral side stress
The problems in collection.
Further, the flight attitude adjustment mechanism is set to below corresponding wing, pulls arm to downward on wing
It stretches.
The beneficial effect is that: flight attitude adjustment mechanism is arranged in the lower section of wing, can be improved the space of body
Utilization rate reduces the wing formula aircraft windage suffered in flight.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of wing centre section formula aircraft of the present invention；
Fig. 2 is the structural schematic diagram of flight attitude adjustment mechanism in the embodiment 1 of wing centre section formula aircraft of the present invention；
Flow chart when Fig. 3 is pulse generating unit work in the embodiment 1 of wing centre section formula aircraft of the present invention；
Fig. 4 is the structural schematic diagram of flight attitude adjustment mechanism in the embodiment 2 of wing centre section formula aircraft of the present invention；
Fig. 5 is the structural schematic diagram of flight attitude adjustment mechanism in the embodiment 3 of wing centre section formula aircraft of the present invention.
In figure: 1. bodies；2. front wing；21. pulling arm；3. empennage；4. electromagnet；5. spring.
Specific embodiment
The specific embodiment of the wing formula aircraft in the present invention is illustrated now in conjunction with attached drawing.
As shown in Figure 1 to Figure 3, be the embodiment 1 of wing centre section formula aircraft of the present invention: wing formula aircraft includes columned machine
Body 1 is provided with wing on the outer peripheral surface of body 1, and wing is divided into front wing 2 and empennage 3 according to the position of setting, front wing 2
Lift can be provided with wing formula aircraft is combined into air in the motion process of wing formula aircraft with empennage 3, wing passes through master
Turn is dynamic or swings to realize the change to the lift of wing, and wherein front wing 2 is hinged in main body, the direction of hinged shaft with
The direction of advance of wing formula aircraft is perpendicular, and front wing 2 can be overturn around hinged shaft.Control machine is also equipped in wing formula aircraft
The flight attitude adjustment mechanism of wing movement, a portion includes electromagnet 4 and for controlling electricity in flight attitude adjustment mechanism
The control system that magnet 4 acts after electromagnet 4 receives the instruction of control system, can correspond to the corresponding movement of generation.
Accordingly, it is fixedly installed on the root of front wing 2 and pulls arm 21 with what electromagnet 4 cooperated, pulling arm 21 can
It is attracting with electromagnet 4, thus realize the movement for driving front wing 2, and flight attitude adjustment mechanism further includes pulling arm on front wing 2
The enabling of 21 connections pulls the elasticity reset device that arm 21 resets, elasticity reset device can will be generated for front wing 2 one with
The opposite elastic force of the electromagnetic force that electromagnet 4 generates, and electromagnet 4 will drive the movement of front wing 2, so that front wing 2 be made to be in electricity
Moment of elasticity collective effect provided by the electromagnetic torque and elasticity reset device that magnet 4 provides, in wing formula aircraft flight
In the process, stable adjustment can be carried out to the movement of front wing 2.In flight attitude adjustment mechanism, further include and electromagnet 4
The pulse generating unit of coil connection, pulse generating unit can carry out the coil to electromagnet 4 with power supply and electronic switch cooperation
Pulse electrifying is carried out, the time of pulse and duty ratio receive the control of control system, by pulse electrifying, can make front wing 2
It swings up and down to drive wing formula aircraft to be rapidly rising or falling, electromagnet 4, front wing 2 and elasticity reset device match, shape
At complete flight attitude adjustment mechanism.
In the direction of advance of wing formula aircraft, electromagnet 4 is arranged in front wing 2 and pulls the front end of arm 21, pulls arm 21
It can be attracted by electromagnet 4 after the electrification of electromagnet 4 and the other end and machine of arm 21 can be pulled towards 4 one end motion of electromagnet
The wing is fixedly connected, and the movement travel swung can be had after the electrification of electromagnet 4 by pulling arm 21, in the close electromagnet for pulling arm 21
4 one end, is connected with the spring 5 as elasticity reset device, and spring 5 is located in wing formula aircraft direction of advance, pulls
The rear end of arm 21, pulling arm 21 will receive resistance provided by spring 5 when being attracted by electromagnet 4, make to pull arm 21 and front wing 2
Effect by electromagnetic torque and moment of elasticity simultaneously.And the power that the position that spring 5 is arranged provides front wing 2 only by spring 5
And be position from the horizontal by 0 degree of angle in horizontal plane, in entire motion process, spring 5 is always to pulling arm
21 generation one prevention pulls resistance of the arm 21 towards 4 one side oscillation of electromagnet, be also due to pull arm 21 and front wing 2 by
It is acted on while moment of elasticity and electromagnetic torque and certain stability can be kept after turning an angle.Fly in wing formula
In the entire flight course of row device, the ferromagnetic fraction for pulling arm 21 is in be attracted by electromagnet 4 completely and contact with electromagnet 4,
And the working condition tensed completely by spring 5.
When technical staff uses the wing formula aircraft in the present invention, control system can be to the electromagnetism in wing formula aircraft
Iron 4 is controlled, and so that electromagnet 4 is realized power on/off to drive and pull arm 21 and the movement of front wing 2, in this example, wing formula aircraft
Entire wing be all it is movable, when electromagnet 4 is not powered, front wing 2 receives the limitation of spring 5, faces upward generally in 0
Angle, the i.e. initial position from the horizontal by 0 degree of angle.The lift that front wing 2 is subject to is normal lift, when 4 energization of electromagnet
Afterwards, electromagnet 4, which can attract, pulls arm 21 towards the movement of electromagnet 4, pulls one end of the close electromagnet 4 of arm 21, that is, pulls arm
21 lower end is moved towards electromagnet 4, and the upper end for pulling arm 21 connect with front wing 2 and drives front wing 2 to facing upward, and makes front wing 2
The elevation angle increases, and air force changes correspondingly, and improves the lift of front wing 2.When electromagnet 4 carry out pulse electrifying after, front wing 2 by
It can be to facing upward, when the lift of front wing 2 is in initial position than front wing 2 at this time after the drive for pulling arm 21 attracted by electromagnet 4
Normal lift it is big, but while being in maximum elevation than front wing 2 it is suffered maximum lift it is small, the width by changing pulse can
To adjust the size of lift in a certain range.
When wing formula aircraft needs to turn to, the lift by increasing side front wing 2 is achieved that: when needing to turn to the right
When, corresponding with the front wing 2 on the left of wing formula aircraft flight attitude adjustment mechanism drives front wing 2 to facing upward, and increases the side
Lift suffered by front wing 2, wing formula aircraft can move right；When needing to turn to the left, before on the right side of wing formula aircraft
The wing 2 corresponding flight attitude adjustment mechanism drives front wing 2 to facing upward, and increases lift suffered by the side front wing 2, and wing formula flies
Row device can move downward.
As shown in figure 4, being the embodiment 2 of wing centre section formula aircraft of the present invention: difference from example 1 is that spring 5
And electromagnet 4 is all disposed within the same side for pulling arm 21, accordingly, electromagnet 4 is at this time repulsion to pull the generation of arm 21, with
It is swung to one end far from spring 5, and spring 5 is produced due to being overcome deformation to the elastic force for pulling arm 21, pulls arm
21 and wing effect while receive moment of elasticity and electromagnetic torque.
As shown in figure 5, being the embodiment 3 of wing centre section formula aircraft of the present invention: with above-described embodiment the difference is that bullet
Spring 5 is directly connected with wing, and the lower section of wing is arranged in, and makes limitation of the wing when swinging up and down by spring 5, and electromagnet
4 are also correspondingly arranged at the lower section of wing, generate repulsion so that wing is rotated up to wing.
In other embodiments, the empennage 3 of wing formula aircraft can also rely on the drive of above-mentioned flight attitude adjustment mechanism
And it realizes and rotates upwardly and downwardly.
In other embodiments, the arm of pulling connecting with wing can also be with the coplanar arrangement of wing, flight attitude adjustment
Mechanism, which will then be located at, to be pulled above or below the plane of arm place, makes to pull arm under the action of flight attitude adjustment mechanism perpendicular
Face movement directly.
In other embodiments, elasticity reset device may be replaced by other forms, such as may be arranged as and pull
The elastic slice of swing arm connection, or with the elastic rubber drawstring pulling arm and connect.
When technical staff utilizes the wing formula aircraft in the present invention, the flight in addition to that can complete wing formula aircraft is appointed
Business can also be carried out many-sided extension using its characteristic and be utilized.For example the wing formula can be utilized by it using in agricultural production
Aircraft sprinkles water, spills medicine；It can also be utilized in industrial production or logistics transportation, to convey the work of some lighter weights
Part；The size of the wing formula aircraft and power can also be reduced, in recreation；Wing formula aircraft in the present invention
It is also applied to other field.
Above-described specific embodiment, to goal of the invention of the invention, technical scheme and beneficial effects carried out into
One step is described in detail, it should be understood that being not used to limit this foregoing is merely a specific embodiment of the invention
The protection scope of invention, all any modification, equivalent substitution, improvement and etc. within the spirit and principles in the present invention, done,
It should be included within protection scope of the present invention.
Claims (4)
1. wing formula aircraft, including body and wing, are equipped with flight attitude adjustment mechanism between body and wing, feature exists
In: the flight attitude adjustment mechanism includes electromagnet and elasticity reset device；The electromagnet is set on body, is connected with arteries and veins
Generating device is rushed, forms Hu Xi mechanism or exclusion mechanism between corresponding wing；The elasticity reset device be set to wing with
It is mating with electromagnet between body.
2. wing formula aircraft according to claim 1, it is characterised in that: the root of the wing, which is fixedly installed, vertically prolongs
That stretches pulls arm, is cooperated by the electromagnet for pulling arm and flight attitude adjustment mechanism and elasticity reset device.
3. wing formula aircraft according to claim 2, it is characterised in that: one far from wing where it for pulling arm
End extends between the electromagnet and elasticity reset device of the flight attitude adjustment mechanism.
4. wing formula aircraft according to claim 2 or 3, it is characterised in that: the flight attitude adjustment mechanism be set to pair
Below the wing answered, the arm of pulling on wing is extended downwardly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810804828.0A CN109131834A (en) | 2018-07-20 | 2018-07-20 | Wing formula aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810804828.0A CN109131834A (en) | 2018-07-20 | 2018-07-20 | Wing formula aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109131834A true CN109131834A (en) | 2019-01-04 |
Family
ID=64801393
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810804828.0A Pending CN109131834A (en) | 2018-07-20 | 2018-07-20 | Wing formula aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131834A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3107882A (en) * | 1962-08-10 | 1963-10-22 | Electric Auto Lite Co | Yaw control system for vtol tilt wing aircraft |
| US5078338A (en) * | 1990-01-19 | 1992-01-07 | Neill Terrence O | Means for maintaining a desired relationship between roll and yaw stability in a swept-wing aircraft by varying dihedral as a function of lift coefficient |
| WO1998023482A1 (en) * | 1996-11-26 | 1998-06-04 | Freewing Aerial Robotics Corp. | Stol/vtol aircraft with improved control during transition |
| KR100615556B1 (en) * | 2005-04-08 | 2006-08-25 | 전상락 | Small-sized flying object |
| US20100230547A1 (en) * | 2008-09-05 | 2010-09-16 | The Government Of The Us, As Represented By The Secretary Of The Navy | Stop-rotor rotary wing aircraft |
| CN106428550A (en) * | 2016-11-04 | 2017-02-22 | 山东萌萌哒航空科技有限公司 | Tilting type unmanned plane and flight control method thereof |
| CN207515628U (en) * | 2017-10-23 | 2018-06-19 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN208979091U (en) * | 2018-07-20 | 2019-06-14 | 中国空空导弹研究院 | A kind of wing formula aircraft |
-
2018
- 2018-07-20 CN CN201810804828.0A patent/CN109131834A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3107882A (en) * | 1962-08-10 | 1963-10-22 | Electric Auto Lite Co | Yaw control system for vtol tilt wing aircraft |
| US5078338A (en) * | 1990-01-19 | 1992-01-07 | Neill Terrence O | Means for maintaining a desired relationship between roll and yaw stability in a swept-wing aircraft by varying dihedral as a function of lift coefficient |
| WO1998023482A1 (en) * | 1996-11-26 | 1998-06-04 | Freewing Aerial Robotics Corp. | Stol/vtol aircraft with improved control during transition |
| KR100615556B1 (en) * | 2005-04-08 | 2006-08-25 | 전상락 | Small-sized flying object |
| US20100230547A1 (en) * | 2008-09-05 | 2010-09-16 | The Government Of The Us, As Represented By The Secretary Of The Navy | Stop-rotor rotary wing aircraft |
| CN106428550A (en) * | 2016-11-04 | 2017-02-22 | 山东萌萌哒航空科技有限公司 | Tilting type unmanned plane and flight control method thereof |
| CN207515628U (en) * | 2017-10-23 | 2018-06-19 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN208979091U (en) * | 2018-07-20 | 2019-06-14 | 中国空空导弹研究院 | A kind of wing formula aircraft |
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