CN208979091U - A kind of wing formula aircraft - Google Patents
A kind of wing formula aircraft Download PDFInfo
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- CN208979091U CN208979091U CN201821157789.1U CN201821157789U CN208979091U CN 208979091 U CN208979091 U CN 208979091U CN 201821157789 U CN201821157789 U CN 201821157789U CN 208979091 U CN208979091 U CN 208979091U
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- wing
- electromagnet
- adjustment mechanism
- attitude adjustment
- formula aircraft
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Abstract
The utility model 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 utility model is able to solve the problem of flight attitude adjustment mechanism complexity in the prior art.
Description
Technical field
The utility model 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.
Utility model content
The purpose of this utility model is to provide a kind of wing formula aircraft, are able to solve the flight of aircraft in the prior art
The problem of attitude-adjusting system complexity.
To achieve the above object, the wing formula aircraft in the utility model adopts the following technical scheme that
Wing formula aircraft, including body and wing are equipped with flight attitude adjustment mechanism, the flight between body and wing
Attitude-adjusting system includes electromagnet and elasticity reset device, and the electromagnet is set on body, 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, with
Electromagnet 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 the utility model wing centre section formula aircraft；
Fig. 2 is the structural schematic diagram of flight attitude adjustment mechanism in the embodiment 1 of the utility model wing centre section formula aircraft；
Flow chart when Fig. 3 is pulse generating unit work in the embodiment 1 of the utility model wing centre section formula aircraft；
Fig. 4 is the structural schematic diagram of flight attitude adjustment mechanism in the embodiment 2 of the utility model wing centre section formula aircraft；
Fig. 5 is the structural schematic diagram of flight attitude adjustment mechanism in the embodiment 3 of the utility model wing centre section formula aircraft.
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 utility model is illustrated now in conjunction with attached drawing.
As shown in Figure 1 to Figure 3, be the embodiment 1 of the utility model wing centre section formula aircraft: wing formula aircraft includes cylindric
Body 1, wing is provided on the outer peripheral surface of body 1, wing is divided into front wing 2 and empennage 3 according to the position of setting, preceding
The wing 2 and empennage 3 can provide lift with wing formula aircraft is combined into air in the motion process of wing formula aircraft, and wing passes through
It actively rotates or swings to realize the change to the lift of wing, wherein front wing 2 is hinged in main body, the direction of hinged shaft
Perpendicular with the direction of advance of wing formula aircraft, front wing 2 can be overturn around hinged shaft.Control is also equipped in wing formula aircraft
The flight attitude adjustment mechanism of wing movement, a portion includes electromagnet 4 and for controlling in flight attitude adjustment mechanism
The control system that electromagnet 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 utility model, control system can be in wing formula aircraft
Electromagnet 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 flies
The entire wing of row device be all it is movable, when electromagnet 4 is not powered, front wing 2 receives the limitation of spring 5, generally in 0
The elevation 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 electromagnet 4 is powered
Later, 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
The lower end of arm 21 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 increase, 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 after to the drive for pulling arm 21 attracted by electromagnet 4, the lift of front wing 2 is in initial position than front wing 2 at this time
When normal lift it is big, but while being in maximum elevation than front wing 2 it is suffered maximum lift it is small, pass through the width for changing pulse
The size of lift can be adjusted 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 the utility model wing centre section formula aircraft: difference from example 1 is that bullet
Spring 5 and electromagnet 4 are all disposed within the same side for pulling arm 21, and accordingly, electromagnet 4 is at this time reprimand to pull the generation of arm 21
Power, to swing 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, is pulled
Effect while swing arm 21 and wing receive moment of elasticity and electromagnetic torque.
As shown in figure 5, being the embodiment 3 of the utility model wing centre section formula aircraft: existing with the difference of above-described embodiment
Directly it is connected with wing in spring 5, the lower section of wing is set, makes limitation of the wing when swinging up and down by spring 5, and it is electric
Magnet 4 is also correspondingly arranged at the lower section of wing, generates 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.
Flight when technical staff utilizes the wing formula aircraft in the utility model, in addition to wing formula aircraft can be completed
Task can also be carried out many-sided extension using its characteristic and be utilized.For example the wing can be utilized by it using in agricultural production
Formula 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 in the utility model flies
Row device is also applied to other field.
Above-described specific embodiment, purpose of utility model, technical scheme and beneficial effects to the utility model
It has been further described, it should be understood that the foregoing is merely specific embodiment of the present utility model, and
Be not used in the restriction protection scope of the utility model, it is all within the spirit and principles of the present invention, done any repair
Change, equivalent replacement, improvement etc., should be included within the scope of protection of this utility model.
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 |
|---|---|---|---|
| CN201821157789.1U CN208979091U (en) | 2018-07-20 | 2018-07-20 | A kind of wing formula aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821157789.1U CN208979091U (en) | 2018-07-20 | 2018-07-20 | A kind of wing formula aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208979091U true CN208979091U (en) | 2019-06-14 |
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ID=66780266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821157789.1U Active CN208979091U (en) | 2018-07-20 | 2018-07-20 | A kind of wing formula aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208979091U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131834A (en) * | 2018-07-20 | 2019-01-04 | 中国空空导弹研究院 | Wing formula aircraft |
-
2018
- 2018-07-20 CN CN201821157789.1U patent/CN208979091U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131834A (en) * | 2018-07-20 | 2019-01-04 | 中国空空导弹研究院 | Wing formula aircraft |
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