CN207346095U - A kind of fixed-wing system of verting that can efficiently take off and fly before efficient - Google Patents
A kind of fixed-wing system of verting that can efficiently take off and fly before efficient Download PDFInfo
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- CN207346095U CN207346095U CN201721348024.1U CN201721348024U CN207346095U CN 207346095 U CN207346095 U CN 207346095U CN 201721348024 U CN201721348024 U CN 201721348024U CN 207346095 U CN207346095 U CN 207346095U
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- wing
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- fuselage
- circulator
- verting
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Abstract
The utility model discloses it is a kind of can efficiently take off and efficiently before winged fixed-wing system of verting, its structure includes the first wing, afterbody movable pulley, balance tail, tail vane, number passes antenna, fuselage, second wing, double helix verts device, propeller, rotation axis, engine, terminal box, lifting/lowering support wheel, head, rise and fall folding stand, the double helix device that verts is equipped with the first circulator, contiguous block, second circulator, vertical connection column, the utility model by equipped with double helix vert device, certain induced effect can be played when taking off, aircraft is set to start at faster speed, and flight speed is more efficient, pilot is set the completion task of color more occur.
Description
Technical field
The utility model is a kind of fixed-wing system of verting that can efficiently take off and fly before efficient, belongs to the fixation that can vert
Wing system regions.
Background technology
Tiltrotor is a kind of course of new aircraft that fixed wing aircraft and helicopter combine together, and someone visually claims
It is aerial " half-breed ", and tiltrotor had not only had the ability of pure helicopter VTOL and hovering, but also had whirlpool
Take turns the ability of the high speed cruise flight of propeller aeroplane.
Prior art discloses Application No.：201520100915.X a kind of band vert more rotor flyings of fixed-wing
Device, the aircraft include fuselage, the fixed-wing for being arranged at by shaft the fuselage both sides, multiple are arranged on the fuselage
Rotor, for driving dynamical system that each rotor wing rotation and fixed-wing vert and for controlling the fixed-wing
Tilt angle and control the rotating speed of each rotor and the control system of pitch, the prior art to take off speed slow,
Prolonged preparation is needed when taking off, delays the stroke of driver, easily dallies over one's work.
Utility model content
In view of the deficienciess of the prior art, the utility model aim be to provide it is a kind of can efficiently take off and efficiently before fly
Can be verted fixed-wing system, with solve the prior art to take off speed slow, needed when taking off it is prolonged prepare, delay
The stroke of driver, the problem of easily dallying over one's work.
To achieve these goals, the utility model is to realize by the following technical solutions：One kind can efficiently take off
And efficiently preceding winged fixed-wing system of verting, its structure include the first wing, afterbody movable pulley, balance tail, tail vane, number biography day
Line, fuselage, the second wing, double helix vert device, propeller, rotation axis, engine, terminal box, lifting/lowering support wheel, head, rise and fall folding
Superimposed, the double helix verts device equipped with two and is respectively perpendicular the top for being welded on the first wing and the second wing, described
Head is horizontally fixed on the left side of fuselage and using being welded to connect, and four angles of the engine are fixed on head by rivet
Left side, the rotation axis is installed in the left side of engine and using mechanically connecting, and the propeller passes through nut and rotation axis
It is threadedly coupled, the vertical gemel connection of the terminal box is in the left side of head and is electrically connected to the right side of engine, the folding of rising and falling
Frame is fixed on the lower section of head by bearing, and the lifting/lowering support wheel is welded in the lower section for the folding stand that rises and falls, and the tail vane is vertically fixed
In the top of fuselage right end and using being welded to connect, the balance tail through the right end of fuselage and orthogonal with fuselage,
The angle of the tail vane and balance tail is 90 °, and the afterbody movable pulley is fixed on the lower section of fuselage right end vertically, and the number passes day
Line is vertically fixed on the position of body upper 1/3rd, and the double helix verts device equipped with the first circulator, contiguous block, the
Two circulators, vertical connection column, the circuit board electrical connection inside the vertical connection column and the first wing, the second wing are described
Contiguous block is threadedly secured to the top of vertical connection column, first circulator, the second circulator be movably connected with
Left and right ends above contiguous block, second circulator are connected to the right side of the first circulator side by side.
Further, the lifting/lowering support wheel is equipped with two and parallel two-by-two.
Further, the afterbody movable pulley is in same level with lifting/lowering support wheel.
Further, second wing vertical is fixed on the left side of fuselage and uses and is welded to connect.
Further, first wing vertical is welded on the right side of fuselage.
Further, the lifting/lowering support wheel is high compounded rubber structure, elastic good, rub resistance.
Further, the tail vane plays the role of balance airplane, enables aircraft more steady in flight.
Beneficial effect
The utility model it is a kind of can efficiently take off and efficiently before winged fixed-wing system of verting, by equipped with double spiral shells
The device that verts is revolved, certain induced effect can be played when taking off, aircraft is started at faster speed, and speed of flying
Rate is more efficient, pilot the completion task of color is more occurred.
Brief description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other spies of the utility model
Sign, objects and advantages will become more apparent upon：
Fig. 1 is a kind of structural representation for the fixed-wing system of verting that can efficiently take off and fly before efficient of the utility model
Figure.
Fig. 2 is that the utility model double helix verts the structure diagram of device.
In figure：First wing -1, afterbody movable pulley -2, balance tail -3, tail vane -4, number pass antenna -5, fuselage -6, the second machine
The wing -7, double helix vert device -8, propeller -9, rotation axis -10, engine -11, terminal box -12, lifting/lowering support wheel -13, head -14,
Rise and fall folding stand -15, the first circulator -801, contiguous block -802, the second circulator -803, vertical connection column -804.
Embodiment
To make the technical means, creative features, achievable purpose and effectiveness that the utility model is realized easy to understand, below
With reference to embodiment, the utility model is expanded on further.
Please refer to Fig.1, Fig. 2, the utility model provides a kind of fixed-wing system of verting that can efficiently take off and fly before efficient
System：Its structure includes the first wing 1, afterbody movable pulley 2, balance tail 3, tail vane 4, number and passes antenna 5, fuselage 6, the second wing 7, double
The spiral device 8 that verts, propeller 9, rotation axis 10, engine 11, terminal box 12, lifting/lowering support wheel 13, head 14, rise and fall folding stand 15,
The double helix verts device 8 equipped with two and is respectively perpendicular the top for being welded on the first wing 1 and the second wing 7, the machine
First 14 are horizontally fixed on the left side of fuselage 6 and using being welded to connect, and four angles of the engine 11 are fixed on by rivet
The left side of head 14, the rotation axis 10 are installed in the left side of engine 11 and using mechanically connecting, and the propeller 9 passes through spiral shell
Mother is threadedly coupled with rotation axis 10, and the 12 vertical gemel connection of terminal box is in the left side of head 14 and is electrically connected to engine 11
Right side, the folding stand 15 that rises and falls are fixed on the lower section of head 14 by bearing, and the lifting/lowering support wheel 13 is welded in the folding stand that rises and falls
15 lower section, the tail vane 4 are vertically fixed on the top of 6 right end of fuselage and using being welded to connect, and the balance tail 3 runs through machine
The right end of body 6 and orthogonal with fuselage 6, the angle of the tail vane 4 and balance tail 3 is 90 °, and the afterbody movable pulley 2 is perpendicular
The straight lower section for being fixed on 6 right end of fuselage, the number passes antenna 5 and is vertically fixed on the position of the top of fuselage 6 1/3rd, described
Double helix verts device 8 equipped with the first circulator 801, contiguous block 802, the second circulator 803, vertical connection column 804, described vertical
Circuit board electrical connection inside 804 and first wing 1 of connecting pole, the second wing 7, the contiguous block 802 are threadedly secured to
The top of vertical connection column 804, first circulator 801, the second circulator 803 are movably connected with contiguous block 802
The left and right ends of side, second circulator 803 are connected to the right side of the first circulator 801 side by side, and the lifting/lowering support wheel 13 is equipped with
Two and parallel two-by-two, the afterbody movable pulley 2 be in same level with lifting/lowering support wheel 13, and second wing 7 is vertically consolidated
It is scheduled on the left side of fuselage 6 and using being welded to connect, first wing 1 is vertically welded in the right side of fuselage 6, the lifting/lowering support wheel 13
For high compounded rubber structure, elastic good, rub resistance, the tail vane 4 plays the role of balance airplane, enables aircraft in flight
It is more steady.
When in use, people are sitting in inside fuselage 6, are started engine 11 by controller, engine 11 is driven rotation
Axis 10 proceeds by rotation, makes propeller 9 start to rotate, and provides power for taking off for aircraft, and people can be by vertical
Electric wire in connecting pole 804 starts the small propeller on the first circulator 80 and the second circulator 803, aircraft is being taken off
When power it is more sufficient, the folding stand 15 that rises and falls after taking off folds, and makes lifting/lowering support wheel 13 downpayment, reduce aircraft flight when it is received
Resistance, more efficient flight.
Engine 11 described in the utility model be it is a kind of can the machine that can be converted into mechanical energy of other forms, wrap
Include such as internal combustion engine such as vehicle fuel machine, external-combustion engine such as Stirling engine, steam engine, motor etc..
Its structure and principle are all that this technology personnel can be learnt by technical manual or be known by normal experiment method,
The utility model solve the problems, such as be the prior art to take off speed slow, needed when taking off it is prolonged prepare, delay
The stroke of driver, easily dallies over one's work, and the utility model is combined with each other by above-mentioned component, can be played when taking off
Certain induced effect, enables aircraft to start at faster speed, and flight speed is more efficient, enables pilot more
Add the completion task for color occur, it is described in detail below：
Circuit board electrical connection inside 804 and first wing 1 of vertical connection column, the second wing 7, the contiguous block
802 are threadedly secured to the top of vertical connection column 804, the activity respectively of first circulator 801, the second circulator 803
The left and right ends of the top of contiguous block 802 are connected to, second circulator 803 is connected to the right side of the first circulator 801 side by side.
The advantages of basic principle and main feature and the utility model of the utility model has been shown and described above, for
For those skilled in the art, it is clear that the utility model is not limited to the details of above-mentioned one exemplary embodiment, and without departing substantially from this
In the case of the spirit or essential attributes of utility model, the utility model can be realized in other specific forms.Therefore, no matter
From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the utility model is by institute
Attached claim rather than described above limit, it is intended that will fall in the implication and scope of the equivalency of claim
All changes are embraced therein.Any reference numeral in claim should not be considered as to the involved right of limitation
It is required that.
Moreover, it will be appreciated that although the present specification is described in terms of embodiments, not each embodiment is only wrapped
Containing an independent technical solution, this narrating mode of specification is only that those skilled in the art should for clarity
Using specification as an entirety, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
It is appreciated that other embodiment.
Claims (5)
- A kind of 1. fixed-wing system of verting that can efficiently take off and fly before efficient, it is characterised in that：Its structure includes the first machine The wing (1), afterbody movable pulley (2), balance tail (3), tail vane (4), number pass antenna (5), fuselage (6), the second wing (7), double helix Vert device (8), propeller (9), rotation axis (10), engine (11), terminal box (12), lifting/lowering support wheel (13), head (14), rise and fall Folding stand (15), the double helix, which verts device (8) equipped with two and is respectively perpendicular, is welded on the first wing (1) and the second wing (7) top, it is characterised in that：The head (14) is horizontally fixed on the left side of fuselage (6) and uses and is welded to connect, four of the engine (11) Angle is fixed on the left side of head (14) by rivet, and the rotation axis (10) is installed in the left side of engine (11) and using machinery Connection, the propeller (9) are threadedly coupled by nut with rotation axis (10), and the vertical gemel connection of the terminal box (12) is in head (14) left side is simultaneously electrically connected to the right side of engine (11), and the folding stand that rises and falls (15) is fixed on head (14) by bearing Lower section, the lifting/lowering support wheel (13) is welded in the lower section of the folding stand that rises and falls (15), and the tail vane (4) is vertically fixed on fuselage (6) The top of right end and using being welded to connect, the balance tail (3) through fuselage (6) right end and hang down mutually with fuselage (6) Directly, the tail vane (4) and the angle of balance tail (3) are 90 °, and the afterbody movable pulley (2) is fixed on fuselage (6) right end vertically Lower section, the number pass antenna (5) and are vertically fixed on above fuselage (6) on 1/3rd position；The double helix vert device (8) equipped with the first circulator (801), contiguous block (802), the second circulator (803), vertically connect Column (804) is connect, the vertical connection column (804) circuit board electrical connection internal with the first wing (1), the second wing (7) is described Contiguous block (802) is threadedly secured to the top of vertical connection column (804), first circulator (801), the second circulator (803) left and right ends being movably connected with above contiguous block (802), second circulator (803) are connected to side by side The right side of one circulator (801).
- 2. a kind of fixed-wing system of verting that can efficiently take off and fly before efficient according to claim 1, its feature exist In：The lifting/lowering support wheel (13) is equipped with two and parallel two-by-two.
- 3. a kind of fixed-wing system of verting that can efficiently take off and fly before efficient according to claim 1, its feature exist In：The afterbody movable pulley (2) is in same level with lifting/lowering support wheel (13).
- 4. a kind of fixed-wing system of verting that can efficiently take off and fly before efficient according to claim 1, its feature exist In：Second wing (7) is vertically fixed on the left side of fuselage (6) and uses and is welded to connect.
- 5. a kind of fixed-wing system of verting that can efficiently take off and fly before efficient according to claim 1, its feature exist In：First wing (1) is vertically welded in the right side of fuselage (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721348024.1U CN207346095U (en) | 2017-10-18 | 2017-10-18 | A kind of fixed-wing system of verting that can efficiently take off and fly before efficient |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721348024.1U CN207346095U (en) | 2017-10-18 | 2017-10-18 | A kind of fixed-wing system of verting that can efficiently take off and fly before efficient |
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| Publication Number | Publication Date |
|---|---|
| CN207346095U true CN207346095U (en) | 2018-05-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201721348024.1U Active CN207346095U (en) | 2017-10-18 | 2017-10-18 | A kind of fixed-wing system of verting that can efficiently take off and fly before efficient |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109649633A (en) * | 2018-12-31 | 2019-04-19 | 江西冠通用飞机有限公司 | A kind of fixed wing aircraft shell that wing frame eyelid retractor is easy to assembly and stable |
-
2017
- 2017-10-18 CN CN201721348024.1U patent/CN207346095U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109649633A (en) * | 2018-12-31 | 2019-04-19 | 江西冠通用飞机有限公司 | A kind of fixed wing aircraft shell that wing frame eyelid retractor is easy to assembly and stable |
| CN109649633B (en) * | 2018-12-31 | 2023-10-03 | 江西冠一通用飞机有限公司 | Fixed wing aircraft casing of easy to assemble and stable of wing frame support ware |
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