CN208834626U - A kind of model aircraft engine - Google Patents
A kind of model aircraft engine Download PDFInfo
- Publication number
- CN208834626U CN208834626U CN201820754258.4U CN201820754258U CN208834626U CN 208834626 U CN208834626 U CN 208834626U CN 201820754258 U CN201820754258 U CN 201820754258U CN 208834626 U CN208834626 U CN 208834626U
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- Prior art keywords
- fixed
- blade
- lifting unit
- aircraft engine
- tail
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- 239000007921 spray Substances 0.000 claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims abstract description 17
- 206010040007 Sense of oppression Diseases 0.000 claims abstract description 15
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 14
- 230000009467 reduction Effects 0.000 claims description 4
- 238000004804 winding Methods 0.000 claims description 4
- 230000007423 decrease Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 230000002285 radioactive effect Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000004744 fabric Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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Abstract
The utility model provides a kind of model aircraft engine, including air inlet and tail spray, and air inlet includes more blades, blade fixed frame, the first driving mechanism；First driving mechanism includes linear drives portion, oppression department, is oppressed portion；The one end in shaft towards the center of circle is fixed with the portion of being oppressed；Linear drives portion drives oppression department linear motion.Tail spray includes that shell is opened in the spray of tubular tail；It is fixed with multi-disc tail spray blade in the bottom end that shell is opened in tail spray, the second driving mechanism includes lifting unit, struts portion, traction rope；More blades are connected in one end of traction rope, and the other end is controlled by lifting unit；The portion of strutting is fixed on lifting unit, is driven and is gone up and down by lifting unit.Oppression department movement is driven by linear drives portion, so that the portion of being oppressed be driven to generate counterclockwise or clockwise rotation, is driven with this and is rotated with the affixed shaft of moving vane, realize that moving vane generates the movement to swing.By realizing opening and closing part blade automatic open-close by lifting unit, traction rope, the cooperation for strutting portion.
Description
Technical field
The utility model relates to model aircraft technical field, a kind of specifically model aircraft engine.
Background technique
Various model aircrafts are that airplane hobbyist is keen to one of collection.Model aircraft is mostly to scale to make with prototype equal proportion
The model made.But since prototype internal structure is complicated, so model aircraft is general only to accomplish simulated effect in appearance.For
Accomplish to emulate to the greatest extent, from outside it can be seen that moving component should can move.Therefore, model manufacturer exists
When designing a model, need to be realized the simulating sports of moving component with simplest structure, to save production cost.
Utility model content
The technical problems to be solved in the utility model is that the air inlet blade of model aircraft engine does not have autorotation
Function provides a kind of model aircraft engine.
The utility model solves above-mentioned technical problem by the following technical programs:
A kind of model aircraft engine, including air inlet and tail spray；
The air inlet includes more blades, blade fixed frame, the first driving mechanism；
The blade includes moving vane；Moving vane described in multi-disc is scheduled on fixed frame by shaft radioactive solid；
First driving mechanism includes linear drives portion, oppression department, is oppressed portion；The one end of the shaft towards the center of circle
It is fixed with the portion of being oppressed；The linear drives portion driving oppression department linear motion, to drive the portion of being oppressed clockwise or the inverse time
Needle movement drives shaft rotation, swings moving vane；
The tail spray includes that shell is opened in the spray of tubular tail；Multi-disc tail spray blade is fixed in the bottom end that shell is opened in tail spray；Described in multi-disc
Tail spray blade is opened shell bottom end circumferencial direction along tail spray and is arranged successively, and opens the fixed tubular that formed of shell bottom end rotation with tail spray and open and close
Portion；
It further include the second driving mechanism；Second driving mechanism is in tail spray and opens above shell；Second driving mechanism
Including lifting unit, strut portion, traction rope；More blades are connected in one end of the traction rope, and the other end is controlled by lifting unit；Institute
It states the portion of strutting to be fixed on lifting unit, is driven and gone up and down by lifting unit；When the lifting unit rises, traction rope is tightened, driven more
Piece blade bottom end collapses, when decline, traction rope relaxation, and strut subordinate general who has surrendered's more blades distraction reduction.
Preferably, the oppression department includes upper and lower part, and the upper and lower part is the output end in linear drives portion
It is affixed；The maximum height for being oppressed portion to be between upper and lower part, and being oppressed portion is less than the spacing between upper and lower part.
Preferably, the upper and lower part is respectively a circular plate structure, and the two is coaxially fixed on the output of driving portion
On axis.
Preferably, the portion of being oppressed is a triangular prism；Pin hole is offered along triangular prism axis direction, the shaft is through
It is fixed in pin hole；When the moving vane is in former posture, the wherein rib and all pin hole axis co-planars of triangular prism.
Preferably, it is respectively fixed with flank in one end two sides in the shaft towards the center of circle, in the corresponding of upper and lower part
Position is provided with thimble and lower thimble, and all upper thimbles correspond to the flank of all same sides, and all lower thimbles correspond to the other side
All flanks.
Preferably, the fixed bracket of the blade includes outrigger and internal frame, and outrigger and internal frame are cylindrical shape, internal frame and outrigger
Between form annular housing, blade one end is fixed on outrigger, and the other end is fixed on internal frame, more blades in radioactivity arrange
Cloth；The blade further includes fixed blade；The both ends of the fixed blade are affixed with internal frame and outrigger respectively；Described shaft one end
Rotation is fixed on outrigger, and other end rotation is fixed on internal frame and passes through internal frame to internal frame inner cavity.
Preferably, the portion of strutting includes pedestal and fixed at least 2 push rods on the base；The lifting unit is fixed
On the base；Spacing between two push rods is equal to the diameter after the opening and closing part is opened；The lifting unit drops to setting position
It postpones, push rod bottom end is in blade middle and lower part.
Preferably, the coil of wire is fixed on the pedestal, the traction rope winding is on the coil of wire；The coil of wire and a gear
It is coaxial；The gear is engaged with a rack gear；The rack gear is fixed on lifting unit.
Preferably, same circumferential position is provided with threading hole on blade inner wall described in multi-disc, traction rope, which sequentially passes through, to be worn
String holes.
Preferably, the pedestal is round pie, and surrounding is evenly distributed with three push rods；The push rod includes horizontal segment and vertical
Section；Described horizontal segment one end is fixed with pedestal, and the other end and the high-end fixation of vertical section, vertical section bottom end are further fixed on push jack, institute
Push jack is stated to be inclined outwardly from up to down.
Utility model has the advantages that
Oppression department movement is driven by linear drives portion, so that the portion of being oppressed be driven to generate counterclockwise or clockwise turn
It is dynamic, it is driven with this and is rotated with the affixed shaft of moving vane, realize that moving vane generates the movement to swing；
By the way that the portion of being oppressed is arranged between the upper, it is only necessary to which a left side for moving vane can be completed in a driving portion
Right wobbling action.
Being oppressed portion is triangular prism shape, and upper and lower part is respectively acting on wherein digonous, realization moving vane swing；Or by
Oppression department is the flank of shaft two sides, acts on two sides flank respectively by upper thimble and lower thimble, and it is dynamic to realize that moving vane is swung
Make.
By realizing opening and closing part blade automatic open-close by lifting unit, traction rope, the cooperation for strutting portion.
When lifting unit rises with rack gear, by gear drive, the coil of wire is set to rotate take-up, thus by concatenated multi-disc leaf
Piece tightening.When lifting unit decline, draught line unclamps, while strutting subordinate and being down to setting position for more blades distraction reduction.
By being evenly distributed at least two push rod on the base, realization uniformly pushes blade open.
The use of push jack, is obliquely installed by it, and realization only needs push jack and blade contact, reduces frictional force.
Detailed description of the invention
Fig. 1 is the schematic perspective view of the utility model；
Fig. 2 is the utility model along blade fixed frame axial cross-sectional views；
Fig. 3 is the structural schematic diagram of embodiment 1 in the utility model；
Fig. 4 is the structural schematic diagram of the utility model embodiment 2；
Fig. 5 is the structural schematic diagram of tail spray in the utility model.
Specific embodiment
To make the structure feature to the utility model and the effect of being reached has a better understanding and awareness, to compared with
Good examples and drawings cooperate detailed description, are described as follows:
As shown in Figure 1 and Figure 2, a kind of model aircraft engine, including more blades 1, blade fixed frame 2, the first driving machine
Structure 3；
Blade fixed frame 2 includes outrigger 21 and internal frame 22, and outrigger 21 and internal frame 22 are cylindrical shape, internal frame 22 and outrigger
Annular housing is formed between 21,1 one end of blade is fixed on outrigger 21, and the other end is fixed on internal frame 22, and more blades 1 are in
Radioactivity arrangement.Blade 1 protects fixed blade 11 and moving vane 12, and moving vane 12 and the rotation of fixed blade 11 are fixed.Gu
The both ends of fixed blade 11 are affixed with internal frame 22 and outrigger 21 respectively.Moving vane 12 is fixed on outrigger 21 and internal frame by shaft 13
On 22, the rotation of 13 one end of shaft is fixed on outrigger 21, and other end rotation is fixed on internal frame 22 and passes through internal frame 22 to internal frame 22
Inner cavity.
First driving mechanism 3 includes linear drives portion 31, oppression department 32, is oppressed portion 33；Linear drives portion 31 is generally
Cylinder.The one end in shaft 13 towards the center of circle is fixed with the portion of being oppressed 33；Linear drives portion 31 drives oppression department 32 to move along a straight line, from
And drive is oppressed portion 33 and moves clockwise or counterclockwise, and shaft 13 is driven to rotate, and swings moving vane 1.
Oppression department 32 includes top 321 and lower part 322, and top 321 and lower part 322 are respectively a circular plate structure, and two
Person is coaxially fixed on the output shaft of driving portion.It is oppressed portion 33 to be between top 321 and lower part 322, and is oppressed portion 33
Maximum height be less than spacing between top 321 and lower part 322.
Embodiment 1
As shown in figure 3, being oppressed portion 33 is a triangular prism；Pin hole is offered along triangular prism axis direction, shaft 13 is through
It is fixed in pin hole；When moving vane 12 is in former posture, the wherein rib and all pin hole axis co-planars of triangular prism.Multiple trigones
The cross section of column is isosceles triangle.
Embodiment 2
As shown in figure 4, flank 131 is respectively fixed in one end two sides in shaft 13 towards the center of circle, in top 321 and lower part
322 corresponding position is provided with thimble 3211 and lower thimble 3221, the flank of all corresponding all same sides of upper thimble 3211
131, all flanks 131 of all corresponding other sides of lower thimble 3221.When linear drives portion 31 drives oppression department 32 to move downward
When, upper thimble 3211 pushes side flank 131, rotates shaft 13, and when moving upwards, lower thimble 3221 pushes up another flank 131,
Shaft 13 is inverted, is acted on by the top power of upper thimble 3211 and lower thimble 3221, shaft 13 is driven to turn clockwise or counterclockwise
It is dynamic, to realize swinging for moving vane 1.
As shown in figure 5, a kind of model aircraft tail spray, tail spray includes that shell 10 is opened in the spray of tubular tail；The bottom end of shell 10 is opened in tail spray
It is fixed with multi-disc tail spray blade 210；The spray blade 210 of tail described in multi-disc is opened 10 bottom end circumferencial direction of shell along tail spray and is arranged successively, and
The rotation fixation of 10 bottom end of shell, which is opened, with tail spray forms tubular opening and closing part 20；
It further include the second driving mechanism；Second driving mechanism is in tail spray and opens 10 top of shell；Second driving mechanism includes rising
Drop portion 310 struts portion 320, traction rope 330；The lifting unit 310 of the present embodiment is a cylinder.
Strutting portion 320 includes pedestal 3210, and the pedestal 3210 is round pie, and surrounding is evenly distributed at least two push rods
3220.This gives 3 push rods 3220；Diameter after circular diameter and the opening of opening and closing part 20 that 3 push rods 3220 surround
It is equal.Lifting unit 310 is fixed on pedestal 3210；After lifting unit 310 drops to setting position, 3220 bottom end of push rod is in blade
21 middle and lower parts.
The push rod 3220 includes horizontal segment 32210 and vertical section 32220；Described 32210 one end of horizontal segment and pedestal
3210 is fixed, and the other end and the high-end fixation of vertical section 32220,32220 bottom end of vertical section is further fixed on push jack 32230, described to push away
Piece 32230 is inclined outwardly from up to down.
The coil of wire 340 is fixed on the pedestal 3210, the winding of traction rope 330 is on the coil of wire 340；The coil of wire
340 is coaxial with a gear 350；The gear 350 is engaged with a rack gear 360；The rack gear 360 is fixed on lifting unit 310.
Same circumferential position is provided with threading hole on 210 inner wall of blade described in multi-disc, traction rope 330 sequentially passes through threading
More blades 210 are connected in hole, and the other end is wound on gear 350.
Concrete operating principle,
Air inlet: the portion of being oppressed is triangular prism shape, and upper and lower part is respectively acting on wherein digonous, realization moving vane pendulum
It is dynamic；Or the portion of being oppressed is the flank of shaft two sides, acts on two sides flank respectively by upper thimble and lower thimble, realizes moving vane
Wobbling action.
Tail spray: when lifting unit 310 rises with rack gear 360, being driven by gear 350, the coil of wire 340 made to rotate take-up,
To which concatenated more blades 210 be tightened.When lifting unit 310 declines, draught line unclamps, while strutting portion 320 and dropping to
Setting position is by 210 distraction reduction of more blades.
The use of push jack 32230, is obliquely installed by it, and realization only needs push jack 32230 to contact with blade 210, is subtracted
Less friction.
The coil of wire 340 is fixed on pedestal 3210, the winding of traction rope 330 is on the coil of wire 340；The coil of wire 340 and a gear
350 is coaxial；Gear 350 is engaged with a rack gear 360；Rack gear 360 is fixed on lifting unit 310.
Basic principles, main features, and advantages of the present invention has been shown and described above.Current row
The technical staff of industry is described in above embodiments and description it should be appreciated that the present utility model is not limited to the above embodiments
Only the principles of the present invention, the utility model also has respectively on the premise of not departing from the spirit and scope of the utility model
Kind changes and improvements, these changes and improvements are both fallen in the range of claimed invention.The requires of the utility model
Protection scope defined by appended claims and its equivalent.
Claims (10)
1. a kind of model aircraft engine, it is characterised in that: sprayed including air inlet and tail；
The air inlet includes more blades, blade fixed frame, the first driving mechanism；
The blade includes moving vane；Moving vane described in multi-disc is scheduled on fixed frame by shaft radioactive solid；
First driving mechanism includes linear drives portion, oppression department, is oppressed portion；The one end in the shaft towards the center of circle is fixed
It is oppressed portion；The linear drives portion driving oppression department linear motion, so that the portion of being oppressed be driven to transport clockwise or counterclockwise
It is dynamic, shaft rotation is driven, moving vane is swung；
The tail spray includes that shell is opened in the spray of tubular tail；Multi-disc tail spray blade is fixed in the bottom end that shell is opened in tail spray；The spray of tail described in multi-disc
Blade is opened shell bottom end circumferencial direction along tail spray and is arranged successively, and opens the rotation fixation of shell bottom end with tail spray and form tubular opening and closing part；
It further include the second driving mechanism；Second driving mechanism is in tail spray and opens above shell；Second driving mechanism includes
Lifting unit struts portion, traction rope；More blades are connected in one end of the traction rope, and the other end is controlled by lifting unit；The support
The portion of opening is fixed on lifting unit, is driven and is gone up and down by lifting unit；When the lifting unit rises, traction rope is tightened, drives multi-disc leaf
Piece bottom end is collapsed, when decline, traction rope relaxation, and strut subordinate general who has surrendered's more blades distraction reduction.
2. a kind of model aircraft engine according to claim 1, it is characterised in that: the oppression department includes top under
Portion, the upper and lower part are that the output end in linear drives portion is affixed；It is oppressed portion to be between upper and lower part, and is pressed
The maximum height in the portion of compeling is less than the spacing between upper and lower part.
3. a kind of model aircraft engine according to claim 2, it is characterised in that: the upper and lower part is respectively one
Circular plate structure, the two are coaxially fixed on the output shaft of driving portion.
4. a kind of model aircraft engine according to claim 3, it is characterised in that: the portion of being oppressed is a trigone
Column；Pin hole is offered along triangular prism axis direction, the shaft is through in pin hole fixed；The moving vane is in former posture
When, the wherein rib and all pin hole axis co-planars of triangular prism.
5. a kind of model aircraft engine according to claim 3, it is characterised in that: in the shaft towards the one of the center of circle
End two sides are respectively fixed with flank, and the corresponding position of upper and lower part is provided with upper thimble and lower thimble, all upper thimbles pair
Should all same sides flank, all lower thimbles correspond to all flanks of the other side.
6. a kind of model aircraft engine according to any one of claims 1 to 5, it is characterised in that: the fixed branch of the blade
Frame includes outrigger and internal frame, and outrigger and internal frame are cylindrical shape, and annular housing is formed between internal frame and outrigger, and blade one end is fixed
On outrigger, the other end is fixed on internal frame, and more blades are arranged in radioactivity；The blade further includes fixed blade；It is described
The both ends of fixed blade are affixed with internal frame and outrigger respectively；Shaft one end rotation is fixed on outrigger, and other end rotation is solid
It is scheduled on internal frame and passes through internal frame to internal frame inner cavity.
7. a kind of model aircraft engine according to claim 1, it is characterised in that: the portion of strutting include pedestal and
Fixed at least 2 push rods on the base；The lifting unit is fixed on the base；Spacing between two push rods is equal to described open
Diameter after conjunction portion opening；After the lifting unit drops to setting position, push rod bottom end is in blade middle and lower part.
8. a kind of model aircraft engine according to claim 7, it is characterised in that: fixed on the pedestal wired
Volume, the traction rope winding is on the coil of wire；The coil of wire is coaxial with a gear；The gear is engaged with a rack gear；The rack gear
It is fixed on lifting unit.
9. a kind of model aircraft engine according to claim 1, it is characterised in that: same on blade inner wall described in multi-disc
One circumferential position is provided with threading hole, and traction rope sequentially passes through threading hole.
10. a kind of model aircraft engine according to claim 7, it is characterised in that: the pedestal is round pie,
Surrounding is evenly distributed with three push rods；The push rod includes horizontal segment and vertical section；Described horizontal segment one end is fixed with pedestal, the other end with
The high-end fixation of vertical section, vertical section bottom end are further fixed on push jack, and the push jack is inclined outwardly from up to down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820754258.4U CN208834626U (en) | 2018-05-18 | 2018-05-18 | A kind of model aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820754258.4U CN208834626U (en) | 2018-05-18 | 2018-05-18 | A kind of model aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208834626U true CN208834626U (en) | 2019-05-07 |
Family
ID=66304668
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820754258.4U Withdrawn - After Issue CN208834626U (en) | 2018-05-18 | 2018-05-18 | A kind of model aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208834626U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108492708A (en) * | 2018-05-18 | 2018-09-04 | 深圳市沃珂科技有限公司 | A kind of model aircraft engine |
-
2018
- 2018-05-18 CN CN201820754258.4U patent/CN208834626U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108492708A (en) * | 2018-05-18 | 2018-09-04 | 深圳市沃珂科技有限公司 | A kind of model aircraft engine |
| CN108492708B (en) * | 2018-05-18 | 2023-12-26 | 深圳市沃珂科技有限公司 | Aircraft model engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20190507 Effective date of abandoning: 20231226 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20190507 Effective date of abandoning: 20231226 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |