CN108392834B - Model airplane structure - Google Patents
Model airplane structure Download PDFInfo
- Publication number
- CN108392834B CN108392834B CN201810448107.0A CN201810448107A CN108392834B CN 108392834 B CN108392834 B CN 108392834B CN 201810448107 A CN201810448107 A CN 201810448107A CN 108392834 B CN108392834 B CN 108392834B
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- Prior art keywords
- adapter
- wing
- main body
- main
- rod piece
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- 230000003014 reinforcing effect Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 240000007182 Ochroma pyramidale Species 0.000 claims description 3
- 230000001154 acute effect Effects 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000003044 adaptive effect Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 3
- 238000004806 packaging method and process Methods 0.000 abstract description 2
- 230000005611 electricity Effects 0.000 description 5
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 230000006978 adaptation Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000001338 self-assembly Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/02—Model aircraft
Landscapes
- Toys (AREA)
Abstract
The invention provides a model airplane structure. The invention comprises the following steps: the aircraft body uses main part member as the truss, connects each main part member through the adapter and realizes the fastening of main part, the aircraft body head, stand tail, main wing and fin respectively through preset adapter with the main part is connected and is fastened, main wing and fin respectively through anchor clamps fastening in on main part and the stand tail, steering mechanism links to each other with main wing or fin. The invention can be assembled and disassembled by itself, is convenient for transportation and storage, and the scattered rod parts are also convenient for packaging, the main body structure is hollow, the installation and the replacement of electronic devices are convenient, the framework is a square truss, the structure is firm, and the invention can be widely popularized in the field of model aircrafts based on the reasons.
Description
Technical Field
The invention relates to the field of airplane models, in particular to a model airplane structure.
Background
The model airplane has the characteristics of simple structure, convenient production and self-assembly on the basis of knowing the overall appearance, and is very popular with consumers. The existing model airplane is mostly formed integrally, only electronic components are needed to be installed, the installation is simple, the body size is too large, the model airplane is not suitable for consumers who intentionally build the model airplane from scratch, the space structure of the model airplane can not bear the impact, and a stronger structural form is necessary to use.
Disclosure of Invention
According to the technical problems, the model airplane structure is simple in structure, capable of being assembled by itself and firm and durable.
The invention adopts the following technical means:
the utility model provides a model aeroplane and model ship aircraft structure, includes fuselage main part, organism head, found tail, main wing, fin, steering mechanism and is used for providing power and adjustment for the model aeroplane and model ship aircraft the power unit that steering mechanism turned to, the fuselage main part uses the main part member as the truss, connects each main part member through the adapter and realizes the fastening of fuselage main part, organism head, found tail, main wing and fin respectively through preset adapter with the fuselage main part is connected and is fastened, main wing and fin respectively through anchor clamps fastening in on fuselage main part and the found tail, steering mechanism links to each other with main wing or fin.
Further, the main body of the machine body is composed of a main body rod piece which is connected by an adapter I and is distributed along the machine body direction and a connecting rod piece which is perpendicular to the main body rod piece, the head of the main body is connected with the front end of the truss through an adapter II, the vertical tail is connected with the rear end of the truss through an adapter III and an adapter IV, the adapter III is provided with a through hole which is matched with the vertical tail rod piece and two openings which are vertically arranged, an acute angle formed by the through hole and the main body rod piece is alpha in a vertical plane, the adapter IV is provided with three openings, wherein the two openings are vertically arranged, an obtuse angle formed by the other opening and the main body rod piece is beta in a vertical plane, and alpha+beta=180 DEG
Further, the main wing is fastened on the truss through the clamp I, the clamp I comprises a clamp plate I used for fastening the main wing, a fixing rod piece used for fixing the clamp plate I, a rectangular plate I used for preventing the main wing from shaking left and right and the adapter I, the upper end and the lower end of the adapter I are respectively provided with a through hole for adapting the main rod piece and an opening perpendicular to the through hole and used for adapting the horizontal direction of the connecting rod piece, the square groove for adapting the fixing rod piece is further formed, the main wing is arranged below the fixing rod piece, the rectangular plate I is arranged above the main wing and between the two fixing rod pieces, the clamp plate I is arranged above the fixing rod piece, and all parts of the clamp I are fastened through adhesive fastening or bolting.
Further, the adaptor I is symmetrically arranged in pairs, so that the square grooves are located at different heights, namely a preset angle gamma exists between the main wing and the horizontal plane, and gamma is larger than 0 degrees.
Further, the fin passes through anchor clamps II fasten in on standing the fin, anchor clamps II including be used for tightly fixing the splint II of fin, be used for prescribing a limit to adapter V of splint II position and be used for preventing fin back and forth rocking rectangular plate II and rectangular plate III, open slot is seted up to adapter V upper end, still sets up the opening that adaptation found the tail member and the opening of the horizontal direction of adaptation connection member, lay in the open slot and be used for consolidating adapter V and enlarge its and fin area of contact's reinforcement member, splint II pass through adapter V fasten in connection member top, rectangular plate I and rectangular plate II fasten respectively in connect member the place ahead and the rear, pass through adhesive fastening or bolted connection fastening between each part of anchor clamps II.
Further, three openings are formed in the adapter II, any two of the three openings are perpendicular to each other, a head front plate is arranged at the front end of a frame formed by the adapter II and the connecting rod piece in a surrounding mode, and a head rear plate is arranged at the rear end of the frame.
Further, the power unit includes battery, electricity transfers, motor, screw, steering wheel and with remote controller assorted acceptor, battery, electricity transfer, the acceptor is built-in the fuselage main part and be fixed in on the fixed plate that the fuselage main part truss is inside to be set up, the motor passes through the motor cabinet to be fixed on the main part head front bezel, screw precession motor main shaft and fasten through the nut, the steering wheel is arranged in on the trailing edge of main wing and fin, electricity transfer respectively with acceptor, motor and battery link to each other, the acceptor respectively with electricity and steering wheel link to each other, the acceptor passes through the steering wheel drive steering mechanism turns to and passes through electricity transfer driving motor in order to drive screw rotation.
Further, the steering mechanism comprises an aileron, a lifting wing, a rudder angle and a rudder stock, wherein the aileron and the lifting wing are respectively connected with the main wing and the tail wing through plane hinges, the rudder angle is embedded into the aileron and the lifting wing, one end of the rudder stock is connected with the rudder angle, and the other end of the rudder stock is connected with the steering engine.
Further, the rod pieces all use carbon fiber tubes, and the plates all use balsawood plates.
The invention can be assembled and disassembled by itself, is convenient for transportation and storage, and the scattered rod parts are also convenient for packaging, the main body structure is hollow, the installation and the replacement of electronic devices are convenient, the framework is a square truss, the structure is firm, and the invention can be widely popularized in the field of model aircrafts based on the reasons.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to the drawings without inventive effort to a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of the head of the body of the present invention;
FIG. 3 is an exploded view of the head structure of the body of the present invention;
FIG. 4 is a schematic view of a fuselage body and main wing section of the present invention;
FIG. 5 is an exploded view of the main body and main wing portion structure of the present invention;
FIG. 6 is a schematic view of a vertical tail portion of the present invention;
FIG. 7 is an exploded view of the vertical tail section of the present invention;
FIG. 8 is a schematic view of a tail section of the present invention;
FIG. 9 is an exploded view of the tail section of the present invention;
FIG. 10 is a schematic view of the steering mechanism on the aileron and lifting wing of the present invention;
FIG. 11 is an exploded view of the steering mechanism of the present invention;
fig. 12 is a schematic view of a power mechanism of the present invention.
In the figure: 101. a nut; 102. a propeller; 103. a screw; 104. a motor; 105. a head front plate; 106. an adapter II; 107. a connecting rod piece; 108. a head rear plate; 109. tightening a nut; 201. a main body rod piece; 202. an adapter I; 203. a main wing; 204. a clamping plate I; 205. a rectangular plate I; 206. a fixed rod piece; 301. adapter IV; 302. an adapter III; 303. setting up tail; 401. an adapter V; 402. a tail wing; 403. a clamping plate II; 404. reinforcing the rod piece; 405. a rectangular plate II; 406. a rectangular plate III; 501. aileron; 502. lifting wings; 503. plane hinges; 504. steering engine; 505. a rudder stock; 506. rudder angle; 601. a receiver; 602. electrically regulating; 603. a battery; 604. and a fixing plate.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1, a model airplane structure comprises a main body, a main body head, a vertical tail 303, a main wing 203, a tail wing 402, a steering mechanism and a power mechanism for providing power for the model airplane and adjusting the steering mechanism to steer, wherein the main body uses main body rods 201 as trusses, the main body rods 201 are connected through adapters to realize the fastening of the main body, the main body head, the vertical tail 303, the main wing 203 and the tail wing 402 are respectively connected and fastened with the main body through preset adapters, the main wing 203 and the tail wing 402 are respectively fastened on the main body and the vertical tail 303 through clamps, and the steering mechanism is connected with the main wing 203 or the tail wing 402.
As shown in fig. 2-7, the main body of the airframe is composed of a main body rod 201 which is connected by an adapter i 202 and is arranged along the airframe direction and a connecting rod 107 which is perpendicular to the main body rod, the main body head is connected with the front end of the truss through an adapter ii 106, the vertical tail 303 is connected with the rear end of the truss through an adapter iii 302 and an adapter iv 301, the adapter iii 302 is provided with a through hole which is adapted to the vertical tail rod 303 and two openings which are vertically arranged, in the vertical plane, the acute angle formed by the through hole and the main body rod 201 is alpha, the adapter iv 301 is provided with three openings, two openings are vertically arranged, in the vertical plane, the obtuse angle formed by the other opening and the main body rod 201 is beta, and alpha+beta=180°.
The main wing 203 is fastened on the truss through the clamp I, the clamp I comprises a clamping plate I204 used for fastening the main wing 203, a fixing rod piece 206 used for fixing the clamping plate I204, a rectangular plate I205 used for preventing the main wing 203 from swinging left and right and the adapter I202, through holes for adapting the main rod piece 201 and openings perpendicular to the through holes in the horizontal direction of the adapting connection rod piece 107 are formed in the upper end and the lower end of the adapter I202, square grooves for adapting the fixing rod piece 206 are formed in the lower portion of the fixing rod piece 206, the main wing 203 is arranged below the fixing rod piece 206, the rectangular plate I205 is arranged above the main wing 203 and between the two fixing rod pieces 206, the rectangular plate I205 is long as the chord length of the main wing 203, the rectangular plate I205 can be clamped by means of inclined surfaces of the front and rear pairs of the adapter I202, the rectangular plate I205 is wide as the distance between the inner sides of the two fixing rod pieces 206, the inner sides of the fixing rod piece 206 can be clamped by means of the inner sides of the fixing rod piece 206, the thickness of the rectangular plate I205 can be flush with the upper side and the right fixing rod piece 206 and the lower side of the rectangular plate 206. The upper parts of the two fixing rods 206 are provided with a rectangular plate with a larger size, namely a clamping plate I204, the length is the chord length of the main wing 203, the two pairs of front and rear connectors I202 are clamped by means of inclined surfaces, the width is the distance between the outer side walls of the two fixing rods 206, and thus the two fixing rods 206 can be completely covered, and the clamping plate I204 prevents the main wing 203 from falling. The clamping plate I204 is arranged above the fixed rod 206, and all parts of the clamp I are fastened through adhesive fastening or bolting. The adapter I202 is arranged in a pairwise symmetrical mode, is arranged back and forth in the length direction, is connected left and right through the connecting rod piece 107, penetrates through four main body rod pieces 201 on the machine body, the front and back arranged adapter I202 inclines at the same certain angle on the inner side face, square grooves are formed in the inclined faces respectively, the machine body is provided with two pairs of adapter I202, which are respectively clamped with fixed rod pieces 206 in equal length, the grooves are correspondingly formed in the mode that the fixed rod pieces 206 are perpendicular to the inclined faces of the adapter I202 after insertion, and the square plates are placed conveniently. A preset angle gamma is present between the main wing 203 and the horizontal plane, and gamma is larger than 0 deg.
The lengths of the exposed parts of the fixing rod pieces 206 at the two adapter joints I202 are equal to the chord length of the main wing 203, and the front adapter joint I and the rear adapter joint I202 clamp the main wing 203 left and right by means of inclined planes so that the main wing 203 is clamped at a certain angle with the horizontal plane.
As shown in fig. 8 and 9, the tail fin 402 is fastened on the vertical tail 303 by a clamp ii, where the clamp ii includes a clamping plate ii 403 for fastening the tail fin 402, an adapter v 401 for limiting the position of the clamping plate ii 403, and a rectangular plate ii 405 and a rectangular plate iii 406 for preventing the tail fin 402 from rocking back and forth, the upper end of the adapter v 401 is provided with a through slot, and the opposite side is also provided with a groove, and the opposite side is connected by a connecting rod 107 with the same embedded specification. The through groove is internally provided with a reinforcement rod 404 for reinforcing the adapter V401 and enlarging the contact area between the adapter V401 and the tail fin 402, and the clamping plate II 403 is fastened above the connecting rod 107 through the adapter V401 and outside the channel of the adapter V401, so that the two adapter V401 can clamp the clamping plate II 403 under the assembly of the connecting rod 107, the front and back dimensions of the clamping plate II 403 are in the range of the channel of the adapter V401, and the upper and lower dimensions are flush with the outside of the channel of the adapter V401. Two small-size rectangular plates II 405 and III 406 are placed in front of and behind the lower sides of the channels of the two adapter V401, the rectangular plates II 405 and III 406 are respectively fastened in front of and behind the connecting rod piece 107, the width direction is flush with the outer side wall of the channels of the adapter V401, the rectangular plates II 405 and III 406 are clamped on two sides of the lower extending ends of the adapter V401, the front ends of the rectangular plates II 405 are flush with the front ends of the channels of the adapter V401, and the rear ends of the rectangular plates III 406 are flush with the rear ends of the channels of the adapter V401. The tail wing plate 402 is placed on the upper side of the groove of the adapter V401, and all parts of the clamp II of the tail wing plate 402 are fastened through adhesive fastening or bolt connection.
Three openings are formed in the adapter II 106, any two of the three openings are perpendicular to each other, square holes with a certain depth are formed in each head for embedding and fixing of carbon tubes, the four adapters II 106 are mutually connected in pairs through connecting rods 107 to form a square frame for clamping, a front head plate 105 is arranged at the front end of the frame surrounded by the adapter II 106 and the connecting rods 107, a rear head plate 108 is arranged at the rear end of the frame, square notches in projection positions of vertical notches of the adapter II 106 are formed in four corners of the rear head plate 108, the rear head plate 108 can be embedded into the four adapters II 106 and attached to the square frame, the front head plate 105 can completely cover the periphery of the whole square frame, compared with notches in the four corners of the rear head plate 108, the rear head plate 108 and the front head plate 105 are perforated in corresponding positions according to the hole positions of a motor base of the motor 104, a screw 103 and a tightening nut 109 are matched and fastened, the motor base is fixed on the front head plate 105, a screw 102 is installed on the motor base, and a motor 104 is screwed on the shaft of the motor base, and the motor base is screwed into the through the hexagonal nut 101 and the front head plate 105.
As shown in fig. 12, the power mechanism includes a battery 603, an electric motor 602, a motor 105, a propeller 102, a steering engine 504 and a receiver 601 matched with the remote controller, the battery 603, the electric motor 602 and the receiver 601 are built in a main body of the main body and are fixed on a fixing plate 604 erected inside a truss of the main body, the motor 105 is fixed on the front plate 105 of the head of the main body through a motor base, the propeller 102 is screwed into a main shaft of the motor 104 and fastened through a nut 101, the steering engine 504 is arranged on the rear edges of the main wing 203 and the tail wing 402, the electric motor 602 is respectively connected with the receiver 601, the motor 104 and the battery 603, the receiver 601 is respectively connected with the electric motor 602 and the steering engine 504, and the steering engine 601 drives the steering mechanism to steer through the steering engine 504 and drives the motor 104 to rotate through the electric motor 602.
As shown in fig. 10 and 11, the steering mechanism comprises an aileron 501, a lifting wing 502, a rudder angle 506 and a rudder bar 505, wherein the aileron 501 and the lifting wing 502 are respectively connected with the main wing 203 and the tail wing 402 through a plane hinge 503, the rudder angle 506 is embedded in the aileron 501 and the lifting wing 502, one end of the rudder bar 505 is connected with the rudder angle 506, and the other end is connected with the steering engine 504. Two movable leaves of the hinge 503 are respectively adhered to the main wing 203 and the aileron 501 to realize the up-and-down rotation of the aileron 501 along the rear edge of the main wing 203. The rotating driving part is powered by a steering engine 504, one end of a steering lever 505 is connected with a rotating arm of the steering engine 504, the other end is connected with one corner of a steering angle 506, the bottom surface of the steering angle 506 is adhered to an aileron 501, the steering engine 504 rotates, the steering lever 505 drives the steering angle 506, the steering angle 506 is then linked with the aileron 501, and the connection mode of the tail wing 402 and the lifting wing 502 is also the same.
The rod pieces all use carbon fiber tubes, and the plates all use balsawood plates.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (7)
1. A model airplane structure, comprising: the aircraft comprises an aircraft body, an aircraft body head, a vertical tail, a main wing, an empennage, a steering mechanism and a power mechanism for providing power for a model airplane and adjusting steering of the steering mechanism, wherein the aircraft body uses main body rods as trusses, the main body rods are connected through adapters to realize fastening of the aircraft body, the aircraft body head, the vertical tail, the main wing and the empennage are respectively connected and fastened with the aircraft body through preset adapters, the main wing and the empennage are respectively fastened on the aircraft body and the vertical tail through clamps, and the steering mechanism is connected with the main wing or the empennage; the clamp comprises a clamp I and a clamp II;
the main body of the machine body is composed of a main body rod piece which is connected by an adapter I and is arranged along the machine body direction and a connecting rod piece which is perpendicular to the main body rod piece, the head of the main body is connected with the front end of the truss through an adapter II, the vertical tail is connected with the rear end of the truss through an adapter III and an adapter IV, the adapter III is provided with a through hole which is adaptive to the vertical tail rod piece and two openings which are vertically arranged, an acute angle formed by the through hole and the main body rod piece is alpha in a vertical plane, the adapter IV is provided with three openings, the two openings are vertically arranged, and an obtuse angle formed by the other opening and the main body rod piece is beta in the vertical plane, and alpha plus beta=180 degrees;
the fixture I comprises a clamping plate I used for fixing the main wing, a fixing rod piece I used for fixing the clamping plate I and an adapter I, wherein the upper end and the lower end of the adapter I are respectively provided with a through hole for adapting to the main body rod piece and an opening perpendicular to the through hole and used for adapting to the horizontal direction of the connecting rod piece, and the adapter I is also provided with a square groove for adapting to the fixing rod piece.
2. A model aircraft structure according to claim 1, wherein a predetermined angle γ is present between the main wing and the horizontal plane, 0 ° < γ.
3. The model airplane structure according to claim 1, wherein the adapter II is provided with three openings, any two of the three openings are mutually perpendicular, a front head plate is arranged at the front end of a frame formed by the adapter II and the head rod piece in a surrounding mode, and a rear head plate is arranged at the rear end of the frame.
4. The model airplane structure according to claim 1, wherein the tail fin is fastened on the vertical tail fin through a clamp II, the clamp II comprises a clamping plate II used for fastening the tail fin, an adapter V used for limiting the position of the clamping plate II, and a rectangular plate I and a rectangular plate II used for preventing the tail fin from shaking back and forth, a through groove is formed in the upper end of the adapter V, a groove is formed in the opposite side of the adapter V, the through groove is internally provided with a reinforcing rod used for reinforcing the adapter V and enlarging the contact area between the adapter V and the tail fin, the clamping plate II is fastened above the connecting rod through the adapter V and outside a channel of the adapter V, and the rectangular plate I and the rectangular plate II are respectively fastened in front of and behind the connecting rod.
5. The model airplane structure according to claim 1, wherein the power mechanism comprises a battery, an electric regulator, a motor, a propeller, a steering engine and a receiver matched with the remote controller, the battery, the electric regulator and the receiver are arranged in a main body of the airplane body and are fixed on a plate erected inside a truss of the main body of the airplane body, the motor is fixed on a front plate of the head of the main body through a motor seat, the propeller is screwed into a motor main shaft and fastened through a nut, the steering engine is arranged on the rear edges of a main wing and a tail wing, the electric regulator is respectively connected with the receiver, the motor and the battery, the receiver is respectively connected with the electric regulator and the steering engine, and the receiver drives the steering mechanism to turn through the steering engine and drives the motor through the electric regulator to drive the propeller to rotate.
6. A model airplane structure according to claim 1, characterized in that the steering mechanism comprises an aileron, a lifting wing, a rudder angle and a rudder stock, wherein the aileron and the lifting wing are respectively connected with the main wing and the tail wing through plane hinges, the rudder angle is embedded in the aileron and the lifting wing, one end of the rudder stock is connected with the rudder angle, and the other end is connected with a steering engine.
7. A model airplane structure according to any one of claims 1-6, characterized in that the bars are all carbon fiber tubes and the plates are all balsawood plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810448107.0A CN108392834B (en) | 2018-05-11 | 2018-05-11 | Model airplane structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810448107.0A CN108392834B (en) | 2018-05-11 | 2018-05-11 | Model airplane structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108392834A CN108392834A (en) | 2018-08-14 |
| CN108392834B true CN108392834B (en) | 2023-11-14 |
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ID=63100978
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810448107.0A Active CN108392834B (en) | 2018-05-11 | 2018-05-11 | Model airplane structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN108392834B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109157847B (en) * | 2018-11-06 | 2023-11-24 | 大连理工大学 | Fixed wing aeromodelling structure based on carbon rod and installation method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000061166A (en) * | 1998-08-25 | 2000-02-29 | Sega Enterp Ltd | Toy airplane |
| CN2619696Y (en) * | 2003-04-07 | 2004-06-09 | 程智斌 | Electric remote-controlled model aircraft |
| KR200398303Y1 (en) * | 2005-07-22 | 2005-10-13 | (주)아카데미과학교재사 | A model plane |
| CN1750860A (en) * | 2003-02-21 | 2006-03-22 | 纽罗斯株式会社 | Rear wing structure for remote-controlled flight assuring fast and stable turning |
| CN2915205Y (en) * | 2006-01-18 | 2007-06-27 | 罗之洪 | Aeromodelling |
| CN103538714A (en) * | 2013-11-06 | 2014-01-29 | 张明 | Vertical take-off and landing model aircraft unmanned aerial vehicle |
| CN207187114U (en) * | 2017-07-19 | 2018-04-06 | 深圳弘惠科技创新有限公司 | The plane toy that a kind of double vertical type tails are formed |
| CN208212530U (en) * | 2018-05-11 | 2018-12-11 | 大连理工大学 | A kind of aeromodelling airplane structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8382030B2 (en) * | 2010-09-02 | 2013-02-26 | Patrick A. Kosheleff | Variable cycle VTOL powerplant |
-
2018
- 2018-05-11 CN CN201810448107.0A patent/CN108392834B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000061166A (en) * | 1998-08-25 | 2000-02-29 | Sega Enterp Ltd | Toy airplane |
| CN1750860A (en) * | 2003-02-21 | 2006-03-22 | 纽罗斯株式会社 | Rear wing structure for remote-controlled flight assuring fast and stable turning |
| CN2619696Y (en) * | 2003-04-07 | 2004-06-09 | 程智斌 | Electric remote-controlled model aircraft |
| KR200398303Y1 (en) * | 2005-07-22 | 2005-10-13 | (주)아카데미과학교재사 | A model plane |
| CN2915205Y (en) * | 2006-01-18 | 2007-06-27 | 罗之洪 | Aeromodelling |
| CN103538714A (en) * | 2013-11-06 | 2014-01-29 | 张明 | Vertical take-off and landing model aircraft unmanned aerial vehicle |
| CN207187114U (en) * | 2017-07-19 | 2018-04-06 | 深圳弘惠科技创新有限公司 | The plane toy that a kind of double vertical type tails are formed |
| CN208212530U (en) * | 2018-05-11 | 2018-12-11 | 大连理工大学 | A kind of aeromodelling airplane structure |
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| Publication number | Publication date |
|---|---|
| CN108392834A (en) | 2018-08-14 |
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