CN211987088U - Electric free-flying gyroidal battle airplane model airplane - Google Patents
Electric free-flying gyroidal battle airplane model airplane Download PDFInfo
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- CN211987088U CN211987088U CN202020459529.0U CN202020459529U CN211987088U CN 211987088 U CN211987088 U CN 211987088U CN 202020459529 U CN202020459529 U CN 202020459529U CN 211987088 U CN211987088 U CN 211987088U
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Abstract
The utility model discloses an electronic free flight gyre battle aircraft model aeroplane and model ship, including the main part of aircraft model aeroplane and model ship, be used for the auxiliary body to remove the descending shock attenuation and remove the structure, be used for the auxiliary body to carry out the collapsible formula fin structure that the collapsible formula wing mechanism that flies and be used for the auxiliary body to fly, the top of main part is being close to its one side edge department and is installing driving motor, driving motor's output department fixed mounting has propeller blade, just propeller blade keeps away from in the main part, the top of main part is being close to in driving motor department and installs the battery, shock attenuation is removed the structrual installation in the bottom of main part, but collapsible formula wing structrual installation is close to in its intermediate position in the front and back both sides. The utility model discloses convenient to use can improve electronic component's protection effect in to the main part through the buffering shock attenuation, simultaneously, when not using the model airplane, can accomodate the protection to the fin, avoids carelessly causing the rupture of fin to damage.
Description
Technical Field
The utility model relates to an aeromodelling field specifically is an electronic free flight gyrocompass aircraft model aeroplane and model ship.
Background
The aviation model is a general term of various aircraft models, including model airplanes and other model aircrafts, and the aviation model activity has attracted people's interest from the beginning and is prosperous for hundreds of years, mainly because it plays an important role in the development of aviation industry and the cultivation of scientific talents, and the electric free-flight rotary combat aircraft model is one of the models.
However, the existing electric free-fly gyrocompass airplane model has the following disadvantages:
1. when the model airplane is landed and contacts with the ground, a large impact force can be generated, various electronic components are installed in the model airplane, and the electronic components are easily damaged by the large impact force, so that the service life of the model airplane is shortened.
2. When the model airplane is not used, the wings and the empennage of the model airplane are not convenient to store and protect, so that the wings and the empennage are easily broken and damaged, and unnecessary loss is caused.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an electronic free flight gyrocompass aircraft model, in order to solve traditional electronic free flight gyrocompass aircraft model when model aeroplane and model ship descends and ground contact, can produce great impact force, and install various electronic component in the model aeroplane and model ship, great impact force fragile arrives these electronic component, thereby reduce the life of model aeroplane and model ship, and when not using the model aeroplane and model ship, be not convenient for accomodate the protection to the wing and the fin of model aeroplane and model ship, thereby easily lead to wing and fin rupture to damage, cause unnecessary problem of loss.
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an electronic free flight gyroidal battle aircraft model aeroplane and model ship, includes the main part of aircraft model aeroplane and model ship, is used for the auxiliary body to remove the shock attenuation removal structure that descends, is used for the auxiliary body to carry out the collapsible formula wing mechanism that flies and is used for the auxiliary aircraft to carry out the collapsible formula fin structure that flies, the top of main part is being close to its one side edge department and is installing driving motor, driving motor's output end department fixed mounting has propeller blade, just propeller blade keeps away from in the main part, the top of main part is being close to near installing the battery in driving motor department, the shock attenuation is removed the structure and is installed in the bottom of main part, but collapsible formula wing structrual installation is close to in its intermediate position in the front and back both sides of main part, collapsible formula fin structru.
Preferably, the shock attenuation is removed the structure and is included a plurality of damping spring and a plurality of universal wheel, and is a plurality of damping spring all fixed mounting is in the bottom of main part, and is a plurality of the top of universal wheel respectively with a plurality of damping spring's bottom fixed connection.
Preferably, a plurality of the damping springs are internally provided with telescopic connecting rods.
Preferably, collapsible formula wing structure includes two first fins and two first fastening knobs, the inside of main part is being close to and is being offered the first groove of accomodating that runs through both sides around it in its intermediate position department, two first fin is respectively through the first groove department of accomodating of installed part movable mounting in both sides around the main part, two first fastening knob runs through the bottom of main part, and two through threaded connection respectively first fastening knob runs through the one end of main part bottom and the bottom butt of two first fins.
Preferably, collapsible formula fin structure includes two second fins and two second fastening knobs, the inside of main part is being close to one side of propeller blade and has been seted up and run through its front and back both sides second and accomodate the groove, two the second fin is respectively through the second of installed part movable mounting in both sides around the main part and accomodates groove department, two second fastening knob runs through the bottom of main part, and two through threaded connection respectively second fastening knob runs through the one end of main part bottom and the bottom butt of two second fins.
Preferably, a plurality of the telescopic connecting rods are made of plastic materials.
The utility model provides an electronic free flight gyrocompass aircraft model aeroplane and model ship that flies back possesses following beneficial effect:
(1) the utility model discloses a be provided with the shock attenuation and remove the structure for the in-process that descends is carried out in the main part, can carry out effectual buffering shock attenuation through spring fit telescopic link to the impact force that produces when universal wheel and ground contact, thereby has reduced the impact force that electronic component received in the main part, has avoided causing the damage to electronic component because of vibrations, has prolonged the life of model airplane then.
(2) The utility model discloses a be provided with collapsible formula wing structure and collapsible formula fin structure for after the aviation model uses up, can accomodate first fin and second fin as far as possible to first groove and the second groove of accomodating through loosening first fastening knob and second fastening knob, reduce the volume that first fin and second fin expose outside, thereby the effectual condition of breaking damage appearing in first fin and second fin of having avoided then, avoided causing the unnecessary loss.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
fig. 2 is a schematic top view of the present invention;
FIG. 3 is an enlarged schematic view taken at A in FIG. 1;
FIG. 4 is an enlarged view of the point B in FIG. 1;
fig. 5 is an enlarged schematic view of the point C in fig. 1.
In the figure: 1. a main body; 2. a drive motor; 3. a propeller blade; 4. a storage battery; 5. a damping spring; 6. a universal wheel; 7. a telescopic connecting rod; 8. a first fin; 9. a first fastening knob; 10. a first receiving groove; 11. a mounting member; 12. a second fin; 13. a second fastening knob; 14. a second receiving groove.
Detailed Description
The technical solution in 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.
As shown in fig. 1-5, the utility model provides a technical solution: an electric free-flying gyroidal battle airplane model comprises a main body 1 of the airplane model, a damping moving structure for assisting the main body 1 to move and land, a retractable wing mechanism for assisting the main body 1 to fly and a retractable empennage structure for assisting the airplane to fly, the top of the main body 1 is provided with a driving motor 2 near one side edge thereof, the output end of the driving motor 2 is fixedly provided with a propeller blade 3, and the propeller blades 3 are far from the main body 1, the top of the main body 1 is mounted with a storage battery 4 near the driving motor 2, the damping moving structure is arranged at the bottom of the main body 1, the retractable wing structures are arranged at the front side and the rear side of the main body 1 close to the middle position of the main body, the retractable tail structure is installed at both front and rear sides of the main body 1 near the propeller blades 3.
The damping moving structure comprises a plurality of damping springs 5 and a plurality of universal wheels 6, the damping springs 5 are all fixedly mounted at the bottom of the main body 1, and the tops of the universal wheels 6 are respectively fixedly connected with the bottoms of the damping springs 5, so that when the main body 1 descends, impact force generated when the universal wheels 6 are contacted with the ground can be buffered and damped by the aid of the damping springs 5 in cooperation with the telescopic connecting rods 7, impact force on the main body 1 is buffered and damped, electronic components in the main body 1 are effectively prevented from being damaged by large impact force, and the service life of the whole main body 1 is prolonged;
the telescopic connecting rods 7 are arranged in the damping springs 5, so that the springs are prevented from being deformed and damaged due to large impact force when the main body 1 descends, and the service life of the springs is prolonged;
the retractable wing structure comprises two first wing pieces 8 and two first fastening knobs 9, first accommodating grooves 10 penetrating through the front side and the rear side of the main body 1 are formed in the position, close to the middle position, of the inner part of the main body 1, the two first wing pieces 8 are movably arranged at the first accommodating grooves 10 at the front side and the rear side of the main body 1 through mounting pieces 11 respectively, the two first fastening knobs 9 are connected through the bottom of the main body 1 through threads respectively, and two of said first fastening knobs 9, which penetrate one end of the bottom of the body 1, abut the bottom of the two first flaps 8, so that after use of the body 1, the first fastening knob 9 can be loosened, the two first tabs 8 are received as far as possible in the first receiving grooves 10, the volume of the first wing piece 8 exposed outside the main body 1 is reduced, so that the situation that the first wing piece 8 is broken and damaged by carelessness is effectively avoided;
the retractable tail structure comprises two second flaps 12 and two second fastening knobs 13, a second accommodating groove 14 penetrating through the front and rear sides of the main body 1 is formed in one side of the main body 1 close to the propeller blade 3, two second fins 12 are movably mounted at the second accommodating grooves 14 on the front and rear sides of the main body 1 through mounting pieces 11, two second fastening knobs 13 are connected through the bottom of the main body 1 through threads, and two of said second fastening knobs 13, which penetrate one end of the bottom of the main body 1, abut the bottom of two second wings 12, so that after the use of the main body 1, the second fastening knobs 13 can be fastened to the second receiving grooves 14 by loosening, receiving the two second wings 12 into the second receiving grooves 14, the volume of the second wing piece 12 exposed outside the main body 1 is reduced, so that the situation that the second wing piece 12 is broken and damaged by carelessness is effectively avoided;
the telescopic connecting rods 7 are all made of plastic materials, the weight of the plastic materials is light, and normal flight of the model airplane is prevented from being influenced.
The working principle is as follows: when the model airplane is used, the driving motor 2 can be started by matching the wireless external remote controller with the storage battery 4 and the screw propeller blades 3 to push the main body 1 to be matched with the universal wheel 6 to move until the main body 1 flies up, and when the main body 1 is subsequently landed, the impact force generated when the universal wheel 6 is contacted with the ground can be buffered and damped by matching the damping springs 5 with the telescopic connecting rods 7, so that the impact force applied to the main body 1 can be buffered and damped, the electronic components in the main body 1 are effectively prevented from being damaged by large impact force, the service life of the whole main body 1 is prolonged, after the main body 1 is used, the two first fins 8 can be accommodated into the first accommodating groove 10 as much as possible by loosening the first fastening knob 9 and the second fastening knob 13, and the two second fins 12 can be accommodated into the second accommodating groove 14, reduce first fin 8 and the second fin 12 and expose at the outside volume size of main part 1, first fin 8 and the second fin 12 after accomodating are fixed to the first fin 8 and the second fin 12 of rethread first fastening knob 9 and second fastening knob 13 at last to the condition of damage of careless rupture appears in first fin 8 and second fin 12 has effectually been avoided, avoids appearing unnecessary loss.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides an electronic free flight gyrocompass aircraft model aeroplane and model ship, includes main part (1) of aircraft model aeroplane and model ship, is used for auxiliary body (1) to remove the shock attenuation of landing and removes the structure, is used for auxiliary body (1) to carry out the collapsible formula wing mechanism that flies and is used for auxiliary aircraft to carry out the collapsible formula fin structure that flies, its characterized in that: the top of main part (1) is being close to its one side edge and is installing driving motor (2), the output department fixed mounting of driving motor (2) has propeller blade (3), just propeller blade (3) are kept away from in main part (1), the top of main part (1) is being close to and is being located to install battery (4) in driving motor (2), the shock attenuation removes the structure and installs in the bottom of main part (1), but retractable wing structrual installation is close to in its intermediate position in both sides around main part (1), both sides are close to in propeller blade (3) department around retractable tail wing structrual installation in main part (1).
2. An electric free-fly gyrocompass airplane model as defined in claim 1, wherein: the shock attenuation is removed the structure and is included a plurality of damping spring (5) and a plurality of universal wheel (6), and is a plurality of damping spring (5) equal fixed mounting is in the bottom of main part (1), and is a plurality of the top of universal wheel (6) respectively with the bottom fixed connection of a plurality of damping spring (5).
3. An electric free-fly gyrocompass airplane model as defined in claim 2, wherein: and telescopic connecting rods (7) are arranged in the damping springs (5).
4. An electric free-fly gyrocompass airplane model as defined in claim 1, wherein: collapsible formula wing structure includes two first wings (8) and two first fastening knobs (9), the inside of main part (1) is being close to and is being offered the first groove (10) of accomodating that runs through both sides around it in its intermediate position department, two first wing (8) are respectively through first groove (10) department of accomodating of installed part (11) movable mounting in both sides around main part (1) first fastening knob (9) run through the bottom of main part (1) through threaded connection respectively, and two first fastening knob (9) run through the one end of main part (1) bottom and the bottom butt of two first wings (8).
5. An electric free-fly gyrocompass airplane model as defined in claim 1, wherein: collapsible formula fin structure includes two second fins (12) and two second fastening knobs (13), the inside of main part (1) is being close to one side of propeller blade (3) and has been seted up and run through its front and back both sides second and accomodate groove (14), two groove (14) department, two are accomodate to second fin (12) through the second of installed part (11) movable mounting in main part (1) front and back both sides respectively second fastening knob (13) run through the bottom of main part (1) through threaded connection respectively, and two second fastening knob (13) run through the one end of main part (1) bottom and the bottom butt of two second fins (12).
6. An electric free-fly gyrocompass airplane model as defined in claim 3, wherein: the telescopic connecting rods (7) are all made of plastic materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020459529.0U CN211987088U (en) | 2020-04-01 | 2020-04-01 | Electric free-flying gyroidal battle airplane model airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020459529.0U CN211987088U (en) | 2020-04-01 | 2020-04-01 | Electric free-flying gyroidal battle airplane model airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211987088U true CN211987088U (en) | 2020-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020459529.0U Expired - Fee Related CN211987088U (en) | 2020-04-01 | 2020-04-01 | Electric free-flying gyroidal battle airplane model airplane |
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| CN (1) | CN211987088U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115089976A (en) * | 2022-07-14 | 2022-09-23 | 代海超 | Aviation model in aviation sports |
-
2020
- 2020-04-01 CN CN202020459529.0U patent/CN211987088U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115089976A (en) * | 2022-07-14 | 2022-09-23 | 代海超 | Aviation model in aviation sports |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201124 |
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| CF01 | Termination of patent right due to non-payment of annual fee |