CN103372321A - Auxiliary propeller folding mechanism of model airplane glider - Google Patents
Auxiliary propeller folding mechanism of model airplane glider Download PDFInfo
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- CN103372321A CN103372321A CN 201210120296 CN201210120296A CN103372321A CN 103372321 A CN103372321 A CN 103372321A CN 201210120296 CN201210120296 CN 201210120296 CN 201210120296 A CN201210120296 A CN 201210120296A CN 103372321 A CN103372321 A CN 103372321A
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- connecting rod
- auxiliary propeller
- fixture
- dynamical element
- pin joint
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Abstract
An auxiliary propeller folding mechanism of a model airplane glider comprises a steering engine and an auxiliary propeller, wherein the steering engine comprises an oscillating arm, the auxiliary propeller is connected with an output shaft of a power element, the power element is connected with a machine body through a parallel four-connection-bar mechanism, the steering engine is fixed in the machine body, and the oscillating arm is connected with any one connection bar in the parallel four-connection-bar mechanism. A position sensor is arranged at the tail end of the stroke of the power element, the first connection bar or the second connection bar and is connected with the control end of a controller or the steering engine through a signal line. The steering engine drives the parallel four-connection-bar mechanism, and the auxiliary propeller and the power element can contract in the machine body or protrude out of the machine body. In the powerless gliding flight process, the auxiliary propeller and the power element contract in the machine body, and accordingly the aerodynamic performance of the machine body can be remarkably improved, resistance can be reduced and the glider hang time can be prolonged.
Description
Technical field:
The present invention relates to mechanical field, relate in particular to fly able model airplane, the particularly aerodone in the model airplane, concrete is a kind of auxiliary propeller fold mechanism of model plane aerodone.
Background technology:
In the prior art, machine towing before the model plane aerodone does not have in the lift-off process needs to rely on self power could arrive the height that glides.Therefore; model plane aerodone of the prior art all is provided with dynamical element and auxiliary propeller; in take-off process, start auxiliary propeller; help model plane aerodone arrival glide height or enter ascending air; after the model plane aerodone arrives the glide height or enters ascending air; close again dynamical element, realize unpowered gliding flight.But in unpowered gliding flight process, auxiliary propeller is subject to air drag, and impact is glided, and has reduced the hang time of aerodone.
Summary of the invention:
The object of the present invention is to provide a kind of auxiliary propeller fold mechanism of model plane aerodone, the auxiliary propeller fold mechanism of described this model plane aerodone will solve auxiliary propeller impact glide, the technical problem of minimizing aerodone hang time of model plane aerodone in the prior art.
The auxiliary propeller fold mechanism of this model plane aerodone of the present invention comprises a steering wheel and an auxiliary propeller; include a swing arm in the described steering wheel; described auxiliary propeller is connected with the output shaft of a dynamical element; wherein; one end of described dynamical element and a first connecting rod is hinged; dynamical element is hinged with an end of a second connecting rod again; the other end of described first connecting rod and a fixture are hinged; the other end of described second connecting rod is also hinged with described fixture; line between the pin joint of the pin joint of dynamical element and first connecting rod and dynamical element and second connecting rod; line between the pin joint of the pin joint of dynamical element and second connecting rod and second connecting rod and fixture; line between the pin joint of the pin joint of second connecting rod and fixture and first connecting rod and fixture; line between the pin joint of the pin joint of first connecting rod and fixture and dynamical element and first connecting rod consists of parallelogram; described steering wheel is relative with fixture fixing, and the swing arm in the steering wheel is connected with first connecting rod or second connecting rod by driving member.
Further, the end of the stroke of described dynamical element, first connecting rod or second connecting rod is provided with a position sensor, described position sensor is connected by the control end of holding wire with a controller or steering wheel, and described controller is connected with the control end of steering wheel.
Further, described position sensor is made of a microswitch.
Further, be fixedly installed an extension arm on the described second connecting rod, an end of described extension arm and an end of described driving member are hinged, and an end of the other end of driving member and described swing arm is hinged.
Further, described extension arm and second connecting rod are lever construction, and the fulcrum of lever is the pin joint of second connecting rod and fixture.
Further, described position sensor is fixedly installed on the described fixture.
Operation principle of the present invention is: steering wheel and fixture all are arranged in the fuselage of model plane aerodone; when the swing arm of operation steering wheel swings; swing arm driving dynamical element, first connecting rod or second connecting rod upwards rotate, and dynamical element and auxiliary propeller are moved to outside the fuselage.During the swing arm backswing of operation steering wheel, swing arm driving dynamical element, first connecting rod or second connecting rod rotate, and dynamical element and auxiliary propeller are moved in the fuselage axially the remaining unchanged of auxiliary propeller.Position sensor can prevent that dynamical element is excessively mobile, thus the protection fuselage.
Concrete, also fold mechanism can be set between auxiliary propeller and the dynamical element, the fold mechanism of auxiliary propeller and dynamical element is prior art, does not repeat them here.
The present invention and prior art are compared, and its effect is actively with obvious.The present invention is connected by a parallel four-bar linkage auxiliary propeller and the dynamical element thereof of model plane aerodone with fuselage; utilize a servo driving parallel four-bar linkage, auxiliary propeller and dynamical element thereof are collapsible in fuselage or protrude into outside the fuselage.In unpowered gliding flight process, auxiliary propeller and dynamical element thereof are contracted in the fuselage, can significantly improve the aerodynamic performance of fuselage, reduce resistance, prolong the aerodone hang time.
Description of drawings:
Fig. 1 is the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention schematic diagram when outstanding in the model plane aerodone.
Fig. 2 is the schematic diagram of the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention when shrinking in the model plane aerodone.。
Fig. 3 is that the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention is at the schematic diagram of dynamical element end of travel position.
Fig. 4 is that the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention is at the schematic diagram of contraction state.
Fig. 5 is the course of action schematic diagram of the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention.
Fig. 6 is another course of action schematic diagram of the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention.
The specific embodiment:
Embodiment 1:
Such as Fig. 1; Fig. 2; Fig. 3; Fig. 4; Fig. 5 and shown in Figure 6; the auxiliary propeller fold mechanism of a kind of model plane aerodone of the present invention; comprise a steering wheel 1 and an auxiliary propeller 9; include a swing arm 11 in the described steering wheel 1; described auxiliary propeller 9 is connected with the output shaft of a dynamical element 2; wherein; one end of described dynamical element 2 and a first connecting rod 3 is hinged; dynamical element 2 is hinged with an end of a second connecting rod 4 again; the other end of described first connecting rod 3 and a fixture 5 are hinged; the other end of described second connecting rod 4 is also hinged with described fixture 5; line between the pin joint of the pin joint of dynamical element 2 and first connecting rod 3 and dynamical element 2 and second connecting rod 4; line between the pin joint of the pin joint of dynamical element 2 and second connecting rod 4 and second connecting rod 4 and fixture 5; line between the pin joint of the pin joint of second connecting rod 4 and fixture 5 and first connecting rod 3 and fixture 5; line between the pin joint of the pin joint of first connecting rod 3 and fixture 5 and dynamical element 2 and first connecting rod 3 consists of parallelogram; described steering wheel 1 is relative fixing with fixture 5, and the swing arm 11 in the steering wheel 1 is connected with first connecting rod 3 or second connecting rod 4 by driving member 7.
Further, the end of the stroke of described dynamical element 2, first connecting rod 3 or second connecting rod 4 is provided with a position sensor 6, described position sensor 6 is connected by the control end of holding wire with a controller (not shown) or steering wheel 1, and described controller is connected with the control end of steering wheel 1.
Further, described position sensor 6 is made of a microswitch.
Further, be fixedly installed an extension arm 41 on the described second connecting rod 4, an end of described extension arm 41 and an end of described driving member 7 are hinged, and an end of the other end of driving member 7 and described swing arm 11 is hinged.
Further, described extension arm 41 is lever construction with second connecting rod 4, and the fulcrum of lever is the pin joint of second connecting rod 4 and fixture 5.
Further, described position sensor 6 is fixedly installed on the described fixture 5.
The course of work of present embodiment is: steering wheel 1 and fixture 5 all are arranged in the fuselage 8 of model plane aerodone; when the swing arm 11 of operation steering wheel 1 swings; swing arm 11 drives dynamical element 2, first connecting rod 3 or second connecting rod 4 and upwards rotates, and dynamical element 2 and auxiliary propeller 9 are moved to outside the fuselage 8.During swing arm 11 backswing of operation steering wheel 1, swing arm 11 drives dynamical elements 2, first connecting rod 3 or second connecting rod 4 and rotates, and dynamical element 2 and auxiliary propeller 9 is moved in the fuselage 8 axially the remaining unchanged of auxiliary propeller 9.Position sensor 6 can prevent that dynamical element 2 is excessively mobile, thus protection fuselage 8.
Claims (6)
1. the auxiliary propeller fold mechanism of a model plane aerodone; comprise a steering wheel and an auxiliary propeller; include a swing arm in the described steering wheel; described auxiliary propeller is connected with the output shaft of a dynamical element; it is characterized in that: an end of described dynamical element and a first connecting rod is hinged; dynamical element is hinged with an end of a second connecting rod again; the other end of described first connecting rod and a fixture are hinged; the other end of described second connecting rod is also hinged with described fixture; line between the pin joint of the pin joint of dynamical element and first connecting rod and dynamical element and second connecting rod; line between the pin joint of the pin joint of dynamical element and second connecting rod and second connecting rod and fixture; line between the pin joint of the pin joint of second connecting rod and fixture and first connecting rod and fixture; line between the pin joint of the pin joint of first connecting rod and fixture and dynamical element and first connecting rod consists of parallelogram; described steering wheel is relative with fixture fixing, and the swing arm in the steering wheel is connected with first connecting rod or second connecting rod by driving member.
2. the auxiliary propeller fold mechanism of a kind of model plane aerodone as claimed in claim 1; it is characterized in that: the end of the stroke of described dynamical element, first connecting rod or second connecting rod is provided with a position sensor; described position sensor is connected by the control end of holding wire with a controller or steering wheel, and described controller is connected with the control end of steering wheel.
3. the auxiliary propeller fold mechanism of a kind of model plane aerodone as claimed in claim 2, it is characterized in that: described position sensor is made of a microswitch.
4. the auxiliary propeller fold mechanism of a kind of model plane aerodone as claimed in claim 1; it is characterized in that: be fixedly installed an extension arm on the described second connecting rod; one end of described extension arm and an end of described driving member are hinged, and an end of the other end of driving member and described swing arm is hinged.
5. the auxiliary propeller fold mechanism of a kind of model plane aerodone as claimed in claim 4, it is characterized in that: described extension arm and second connecting rod are lever construction, and the fulcrum of lever is the pin joint of second connecting rod and fixture.
6. the auxiliary propeller fold mechanism of a kind of model plane aerodone as claimed in claim 2, it is characterized in that: described position sensor is fixedly installed on the described fixture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201210120296 CN103372321A (en) | 2012-04-23 | 2012-04-23 | Auxiliary propeller folding mechanism of model airplane glider |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201210120296 CN103372321A (en) | 2012-04-23 | 2012-04-23 | Auxiliary propeller folding mechanism of model airplane glider |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103372321A true CN103372321A (en) | 2013-10-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201210120296 Pending CN103372321A (en) | 2012-04-23 | 2012-04-23 | Auxiliary propeller folding mechanism of model airplane glider |
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| Country | Link |
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| CN (1) | CN103372321A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109080826A (en) * | 2018-08-23 | 2018-12-25 | 深圳市华力航空科技有限公司 | It is a kind of can folding and unfolding power device motor glider and parachute active control system |
| KR101967091B1 (en) * | 2018-01-11 | 2019-04-08 | 부산대학교 산학협력단 | Reducing drag force Hybrid Unmanned Aerial Vehicle |
| CN114715804A (en) * | 2022-03-31 | 2022-07-08 | 三一海洋重工有限公司 | Detection device and engineering machinery |
-
2012
- 2012-04-23 CN CN 201210120296 patent/CN103372321A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101967091B1 (en) * | 2018-01-11 | 2019-04-08 | 부산대학교 산학협력단 | Reducing drag force Hybrid Unmanned Aerial Vehicle |
| CN109080826A (en) * | 2018-08-23 | 2018-12-25 | 深圳市华力航空科技有限公司 | It is a kind of can folding and unfolding power device motor glider and parachute active control system |
| CN109080826B (en) * | 2018-08-23 | 2022-04-19 | 深圳市华力航空科技有限公司 | Electric glider and parachute active control system with retractable power device |
| CN114715804A (en) * | 2022-03-31 | 2022-07-08 | 三一海洋重工有限公司 | Detection device and engineering machinery |
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Application publication date: 20131030 |