CN1321712C - Rudder plane controlling mechanism for miniature remote controlled model airplane - Google Patents
Rudder plane controlling mechanism for miniature remote controlled model airplane Download PDFInfo
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- CN1321712C CN1321712C CNB2004100773970A CN200410077397A CN1321712C CN 1321712 C CN1321712 C CN 1321712C CN B2004100773970 A CNB2004100773970 A CN B2004100773970A CN 200410077397 A CN200410077397 A CN 200410077397A CN 1321712 C CN1321712 C CN 1321712C
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- rudder
- solenoid
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- electromagnet
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- 230000005674 electromagnetic induction Effects 0.000 claims abstract description 10
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 230000003993 interaction Effects 0.000 abstract description 2
- 239000002390 adhesive tape Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
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Abstract
The present invention relates to a rudder surface control mechanism of a miniature remote-control aeromodelling plane, which has the technical scheme that a V-shaped tail wing with a left rudder surface and a right rudder surface are arranged at the back end of a tail tube of a plane body, wherein the V-shaped tail wing is hinged with the tail tube of the plane body by tail wing brackets; the left rudder surface and the right rudder surface are respectively hinged with the back end of the V-shaped tail wing; and electromagnetic induction devices which can remotely control the rudder surfaces of an aeromodelling plane to move are arranged between the left rudder surface and the right rudder surface, and the corresponding tail wing brackets of the left rudder surface and the right rudder surface. Due to the adoption of the electromagnetic induction devices which can remotely control the rudder surfaces of the aeromodelling plane to move, wobble angles of the left rudder surface and the right rudder surface are adjusted by using the principle of the interaction of a pair of energized electromagnetic coils and electromagnets adjacent to the rudder surfaces, and thereby, the functions of the left steering, the right steering and the turning of the aeromodelling plane are realized. When the electromagnetic coils are not energized, because of the action of the mutually exclusive acting force of the electromagnets which are arranged on the left rudder surface and the right rudder surface, the rudder surfaces of the tail wing are still in the state of symmetric centrality so as to guarantee the straight-line flight of the aeromodelling plane.
Description
Technical field
The present invention relates to the rudder plane controlling mechanism of a kind of remote controlled model airplane, particularly a kind of miniature remote controlled model of an airplane.
Background technology
At present, the rudder plane controlling mechanism of remote-controlled model aircraft is mostly controlled by steering wheel, existing steering wheel all is to adopt pulse signal control usually, the servo-drive system of forming by motor decelerating mechanism and feedback circuit, rotating disk and connecting rod by steering wheel drive the rudder face motion, the shortcoming of this rudder face control mode is: comprise motor in the steering wheel, circuit board, parts such as gear-box, make the load of miniplane heavier, manufacturing cost is also than higher simultaneously, and now in miniature aeromodelling airplane, the outstanding problem that is faced is exactly the overall weight that how to alleviate aircraft, and the problem that reduces manufacturing cost, the solution of the problems referred to above is directly connected to further carrying out of aeromodelling airplane motion.Chinese patent CN2560404Y discloses the automatically reset aeromodelling airplane empennage of a kind of rudder face energy, its main points are: " being connected with a spring leaf between the stabilization of aircraft tail and steering vane; backguy one end of its control steering vane is fixed on the steering vane, and the other end is connected on the steering wheel that is arranged in the aeromodelling airplane fuselage ".This technical scheme is still prolonged and has been used conventional rudder face behaviour to draw unit principle by the control of fuselage steering wheel, though than structurally comparatively simple in the prior art, it is many not overcome the transmission mechanism that mechanical handling self exists, and cuts loading and the high deficiency of manufacturing cost.
Summary of the invention
Technical problem to be solved by this invention is: a kind of rudder plane controlling mechanism according to the simple light of electromagnetic induction principle design and the miniature remote controlled model airplane that is easy to control is provided.
Technical scheme of the present invention is: a kind of rudder plane controlling mechanism of miniature remote controlled model airplane, comprise the band left rudder face that is installed on fuselage tail pipe rear end and the vee tail of right standard rudder face, described vee tail is hinged by empennage support and fuselage tail pipe, described left rudder face and right standard rudder face are hinged with the vee tail rear end respectively, it is characterized in that being provided with between described left rudder face and right standard rudder face and its pairing empennage support electromagnetic induction device that can make the action of aeromodelling airplane rudder face by remote control, above-mentioned electromagnetic induction device comprises left rudder solenoid and the right standard rudder solenoid that is arranged on the empennage support and is arranged at the left rudder face respectively and the left electromagnet of right standard rudder face and right electromagnet, wherein:
Above-mentioned left rudder solenoid and right standard rudder solenoid are the both sides that are fixed on the empennage support of symmetry respectively, and can under positive and negative two different directions functions of current that receiver sends, make the N-S magnetic pole of left rudder solenoid and right standard rudder solenoid two ends generation by the respective direction conversion.
Above-mentioned left electromagnet and right electromagnet are installed on left rudder face and the right standard rudder face position over against left rudder solenoid and right standard rudder solenoid respectively, the surface of the corresponding solenoid of described two permanent magnets should be N level or S level simultaneously, and residing left rudder face of above-mentioned two permanent magnets and the formed angle of right standard rudder face upper surface should be less than 180 °.
The electromagnetic induction device that can the aeromodelling airplane rudder face be moved by remote control that the present invention owing to adopted is provided with between the left rudder face of vee tail and right standard rudder face and empennage support, by utilizing near rudder face a pair of energising solenoid and the interaction principle of electromagnet, to a left side, the adjustment of right standard rudder face pendulum angle, thereby realized turning to about aeromodelling airplane, the function of turning round, and when solenoid is not switched on, owing to be arranged on a left side, the active force effect that electromagnet on the right standard rudder face repels mutually, make the empennage rudder face be in a kind of symmetry all the time and return middle state, guaranteed the rectilinear flight of model plane mould aircraft.
Description of drawings
The present invention is further illustrated below in conjunction with accompanying drawing.
Fig. 1 is a structural representation of the present invention.
Fig. 2 is that the K of Fig. 1 is to structural representation.
Rudder face and empennage backing positions schematic diagram when Fig. 3 does not switch on for solenoid of the present invention.
Schematic diagram when Fig. 4 is Fig. 3 state.
Position view when Fig. 5 lifts for left rudder face of the present invention.
Fig. 6 is the electromagnetic action schematic diagram of Fig. 5.
Position view when Fig. 7 lifts for right standard rudder face of the present invention.
Fig. 8 is the electromagnetic action schematic diagram under Fig. 7 state.
The specific embodiment
The present invention as shown in Figure 1 and Figure 2, a kind of rudder plane controlling mechanism of miniature remote controlled model airplane, comprise the band left rudder face 4 that is installed on fuselage tail pipe rear end and the vee tail 10 of right standard rudder face 5, described vee tail 10 is hinged by empennage support 1 and fuselage tail pipe, described left rudder face 4 and right standard rudder face 5 are hinged with vee tail 10 rear ends respectively, are provided with the electromagnetic induction device that can make the action of aeromodelling airplane rudder face by remote control between described left rudder face 4 and right standard rudder face 5 and its pairing empennage support 1.
Above-mentioned electromagnetic induction device comprises left rudder solenoid 2 and the right standard rudder solenoid 3 that is arranged on the empennage support 1 and is arranged at left rudder face 4 respectively and the left electromagnet 6 of right standard rudder face 5 and right electromagnet 7, wherein:
Above-mentioned left rudder solenoid 2 is the symmetrical both sides that are fixed on empennage support 1 respectively with right standard rudder solenoid 3, and can under positive and negative two different directions functions of current that receiver sends, make the N-S magnetic pole of left rudder solenoid 2 and right standard rudder solenoid 3 two ends generation by the respective direction conversion.
Above-mentioned left electromagnet 6 and right electromagnet 7 are installed on left rudder face 4 and right standard rudder face 5 position over against left rudder solenoid 2 and right standard rudder solenoid 3 respectively, the surface of the corresponding solenoid of described two permanent magnets should be N level or S level simultaneously, and residing left rudder face 4 of above-mentioned two permanent magnets and the formed angle of right standard rudder face 5 upper surfaces should be less than 180.
Above-mentioned left electromagnet 6 is that its identical top projection of material is circular electromagnet with right electromagnet 7.
Above-mentioned left rudder face 4 and the right standard rudder face 5 used hinges that are hinged with vee tail 10 rear ends respectively are an adhesive tape.
Above fixing empennage support 1 rear portion tail pipe, be provided with and adjust the bolt 8 that rudder face lifts angle.
Further version of the present invention and operation principle, as Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, shown in Figure 8:
Comprise a V-shaped empennage support 1, left rudder solenoid 2, right standard rudder solenoid 3, left rudder face 4, right standard rudder face 5, left side electromagnet 6, right electromagnet 7, rudder face angle adjustment bolt 8 and adhesive tape 9, wherein: V-shaped empennage support 1 is fixed on the rear end of fuselage tail pipe, left rudder solenoid 2, right standard rudder solenoid 3 respectively fixedly embedding be formed on the left and right sides of vee tail support 1, left rudder face 4, right standard rudder face 5 is hinged by rudder face adhesive tape 9 and vee tail 10 respectively, above-mentioned left electromagnet 6, right electromagnet 7 is installed on the rudder face of the left and right sides position over against coil respectively, and each electromagnet can be swung around adhesive tape together with rudder face, above-mentioned left electromagnet 6, right electromagnet 7 is to be circular by two top projections, material is identical, placing on left rudder face 4 and the right standard rudder face 5 of two electromagnet symmetries that surface polarity is also identical, and with aircraft longitudinal axis line vertical symmetry.Above-mentioned left electromagnet 6, the upper surface of right electromagnet 7 should be N level or S level simultaneously.The course of work of the present invention and principle such as Fig. 3, shown in Figure 4, when not to the left and right sides rudder face remote operation, left and right sides solenoid does not all have electric current to pass through, because close together between the electromagnet of the left and right sides, and the upper surface mutual alignment is less than 180 °, produce mutual repulsive force between the electromagnet of the left and right sides described this moment, left and right sides rudder face is pressed in respectively on the vee tail support, and then middle state is returned in maintenance, when implementing remote operation adjustment left rudder face, as Fig. 5, shown in Figure 6, receiver sends the signal of telecommunication after receiving instruction, make in the left rudder solenoid 2 and produce forward current, produce reversing the current in the right standard rudder solenoid 3, form S level magnetic field on left rudder solenoid 2 surfaces this moment, right standard rudder solenoid 3 surfaces produce N level magnetic field, because left electromagnet 6 lower surface magnetic poles are the S level, so the time and left rudder solenoid 2 between produce the active force that repels mutually, effect bottom left electromagnet 6 drive left rudder faces 4 at magnetic force upward deflect, thereby the implementation model aircraft turns round to the right, otherwise, as Fig. 7, shown in Figure 8, the signal of telecommunication of receiving when receiver makes left rudder solenoid 2 produce reversing the current, and right standard rudder solenoid 3 is when producing forward currents, the model of an airplane can be realized the action of right standard rudder face 5, and its operation principle is identical with left rudder face 4.
Claims (3)
1. the rudder plane controlling mechanism of a miniature remote controlled model airplane, comprise the band left rudder face (4) that is installed on fuselage tail pipe rear end and the vee tail (10) of right standard rudder face (5), described vee tail (10) is hinged by empennage support (1) and fuselage tail pipe, described left rudder face (4) and right standard rudder face (5) are hinged with vee tail (10) rear end respectively, it is characterized in that being provided with between described left rudder face (4) and right standard rudder face (5) and its pairing empennage support (1) electromagnetic induction device that can make the action of aeromodelling airplane rudder face by remote control, above-mentioned electromagnetic induction device comprises left rudder solenoid (2) and the right standard rudder solenoid (3) that is arranged on the empennage support (1) and is arranged at left rudder face (4) respectively and the left electromagnet (6) of right standard rudder face (5) and right electromagnet (7), wherein:
Between above-mentioned left rudder solenoid (2) and right standard rudder solenoid (3) for connecting, described left rudder solenoid (2) is the symmetrical both sides that are fixed on empennage support (1) respectively with right standard rudder solenoid (3), and can be under positive and negative two different directions functions of current that receiver sends, make left rudder solenoid (2) and right standard rudder solenoid (3) two ends produce the N-S magnetic pole of pressing the respective direction conversion
Above-mentioned left electromagnet (6) and right electromagnet (7) are installed on left rudder face (4) and right standard rudder face (5) position over against left rudder solenoid (2) and right standard rudder solenoid (3) respectively, the surface of the corresponding solenoid of described two permanent magnets should be N level or S level simultaneously, and residing left rudder faces of above-mentioned two permanent magnets (4) and the formed angle of right standard rudder face (5) upper surface should be less than 180.
2. rudder plane controlling mechanism according to claim 1 is characterized in that above-mentioned left electromagnet (6) is circular electromagnet with right electromagnet (7) for its identical top projection of material.
3. rudder plane controlling mechanism according to claim 1 is characterized in that fixedly being provided with the bolt (8) that can adjust rudder face and lift angle above the tail pipe of empennage support (1) rear portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100773970A CN1321712C (en) | 2004-12-17 | 2004-12-17 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100773970A CN1321712C (en) | 2004-12-17 | 2004-12-17 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1636616A CN1636616A (en) | 2005-07-13 |
| CN1321712C true CN1321712C (en) | 2007-06-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004100773970A Expired - Fee Related CN1321712C (en) | 2004-12-17 | 2004-12-17 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
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| CN (1) | CN1321712C (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102078695B (en) * | 2010-11-10 | 2012-07-25 | 黄宇嵩 | Simulation run debugging device for model airplane steering engine |
| CN102229357B (en) * | 2011-05-12 | 2013-07-03 | 北京航空航天大学 | Empennage with installing angle and adjustable horizontal tail |
| CN106669165A (en) * | 2015-11-07 | 2017-05-17 | 马铿杰 | Steering gear simulation operation debugger |
| CN108241463B (en) * | 2018-01-02 | 2021-02-12 | 京东方科技集团股份有限公司 | Control method and control device of projection device and projection device |
| CN108674633A (en) * | 2018-07-25 | 2018-10-19 | 北京因时机器人科技有限公司 | Rudder plane controlling mechanism and model plane |
| CN110460298A (en) * | 2019-06-28 | 2019-11-15 | 常州中信博新能源科技有限公司 | Adjustable solar photovoltaic bracket |
| CN111377060B (en) * | 2020-03-23 | 2022-06-10 | 南京航空航天大学 | Mechanical arm based on pneumatic control surface and working method thereof |
| CN114558329B (en) * | 2022-02-11 | 2024-06-14 | 东莞市飞翼电子科技有限公司 | Steering control structure of model airplane |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2431026Y (en) * | 2000-07-14 | 2001-05-23 | 上海合朗电子有限公司 | Electric remote-controlled aircraft |
| JP2001190861A (en) * | 2000-01-12 | 2001-07-17 | Akuson Data Machine Kk | Control device for posture of radio control type model plane |
| CN2560404Y (en) * | 2002-07-09 | 2003-07-16 | 楼英俊 | Model airplane tail surface capable of automatically resetting rudder |
| CN1522778A (en) * | 2003-09-05 | 2004-08-25 | 广西梧州温特自动化工程有限公司 | Model helicopter rotor control mechanism |
| CN2642378Y (en) * | 2003-08-05 | 2004-09-22 | 廖煜晴 | Electromagnetic drive rudder-face device |
| FR2852857A1 (en) * | 2003-03-25 | 2004-10-01 | Franck Maurice Higuet | Aircraft rotor blade inclination control device, has actuator with pair of solenoids controlled by control unit and situated in symmetrical manner with respect to self-propelled axis of rotation |
-
2004
- 2004-12-17 CN CNB2004100773970A patent/CN1321712C/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001190861A (en) * | 2000-01-12 | 2001-07-17 | Akuson Data Machine Kk | Control device for posture of radio control type model plane |
| CN2431026Y (en) * | 2000-07-14 | 2001-05-23 | 上海合朗电子有限公司 | Electric remote-controlled aircraft |
| CN2560404Y (en) * | 2002-07-09 | 2003-07-16 | 楼英俊 | Model airplane tail surface capable of automatically resetting rudder |
| FR2852857A1 (en) * | 2003-03-25 | 2004-10-01 | Franck Maurice Higuet | Aircraft rotor blade inclination control device, has actuator with pair of solenoids controlled by control unit and situated in symmetrical manner with respect to self-propelled axis of rotation |
| CN2642378Y (en) * | 2003-08-05 | 2004-09-22 | 廖煜晴 | Electromagnetic drive rudder-face device |
| CN1522778A (en) * | 2003-09-05 | 2004-08-25 | 广西梧州温特自动化工程有限公司 | Model helicopter rotor control mechanism |
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| Publication number | Publication date |
|---|---|
| CN1636616A (en) | 2005-07-13 |
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| C14 | Grant of patent or utility model | ||
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Owner name: GUANGDONG AOFEI CARTOON CULTURE CO., LTD. Free format text: FORMER OWNER: CAI DONGQING Effective date: 20071228 |
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Effective date of registration: 20071228 Address after: The middle of the road. Audi Industrial Park of Chenghai District of Guangdong city in Shantou Province Patentee after: Guangdong Alpha Animation and Culture Co., Ltd. Address before: The middle of the road. Audi Industrial Park of Chenghai District of Guangdong city in Shantou Province Patentee before: Cai Dongqing |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20070620 Termination date: 20101217 |