CN200951320Y - Remote controlled airplane - Google Patents
Remote controlled airplane Download PDFInfo
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- CN200951320Y CN200951320Y CN 200620051220 CN200620051220U CN200951320Y CN 200951320 Y CN200951320 Y CN 200951320Y CN 200620051220 CN200620051220 CN 200620051220 CN 200620051220 U CN200620051220 U CN 200620051220U CN 200951320 Y CN200951320 Y CN 200951320Y
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- fuselage
- wing
- control device
- rudder face
- wings
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Abstract
A remote control airplane comprises an airframe (1), a main wing (2), a power supply (3), a driving device (4), a receiving and control device of remote signal (5), and a control surface of aileron and a control device of control surface (6) which are connected with each other. Two wings (8) are symmetrically arranged at both sides of the airframe. The driving device (4) is arranged in airframe (1); the power supply (3) is arranged in the airframe (1). The utility model is characterized in that at least one direction rear control (7) is arranged at the end of trunk of the airframe (1). A power control system is formed by the connection between the remote signal receiving and control device (5) and the driving device (4), the control surface of aileron and the control device of control surface (6) or/and the rear control (7). The main wing (2) consists of at least two wings (8). One end of the wing (8) is connected with the airframe (1) into a whole. The other end of the wing (8) is connected with each other into a whole. The plane is applicable to various aviation flying shows and special technical flying shows.
Description
(1) technical field
The utility model relates to a kind of telecontrolled aircraft.
(2) background technology
At present, along with the development of society and the development of aeronautical technology, the development of model plane motion has also received personages of various circles of society's concern, and increasing people join in the model plane cause.Many various aeromodelling airplanes have also appearred on the market, but become a kind of main flow trend to the telecontrolled aircraft development of the free flight of no electric wire connection by the aircraft that can in subrange, fly that has power line to connect, for example the patent No. of the Cheng Zhibin in Yongkang, Zhejiang Province city invention is ZL03230187.1, the utility model that name is called " the electric remote control model of an airplane " discloses a kind of electric remote control model of an airplane, be specially a kind of fuselage that comprises, main wing, front-wheel, the fuselage fibre pipe, empennage, trailing wheel and power set and remote control, main wing is fixed on the fuselage, fuselage fibre pipe and fuselage are fixed, empennage is fixed on the afterbody of fuselage fibre pipe, empennage is by a left side, a right stabilization and a left side, the right standard rudder face is formed, between left rudder face and the left stabilization and between right standard rudder face and the right stabilization, the bonding flakiness of upper and lower surface is flexible coupling, empennage becomes the remote-controlled model aircraft scheme of V font structure, this model of an airplane can be realized climbing by receiver received signal and operating aircraft, descend, turn to and function such as flying speed, control and easy to operate, flying quality is good, be connected firmly, the good advantage of crashproof and windproof performance, but only depend on the fuselage fibre pipe to connect between this model of an airplane fuselage main body and the tail, and the change of its flight control mainly realizes by empennage, make the easy unstability of the model of an airplane, fuselage fibre pipe easy deformation when model of an airplane flight is in wind particularly, a little less than making whole model of an airplane wind resistance flight performance, and, the lift that main wing provides is limited, the power that power set are provided can not get comprehensive utilization, therefore, develop a kind of novel telecontrolled aircraft for being badly in need of.
(3) utility model content
The purpose of this utility model is to provide a kind of telecontrolled aircraft, have good integrity, flight stability, wind resistance good, turn to and landing is quick on the draw fast, fuselage light and handy, can realize characteristics such as various aerobatics easily, particularly its security performance is outstanding.
Solution of the present utility model is on the basis of existing technology, draw together by fuselage, main wing, power supply, drive unit, the remote signal receiving control device, aileron rudder face and rudder face control device interconnect composition, two wings are symmetricly set on the fuselage both sides, drive unit is arranged on the fuselage, power supply is arranged in the fuselage, it is characterized in that being provided with at least one direction tail vane at the trunk tail end of fuselage, remote signal receiving control device and drive unit, aileron rudder face and rudder face control device are or/and tail vane connects into the power control system, main wing is combined by at least two wings, one end and the fuselage of wing connect into integral body, and the other end is interconnected to integral body.Like this, power supply can provide the energy for the flight and the control of aircraft, because main wing is combined by at least two wings, increased the airfoil lift area of aircraft, one end and the fuselage of wing connect into integral body, the other end connects into integral body, make main wing in flight course, be difficult for deformed damaged, and can give full play to the gliding ability of aircraft, make aircraft when power supply is used up, rely on the glide stable landing, make aircraft not fragile, simultaneously, interlock by the aileron rudder face on the main wing and differentially control turning to and lifting of aircraft, cancelled traditional empennage that upwarps, significantly reduced the level of aircraft when the making a stunt flying resistance that rolls, make aircraft can be flexibly tumbling flight freely, and, remote signal receiving control device and drive unit, aileron rudder face and rudder face control device are or/and rudder connects into the power control system, can very easily realize the landing of aircraft and make various acceleration, slow down, underriding is rolled, acrobatic maneuvers such as direction finding drift, and main wing is combined by at least two wings, one end and the fuselage of wing connect into integral body, the other end is interconnected to the whole globality that has then increased substantially aircraft, even make aircraft that characteristics such as collision is not fragile yet be arranged in the middle of the landing process, thereby reached the purpose of this utility model, be applicable to various aviation flight performance and acrobatic maneuver.
Feature of the present utility model is that also described main wing is combined by two wings, two wing upper and lower settings, at least one flap is arranged in the middle of above-mentioned two wings, one end of flap extends into fore-body and connects into integral body with fuselage 1, the other end be interconnected in end and wing end integral body or by the wing slightly side plate the end of flap and wing is connected into integral body.Like this, main wing is combined by two wings, two wing upper and lower settings, at least one flap is arranged in the middle of above-mentioned two wings and near the fore-body position and with fuselage and connects into integral body, the wing slightly then by the wing slightly side plate the flap and the two wing wings are connected into integral body slightly, flap top airfoil and lower aerofoil all have radian, can make full use of Coanda effect, enhanced flow is through the air-flow velocity of lower wing upper surface, make aircraft obtain bigger lift, and increased aloft stability, be not prone to situation such as shake, rock.And, one end of flap extends into fore-body and connects into integral body with fuselage, the other end the wing slightly portion by two wings self be interconnected to integral body or by the wing slightly side plate with the wing of flap and two wings slightly portion connect into whole layout, make flap to work, can not swing up and down because of the sudden change of air-flow, and the wing slightly the aircraft that is arranged so that of side plate have better heading stability, make the aircraft can flight diversion when running into bigger crosswind force, improved the flight stability of aircraft.
Feature of the present utility model is that also described aileron rudder face and rudder face control device are arranged on the wing of main wing.Like this, when described aileron rudder face and rudder face control device are arranged on the wing of main wing, can change flying height, the direction of aircraft fast by regulating aileron rudder face and rudder face control device, make aircraft flight more flexible, and, can realize quick landing very easily.
Feature of the present utility model is that also described remote signal receiving control device is arranged on the wing, and is connected with aileron rudder face and rudder face control device.Like this,, can change the location status of regulating the aileron rudder face very rapidly, change flying height, the direction of aircraft fast, make aircraft flight more flexible, conveniently realize quick landing by remote signal control aileron rudder face and rudder face control device.
Feature of the present utility model also is the front end of described fuselage or/and the bottom is provided with the anti-wear device that collides, and anti-collision wear device is that rubber, rigid foam, coating foam or plastics are made.Like this, at the front end of fuselage or/and the bottom be provided with anti-collide wear device after, making aircraft occur stall in the landing process or in the flight course or controlling abnormal conditions such as error causes aircraft to fall ground, even friction is touched on head and ground, can not produce yet and destroy fuselage, improved the anti-ability of falling of aircraft, reduced aloft spoilage, and anti-collision wear device is a rubber, rigid foam, when coating foam or plastics are made, when effectively improving the crashproof ability of aircraft, aircraft with low cost, and weight changes and not obvious, can the flight flexibility of aircraft do not exerted an influence.
Feature of the present utility model is that also described drive unit is the letter road formula dynamical system that brushless electric machine drives.Like this; when drive unit be brushless electric machine drive letter road formula dynamical system the time; drive unit can be aircraft powerful power is provided; electric energy can the overwhelming majority be converted into kinetic energy; a kind of injection power that jet engine produces that is similar to can be provided; reduced the flying power loss significantly; for aircraft provides abundant stable flying power; make aircraft can quicken and fly higher fartherly fast; and; letter road formula dynamical system makes screw to be effectively protected, and makes it in the middle of landing and flight course, is difficult for by weeds; rope; line; foreign material such as feather twine and damage.Also improved simultaneously aloft security.
Feature of the present utility model is that also described fuselage and main wing are Integratively formed or make monolithic respectively and adopt splicing, riveted joint, welding or bolt/nail to be connected to be put together.Like this, when fuselage and main wing when being Integratively formed, the globality of aircraft has obtained significantly improving, make it not fragile, make monolithic respectively and adopt splicing, riveted joint, welding or bolt/when nail connection is put together when adopting, then make things convenient for making, dismounting, the transportation of aircraft, be particularly suitable for making bigger aircraft.
Feature of the present utility model is that also the bottom of described fuselage can also be provided with at least three and support pulley.Like this, when the bottom of fuselage also was provided with three support pulleys, aircraft can be fit to the landing of large aircraft by the mode landing of sliding.
Feature of the present utility model is that also described at least two drive units are arranged at the both sides of fuselage respectively.Like this, when at least two drive units are arranged at the both sides of fuselage respectively, can provide powerful power for aircraft, and, make aircraft when a drive unit breaks down, can rely on another drive unit flight, landing, guaranteed the flight stability and the reliability of aircraft, and, two drive units can provide the flying power of symmetry for aircraft, make aircraft flight more steady.
Feature of the present utility model also is the described afterbody that has the remote signal receiving control device to be arranged on fuselage, and is connected with the direction tail vane.Like this, be arranged on the afterbody of fuselage, and when being connected, can control the heading that the remote signal receiving control device is controlled aircraft, made things convenient for the control of aircraft by remote signal with the direction tail vane as the remote signal receiving control device.
(4) description of drawings
Fig. 1 is the structural representation of the utility model embodiment 1.
Fig. 2 is the structural representation of the utility model embodiment 2.
Fig. 3 is the structural representation of the utility model embodiment 3.
Fig. 4 is the structural representation of the utility model embodiment 4.
Fig. 5 is the structural representation of the utility model embodiment 5.
(5) specific embodiment
Below in conjunction with accompanying drawing and example the utility model is further described.
The utility model as shown in drawings, comprise by fuselage 1, main wing 2, power supply 3, drive unit 4, remote signal receiving control device 5, aileron rudder face and rudder face control device 6 interconnect composition, two wings 8 are symmetricly set on the fuselage both sides, drive unit 4 is arranged on the fuselage 1, power supply 3 is arranged in the fuselage 1, it is characterized in that being provided with at least one direction tail vane 7 at the trunk tail end of fuselage 1, remote signal receiving control device 5 and drive unit 4, aileron rudder face and rudder face control device 6 are or/and tail vane 7 connects into the power control system, main wing 2 is combined by at least two wings 8, one end and the fuselage 1 of wing 8 connect into integral body, and the other end is interconnected to integral body.In each accompanying drawing, 1 is fuselage, and 2 is main wing, and 3 is power supply, and 4 is drive unit, 5 is the remote signal receiving control device, and 6 is aileron rudder face and rudder face control device, and 7 is the direction tail vane, and 8 is wing, 9 is flap, below in each accompanying drawing, number identically, its explanation is identical.As shown in Figure 1, aircraft is by fuselage 1, main wing 2, power supply 3, drive unit 4, remote signal receiving control device 5, aileron rudder face and rudder face control device 6 interconnect composition, main wing 2 is symmetricly set on the fuselage both sides, drive unit 4 is arranged on the fuselage 1, power supply 3 is arranged in the fuselage 1, trunk tail end at fuselage 1 is provided with a tail vane 7, remote signal receiving control device 5 and drive unit 4 and aileron rudder face and rudder face control device 6 and tail vane 7 are connected, main wing 2 is combined by two wings 8, be provided with a flap 9 between two wings 8, one end and the fuselage 1 of wing 8 connect into integral body, and the other end is interconnected to integral body.
The utility model is that also described main wing 2 is combined by two wings 8, two wing 8 upper and lower settings, at least one flap 9 is arranged in the middle of above-mentioned two wings 8, it is anterior and connect into integral body with fuselage 1 that one end of flap 9 extends into fuselage 1, the other end in the end by wing 8 self be interconnected to integral body or by the wing slightly side plate 10 end of flap 9 and wing 8 is connected into integral body.As shown in Figure 2, the main wing 2 of aircraft is combined by two wings 8, two wing 8 upper and lower settings, a flap 9 is arranged in the middle of above-mentioned two wings 8, it is anterior and connect into integral body with fuselage 1 that one end of flap 9 extends into fuselage 1, the other end in the end by the wing slightly side plate 10 end of flap 9 and wing 8 is connected into integral body.
The utility model is that also described aileron rudder face and rudder face control device 6 are arranged on the wing 8 of main wing 2.Shown in Fig. 1,2,3 or 4, aileron rudder face and rudder face control device 6 are arranged on the wing 8 of main wing 2.
The utility model also is the front end of described fuselage 1 or/and the bottom is provided with the anti-wear device 11 that collides, and the anti-wear device 11 that collides is made for rubber, rigid foam, coating foam or plastics.As shown in Figure 3, be provided with the anti-wear device 11 that collides in the front end and the bottom of the fuselage 1 of aircraft, the anti-wear device 11 that collides of diagram is made for rigid foam.
The utility model also is the letter road formula dynamical system that described drive unit 4 drives for brushless electric machine.Shown in Fig. 1,2,3 or 4, the letter road formula dynamical system that drive unit 4 drives for brushless electric machine.
The utility model is that also described fuselage 1 and main wing 2 is for Integratively formed or make monolithic respectively and adopt splicing, riveted joint, welding or bolt/nail to be connected to be put together.Shown in Fig. 1,2,3 or 4, fuselage 1 and main wing 2 are Integratively formed forming.
The utility model is that also the bottom of described fuselage 1 also is provided with at least three and supports pulley 12.As shown in Figure 4, be provided with three in the bottom of fuselage 1 and support pulley 12.
The utility model is that also described at least two drive units 4 are arranged at the both sides of fuselage 1 respectively.As shown in Figure 5, two drive units 4 are arranged at the both sides of fuselage 1 respectively.
The utility model is that also described remote signal receiving control device 5 is arranged on the afterbody of fuselage 1, and is connected with direction tail vane 7.As shown in Figure 5, remote signal receiving control device 5 is arranged on the afterbody of fuselage 1, and is connected with direction tail vane 7.
Claims (10)
1, a kind of telecontrolled aircraft, comprise by fuselage (1), main wing (2), power supply (3), drive unit (4), remote signal receiving control device (5), aileron rudder face and rudder face control device (6) interconnect composition, two wings (8) are symmetricly set on the fuselage both sides, drive unit (4) is arranged on the fuselage (1), power supply (3) is arranged in the fuselage (1), it is characterized in that being provided with at least one direction tail vane (7) at the trunk tail end of fuselage (1), remote signal receiving control device (5) and drive unit (4), aileron rudder face and rudder face control device (6) are or/and tail vane (7) connects into the power control system, main wing (2) is combined by at least two wings (8), one end of wing (8) and fuselage (1) connect into integral body, and the other end is interconnected to integral body.
2, a kind of telecontrolled aircraft according to claim 1, it is characterized in that main wing (2) is combined by two wings (8), two wings (8) upper and lower settings, at least one flap (9) is arranged in the middle of above-mentioned two wings (8), it is anterior and connect into integral body with fuselage (1) that one end of flap (9) extends into fuselage (1), the other end be interconnected in end and wing (8) end integral body or by the wing slightly side plate (10) end of flap (9) and wing (8) is connected into integral body.
3,, it is characterized in that aileron rudder face and rudder face control device (6) are arranged on the wing (8) on the main wing (2) according to claim 1 or 2 described a kind of telecontrolled aircrafts.
4, a kind of telecontrolled aircraft according to claim 3 is characterized in that remote signal receiving control device (5) is arranged on the wing (8), and is connected with aileron rudder face and rudder face control device (6).
5, according to claim 1,2 or 4 described a kind of telecontrolled aircrafts, it is characterized in that the front end of fuselage (1) or/and the bottom is provided with the anti-wear device (11) that collides, anti-collision wear device (11) is that rubber, rigid foam, coating foam or plastics are made.
6,, it is characterized in that the letter road formula dynamical system that described drive unit (4) drives for brushless electric machine according to claim 1,2 or 4 described a kind of telecontrolled aircrafts.
7,, it is characterized in that described fuselage (1) and main wing (2) are for Integratively formed or make monolithic respectively and adopt splicing, riveted joint, welding or bolt/nail to be connected to be put together according to claim 1,2 or 4 described a kind of telecontrolled aircrafts.
8,, it is characterized in that the bottom of described fuselage (1) also is provided with at least three support pulleys (12) according to claim 1,2 or 4 described a kind of telecontrolled aircrafts.
9,, it is characterized in that at least two drive units (4) are arranged at the both sides of fuselage (1) respectively according to claim 1,2 or 4 described a kind of telecontrolled aircrafts.
10,, it is characterized in that having remote signal receiving control device (5) to be arranged on the afterbody of fuselage (1), and be connected with direction tail vane (7) according to claim 1,2 or 4 described a kind of telecontrolled aircrafts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620051220 CN200951320Y (en) | 2006-06-05 | 2006-06-05 | Remote controlled airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620051220 CN200951320Y (en) | 2006-06-05 | 2006-06-05 | Remote controlled airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200951320Y true CN200951320Y (en) | 2007-09-26 |
Family
ID=38809618
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620051220 Expired - Fee Related CN200951320Y (en) | 2006-06-05 | 2006-06-05 | Remote controlled airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200951320Y (en) |
-
2006
- 2006-06-05 CN CN 200620051220 patent/CN200951320Y/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
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| C57 | Notification of unclear or unknown address | ||
| DD01 | Delivery of document by public notice |
Addressee: Xiao Xuping Document name: Notification of authorisation and registration |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |