CN100522304C

CN100522304C - Propulsion system of model airplane

Info

Publication number: CN100522304C
Application number: CNB2005100542241A
Authority: CN
Inventors: 蔡奇逢
Original assignee: Individual
Current assignee: Individual
Priority date: 2005-02-08
Filing date: 2005-02-08
Publication date: 2009-08-05
Anticipated expiration: 2025-02-08
Also published as: CN1817398A

Abstract

A miniature aviation model airplane is provided, wherein a motor and a propeller are arranged on the rear side surface of an upper layer wing of the airplane by applying a double-layer wing design, so that the propeller and the motor of the airplane can be well protected from being damaged in the event of a crash event. The miniature aeromodelling aircraft includes: the airplane comprises a fuselage, a first wing and a second wing, wherein the fuselage is provided with the first wing and the second wing which respectively extend out from the left direction and the right direction of the fuselage; a first propulsion device having a first motor and a first propeller rotated by the first motor, the propulsion device being mounted under the first wing; and a second propulsion device having a second motor and a second propeller rotated by the second motor, the propulsion device being mounted under the second wing.

Description

The propulsion system of the model of an airplane

Technical field

The present invention relates generally to the flight model aircaft configuration, particularly relates to the propulsion system that is used for the flight model aircraft.

Background technology

The flight model aircraft is commonly referred to as toy flight aircraft, for many years lasting and extensive situation of selling well in children and adult.The continuous development of the model of an airplane has comprised and has been intended to be used for amusement and the small-sized self-powered toy of pastime purpose or the development of the model of an airplane.In addition, use the remote control airborne vehicle of control tether or radio signal transmission link to make the toy and the model of an airplane have further improved true effect and enjoyment enjoyment.

The model of an airplane that can fly generally uses one or more compact internal combustion engines or the electric notor that drives one or more screws.These motors and screw are installed in the front portion of aircraft wing.Because usually can crashing on ground, the model of an airplane maybe can run into other obstacle, so when air crash, the preposition damage that usually can cause screw and/or motor of this screw.

Particularly, most commercially available radio control (RC) toy airplane generally has a screw on aeroplane nose, has two actuators that are used for elevator and rudder control, for example servo motor or solenoids.This structure is expensive, has used complicated hardware and heaviness.Other commercially available RC toy airplane can have two screws that are positioned on the leading edge of a wing, and without any elevator and rudder control.In these two kinds of designs, screw and/or motor drive shaft can be very easy to deform or or even fracture in landing or crash process.Flying quality after will being reduced in like this and or even life-span of product.Simultaneously, for darts, it is dangerous using high performance airscrew in the front portion of aircraft.The result can damage children.

Summary of the invention

Therefore, desirable is the improved structure with a kind of flight model aircraft, and described structure is not easy to be damaged when crash and/or conventional application as landing more.

According to an aspect of of the present present invention, a kind of miniature model airplane aircraft is provided, comprising: fuselage, described fuselage have first wing and second wing, and described first wing and described second wing extend out from the left and right direction of described fuselage respectively; First propulsion plant, first screw that has first motor and rotate by first motor, this thrust unit is installed in below first wing; With second propulsion plant, second screw that has second motor and rotate by second motor, this thrust unit is installed in below second wing.

Description of drawings

In order more completely to understand the disclosed content of the application, in institute's drawings attached, use identical Reference numeral to represent identical parts, wherein:

Fig. 1 shows the rearview according to the flight model aircraft of an exemplary embodiments of the present invention;

Fig. 2 shows the right view of aircraft shown in Figure 1;

Fig. 3 shows the top view of aircraft shown in Figure 1;

Fig. 4 shows the left view of aircraft shown in Figure 1;

Fig. 5 shows another right view of aircraft shown in Figure 1;

Fig. 6 shows the aircraft of the employed emitter of aircraft shown in Figure 1 and receiving system and another embodiment;

Fig. 7 shows shown in Figure 1 and according to the perspective view of the aircraft of two other exemplary embodiments of the present invention;

Fig. 8 is the block diagram of control system that is used to control aircraft shown in Figure 1 according to an exemplary embodiments of the present invention;

Fig. 9 is the block diagram that carries out the transmitter system of telecommunication according to the ground user of the permission of an exemplary embodiments of the present invention and control system shown in Figure 8;

Figure 10 is the cross-sectional view strength according to the aircraft shown in Figure 1 of an exemplary embodiments of the present invention;

Figure 11-16 shows the different views of other thin portion of aircraft shown in Figure 1;

Figure 17-20 shows the different views of other thin portion of emitter shown in Figure 6;

Figure 21 is the side view according to the aircraft of the use single-blade design of an exemplary embodiments of the present invention;

Figure 22 shows the top view of aircraft shown in Figure 21; With

Figure 23 shows the perspective view of aircraft shown in Figure 21 and according to other two width of cloth perspective view of the aircraft of the use single-blade of other exemplary embodiments of the present invention design.

Show certain embodiments at this example of listing, and described example is not intended to limit the invention by any way.

The specific embodiment

Below explanation and accompanying drawing are for example understood the specific embodiment that is enough to enable those skilled in the art to implement system and method described herein.Other embodiment can comprise structure, method and radio-opaque distal marking.The variation that example only expresses possibility.

The present invention proposes a kind of improved structure and method that is used for providing power to the flight of the model of an airplane, if so that the generation crash can protect wind stick and motor not to be damaged preferably.

Fig. 1 shows the rearview of flight model aircraft 100.Flight model aircraft 100 has fuselage 102 and is attached to and from extended wing 108 of the opposite side of fuselage 102 and wing 114.Have motor 116 and be installed in the rear portion of wing 108 by first propulsion plant of the screw 118 of first motor 116 rotation.Have motor 120 and be installed in the rear portion of wing 114 by second propulsion plant of the screw 122 of motor 120 rotation.Afterbody 104 is connected to fuselage 102.

The trailing edge that motor and screw is installed in wing helps in crash or hard landing or other hard use the damage to motor, driving shaft and/or screw to be reduced to minimum degree.Reduced simultaneously from the danger of the screw that is installed in the place ahead children.

Aircraft 100 further comprises and is arranged on the wing 106 below the wing 108 and is arranged on wing 112 below the wing 114.Preferably, aircraft 100 has by anticracking material for example foamed plastics or other is soft and/or deformable material is made fuselage 102, makes the crash of aircraft 100 or hard landing can not cause great structural damage.The wing of aircraft 100 and afterbody are also preferably made by this anticracking material.

Wing 106 for example is connected by first pillar 110 with 108, and wing 112 for example is connected by second pillar 111 with 114.First propulsion plant for example can be installed between the fuselage 102 and first pillar 110, and second propulsion plant for example can be installed between the fuselage 102 and second pillar 111.

Fig. 2 shows the right view of aircraft 100 shown in Figure 1.In this embodiment,

motor

116 and 120 be installed in respectively

wing

108 and 114 below.Also can use other installation site, for

example wing

108 and 114 upper strata and rear portion.Screw can be directly mounted on the motor, and does not use geared system.Simultaneously, in some other embodiment, motor can be installed on

lower wing

106 and 112.

Aircraft 100 can have away from bottom and the tapered rounded nose 206 of the guiding point on the top (leadingpoint) at described head, and fuselage 102 can reach the front of first and

second wings

108 and 114 forward.Here note: the top 208 of fuselage 206 is increased near the leading edge of first and

second wings

108 and 114 basically from the head continuously, and 206 1: 210 places that drop to

wing

106 and 112 fronts continuously from the head basically, the bottom 209 of fuselage 102.In addition, in this embodiment, the bottom 212 of fuselage 102 is flat from putting the 210 following rear sections of getting back to fuselage 102 basically.

Aircraft 100 for example can further comprise by long thin bar or other slender member 204 and is connected respectively to rudder 200 and elevator 202 on the fuselage.Be noted that for example reducible height that is equal to or greater than rudder 200 of vertical range between wing 108 and 106.Equally, the width of elevator 202 for example can be less than the twice of the height of rudder 200.In addition,

wing

106 and 112 for example can be set at the roughly the same plane of elevator 202 in.Equally, the lower wing 106 in double-deck wing design and 112 can prevent that screw contacts with ground or place when landing as linear beam.

The length and width ratio that the length-width ratio that each wing adopted is preferably bigger.This generally helps aircraft 100 to produce bigger lifting force awing.The flight that application and the design of double-deck wing than the aspect ratio as shown in Figure 1 generally should be aircraft 100 provides enough big upthrust, and feasible for example aircraft 100 can hang down flying speed (for example: less than 3 meter per seconds) and fly.

It should be noted: the rotation of each in first and second screws can be angled along downward direction.By increasing gate throttle (throttle), aircraft 100 generally is tending towards upwards flight, rather than flies sooner.

Equally, the distance between first and second screws and the airplane tail group is preferred enough short, produces some downward power so that flow to the air stream of elevator 202 on afterbody 104.For example, this distance can be less than about 120 millimeters, and can be about 85 millimeters in instantiation.As this air-flow and more short-range result, moment of torsion can be added on the afterbody, make aircraft 100 head points slightly upward to, this helps upwards flight of aircraft 100.

Fig. 3 shows the top view of aircraft 100.Fig. 4 shows the left view of aircraft 100.Fig. 5 shows another right view of aircraft 100.

Fig. 6 shows employed emitter 600 of flight and the receiving system 620 that is used to control aircraft 100.Emitter 600 has antenna 602.Emitter 600 has left handle or control stick 604 and right handles or control stick 606.Left side control stick 604 for example can be gate throttle control, and for example can be divided into seven grades, has numerical scale control.Aircraft 100 can upwards fly by increasing gate throttle, and can fly downwards by reducing gate throttle.About for example can be, right control stick 606, and can connect variation with the relative velocity of controlling left and right sides screw as described below to control.

When pushing direction joystick not, can use and drive or align trimmer 610 to produce the rectilinear flight of aircraft 100.When not using handle 606 to start direction control, can regulate, provide roughly the same power output until left and right sides screw to trimmer 610.

Emitter 600 also can comprise the built-in charger that can charge fully to rechargeable battery in the aircraft 100.Emitter 600 can comprise that power supply " opens " indicator (for example light emitting diode) and state-of-charge indicator (for example another light emitting diode).Emitter 600 for example can use the time division multiplex programming technique, wherein for example can operate simultaneously up to three to have identical rf frequency, for example the aircraft of 27.145MHz.

Receiving system 620 can be installed in the fuselage of aircraft 100.The charging socket 612 of receiving system 620 can be used to be mounted on rechargeable battery in the aircraft 100 and the charger in the emitter 600.Emitter 600 can comprise connector or be used for being connected on the charging socket 612 is other charging device 608 of the battery charge of aircraft 100.

Fig. 7 shows the perspective view of the aircraft of the perspective view of aircraft 100 shown in the view 700 and two other exemplary embodiments shown in

view

700 and 702, wherein shown in also can use improved structure as described below and propelling and method for designing in the aircraft.

Fig. 8 is the block diagram that is used for controlling by radio control the control system 800 of aircraft 100.Control system 800 can be included as the part of receiving system 620 in the aircraft 100.Control system 800 comprises the processor 802 (for example, microcontroller) that is connected in order to control first and second motors 116 and 120.Radio frequency (RF) signal is by radio frequency receiver 804 demodulation, and decoded device 806 and processor 802 decodings, so that utilize the speed of controller 808 and 810 control motors.

Can programme to processor, poor with the rotary speed of controlling between first and

second screws

118 and 122, thus help aircraft to turn.In order to control the heading of aircraft 100, for example left-hand airscrew should change sooner than right-hand screw oar, turning right, otherwise turns left.

As another example, to turn left for the control aircraft, the upthrust on starboard wing can increase (can control the right-hand screw oar should change sooner than left-hand airscrew).The result is that the right side is higher than the left side, and therefore aircraft will turn to the left side.When turning to the right side, aircraft can use similar principle.In other embodiments, can further control turn to or selectively service orientation rudder control turn to.

Battery 812 can be installed in the fuselage 102, and is connected for providing power with operation radio frequency receiver 804.Battery for example can be the lithium polymer battery of lightweight.This battery helps to be used in the maximum output electric energy of small, light aircraft and the ratio maximum of weight.For example aircraft 100 can be with about 10 minutes of the battery running of such charging fully.

Fig. 9 allows ground user and control system 800 to carry out the block diagram of the transmitter system 900 of telecommunication.Transmitter system 900 is combined as the part of emitter 600.Transmitter system 900 comprises by main control unit 904 and is connected to a left side/right control lever 606, throttle-control lever 604 and align radio frequency sending set 902 on the trimmer 610.Charger 906 is connected so that battery 908 is charged, and is used to radio frequency sending set 902 that power is provided.

Figure 10 is the cross-sectional view strength of aircraft 100.For example battery 812 is positioned in the inside of fuselage 102.Receiving system 620 is connected to receive the operation power from battery 812.

Figure 11-the 16th, the different views of other thin portion of aircraft 100.Figure 17-20 shows the different views of other thin portion of expression emitter 600.

It should be noted that this push structure and method also can be used in some aircrafts of only having single-blade on each side of fuselage and have three wings on each side of fuselage or more on the aircraft of multiple wing.Simultaneously, control infrared or able to programme can be used as the optional mode of radio controlled another kind.In addition, lithium ion battery, high-density capacitor and other power source can be used in the aircraft 100.

The size of aircraft 100 for example can be less than 12 inches long and 10 inches wide, and comprise that the weight of the aircraft 100 of rechargeable battery for example can be less than about 20 grams.

Figure 21 be according to another exemplary embodiments of the present invention and said method but be to use the side view of the aircraft of single-blade design.Figure 22 shows the top view of aircraft shown in Figure 21.Figure 23 shows the perspective view of aircraft shown in Figure 21 and according to other two width of cloth perspective view of the aircraft of the use single-blade of other exemplary embodiments design.

According to the disclosed content in front, improved structure and the method to the model of an airplane that is used to advance flight is described.Description to the front of specific embodiment demonstrates abundant general essence of the present disclosure, makes other people to change and/or to transform being used for multiple use it, and does not depart from this universal.Therefore, this transformation and change are in the scope and the meaning of the equivalent of the disclosed embodiments.At this employed expression way or term only for the purpose of illustration, and non-limiting purpose.

Claims

1. A miniature aviation model aircraft, comprising:

a fuselage, the fuselage has a first wing and a second wing, and the first wing and the second wing respectively extend from the left and right directions of the fuselage,

a first propulsion device having a first motor and a first propeller rotated by the first motor, the propulsion device being mounted under the first wing, and

A second propulsion device, having a second motor and a second propeller rotated by the second motor, is installed under the second wing.

2. The aircraft of claim 1, further comprising a third wing disposed below the first wing and a fourth wing disposed below the second wing.

3. The aircraft of claim 1, wherein the fuselage is made of a crack resistant material.

4. The aircraft of claim 3, wherein said material is foamed plastic.

5. The aircraft of claim 1 wherein said fuselage has a rounded nose that tapers away from a pilot point on the bottom and top of said nose.

6. The aircraft of claim 2, wherein the first and third wings are connected by a first strut, and the second and fourth wings are connected by a second strut, and wherein the first propulsion The device is mounted between the fuselage and the first strut, and the second propulsion device is mounted between the fuselage and the second strut.

7. The aircraft of claim 6, wherein the first and second wings have an aspect ratio of 110MM/60MM, respectively.

8. The aircraft of claim 1, further comprising a rudder and an elevator respectively connected to the fuselage by elongated slender rods.

9. The aircraft of claim 2, further comprising fifth and sixth wings disposed on opposite sides of the fuselage.

10. The aircraft of claim 8, wherein the distance between the first and third wings is equal to or greater than the height of the rudder.

11. The aircraft of claim 10, wherein the width of the elevator is less than twice the height of the rudder.

12. The aircraft of claim 1, wherein the first and second motors are mounted under the first and second wings, respectively.

13. The aircraft of claim 2, wherein the third and fourth motors are disposed in the same horizontal plane as the elevator.

14. The aircraft of claim 1, wherein the fuselage has a nose and the top of the fuselage rises continuously from the nose to near the leading edges of the first and second wings.

15. An aircraft according to claim 14, wherein the bottom of the fuselage descends continuously from the nose to the leading edges of the third and fourth wings.

16. An aircraft according to claim 15, wherein the bottom of the fuselage is flat from the third and fourth wing leading edges back to the rear of the fuselage.

17. The aircraft of claim 1, wherein the axis of rotation of each of the first and second propellers is angleable in a downward direction.

18. An aircraft as claimed in claim 17, wherein the aircraft has a tail and the distance between the first and second propellers and the tail is short so that the air flow towards the elevator produces some downward force on the tail.

19. The aircraft of claim 18, wherein the distance is less than 120 millimeters.

20. The aircraft of claim 18, wherein the distance is 85 millimeters.

21. The aircraft of claim 1, further comprising a processor coupled to control the first and second motors.

22. The aircraft of claim 21, wherein the processor is operable to control a difference in rotational speed between the first and second propellers to assist the aircraft in turning.

23. The aircraft of claim 21, further comprising a radio receiver coupled to said processor.

24. The aircraft of claim 23, further comprising a battery mounted in the fuselage and connected to provide power to operate the radio receiver.