CN206218225U - A kind of indoor low speed glide vehicle - Google Patents
A kind of indoor low speed glide vehicle Download PDFInfo
- Publication number
- CN206218225U CN206218225U CN201621038050.XU CN201621038050U CN206218225U CN 206218225 U CN206218225 U CN 206218225U CN 201621038050 U CN201621038050 U CN 201621038050U CN 206218225 U CN206218225 U CN 206218225U
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- tail
- fuselage
- host wing
- low speed
- glide vehicle
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Abstract
The utility model is related to model plane and toy art, a kind of indoor low speed glide vehicle, including fuselage, control electron plate, host wing, tailplane and vertical tail, two host wings have the main motor for installing main screw respectively, the empennage is provided with the tail motor of magnetic tape trailer propeller, the position of the main wing leading edge higher than trailing edge position and leading edge is bigger than traditional glide vehicle with the difference in height of trailing edge, host wing is set to form larger Windward angle, and the lower surface of the host wing is convex arc；The main screw is relative with the lower surface of the host wing so that the gas that the main screw drives blows to the lower surface of host wing and provides lift to host wing.By the shape of the larger Windward angle of host wing so that obtain additional lift during host wing low-speed operations.The control electron plate is provided with sensing element, this glide vehicle is realized that fuselage is balanced when compared with low velocity, is suitable to be glided at a slow speed in small space.
Description
Technical field
The utility model is related to model plane and toy art, particularly it is a kind of can low speed gliding indoors/wing dress aircraft/
The aircraft such as bionical glide vehicle.
Background technology
In the modern life, glide vehicle has obtained increasing people to be liked and praises highly.It is well known that traditional cunning
Xiang aircraft, under state at a slow speed, is easy to the air crash because of stall, and glide vehicle realizes that the principle of stabilized flight seeks to
Ask flying speed higher, host wing Windward angle is smaller.And in this case, it is desirable to the place of flight is larger can be realized
The flare maneuvers such as turning.This kind of aircraft, cannot typically manipulate flight indoors.
And the glide vehicle of another model plane class, the aileron of wing is changed by the steering wheel of the 2-3 set above, although
Indoor flight can be realized, but manipulation skill requirement of this kind of aircraft to user is especially high, meanwhile, product is very complicated,
High cost, it is impossible to popularized towards masses.
Utility model content
To solve the above problems, the utility model is related to a kind of glide vehicle, with manipulation is simple, low cost, can be
The advantages of indoor flight.
To achieve the above object, the utility model provides a kind of indoor low speed glide vehicle, including fuselage, is arranged on machine
The host wing of body head both sides, the tailplane and vertical tail that are arranged on afterbody both sides, two host wing difference
With the main motor for installing main screw, it is characterised in that：The host wing is leading edge, is close to machine near the edge of heading
The edge in tail direction is trailing edge, and the position of the leading edge is higher than the position of reinforcement, and the lower surface of the host wing is convex
Arc；
The main screw is relative with the lower surface of the host wing so that the high velocity air that the main screw drives blows
To host wing lower surface and host wing is produced main lift.
In one embodiment, the afterbody also has the tail motor for installing tail-rotor, the driving institute of the tail motor
Tail-rotor is stated to fuselage lower section jet.
In one embodiment, the leading edge of the host wing and trailing edge form larger Windward angle, need to reach 25 degree with
On angle windward.
In one embodiment, the axle center of the tail motor forms 13 ° -17 ° of angle, and tail-rotor with the endways direction
Deflection tail direction.
In one embodiment, tailplane tool fuselage junction has the first hollow part, the vertical tail with
First hollow part relative position has the second hollow part, and the tail motor is arranged on the first hollow part of vertical tail, and tail-rotor
Center is in the center of the second hollow part.
In one embodiment, the main motor and tail motor are drag cup motor.
In one embodiment, the fuselage, host wing, tailplane and vertical tail are foamed material and are made.
In one embodiment, the host wing is " V " font layout in fuselage both sides.
In one embodiment, the indoor low speed glide vehicle further includes to be placed in the control module in fuselage,
The control module includes the sensor assembly for obtaining fuselage status data of signal connection, treatment fuselage status number successively
According to main control board and tail motor control module for sending control instruction to tail motor.
In one embodiment, the sensor assembly includes band angular transducer and/or acceleration transducer.
It is using the beneficial effects of the utility model：
The position of the leading edge of this glide vehicle host wing is higher than the position of reinforcement, and the lower surface of host wing is arc；
Main screw is relative with the lower surface of the host wing, and the leading edge of host wing is with the difference in height of trailing edge than traditional glide vehicle
It is big, host wing is formed larger Windward angle so that the lower surface that the gas that main screw drives blows to host wing makes master
Wing produces main lift.By the setting of the shape of host wing, in slower flight, host wing can be produced necessarily aircraft
Additional lift, by making a concerted effort for the superposition of lift and air drag so that this glide vehicle can be when compared with low velocity
Enough lift can be obtained and maintain flight.And sensor assembly and the co-ordination of tail motor, the angle stabilization of fuselage can be maintained,
And realize that fuselage is balanced, it is suitable to be flown under small space.
Brief description of the drawings
Fig. 1 is low speed glide vehicle overlooking the structure diagram in the utility model room.
Fig. 2 is low speed glide vehicle side structure schematic view in the utility model room.
Fig. 3 is low speed glide vehicle schematic rear view in the utility model room.
Fig. 4 is low speed glide vehicle dimensional structure diagram in the utility model room.
Fig. 5 is M portions partial enlarged drawing in the utility model Fig. 2.
Fig. 6 is control module connection diagram in low speed glide vehicle in the utility model room.
Fig. 7 is low speed glide vehicle fuselage stress diagram in the utility model room.
Reference includes：
100- fuselage 110- lifting wheel 200- host wings
The main hollow parts of motor 300- tailplanes 310- first of 210-
400- vertical tails 410- the second hollow part 420- tail motors
500- control module 510- sensor assembly 520- main control boards
530- tail motor control modules
Specific embodiment
The utility model is described in detail below in conjunction with accompanying drawing.
As shown in Fig. 1-Fig. 7, the present embodiment provides a kind of indoor low speed glide vehicle, including fuselage 100, is arranged on machine
The host wing 200 of the head both sides of body 100, the tailplane 300 and vertical tail 400 that are arranged on the two sides of tail of fuselage 100, two
Host wing 200 has the main motor 210 for installing main screw respectively, and host wing 200 is leading edge, leans near the edge of heading
The edge in nearly tail direction is trailing edge, and the position of leading edge is higher than the position of trailing edge, and the lower surface of host wing 200 is convex arc
Shape；Main screw is relative with the lower surface of host wing 200, and the leading edge of host wing is with the difference in height of trailing edge than traditional glide vehicle
It is big, host wing 200 is formed larger Windward angle so that the gas that main screw drives is blowed under host wing 200
Surface simultaneously makes host wing 200 produce main lift.
Specifically, as shown in Figure 1 and Figure 2, the airflow design of fuselage 100 of this glide vehicle, host wing 200 is sheet
Wing and first extend away from the direction of fuselage 100, the cross section of host wing 200 is arc, and two lower sections of host wings 200 are pacified respectively
A main motor 210 is filled, main screw is arranged on the round end of main motor 210, and main motor 210 can drive principal screw to rotate and produce
Air flow direction tail direction, provide the power that glides forward, arc of the jet-impingement in host wing 200 to this glide vehicle
Shape lower surface, you can make host wing 200 produce upward lift, while this glide vehicle is during aircraft glides,
Host wing 200 is flowed in lower surface by air-flow and produces upward lift, while host wing 200 and the other positions shape of fuselage 100
Into resistance, its force action is on fuselage 100 so that fuselage 100 obtains less power forward, you can keep this gliding flight
Device glides under lower-speed state.
As shown in figure 3, host wing 200 is " V " font layout in both sides of fuselage 100 or so, this kind layout is mainly protected
Hold fuselage or so stabilization.
In the present embodiment, the leading edge of host wing is bigger than traditional glide vehicle with the difference in height of trailing edge, makes main frame
The wing 200 forms larger Windward angle, and Windward angle need to be conducive to this glide vehicle to obtain enough lift up to more than 25 degree
And keep width smaller.
As Figure 1-Figure 5, the afterbody of fuselage 100 also has the tail motor 420 for installing tail-rotor, the driving tail of tail motor 420
Oar is to the lower section jet of fuselage 100.Tail motor 420 can provide lift to aircraft afterbody, and lift is received with reference to host wing 200, can protect
Hold the flight of aircraft monolithic stability.
As shown in fig. 7, specifically, host wing 200 is using the big design of Windward angle, the Windward angle of host wing 200 is big,
In longitudinal surface chart of host wing 200, the height difference size A of host wing 200 is than larger, the power that main screw generation is pushed away forward
B, and the air blast major part high that main screw is produced is blown on host wing 200, forms larger lift C and resistance D, meanwhile,
The Windward angle of host wing 200 is big, and certain lift E and resistance F can be still produced in flight at a slow speed.The afterbody of aircraft
1 tail motor 420 of design, drives tail-rotor to dry downwards, produces a power G, and according to force resolution principle, power G can be resolved into
One component H and upward component J forward, so, the onward impulse=thrust B+ component H- resistance D- resistance F of aircraft,
Onward impulse is smaller, and flying speed is slow.And the lift of aircraft=lift C+ lift E+ component J, if greater than or equal to fly
The gross weight of row device, then can maintain airflight.
As shown in figure 5, the axle center of tail motor 420 forms 13 ° -17 ° of angle, i.e., angle N in figure, and tail-rotor with endways direction
Deflection tail direction.Tail motor 420 drives tail-rotor to produce lift and certain thrust, to keep fuselage 100 to balance.
As shown in figure 4, the tool of tailplane 300 fuselage 100 junction has the first hollow part 310, vertical tail 400 and the
The relative position of one hollow part 310 has the second hollow part 410, and tail motor 420 is arranged on the first hollow part of vertical tail 400
310, and tail-rotor is arranged on the centre position of the second hollow part 410, it is to avoid tail propeller encounters empennage when rotating.Tail motor 420
Installed in tailplane 300 and the intersection of vertical tail 400, and it is hidden in inside fuselage 100, on the one hand may be such that this flight
During device landing, tail motor 420 is not contacted with ground, effectively protection tail motor 420, the position of another aspect tail motor 420
So that the more compact structure of fuselage 100.Fuselage bottom installs a lifting wheel 110, and tail motor 420 is located at the rear of lifting wheel 110.
Used as preferred, main motor 210 and tail motor 420 are drag cup motor, and drag cup motor has very prominent
High efficiency, rotary speed property high, can use cooperatively light small propeller.Fuselage 100, host wing 200, tailplane 300 and vertical
Empennage 400 is foamed material and is made, and is beneficial to the lightweight of fuselage 100.
This indoor low speed glide vehicle further includes the control module 500 being placed in fuselage 100, control module 500
The sensor assembly 510 for obtaining the status data of fuselage 100 including the connection of signal successively, the treatment status data of fuselage 100
Main control board 520 and the tail motor control module 530 for sending control instruction to tail motor 420.Sensor assembly 510
Including band angular transducer and/or acceleration transducer.When fuselage 100 produces angle change or fuselage 100 to add deduct speed fortune
When dynamic, sensor assembly 510 monitors fuselage 100 state change in time, and the status data of fuselage 100 is delivered into governor circuit
The status data of fuselage 100 is converted into control signal by plate 520, the built-in treatment of main control board 520, and control instruction is delivered to
Tail motor control module 530, the rotating speed of the control tail of tail motor control module 530 motor 420, so as to realize to the afterbody of fuselage 100
The control of lift is inclined correcting fuselage 100, it is ensured that the angle of aircraft fuselage 100 is constant.
For example, if fuselage 100 has change or the trend of new line, sensor assembly 510 sends positive signal, governor circuit
Plate 520 receives the signal, then send positive signal and accelerate rotation to the controller of tail motor 420, tail motor 420, produces bigger liter
Power J, afterbody is raised, constant with the angle for ensureing fuselage 100., whereas if head has the trend for becoming underriding down, then sense
Device module 510 sends negative signal, and main control board 520 receives the signal, then send negative signal and give the controller of tail motor 420, tail
Motor 420 is then rotated in deceleration, and reduces lift J, makes afterbody drop-down, constant with the angle for ensureing fuselage 100.
Above content is only preferred embodiment of the present utility model, for one of ordinary skill in the art, according to this reality
With new thought, in specific embodiments and applications can be so that many changes may be made, as long as these changes are without departing from this
The design of utility model, belongs to protection domain of the present utility model.
Claims (10)
1. a kind of indoor low speed glide vehicle, including fuselage (100), the host wing for being arranged on fuselage (100) head both sides
(200) tailplane (300) and vertical tail (400) of fuselage (100) two sides of tail, two host wings, are arranged on
(200) there is the main motor (210) for installing main screw respectively, it is characterised in that：The host wing (200) is near heading
Edge be leading edge, near the edge in tail direction be trailing edge, the position of the leading edge higher than trailing edge position, and the main frame
The lower surface of the wing (200) is convex arc；
The main screw is relative with the lower surface of the host wing (200) so that the gas that the main screw drives is blowed to
The lower surface of host wing (200) simultaneously provides lift to host wing (200).
2. indoor low speed glide vehicle according to claim 1, it is characterised in that：Fuselage (100) afterbody also has
There is the tail motor (420) for installing tail-rotor, the tail motor (420) drives the tail-rotor to fuselage (100) lower section jet.
3. indoor low speed glide vehicle according to claim 1, it is characterised in that：The host wing (200) is windward
Angle is more than 25 °.
4. indoor low speed glide vehicle according to claim 2, it is characterised in that：The axle center of the tail motor (420)
With the angle that vertical direction forms 13 ° -17 °, and tail-rotor deflection tail direction.
5. indoor low speed glide vehicle according to claim 2, it is characterised in that：The tailplane (300) and machine
Body (100) junction has the first hollow part (310), and the vertical tail (400) has with the first hollow part (310) relative position
Have the second hollow part (410), the tail motor (420) installed in vertical tail (400) the first hollow part (310), and tail-rotor
By the centre position of the second hollow part (410).
6. indoor low speed glide vehicle according to claim 2, it is characterised in that：The main motor (210) and tail horse
It is drag cup motor up to (420).
7. indoor low speed glide vehicle according to claim 1, it is characterised in that：The fuselage (100), host wing
(200), tailplane (300) and vertical tail (400) are foamed material and are made.
8. indoor low speed glide vehicle according to claim 1, it is characterised in that：The host wing (200) is in fuselage
(100) both sides are " V " font layout.
9. indoor low speed glide vehicle according to claim 1, it is characterised in that：The indoor low speed glide vehicle
The control module (500) being placed in fuselage (100) is further included, what the control module (500) connected including signal successively
For obtaining the sensor assembly (510) of fuselage (100) status data, processing the main control board of fuselage (100) status data
(520) and for sending the tail motor control module (530) of control instruction to tail motor (420).
10. indoor low speed glide vehicle according to claim 9, it is characterised in that：Sensor assembly (510) bag
Include band angular transducer and/or acceleration transducer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621038050.XU CN206218225U (en) | 2016-09-05 | 2016-09-05 | A kind of indoor low speed glide vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621038050.XU CN206218225U (en) | 2016-09-05 | 2016-09-05 | A kind of indoor low speed glide vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206218225U true CN206218225U (en) | 2017-06-06 |
Family
ID=58781707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621038050.XU Expired - Fee Related CN206218225U (en) | 2016-09-05 | 2016-09-05 | A kind of indoor low speed glide vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206218225U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651186A (en) * | 2017-08-29 | 2018-02-02 | 深圳市华力航空科技有限公司 | A kind of electric power aerodone |
| CN113815873A (en) * | 2021-10-09 | 2021-12-21 | 中国人民解放军国防科技大学 | Electric aircraft trajectory optimization method and system |
-
2016
- 2016-09-05 CN CN201621038050.XU patent/CN206218225U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651186A (en) * | 2017-08-29 | 2018-02-02 | 深圳市华力航空科技有限公司 | A kind of electric power aerodone |
| CN113815873A (en) * | 2021-10-09 | 2021-12-21 | 中国人民解放军国防科技大学 | Electric aircraft trajectory optimization method and system |
| CN113815873B (en) * | 2021-10-09 | 2023-07-14 | 中国人民解放军国防科技大学 | Electric aircraft track optimization method and system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170606 Termination date: 20190905 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |