CN202128908U - Infrared sensing air vehicle - Google Patents
Infrared sensing air vehicle Download PDFInfo
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- CN202128908U CN202128908U CN201120184719U CN201120184719U CN202128908U CN 202128908 U CN202128908 U CN 202128908U CN 201120184719 U CN201120184719 U CN 201120184719U CN 201120184719 U CN201120184719 U CN 201120184719U CN 202128908 U CN202128908 U CN 202128908U
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Abstract
An infrared sensing air vehicle comprises an air vehicle base provided with an infrared sensing component, a power module arranged in the air vehicle base and two propeller components arranged coaxially; the two propeller components are arranged up and down, both are positioned above the air vehicle base and are connected with the power module arranged in the air vehicle base through a first rotating shaft and a second rotating shaft which are sleeved with each other; the power module supplies rotation power, and the first and the second rotating shafts transmit the power to the two propeller components so as to achieve rotation; and the two propeller components rotate in the reverse direction. The shape design of the infrared sensing air vehicle is more convenient and more diversified, so that the interest and interaction of the air vehicle are greatly increased, then the consumer affinity can be increased, and the market adaptability can be more extensive; and while, the propeller components are not easy to damage during flying and landing, so that the service life of the product is ensured.
Description
Technical field
The utility model relates to a kind of aircraft, especially a kind of infrared induction aircraft.
Background technology
Infrared induction aircraft and flying saucer are a kind of wide popular products, and its basic principle is to adopt the rotation of screw assembly and produce lift, and aircraft is risen in the air; This external aircraft bottom sets RF transmitter, can launch infrared signal by this downwards, as runs into barrier and then reflect; Infrared receiver receives reflected signal, responds to the environment of aircraft below, thereby makes aircraft can guarantee enough flying heights aloft; And when the infrared ray receiver does not receive reflected signal; The flying height that aircraft then is described exceeds setting range, and the rotary speed of propeller blade promptly can suitably reduce, and makes aircraft decline certain distance; Can receive again until infrared receiver till the reflected signal of below obstacle; So repeatedly, just can guarantee that aircraft is in aerial suitable height all the time, person's control easy to use.
Common infrared induction aircraft for the smoothness that guarantees to fly, all is to be designed to discoid flying saucer style mostly at present; Wherein the screw assembly is positioned at the bottom of flying saucer; And cover by flying saucer, so will obtain the structure of a balance, the screw assembly is positioned at the flying saucer center; But support plays flying saucer during rotation; Flying saucer can fly up reposefully, and the flying saucer main body of this shape can also protect the screw assembly not allow to be subject to ectocine simultaneously, has guaranteed the stationarity of flight and the safety of use.Yet the aircraft of this traditional structure need design the flying saucer body volume bigger; Can guarantee that it is coated to the screw assembly, volume and shape that it has then limited aircraft body thus make aircraft body only can be UFO-like mostly and can keep flight balance; And that its its volume can not design is too small, otherwise can not envelope the screw assembly, thus; The profile of aircraft only has been confined to the disk flying saucer in shape, and the profile that seems unavoidably is outmoded, and is stereotyped; It is very novel not have, and its bigger profile makes that also the bulk wight amount is heavier, needs bigger power could guarantee airflight; Increased power consumption, airborne hours will reduce relatively.
Summary of the invention
The purpose of the utility model is to provide a kind of novel structure, and profile is changeable, and weight is lighter, and has more interesting and interactive infrared induction aircraft.
The utility model is that the technical scheme that its technical problem of solution is adopted is:
The infrared induction aircraft comprises:
Be provided with the aircraft base of infrared, receiving unit;
Be arranged at the power plant module in the aircraft base; And it is coaxial and go to upper and lower two screw assemblies of position relation each other; Be positioned at said aircraft base top jointly; And respectively through two with one heart and first, second rotating shaft that is set-located each other be connected with power plant module in the aircraft base; According to power plant module rotary power is provided, passes to two screw assemblies respectively by first, second rotating shaft and realize rotation; Wherein
The direction of rotation of said two screw assemblies is opposite.
Above-mentioned power plant module comprises: power supply; Motor sub-assembly by the power supply power supply; And the transmission component that the rotation of motor sub-assembly is passed to first, second rotating shaft.
As a kind of selection scheme; Motor sub-assembly comprises active motor, and said transmission component comprises intermeshing driving tooth wheels and driven tooth wheels, and active motor and driving tooth wheels are in transmission connection; The driving tooth wheels and first rotating shaft are in transmission connection, and the driven tooth wheels and second rotating shaft are in transmission connection.
As another kind of selection scheme; Above-mentioned motor sub-assembly comprises first, second motor; Above-mentioned transmission component comprises first, second gear train, and wherein first motor is through first rotating shaft that is in transmission connection of first gear train, and second motor is through second rotating shaft that is in transmission connection of second gear train.
The beneficial effect of the utility model is: the utility model adopts the aircraft base, and the novel structure of screw assembly is set above it, makes the aircraft base not be confined to the flying saucer disc-shape; Configuration design is more convenient, and is more diversified, can increase the interesting and interactive of aircraft greatly; So can increase consumer's affinity; Market adaptability will be more extensive also, and the screw assembly of when flight and landing, not damaging has more easily simultaneously guaranteed life-span of product; And the employing said structure also helps reducing the volume of aircraft base, and then can alleviate the weight and the power consumption of whole aircraft, and structure is more reasonable, and the flight time is also more permanent; And be to guarantee balance; Can adopt two screw assemblies coaxial and direction of rotation is opposite, when flight, rotate and the rotation of the counteracting aircraft base that can interact, make that the flight of aircraft is more steady towards different directions; And safer, structure is also more reasonable.
Description of drawings
Further explain below in conjunction with the accompanying drawing and the specific embodiment:
Fig. 1 is the perspective view of the utility model;
Fig. 2 is the internal structure sketch map of first kind of embodiment of the utility model;
Fig. 3 is the internal structure sketch map of second kind of embodiment of the utility model;
Fig. 4 is the structural representation of screw assembly;
Fig. 5 is the structural representation of rotor head;
Fig. 6 is the structural representation of blade support.
The specific embodiment
Like Fig. 1 ~ shown in Figure 3; The infrared induction aircraft that the utility model provided; Primary structure comprises: as the aircraft base 1 of main body and as the screw assembly 2 of flight structure; Wherein aircraft base 1 is provided with infrared induction assembly 3, is generally positioned at aircraft base 1 bottom, induction below environment and flight is adjusted; According to product needed, can set up remotely monitored sensor in addition, realize remote control control; And, then power is provided by the power plant module 4 in the aircraft base 1 for screw assembly 2.
The utility model is selected two groups of screw assemblies 2 for use, and they are coaxial and go to upper and lower position relation each other and be set together, and is positioned at the top of aircraft base 1 jointly; So form aircraft base 1 following; Screw assembly 2 is in the structure of last similar helicopter, and so aircraft base 1 needn't be designed to envelope the appearance attitude of screw assembly 2 again, and configuration design is also more diversified; It is UFO-like no longer to be limited as disk; Help increasing the product interest, save cost simultaneously, and reduce the power consumption when flying; In addition aircraft base 1 under structure, when taking off and land, can also live with staff or instrument support, help increasing the interactive of product.
The utility model adopts two groups of screw assemblies 2; Purpose is a stress balance in order to guarantee to fly, because aircraft base 1 is less and lighter in the utility model, if one group of screw assembly 2 only; When producing lift towards a direction rotation; Can have a reverse revolving force to aircraft base 1, so can make 1 rotation of aircraft base to be unfavorable for flight; And in the utility model, two groups of screw assemblies 2, respectively through two with one heart and first rotating shaft 51 that is set-located each other, second rotating shaft 52 be connected with power plant module 4 in the aircraft base 1; According to power plant module 4 rotary power is provided; Pass to two screw assemblies 2 respectively by first rotating shaft 51, second rotating shaft 52 and realize rotation, and the direction of rotation of two groups of screw assemblies 2 is opposite, when one group of screw assembly 2 produces lift towards a direction rotation so therein; Another group screw assembly 2 produces lift towards another direction rotation; Both are superimposed, then on aircraft base 1, are cancelled out each other, and make aircraft base 1 can not rotate awing; Flying power is stronger, and flight effect is also better.
The power plant module 4 of the utility model; Mainly comprise power supply 41; Motor sub-assembly and transmission component, power supply 41 are the electronic devices and components power supply in motor sub-assembly and the aircraft base 1, the motor sub-assembly rotation; Through the transmission component transmission is the rotation of first rotating shaft 51 and second rotating shaft 52, thereby drives the rotation of two groups of screw assemblies respectively.Motor sub-assembly and transmission component need produce two rightabout selections respectively, first rotating shaft 51 and second rotating shaft 52 are controlled, made the direction of rotation of the rotating shaft 51 and second rotating shaft 52 of winning; So can realize the rotation of two groups of screw assembly different directions, generally speaking, motor sub-assembly can adopt single or two motors; Situation at single-motor; Then transmit the revolving force of two different directions respectively, give first rotating shaft 51 and second rotating shaft 52 respectively, in the structure of two motors by transmission component; Then can one group of transmission component be set corresponding respectively motor; Wherein one group of transmission cooperates first rotating shaft 51, and another group transmission cooperates second rotating shaft 52, realizes the different directions rotation of two groups of screw assemblies 2.
Provided two kinds of different transmission schemes below:
As shown in Figure 2; At the single motor transmission scheme that is first kind of embodiment; Wherein motor sub-assembly comprises active motor 420, and transmission component comprises intermeshing driving tooth wheels 433 and driven tooth wheels 434, and active motor 420 is in transmission connection with driving tooth wheels 433; The driving tooth wheels 433 and first rotating shaft 51 are in transmission connection, and the driven tooth wheels 434 and second rotating shaft 52 are in transmission connection.This embodiment is when work, and active motor 420 transmits the rotation of coming out, and at first passes to driving tooth wheels 433; Passing to first rotating shaft 51 by driving tooth wheels 433, rotate thereby drive first rotating shaft 51, is that first group of screw assembly 2 provides rotatory force; And for second group of screw assembly 2; Driven tooth wheels 434 that match with driving tooth wheels 433 then are set, and so the rotation direction of driving tooth wheels 433 has been passed through the once transformation of driven tooth wheels 434; Just pass to second rotating shaft 52 by driven tooth wheels 434; Make that the rotation direction of second rotating shaft 52 is just opposite with first rotating shaft 51, thus, promptly obtained two groups of screw assemblies 2 that make a good job of switched in opposite.
As shown in Figure 3, in another kind of embodiment, the preferred version of two motor transmissions is provided; Concrete; Motor sub-assembly comprises that first motor 421, second motor, 422, two motors can distinguish balance setting in aircraft base 1, and the revolving force of different directions is provided; Corresponding transmission component comprises first gear train 431, second gear train 432; Wherein first motor 421 is in transmission connection first rotating shaft, 51, the second motors 422 through second rotating shaft 52 that is in transmission connection of second gear train 432 through first gear train 431, realizes being in transmission connection of corresponding two rotating shafts respectively.
In order to reach flight effect preferably, except being optimized the design at aircraft base 1 and power section, the effect of screw assembly 2 is also particularly important; The utility model has provided a kind of preferable embodiment of screw assembly 2 by this; As shown in Figure 4, screw assembly 2 comprises blade support 21, rotor head 22 and blade 23, and is as shown in Figure 6; Blade support 21 middle parts are provided with rotor head jack 24, and rotor head jack 24 sidewalls are provided with the axle fixing hole 25 of two symmetries; As shown in Figure 5; Rotor head 22 lower ends are fixedly connected with first rotating shaft 51 or second rotating shaft 52; Fixed axis 221, two fixed axis 221 that rotor head 22 is provided with two symmetries insert respectively and are fixed in the diaxon fixing hole 25, form a similar hinged structure; Guarantee stress balance simultaneously, and reduced the vibration in screw assembly 2 rotary courses; Rotor head 22 tops or lower hinge are equipped with balance wing 24; Balance wing 24 both sides are articulated with auxiliary fixing arm 241 respectively; Two auxiliary fixing arms, 241 bottoms articulate with the both sides of rotor head 22 respectively; So can guarantee balance wing 24 comparatively balance be installed in rotor head 22 tops, can not distort, reach the effect of symmetric screw propeller assembly 2; Blade 23 is installed on blade support 21 ends; Usually can adopt symmetrical structure, two blades 23 are installed on the two ends of blade support 21 respectively, and rotatable blade 23 is hinged with blade support 21; Be beneficial in rotary course, to produce to cushion and reduce and vibrate, flight effect gets a promotion; During work, the power that first rotating shaft 51 or second rotating shaft 52 are rotated passes to blade support 21 through rotor head 22, makes blade support 21 and end blade 23 follow rotation, disturbance surrounding air and produce lift.
As preferred version; Blade support 21 is combined by the first blade support 211, the second blade support 212; Wherein surround rotor head jack 24 between the first blade support 211 and the second blade support 212; Diaxon fixing hole 25 respectively is arranged at the sidewall of the first blade support 211 and the second blade support 212, and so structure helps improving the convenience when making assembling.
Owing to adopt two groups of screw assemblies 2 up and down; Below that group screw assembly 2, its rotor head 22 middle parts are provided with through hole 222, first rotating shaft 51 that is used to the one group of screw assembly 2 in the side of keeping supplying is passed; So that the structure of two groups of screw assemblies 2 is independent mutually, rotation is independent of each other.
Adopt the screw assembly 2 of this structure, easy accessibility not only, and also harmonious property is good, precision is high, and flight effect is very good.
Claims (7)
1. infrared induction aircraft is characterized in that comprising:
Be provided with the aircraft base (1) of infrared induction assembly (3);
Be arranged at the power plant module (4) in the aircraft base (1); And
Coaxial and go to upper and lower two screw assemblies (2) of position relation each other; Be positioned at said aircraft base (1) top jointly; And respectively through two with one heart and the power plant module (4) in first, second rotating shaft that is set-located each other (51,52) and the aircraft base (1) be connected; According to power plant module (4) rotary power is provided, passes to two screw assemblies (2) respectively by first, second rotating shaft (51,52) and realize rotation; Wherein
The direction of rotation of said two screw assemblies (2) is opposite.
2. infrared induction aircraft according to claim 1 is characterized in that said power plant module (4) comprising:
Power supply (41);
Motor sub-assembly by power supply (41) power supply; And
The rotation of motor sub-assembly is passed to the transmission component of first, second rotating shaft (51,52).
3. infrared induction aircraft according to claim 2; It is characterized in that said motor sub-assembly comprises active motor (420); Said transmission component comprises intermeshing driving tooth wheels (433) and driven tooth wheels (434); Active motor (420) is in transmission connection with driving tooth wheels (433), and driving tooth wheels (433) are in transmission connection with first rotating shaft (51), and driven tooth wheels (434) are in transmission connection with second rotating shaft (52).
4. infrared induction aircraft according to claim 2; It is characterized in that said motor sub-assembly comprises first, second motor (421,422); Said transmission component comprises first, second gear train (431,432); Wherein first motor (421) is through first gear train (431), first rotating shaft (51) that is in transmission connection, and second motor (422) is through second gear train (432), second rotating shaft (52) that is in transmission connection.
5. infrared induction aircraft according to claim 1 is characterized in that said screw assembly (2) comprises blade support (21), rotor head (22) and blade (23); Said blade support (21) middle part is provided with rotor head jack (24), and rotor head jack (24) sidewall is provided with the axle fixing hole (25) of two symmetries; Rotor head (22) lower end is fixedly connected with first rotating shaft (51) or second rotating shaft (52), and rotor head (22) is provided with the fixed axis (221) of two symmetries, and two fixed axis (221) insert respectively and are fixed in the diaxon fixing hole (25); Rotor head (22) top or lower hinge are equipped with balance wing (24), and balance wing (24) both sides are articulated with auxiliary fixing arm (241) respectively, and two auxiliary fixing arm (241) bottoms articulate with the both sides of rotor head (22) respectively; Said blade (23) is installed on blade support (21) end.
6. infrared induction aircraft according to claim 5; It is characterized in that said blade support (21) is combined by first, second blade support (211,212); First, second blade support surrounds rotor head jack (24) between (211,212), and said diaxon fixing hole (25) respectively is arranged at first, second blade support (21) sidewall.
7. according to claim 5 or 6 described infrared induction aircraft, it is characterized in that said blade (23) and blade support (21) are hinged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120184719U CN202128908U (en) | 2011-06-03 | 2011-06-03 | Infrared sensing air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120184719U CN202128908U (en) | 2011-06-03 | 2011-06-03 | Infrared sensing air vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202128908U true CN202128908U (en) | 2012-02-01 |
Family
ID=45517694
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120184719U Ceased CN202128908U (en) | 2011-06-03 | 2011-06-03 | Infrared sensing air vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202128908U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103816671A (en) * | 2014-02-26 | 2014-05-28 | 中山市泰宝电子科技有限公司 | Infrared induction toy aircraft structure and application |
| CN105311839A (en) * | 2014-06-25 | 2016-02-10 | 上海本星电子科技有限公司 | Balloon aerial height positioner |
| CN108043041A (en) * | 2018-01-19 | 2018-05-18 | 广东美奇林互动科技股份有限公司 | A electric top with propeller |
-
2011
- 2011-06-03 CN CN201120184719U patent/CN202128908U/en not_active Ceased
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103816671A (en) * | 2014-02-26 | 2014-05-28 | 中山市泰宝电子科技有限公司 | Infrared induction toy aircraft structure and application |
| CN105311839A (en) * | 2014-06-25 | 2016-02-10 | 上海本星电子科技有限公司 | Balloon aerial height positioner |
| CN108043041A (en) * | 2018-01-19 | 2018-05-18 | 广东美奇林互动科技股份有限公司 | A electric top with propeller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| IW01 | Full invalidation of patent right |
Decision date of declaring invalidation: 20140728 Decision number of declaring invalidation: 23262 Granted publication date: 20120201 |