CN205730366U - A kind of wing horizontal tail full dynamic formula aircraft model plane - Google Patents
A kind of wing horizontal tail full dynamic formula aircraft model plane Download PDFInfo
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- CN205730366U CN205730366U CN201620414035.4U CN201620414035U CN205730366U CN 205730366 U CN205730366 U CN 205730366U CN 201620414035 U CN201620414035 U CN 201620414035U CN 205730366 U CN205730366 U CN 205730366U
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- tail
- propeller
- fuselage
- motor
- model plane
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Abstract
The utility model discloses a kind of wing horizontal tail full dynamic formula aircraft model plane, including tail, fuselage and head, described tail and head are respectively and fixedly installed to rear end and the front end of fuselage, vertical tail and tailplane are installed on described tail, and vertical tail is vertically mounted on the upper end of tailplane, described head front end is installed with propeller, described propeller is rotationally connected by propeller drive shaft with propeller motor, and propeller motor is arranged on the inside of head, the lower end of described fuselage is provided with undercarriage and hydraulic telescopic device, described vertical tail, tailplane and wing be internally provided with fixed transverse rod and rotary shaft, and fixed transverse rod is fixing on the rotating shaft, described rotary shaft is connected by shaft coupling and drive axis with motor of operating the rudder, and motor of operating the rudder is arranged on the inside of fuselage.This utility model realizes wing horizontal tail and entirely moves function so that model plane operate the rudder simpler precisely, fly more steady.
Description
Technical field
This utility model relates to model plane equipment technical field, is specially a kind of wing horizontal tail full dynamic formula aircraft model plane.
Background technology
At present, the wing of traditional model plane, vertical tail and tailplane are integrally fixed on fuselage, the landing of model plane and the regulation of flight angle are all to be controlled by the elevator on wing, vertical tail and tailplane and rudder, control accuracy it is difficult to ensure that, cause taking off of model plane poor with stationarity in-flight, often fall phenomenon, it is difficult to meet the demand of user.
Summary of the invention
The purpose of this utility model is to provide a kind of wing horizontal tail full dynamic formula aircraft model plane, to solve the problem proposed in above-mentioned background technology, is had an advantageous effect in that；Control device, operate the rudder motor and rotary shaft with the use of, it is achieved wing horizontal tail moves function entirely so that the direction controlling of model plane is simpler and accurate.
nullFor achieving the above object，This utility model following technical scheme of offer: a kind of wing horizontal tail full dynamic formula aircraft model plane，Including tail、Fuselage and head，Described tail and head are respectively and fixedly installed to rear end and the front end of fuselage，Vertical tail and tailplane are installed on described tail，And vertical tail is vertically mounted on the upper end of tailplane，Described head front end is installed with propeller，Described propeller is rotationally connected by propeller drive shaft with propeller motor，And propeller motor is arranged on the inside of head，The lower end of described fuselage is provided with undercarriage and hydraulic telescopic device，And undercarriage is connected by hydraulic stem is fixing with hydraulic telescopic device，Described vertical tail、Tailplane and wing be internally provided with fixed transverse rod and rotary shaft，And fixed transverse rod is fixing on the rotating shaft，Described rotary shaft is connected by shaft coupling and drive axis with motor of operating the rudder，And motor of operating the rudder is arranged on the inside of fuselage.
Preferably, the input of described propeller motor and motor of operating the rudder is electrically connected with the outfan controlling device respectively, and the input controlling device is electrically connected with the outfan of supply unit and signal processing apparatus respectively.
Preferably, the input of described signal processing apparatus is electrically connected with the outfan of radio receiver.
Preferably, the input of described control device outfan and signal processing apparatus is electrically connected with the input of homeostasis device and outfan respectively.
Preferably, described fuselage be provided above driving cabin.
Compared with prior art, the beneficial effects of the utility model are: this plant control unit, operate the rudder motor and rotary shaft with the use of, it is achieved wing horizontal tail moves function entirely so that the direction controlling of model plane is simpler and accurate；The use of radio receiver, it is simple to ground handling operator's control to model plane；The use of homeostasis device, it is ensured that the flight of model plane is more steady；Undercarriage and hydraulic telescopic device with the use of so that rising and falling more steadily smoothly of model plane；This utility model uses wing horizontal tail entirely to move, and is greatly improved flight angle and the balance property regulation precision of model plane, it is achieved intelligentized controlled in wireless.
Accompanying drawing explanation
Fig. 1 is the structural representation that this utility model is overall；
Fig. 2 is that this utility model is operated the rudder the structural representation of motor；
Fig. 3 is system block diagram of the present utility model.
In figure: 1-vertical tail；2-tail；3-tailplane；4-driving cabin；5-fuselage；6-propeller；7-propeller drive shaft；8-head；9-propeller motor；10-undercarriage；11-hydraulic telescopic device；12-wing；13-shaft coupling；14-fixed transverse rod；15-rotary shaft；16-operates the rudder motor；17-power transmission shaft；18-radio receiver；19-supply unit；20-signal processing apparatus；21-controls device；22-homeostasis device.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is clearly and completely described, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole embodiments.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of this utility model protection.
nullRefer to Fig. 1-3，A kind of embodiment that this utility model provides: a kind of wing horizontal tail full dynamic formula aircraft model plane，Including tail 2、Fuselage 5 and head 8，Tail 2 and head 8 are respectively and fixedly installed to rear end and the front end of fuselage 5，Vertical tail 1 and tailplane 3 are installed on tail 2，And vertical tail 1 is vertically mounted on the upper end of tailplane 3，Head 8 front end is installed with propeller 6，Propeller 6 is rotationally connected by propeller drive shaft 7 with propeller motor 9，And propeller motor 9 is arranged on the inside of head 8，The lower end of fuselage 5 is provided with undercarriage 10 and hydraulic telescopic device 11，And undercarriage 10 is connected by hydraulic stem is fixing with hydraulic telescopic device 11，Vertical tail 1、Tailplane 3 and wing 12 be internally provided with fixed transverse rod 14 and rotary shaft 15，And fixed transverse rod 14 is fixed in rotary shaft 15，Rotary shaft 15 is rotationally connected by shaft coupling 13 and power transmission shaft 17 with motor 16 of operating the rudder，And motor 16 of operating the rudder is arranged on the inside of fuselage 5，The input of propeller motor 9 and motor 16 of operating the rudder is electrically connected with the outfan controlling device 21 respectively，And the input controlling device 21 is electrically connected with the outfan of supply unit 19 and signal processing apparatus 20 respectively，The input of signal processing apparatus 20 is electrically connected with the outfan of radio receiver 18，Control the input of device 21 outfan and signal processing apparatus 20 input and the outfan respectively with homeostasis device 22 to be electrically connected with，Fuselage 5 be provided above driving cabin 4.
Operation principle；During use, model plane are fully charged, followed by bottom surface wireless remote controller, model plane are carried out wireless control, after radio receiver 18 on model plane receives the low wireless signal in ground, carry out the process of signal, then pass through control device 21 and control propeller motor 9 and model plane are taken off by motor 16 of operating the rudder, speed and the manipulation in direction, the internal homeostasis device 22 arranged of fuselage 5 can detect in real time in-flight, and the information detected is fed back to signal processing apparatus 20, finally by controlling device 21, model plane are adjusted, to keep the balance of self, can be buffered by undercarriage 10 during landing, it is finally completed stable landing.
It is obvious to a person skilled in the art that this utility model is not limited to the details of above-mentioned one exemplary embodiment, and in the case of without departing substantially from spirit or essential attributes of the present utility model, it is possible to realize this utility model in other specific forms.Therefore, no matter from the point of view of which point, embodiment all should be regarded as exemplary, and be nonrestrictive, scope of the present utility model is limited by claims rather than described above, it is intended that all changes fallen in the implication of equivalency and scope of claim included in this utility model.Should not be considered as limiting involved claim by any reference in claim.
Claims (5)
- null1. wing horizontal tail full dynamic formula aircraft model plane，Including tail (2)、Fuselage (5) and head (8)，It is characterized in that: described tail (2) and head (8) are respectively and fixedly installed to rear end and the front end of fuselage (5)，Vertical tail (1) and tailplane (3) are installed on described tail (2)，And vertical tail (1) is vertically mounted on the upper end of tailplane (3)，Described head (8) front end is installed with propeller (6)，Described propeller (6) is rotationally connected by propeller drive shaft (7) with propeller motor (9)，And propeller motor (9) is arranged on the inside of head (8)，The lower end of described fuselage (5) is provided with undercarriage (10) and hydraulic telescopic device (11)，And undercarriage (10) is connected by hydraulic stem is fixing with hydraulic telescopic device (11)，Described vertical tail (1)、Tailplane (3) and wing (12) be internally provided with fixed transverse rod (14) and rotary shaft (15)，And fixed transverse rod (14) is fixed in rotary shaft (15)，Described rotary shaft (15) is rotationally connected by shaft coupling (13) and power transmission shaft (17) with motor of operating the rudder (16)，And motor of operating the rudder (16) is arranged on the inside of fuselage (5).
- A kind of wing horizontal tail full dynamic formula aircraft model plane the most according to claim 1, it is characterized in that: the input of described propeller motor (9) and motor of operating the rudder (16) is electrically connected with the outfan controlling device (21) respectively, and control the input of device (21) respectively with the electric connection of the outfan of supply unit (19) and signal processing apparatus (20).
- A kind of wing horizontal tail full dynamic formula aircraft model plane the most according to claim 2, it is characterised in that: the input of described signal processing apparatus (20) is electrically connected with the outfan of radio receiver (18).
- A kind of wing horizontal tail full dynamic formula aircraft model plane the most according to claim 2, it is characterised in that: the input of described control device (21) outfan and signal processing apparatus (20) input and outfan with homeostasis device (22) respectively is electrically connected with.
- A kind of wing horizontal tail full dynamic formula aircraft model plane the most according to claim 1, it is characterised in that: described fuselage (5) be provided above driving cabin (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620414035.4U CN205730366U (en) | 2016-05-10 | 2016-05-10 | A kind of wing horizontal tail full dynamic formula aircraft model plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620414035.4U CN205730366U (en) | 2016-05-10 | 2016-05-10 | A kind of wing horizontal tail full dynamic formula aircraft model plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205730366U true CN205730366U (en) | 2016-11-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620414035.4U Expired - Fee Related CN205730366U (en) | 2016-05-10 | 2016-05-10 | A kind of wing horizontal tail full dynamic formula aircraft model plane |
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| Country | Link |
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| CN (1) | CN205730366U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109157847A (en) * | 2018-11-06 | 2019-01-08 | 大连理工大学 | A kind of fixed-wing model plane structure and installation method based on carbon beam |
| CN109395411A (en) * | 2018-11-14 | 2019-03-01 | 郑岚心 | A kind of implementation method for preventing blade from fractureing when model plane low-latitude flying |
-
2016
- 2016-05-10 CN CN201620414035.4U patent/CN205730366U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109157847A (en) * | 2018-11-06 | 2019-01-08 | 大连理工大学 | A kind of fixed-wing model plane structure and installation method based on carbon beam |
| CN109157847B (en) * | 2018-11-06 | 2023-11-24 | 大连理工大学 | Fixed wing aeromodelling structure based on carbon rod and installation method |
| CN109395411A (en) * | 2018-11-14 | 2019-03-01 | 郑岚心 | A kind of implementation method for preventing blade from fractureing when model plane low-latitude flying |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161130 Termination date: 20170510 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |