CN204473125U - The unmanned plane of flight stability - Google Patents
The unmanned plane of flight stability Download PDFInfo
- Publication number
- CN204473125U CN204473125U CN201420792750.2U CN201420792750U CN204473125U CN 204473125 U CN204473125 U CN 204473125U CN 201420792750 U CN201420792750 U CN 201420792750U CN 204473125 U CN204473125 U CN 204473125U
- Authority
- CN
- China
- Prior art keywords
- aileron
- fuselage
- rudder
- horizontal tail
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The utility model discloses a kind of unmanned plane of flight stability, it comprises: fuselage; Wing group, wing group comprises two wings, and two wings are separately positioned on the two ends of fuselage, and each wing is all arranged on aileron assembly, and aileron assembly comprises aileron and aileron driver train, and aileron driver train and aileron are in transmission connection; Power system, this power system comprises Power train and screw propeller, and screw propeller is rotatably installed on fuselage, and Power train drives screw propeller to rotate on fuselage; Empennage group, empennage group comprises horizontal tail and two vertical fins, each wing all connects a vertical fin, the two ends of horizontal tail are connected on two vertical fins, each vertical fin is provided with yaw rudder, horizontal tail is provided with yaw rudder driver train, yaw rudder driver train and yaw rudder are in transmission connection, and horizontal tail are provided with elevating rudder assembly.The utility model regulates direction flexible, and air flow method is even, effectively can improve its stability run and safety, avoid acutely rocking or phenomenon out of control of fuselage.
Description
Technical field
The utility model relates to a kind of unmanned plane of flight stability, belongs to vehicle technology field.
Background technology
At present, unmanned plane is that a kind of by radio robot or self programming control, it carries out the unpiloted flight equipment flown, it comes across the twenties in 20th century the earliest, target drone at that time as training uses, the purposes of unmanned plane is very extensive and cost is lower, in use procedure, surprisingly also there will not be personal casualty situation even if run into.The viability of unmanned plane is strong, and manoevreability is good, easy to use, has extremely important effect in modern war, even also gathers around at civil area and holds out broad prospects.
Due to unmanned plane not establishing driving compartment, because this reducing the consumption of power, being beneficial to and carrying out miniaturization and light-weight design.But due to unmanned plane lighter weight, be therefore easily subject to the impact of air-flow, when air-flow is at fuselage and wing section skewness, easily cause rocking of fuselage.If unmanned plane is for taking use, the picture that photographs will be caused unstable, when rocking too serious, will causing unmanned plane to crash, and not only causing loss economically, also easily injure ground people with.
Summary of the invention
Technical problem to be solved in the utility model is the defect overcoming prior art, there is provided a kind of unmanned plane of flight stability, it regulates direction flexible, and air flow method is even, effectively can improve its stability run and safety, avoid acutely rocking or phenomenon out of control of fuselage.
The utility model solves the problems of the technologies described above the technical scheme taked: a kind of unmanned plane of flight stability, and it comprises:
Fuselage;
Wing group, wing group comprises two wings, and two wings are separately positioned on the two ends of fuselage, and each wing is all arranged on aileron assembly, aileron assembly comprises aileron and aileron driver train, and aileron driver train and aileron are in transmission connection so that it drives aileron to swing up and down relative to wing;
Power system, this power system comprises Power train and screw propeller, and screw propeller is rotatably installed on fuselage, and Power train drives screw propeller to rotate on fuselage;
Empennage group, empennage group comprises horizontal tail and two vertical fins, each wing all connects a vertical fin, the two ends of horizontal tail are connected on two vertical fins, each vertical fin is provided with yaw rudder, horizontal tail is provided with yaw rudder driver train, yaw rudder driver train and yaw rudder are in transmission connection so that its driving direction rudder swings relative to vertical fin, horizontal tail is provided with elevating rudder assembly, elevating rudder assembly comprises elevating rudder and elevating rudder driver train, and elevating rudder driver train and elevating rudder are in transmission connection so that it drives elevating rudder to swing up and down relative to horizontal tail.
Further in order to make design comparison attractive in appearance, the front portion of fuselage is also provided with a window.
Time further in order to make unmanned plane landing relatively smoothly and steadily, the unmanned plane of flight stability also comprises pulley assembly, this pulley assembly comprises head pulley assembly and auxiliary pulley assembly, and head pulley assembly is arranged on the lower end of fuselage, and the lower end of each wing is provided with an auxiliary pulley assembly.
Further provide a kind of concrete structure of screw propeller, screw propeller is three bladed propeller.
Further provide a kind of concrete structure of yaw rudder driver train, yaw rudder driver train comprises motor, connect block, two first connecting rods, two swiveies, two second connecting rods and two connectors, connecting block is arranged on the output shaft of motor, one end of two first connecting rods is respectively on the company's of being hinged on block, the other end of first connecting rod is hinged with corresponding swivel respectively, one end of second connecting rod is hinged with corresponding swivel, the other end of second connecting rod is hinged with corresponding connector, two connectors are separately positioned on corresponding yaw rudder, motor is arranged in horizontal tail, swivel is hinged in horizontal tail.
After have employed technique scheme, the utility model is provided with wing and empennage, and empennage has horizontal tail and two vertical fins, and is provided with aileron assembly on wing, regulates its air balance, make air flow method even, thus effectively can improve its stability run and safety, avoid acutely rocking or phenomenon out of control of fuselage, horizontal tail is provided with elevating rudder assembly, vertical fin is provided with yaw rudder, is conducive to regulating its heading.
Accompanying drawing explanation
Fig. 1 is the block diagram of the unmanned plane of flight stability of the present utility model;
Fig. 2 is the upward view of the unmanned plane of flight stability of the present utility model;
Fig. 3 is the A portion enlarged drawing in Fig. 2.
Detailed description of the invention
In order to make content of the present utility model more easily be clearly understood, below according to specific embodiment also by reference to the accompanying drawings, the utility model is described in further detail.
As shown in Fig. 1 ~ 3, a kind of unmanned plane of flight stability, it comprises:
Fuselage 1;
Wing group, wing group comprises two wings 2, two wings 2 are separately positioned on the two ends of fuselage 1, each wing 2 is all arranged on aileron assembly, aileron assembly comprises aileron 3 and aileron driver train, and aileron driver train and aileron 3 are in transmission connection so that it drives aileron 3 to swing up and down relative to wing 2;
Power system, this power system comprises Power train 4 and screw propeller 5, and screw propeller 5 is rotatably installed on fuselage 1, and Power train 4 drives screw propeller 5 to rotate on the fuselage 1;
Empennage group, empennage group comprises horizontal tail 7 and two vertical fins 6, each wing 2 all connects a vertical fin 6, the two ends of horizontal tail 7 are connected on two vertical fins 6, each vertical fin 6 is provided with yaw rudder 8, horizontal tail 7 is provided with yaw rudder driver train, yaw rudder driver train and yaw rudder 8 are in transmission connection so that its driving direction rudder 8 swings relative to vertical fin 6, horizontal tail 7 is provided with elevating rudder assembly, elevating rudder assembly comprises elevating rudder 9 and elevating rudder driver train, elevating rudder driver train and elevating rudder 9 are in transmission connection so that it drives elevating rudder 9 to swing up and down relative to horizontal tail 7.
As shown in Figure 1, the front portion of fuselage 1 is also provided with a window 11.
As shown in Figure 1, 2, the unmanned plane of flight stability also comprises pulley assembly, and this pulley assembly comprises head pulley assembly 10 and auxiliary pulley assembly 12, and head pulley assembly 10 is arranged on the lower end of fuselage 1, and the lower end of each wing 2 is provided with an auxiliary pulley assembly 12.
As shown in Figure 1, screw propeller 5 is three bladed propeller, but is not limited thereto.
As shown in Figure 3, yaw rudder driver train comprises motor 13, connect block 14, two first connecting rods 15, two swiveies 16, two second connecting rods 17 and two connectors 18, connecting block 14 is arranged on the output shaft of motor 13, one end of two first connecting rods 15 is respectively on the company's of being hinged on block 14, the other end of first connecting rod 15 is hinged with corresponding swivel 16 respectively, one end of second connecting rod 17 is hinged with corresponding swivel 16, the other end of second connecting rod 17 is hinged with corresponding connector 18, two connectors 18 are separately positioned on corresponding yaw rudder 8, motor 13 is arranged in horizontal tail 7, swivel 16 is hinged in horizontal tail 7.
Power train 4 in the utility model adopts the Power train of conventional unmanned plane to be driven by servomotor, aileron driver train in the utility model and elevating rudder driver train all adopt Conventional mechanisms, and namely motor drives corresponding driven member to swing by connecting rod mechanism.
Principle of work of the present utility model is as follows:
The utility model is provided with wing 2 and empennage, and empennage has horizontal tail 7 and two vertical fins 6, and aileron assembly is provided with on wing 2, regulate its air balance, make air flow method even, thus effectively can improve its stability run and safety, avoid acutely rocking or phenomenon out of control of fuselage, horizontal tail 7 is provided with elevating rudder assembly, vertical fin 6 is provided with yaw rudder 8, be conducive to regulating its heading.
Above-described specific embodiment; technical matters, technical scheme and beneficial effect that the utility model solves are further described; be understood that; the foregoing is only specific embodiment of the utility model; be not limited to the utility model; all within spirit of the present utility model and principle, any amendment made, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (5)
1. a unmanned plane for flight stability, is characterized in that, it comprises:
Fuselage (1);
Wing group, wing group comprises two wings (2), two wings (2) are separately positioned on the two ends of fuselage (1), (2) are all arranged on aileron assembly to each wing, aileron assembly comprises aileron (3) and aileron driver train, and aileron driver train and aileron (3) are in transmission connection so that it drives aileron (3) to swing up and down relative to wing (2);
Power system, this power system comprises Power train (4) and screw propeller (5), and screw propeller (5) is rotatably installed on fuselage (1), and described Power train (4) drives screw propeller (5) in the upper rotation of fuselage (1);
Empennage group, empennage group comprises horizontal tail (7) and two vertical fins (6), each wing (2) all connects a vertical fin (6), the two ends of horizontal tail (7) are connected on two vertical fins (6), each vertical fin (6) is provided with yaw rudder (8), (7) are provided with yaw rudder driver train to horizontal tail, yaw rudder driver train and yaw rudder (8) are in transmission connection so that its driving direction rudder (8) swings relative to vertical fin (6), (7) are provided with elevating rudder assembly to horizontal tail, elevating rudder assembly comprises elevating rudder (9) and elevating rudder driver train, elevating rudder driver train and elevating rudder (9) are in transmission connection so that it drives elevating rudder (9) to swing up and down relative to horizontal tail (7).
2. the unmanned plane of flight stability according to claim 1, is characterized in that: the front portion of described fuselage (1) is also provided with a window (11).
3. the unmanned plane of flight stability according to claim 1 and 2, it is characterized in that: also comprise pulley assembly, this pulley assembly comprises head pulley assembly (10) and auxiliary pulley assembly (12), head pulley assembly (10) is arranged on the lower end of fuselage (1), and the lower end of described each wing (2) is provided with an auxiliary pulley assembly (12).
4. the unmanned plane of flight stability according to claim 1, is characterized in that: described screw propeller (5) is three bladed propeller.
5. the unmanned plane of flight stability according to claim 1, it is characterized in that: yaw rudder driver train comprises motor (13), connect block (14), two first connecting rods (15), two swiveies (16), two second connecting rods (17) and two connectors (18), connecting block (14) is arranged on the output shaft of motor (13), one end of two first connecting rods (15) is respectively on the company's of being hinged on block (14), the other end of first connecting rod (15) is hinged with corresponding swivel (16) respectively, one end of second connecting rod (17) is hinged with corresponding swivel (16), the other end of second connecting rod (17) is hinged with corresponding connector (18), two connectors (18) are separately positioned on corresponding yaw rudder (8), motor (13) is arranged in horizontal tail (7), swivel (16) is hinged in horizontal tail (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420792750.2U CN204473125U (en) | 2014-12-16 | 2014-12-16 | The unmanned plane of flight stability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420792750.2U CN204473125U (en) | 2014-12-16 | 2014-12-16 | The unmanned plane of flight stability |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204473125U true CN204473125U (en) | 2015-07-15 |
Family
ID=53628914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420792750.2U Expired - Fee Related CN204473125U (en) | 2014-12-16 | 2014-12-16 | The unmanned plane of flight stability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204473125U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005371A (en) * | 2016-05-27 | 2016-10-12 | 东北师范大学 | Differential and transfer direct-drive unmanned aerial vehicle with three full-flying control surfaces |
-
2014
- 2014-12-16 CN CN201420792750.2U patent/CN204473125U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005371A (en) * | 2016-05-27 | 2016-10-12 | 东北师范大学 | Differential and transfer direct-drive unmanned aerial vehicle with three full-flying control surfaces |
| CN106005371B (en) * | 2016-05-27 | 2018-07-31 | 东北师范大学 | Difference directly drives dynamic three rudder face unmanned planes entirely |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204473123U (en) | Unmanned plane | |
| CN105346719A (en) | Perpendicular take-off and landing aircraft | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN101633409A (en) | Bidirectional synchronous automatic turning flapping-wing aircraft | |
| CN104229138A (en) | Split differential tail wing control mechanism of flapping-wing micro air vehicle | |
| CN203544372U (en) | Fixed-wing aircraft additionally provided with cross-flow fan | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN105775128A (en) | Flight vehicle | |
| CN106864744A (en) | A kind of co-axial rotor variant vertically taking off and landing flyer | |
| CN105059541A (en) | Novel multi-axis unmanned aerial vehicle | |
| CN204473119U (en) | Lightweight unmanned plane | |
| CN105775110A (en) | Unmanned aerial vehicle with flight stability | |
| CN206434864U (en) | A kind of aircraft of VTOL | |
| CN205381400U (en) | Aircraft | |
| CN106275416A (en) | The composite aircraft that fixed-wing forms with many rotors | |
| CN204473125U (en) | The unmanned plane of flight stability | |
| CN104875875A (en) | Air wing type airflow directional load transportation air vehicle | |
| CN105346725A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN205256672U (en) | Manpower drive fixed -wing aircraft | |
| CN203996872U (en) | A kind of unmanned airplane empennage balance adjusting structure | |
| CN202526908U (en) | Double-leaf propeller of model plane | |
| CN204473124U (en) | Without empennage unmanned plane | |
| CN204473122U (en) | A kind of unmanned plane | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN105438466A (en) | Human-powered fixed-wing aeroplane |
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: 20150715 Termination date: 20171216 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |