CN210455186U - Unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof - Google Patents
Unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof Download PDFInfo
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- CN210455186U CN210455186U CN201920987600.XU CN201920987600U CN210455186U CN 210455186 U CN210455186 U CN 210455186U CN 201920987600 U CN201920987600 U CN 201920987600U CN 210455186 U CN210455186 U CN 210455186U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The utility model provides an unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof, include: wings, split ailerons and transmission; the transmission device comprises a driving steering engine, an adjusting clamp hole, a transmission connecting rod and a twisting machine arm, the driving steering engine transmits power to the adjusting clamp hole, one end of the transmission connecting rod is connected with the adjusting clamp hole, and the other end of the transmission connecting rod is abutted to the twisting machine arm; the split ailerons are located behind and below the wings. The utility model adopts the cracking type aileron structure, no gap is formed on the surface of the airfoil, thereby not only meeting the excellent pneumatic performance of the airfoil, but also providing favorable guarantee for laying a solar cell panel on the airfoil; meanwhile, due to the matching of the cracking type ailerons and the driving device, the operation mode is simplified, the operation efficiency is improved, and the weight of the driving device is reduced.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, especially, unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof.
Background
Roll control of a conventional fixed wing drone is accomplished by an aileron control system. The differential deflection of the left and right ailerons is controlled simultaneously by controlling the rudder stock, so that the lift force generated by one side of the lower aileron is increased, and the lift force of the aileron on the upper side is reduced. Based on the lift difference on the two sides of the wing, the rolling moment of the airplane is generated. However, controlling the flap based on this form has resulted in some undesirable consequences. Firstly, the left aileron and the right aileron are controlled to simultaneously deflect and move, so that difficulty is brought to a pilot or a flying hand, and misoperation is easily caused; secondly, the left aileron and the right aileron are controlled to move simultaneously, so that the power consumption of the airplane is increased; thirdly, when the ailerons are in a deflection state, discontinuous points appear on the trailing edge surface of the wings, and the smooth aerodynamic shape of the upper surface of the wings is damaged; fourthly, the method comprises the following steps: the conventional aileron structure has the defect that when the aileron structure on one side of the wing is deflected due to the insufficient design, the generated rolling torque is too small, so that the rolling operation of an aircraft cannot be met.
Conventional fixed wing unmanned aerial vehicle, the operation of rolling is realized through differential drive's aileron, and this kind of mode causes a series of realistic problems, and if the wing trailing edge surface is not smooth, aileron structure weight is too big, the power consumption too big scheduling problem that the aileron was controlled. Therefore, for the current industrial-grade fixed-wing unmanned aerial vehicle, a set of control structure of a split type aileron needs to be provided based on a split type aileron structure of an aircraft aiming at the problem of the existing aileron.
SUMMERY OF THE UTILITY MODEL
The utility model provides an unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof to solve the aileron operating efficiency low, the complicated scheduling problem of operation mode that current fixed wing unmanned aerial vehicle exists.
The specific technical scheme is as follows:
a drive arrangement for a split flap of an unmanned aerial vehicle, comprising: wings, split ailerons and transmission; the transmission device comprises a driving steering engine, an adjusting clamp hole, a transmission connecting rod and a twisting machine arm, the driving steering engine transmits power to the adjusting clamp hole, one end of the transmission connecting rod is connected with the adjusting clamp hole, and the other end of the transmission connecting rod is abutted to the twisting machine arm; the split ailerons are located behind and below the wings.
Preferably, the driving steering engine is a brushless motor and is installed inside the wing.
Preferably, the deflection angle of the split aileron is 0-90 degrees, and the deflection of the split aileron is controlled by the transmission device.
Preferably, the wing surface is covered with a solar panel.
Preferably, the material of the wing comprises one or more of an aircraft layer wood, a composite material, a carbon fiber material and an aluminum alloy material.
Preferably, the material of the split flap comprises one or more of balsa wood, a composite material, a carbon fiber material and an aluminum alloy material.
Preferably, the connection means of the wing and the split aileron comprises one or more of a connecting rod, a bearing and a screw connection.
An unmanned aerial vehicle comprising a drive arrangement for a split flap of an unmanned aerial vehicle as claimed in any of claims 1 to 7.
Compared with the prior art, an unmanned aerial vehicle and drive arrangement of formula aileron that splits thereof have following advantage:
the utility model provides an unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof adopts the fracture formula aileron structure, and there is not the gap on the wing surface, not only satisfies the good aerodynamic performance of wing, also provides favourable assurance for the wing is laid solar cell panel; meanwhile, due to the matching of the cracking type ailerons and the driving device, the operation mode is simplified, the operation efficiency is improved, and the weight of the driving device is reduced.
Drawings
Fig. 1 is a schematic view of a driving device of a split type aileron of an unmanned aerial vehicle according to the present invention;
fig. 2 is a top view of a driving device of a split type aileron of an unmanned aerial vehicle according to the present invention;
fig. 3 is an isometric view of the driving device of the split type aileron of the unmanned aerial vehicle provided by the utility model.
Description of reference numerals:
1 wing 2 fracture formula aileron 3 drive steering wheel 4 adjustment card hole 5 transmission connecting rod
6 torsion machine arm 7 front carbon rod hole 8 rear carbon rod hole 9 ribbed plate 10 wing rib
Detailed Description
The technical solution of the present invention will be described in detail with reference to the specific embodiments. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Fig. 1 is the utility model provides a drive arrangement schematic diagram of unmanned aerial vehicle formula aileron that splits, include: the aircraft comprises a wing 1, a cracking type aileron 2 and a transmission device; the transmission device comprises a driving steering engine 3, an adjusting clamp hole 4, a transmission connecting rod 5 and a twisting machine arm 6, wherein the driving steering engine 3 transmits power to the adjusting clamp hole 4, the driving steering engine 3 is a brushless motor and is installed inside the wing 1, one end of the transmission connecting rod 5 is connected with the adjusting clamp hole 4, and the other end of the transmission connecting rod is abutted to the twisting machine arm 6; the split aileron 2 is positioned at the lower rear part of the wing 1.
The brushless motor (as shown in fig. 2) installed inside the wing 1 transmits power to the adjusting clamp hole 4, the adjusting clamp hole 4 drives the transmission connecting rod 5 to move, and then the torsion arm 6 is controlled to move, the torsion arm 6 is connected with the cracking type aileron 2, and deflection of the cracking type aileron 2 is achieved. The deflection angle range of the cracking type aileron 2 is 0-90 degrees, and when the deflection angle is 0 degree, the cracking type aileron 2 is completely attached to the upper surface of the wing 1; when the deflection angle is 90 degrees, the combined type wind power generating device can be used as a spoiler for increasing the resistance of an aircraft to reduce the flying speed; when the deflection angle is in the range of 0-90 degrees, the flares are in the middle state of deflection of the split type ailerons 1; in particular, the adjusting range of the rolling moment of the aircraft is controlled when the deflection angle of the cracking type aileron 1 is in the range of 0-45 degrees.
The solar cell panel is covered on the surface of the wing 1, so that the endurance time can be prolonged. On the other hand, the fracture type aileron 2 is positioned at the rear lower part of the wing 1, so that an assembly gap can not be generated on the upper surface of the wing 1, and the integrity and smoothness of the surface of the wing 1 can not be damaged. Meanwhile, the laying efficiency of the solar cell panel cannot be reduced.
As shown in fig. 2 and 3, the wing 1 further includes a rib 9, a rib 10, and a carbon rod passing through the front carbon rod hole 7 and the rear carbon rod hole 8 to cross inside the wing 1 in parallel with the rib 9, and the rib 10 is perpendicular to the rib 9 and the carbon rod. The crossed arrangement of the structures improves the strength of the wing 1.
The material of the wing 1 comprises one or more of aviation laminated wood, composite materials, carbon fiber materials and aluminum alloy materials.
The material of the cracking type aileron 2 comprises one or more of balsa wood, composite material, carbon fiber material and aluminum alloy material.
The connection mode of the wing 1 and the split aileron 2 comprises one or more of connecting rods, bearings and screw connection.
The utility model also provides an unmanned aerial vehicle, including the above drive arrangement of fracture formula aileron. On the other hand, the aircraft further comprises an airframe, a nose, the wing 1, a control system and an energy supply device. The control system is electrically connected with the driving steering engine 3, and the driving steering engine 3 is arranged inside the wing 1.
The patent of the utility model provides an unmanned aerial vehicle formula aileron's that ftractures drive arrangement when guaranteeing operating efficiency, can accomplish aileron structure weight lighter and manipulate more power saving.
Conventional fixed wing unmanned aerial vehicle, the operation of rolling is realized through differential drive's aileron, and this kind of mode causes a series of realistic problems, and if the wing trailing edge surface is not smooth, aileron structure weight is too big, the power consumption too big scheduling problem that the aileron was controlled. Therefore, for the current industrial-grade fixed wing unmanned aerial vehicle, a set of driving device of a split type aileron is needed to be provided based on a split type aileron structure of an aircraft aiming at the problem of the existing aileron. The split type aileron driving device is a feasible scheme with lower cost and in engineering.
An object of the utility model is to provide a fracture formula aileron drive arrangement to solve the aileron operating efficiency that current fixed wing unmanned aerial vehicle exists low, the operation mode is complicated, and bring control structure weight overweight from this, the complicated and the inconvenient scheduling problem of installation of aileron structure of processing technology. Meanwhile, the technical problems that due to the fact that assembly gaps are generated on the upper surface of the wing and damage the integrity and smoothness of the surface of the wing, aerodynamic efficiency of the wing is reduced and the like caused by the fact that the wing and the aileron are assembled are solved. And the utility model discloses a fracture formula aileron structure, the area and the mounted position of the fracture formula aileron size of size, the fracture formula aileron of its design can realize when the fracture formula aileron takes place to deflect in wing unilateral, and the roll-over moment of production satisfies unmanned aerial vehicle's roll-over motion.
The utility model discloses a fracture formula aileron drive arrangement, its theory of operation is: by adopting a cracking type aileron control scheme, when the cracking type aileron of the left wing deflects downwards, the lift force of the wing on the side is increased, but the cracking type aileron of the right wing does not deflect, and at the moment, the aircraft generates a rightward rolling moment, so that the aircraft rolls rightward; when the cracking type aileron of the right wing deflects upwards, the lifting force of the wing on the side is reduced, but the cracking type aileron of the left wing does not deflect, and at the moment, the aircraft generates leftward rolling torque, so that the aircraft rolls leftward.
The structural composition of the flap will now be described in detail. The utility model discloses a fracture formula aileron drive arrangement includes: the airplane comprises an airplane body, wherein the airplane body comprises a wing 1, and a split type aileron 2 is arranged below the trailing edge of the wing; the brushless motor is arranged in the machine body and is provided with an adjusting clamping hole 4, and a transmission connecting rod 5 for driving the cracking type aileron is connected to the adjusting clamping hole 4; the other end of the transmission connecting rod 5 is sleeved on a torsion arm 6 and used for controlling deflection of the split type aileron.
According to the aircraft cracking type aileron driving device, the cracking type ailerons 2 are arranged below the rear edges of the wings 1, and the brushless motors are arranged in the wings 1, so that the appearance structure of the aircraft is improved, and the good aerodynamic appearance of the wings is ensured. The other end of the transmission connecting rod 5 is connected with a torsion arm 6 and controls the deflection of the cracking type aileron 2. Finally, the technical effect that the linear motion of the driving steering engine 3 is converted into the rotary motion of the control surface of the split aileron 2 through the transmission connecting rod 5 so as to drive the control surface of the split aileron is achieved.
In the aircraft cracking type aileron structure, the theoretical deflection angle is 0-90 degrees, and when the deflection angle is 0 degree, the cracking type aileron 2 is completely jointed with the upper surface of the wing 1; when the deflection angle is 90 degrees, the combined type wind power generating device can be used as a spoiler for increasing the resistance of an aircraft to reduce the flying speed; when the deflection angle is in the range of 0-90 degrees, the flares are in the middle state of deflection of the split type ailerons 2; in particular, the adjusting range of the rolling moment of the aircraft is controlled when the deflection angle of the cracking type aileron 2 is in the range of 0-45 degrees.
The main reasons for innovating the control mode of the split aileron are as follows: for the first, for current fixed wing drones, in particular, for industrial-grade fixed wing drones. Due to the adoption of the traditional aileron layout form, the surface of the wing is discontinuous under the condition of aileron deflection, and the streamline aerodynamic shape of the wing is damaged. Secondly, especially for the fixed wing solar unmanned aerial vehicle, the area of the wing for effectively installing the solar cell panel is reduced due to the assembly clearance of the ailerons; thirdly, due to the adoption of a differential control strategy, the control of the ailerons is too complex, and operation errors are easily caused; fourthly, the simultaneous operation of the left and right ailerons causes an increase in the loss of electric power, and in particular, for the industrial-grade fixed wing of a lithium battery, a reduction in the endurance time is brought about.
The material of the wing adopts aviation laminated wood, composite material, carbon fiber material, aluminum alloy material and the like;
the materials of the split type ailerons adopt balsa, composite materials, carbon fiber materials, aluminum alloy materials and the like;
the connection mode of the wings and the cracking type ailerons can be realized through connecting rods, bearings, screws and the like.
To sum up, the utility model provides an unmanned aerial vehicle and a driving device of a cracking type aileron thereof, which adopts a cracking type aileron structure, and the surface of the wings has no gap, thereby not only meeting the excellent pneumatic performance of the wings, but also providing favorable guarantee for laying a solar cell panel on the wings; meanwhile, due to the matching of the cracking type ailerons and the driving device, the operation mode is simplified, the operation efficiency is improved, and the weight of the driving device is reduced.
The above embodiments are preferred embodiments of the present invention, and do not limit the scope of the present invention. Any technical personnel in the technical field that the utility model belongs to, under the prerequisite that does not deviate from the spirit and scope of the utility model discloses, it is right that the equivalent structure that the content was done of the utility model all falls into within the patent scope that the utility model claims protection.
Claims (8)
1. The utility model provides a drive arrangement of unmanned aerial vehicle formula aileron that splits which characterized in that includes: the aircraft comprises a wing (1), a split type aileron (2) and a transmission device;
the transmission device comprises a driving steering engine (3), an adjusting clamping hole (4), a transmission connecting rod (5) and a torsion machine arm (6), the driving steering engine (3) transmits power to the adjusting clamping hole (4), one end of the transmission connecting rod (5) is connected with the adjusting clamping hole (4), and the other end of the transmission connecting rod is abutted to the torsion machine arm (6);
the cracking type aileron (2) is positioned at the lower rear part of the wing (1).
2. The driving device of the unmanned aerial vehicle split aileron of claim 1, wherein the driving steering engine (3) is a brushless motor and is installed inside the wing (1).
3. The driving device of the split aileron of the drone according to claim 1, wherein the deflection angle of the split aileron (2) is 0-90 °, the transmission controlling the deflection of the split aileron (2).
4. The drive device of a split aileron for unmanned aerial vehicle of claim 1, wherein the surface of the wing (1) is covered with a solar panel.
5. The driving device of a split aileron for unmanned aerial vehicle as claimed in claim 1, wherein the material of the wing (1) comprises one or more of an aircraft laminated wood, a composite material, a carbon fiber material, and an aluminum alloy material.
6. A split flap drive arrangement for unmanned aerial vehicles according to claim 1, wherein the material of the split flap (2) comprises one or more of balsa wood, composite material, carbon fiber material, aluminium alloy material.
7. The drive device of the split aileron of the drone of claim 1, wherein the connection of the wing (1) and the split aileron (2) comprises one or more of a connecting rod, a bearing and a screw connection.
8. An unmanned aerial vehicle comprising a drive arrangement for a split flap of an unmanned aerial vehicle as claimed in any of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920987600.XU CN210455186U (en) | 2019-06-28 | 2019-06-28 | Unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920987600.XU CN210455186U (en) | 2019-06-28 | 2019-06-28 | Unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof |
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| CN210455186U true CN210455186U (en) | 2020-05-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313223A (en) * | 2021-11-29 | 2022-04-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Dynamic enhancing method and system for steering efficiency of cracking type resistance rudder |
-
2019
- 2019-06-28 CN CN201920987600.XU patent/CN210455186U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313223A (en) * | 2021-11-29 | 2022-04-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Dynamic enhancing method and system for steering efficiency of cracking type resistance rudder |
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