CN209972805U - Indoor flight attitude simulator of fixed-wing unmanned aerial vehicle - Google Patents
Indoor flight attitude simulator of fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN209972805U CN209972805U CN201920391699.7U CN201920391699U CN209972805U CN 209972805 U CN209972805 U CN 209972805U CN 201920391699 U CN201920391699 U CN 201920391699U CN 209972805 U CN209972805 U CN 209972805U
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Abstract
The utility model discloses an indoor flight gesture simulator of fixed wing unmanned aerial vehicle relates to the simulator field, this indoor flight gesture simulator of fixed wing unmanned aerial vehicle, including the every single move control panel, the upper surface of every single move control panel is provided with the fuselage draw-in groove, every single move control panel upper surface corresponds the fuselage draw-in groove and inlays the position department of flank outward and all is provided with the fuselage buckle, the front of every single move control panel and the back all with the output shaft fixed connection of first motor, the every single move control panel is through first motor and roll-over control panel swing joint, first motor fixed connection is at the upper surface of roll-over control panel, the outer wall fixedly connected with side bearer of roll-over control panel, the quantity of side bearer is two. The utility model discloses a set up every single move control panel, first motor, roll-over control panel, second motor and motor base, solved traditional fixed wing unmanned aerial vehicle indoor flight attitude simulator and can not audio-visual observation unmanned aerial vehicle at the flight in-process between each passageway complex problem.
Description
Technical Field
The utility model relates to a simulator technical field specifically is an indoor flight attitude simulator of fixed wing unmanned aerial vehicle.
Background
The indoor flight attitude simulator of the fixed-wing unmanned aerial vehicle is arranged indoors, can fix the fuselage and wings of the unmanned aerial vehicle, realizes the attitude of the fixed-wing unmanned aerial vehicle during indoor simulated flight, enables the aircraft to perform pitching, rolling and yawing attitude simulation through a plurality of motors, thereby saving the time for outdoor adjustment of the unmanned aerial vehicle, and being capable of adjusting the unmanned aerial vehicle into the correct attitude in the limited space.
The indoor flight attitude simulator of traditional fixed wing unmanned aerial vehicle adopts has a complicated structure, and the structure is complicated, still can't go on pitch, roll over and three kinds of gestures of driftage simultaneously when leading to the cost higher, can not audio-visual observation unmanned aerial vehicle in the cooperation between each passageway of flight in-process, for solving above-mentioned problem, we have provided an indoor flight attitude simulator of fixed wing unmanned aerial vehicle.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The not enough to prior art, the utility model provides an indoor flight gesture simulator of fixed wing unmanned aerial vehicle has solved traditional indoor flight gesture simulator of fixed wing unmanned aerial vehicle and can not audio-visually observe unmanned aerial vehicle at flight in-process complex problem between each passageway.
(II) technical scheme
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an indoor flight attitude simulator of fixed wing unmanned aerial vehicle, includes the every single move control panel, the upper surface of every single move control panel is provided with the fuselage draw-in groove, the position department that the every single move control panel upper surface corresponds fuselage draw-in groove and inlays the flank outward all is provided with the fuselage buckle, the front and the back of every single move control panel all with the output shaft fixed connection of first motor, the every single move control panel is through first motor and roll control panel swing joint, first motor fixed connection is at the upper surface of roll control panel, the outer wall fixed connection side bearer of roll control panel, the quantity of side bearer is two, two the side bearer is located the both sides of first motor respectively, the inner wall of side bearer and the output shaft fixed connection of second motor, the side bearer passes through second motor and support swing joint, two the second motor is fixed connection respectively at the both ends of support, the equal fixedly connected with bracing piece in the front and the back of support, the bottom of bracing piece and the lower surface of support all are connected with motor base's last fixed surface, the support is located the roll-over control panel under.
Preferably, the axis of the pitching control disc and the axes of the two first motors are located on the same straight line.
Preferably, the axes of the two second motors are located on the same straight line, the axes of the second motors and the axis of the first motor are located on the same horizontal plane, and the axes of the second motors and the axis of the first motor are perpendicular to each other.
Preferably, the rolling control disc is in an elliptical ring shape, and the pitching control disc is arranged at the position of the circle center corresponding to the rolling control disc.
Preferably, the motor base comprises a chassis, a rotating motor and a rotating disk, the rotating motor is embedded in the center of the upper surface of the chassis, an output shaft of the rotating motor is fixedly connected with the lower surface of the rotating disk, and the rotating disk is located right above the chassis.
(III) advantageous effects
The utility model provides an indoor flight attitude simulator of fixed wing unmanned aerial vehicle possesses following beneficial effect:
the utility model discloses a set up the every single move control panel, first motor, the roll-over control panel, second motor and motor base, the driftage problem of the adjustable unmanned aerial vehicle of motor base, can drive the rotation of above-mentioned overall structure, thereby control unmanned aerial vehicle carries out yawing motion, simultaneously the every single move control panel drives it through two first motors and rotates around self axis, the roll-over control panel makes its axis around the second motor rotate through two second motors, avoid unmanned aerial vehicle overweight to cause the damage, reached and made unmanned aerial vehicle carry out the every single move, roll over and the simulation of driftage gesture, adjust unmanned aerial vehicle for the correct gesture in limited space, the purpose of conveniently observing directly perceivedly, the problem of traditional fixed wing unmanned aerial vehicle indoor flight gesture simulator can not audio-visual observation unmanned aerial vehicle complex between each passageway of in-process of flying is solved.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
fig. 2 is a left side view of the present invention;
fig. 3 is a top view of the present invention.
In the figure: 1. a pitching control panel; 2. a machine body clamping groove; 3. buckling the machine body; 4. a first motor; 5. a rolling control panel; 6. a side frame; 7. a second motor; 8. a support; 9. a support bar; 10. a motor base; 1001. a chassis; 1002. a rotating electric machine; 1003. and rotating the disc.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
As shown in fig. 1-3, the utility model provides a technical solution: an indoor flight attitude simulator of a fixed wing unmanned aerial vehicle comprises a pitching control panel 1, wherein the shape of the pitching control panel 1 is matched with that of the unmanned aerial vehicle, the pitching control panel 1 comprises a body supporting plate and an externally-embedded side wing, a body clamping groove 2 is arranged at the position, corresponding to the position of the body supporting plate, of the upper surface of the pitching control panel 1, the body clamping groove 2 is used for clamping the body of the unmanned aerial vehicle, body buckles 3 are arranged at the positions, corresponding to the body clamping groove 2 and the externally-embedded side wing, of the upper surface of the pitching control panel 1, the front surface and the back surface of the pitching control panel 1 are fixedly connected with an output shaft of a first motor 4, the pitching control panel 1 is movably connected with a rolling control panel 5 through the first motor 4, the first motor 4 is fixedly connected to the upper surface of the rolling control panel 5, side frames 6 are fixedly connected to the outer wall of, the inner wall of side bearer 6 and the output shaft fixed connection of second motor 7, side bearer 6 passes through second motor 7 and support 8 swing joint, two second motors 7 are fixed connection respectively at the both ends of support 8, the equal fixedly connected with bracing piece 9 in front and the back of support 8, the bottom of bracing piece 9 and the lower surface of support 8 all are connected with motor base 10's upper surface fixed, support 8 is located roll control panel 5 under, first motor 4, the power supply mode of second motor 7 and rotating electrical machines 1002 is the external power source power supply, and first motor 4, second motor 7 and rotating electrical machines 1002 all have independent rotational speed and rotation mode and do not influence each other.
As the utility model discloses a technical optimization scheme, the axis of every single move control panel 1 and the axis of two first motors 4 all are located same straight line, and two first motors 4 all set up the whole atress balance of guaranteeing every single move control panel 1 in the axis position department of every single move control panel 1 promptly, prevent to lead to after the atress is inhomogeneous unmanned aerial vehicle installation unbalanced in atress, receive self gravity to damage easily.
As a technical optimization scheme of the utility model, the axis of two second motors 7 is located same straight line, and the axis of second motor 7 is located same horizontal plane with the axis of first motor 4, and the axis of second motor 7 and the axis mutually perpendicular of first motor 4, and the axis of second motor 7 intersects in the mid point position department of roll-over control panel 5 with the axis of first motor 4, guarantees that overall structure all is in balanced position, improves the accuracy nature of regulation.
As a technical optimization scheme of the utility model, the control panel 5 that rolls over is oval ring form, and every single move control panel 1 sets up in the centre of a circle position department that control panel 5 corresponds of rolling over to support through support 8 and bracing piece 9, bracing piece 9 divide into two sets ofly set up respectively at the front and the back of support 8, play firm effect.
As the utility model discloses a technical optimization scheme, motor base 10 includes chassis 1001, rotating electrical machines 1002 and rotary disk 1003, and the central point department of putting of inlaying at chassis 1001 upper surface is taken turns to rotating electrical machines 1002, and the lower fixed surface of the output shaft of rotating electrical machines 1002 and rotary disk 1003 is connected, and rotary disk 1003 is located chassis 1001 directly over, and chassis 1001 plays fixed effect, and rotary disk 1003 plays rotatory effect, and rotating electrical machines 1002 provides rotary power.
When the unmanned aerial vehicle is used, firstly, the unmanned aerial vehicle is arranged above the pitching control panel 1, the body of the unmanned aerial vehicle is arranged in the body clamping groove 2 and is clamped by three body buckles 3, the wings of the unmanned aerial vehicle are arranged at the position of the externally embedded side wing and are clamped by one body buckle 3, the body buckle 3 is matched with the body in shape, after the body buckle 3 clamps the unmanned aerial vehicle, two ends of the body buckle 3 are fixed on the pitching control panel 1 through bolts, after the power supply is started, the first motor 4, the second motor 7 and the rotating motor 1002 are simultaneously electrified and then started, the two first motors 4 drive the pitching control panel 1 to turn clockwise or anticlockwise around the axis of the pitching control panel, the two second motors 7 drive the rolling control panel 5 to turn around the axes of the two second motors 7 through the side frame 6, the rolling posture of the unmanned aerial vehicle is realized, the motor base 10 is provided with the high, rotating electrical machines 1002 drives the axis rotation of rotary disk 1003 around rotating electrical machines 1002, can drive the rotation of whole structure above to control unmanned aerial vehicle and carry out the yawing motion, fix on rotary disk 1003 through support 8 and bracing piece 9, in order to guarantee the stability of whole above structure.
To sum up can, the utility model discloses a set up every single move control panel 1, first motor 4, roll control panel 5, second motor 7 and motor base 10, solved traditional fixed wing unmanned aerial vehicle indoor flight attitude simulator and can not audio-visual observation unmanned aerial vehicle complex problem between each passageway of flight in-process.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides an indoor flight attitude simulator of fixed wing unmanned aerial vehicle, includes every single move control panel (1), its characterized in that: the upper surface of every single move control panel (1) is provided with fuselage draw-in groove (2), every single move control panel (1) upper surface all is provided with fuselage buckle (3) to corresponding fuselage draw-in groove (2) and the position department of outer embedded flank, the front and the back of every single move control panel (1) all with the output shaft fixed connection of first motor (4), every single move control panel (1) is through first motor (4) and roll control panel (5) swing joint, first motor (4) fixed connection is at the upper surface of roll control panel (5), the outer wall fixed connection of roll control panel (5) has side bearer (6), the quantity of side bearer (6) is two, two side bearer (6) are located the both sides of first motor (4) respectively, the inner wall of side bearer (6) and the output shaft fixed connection of second motor (7), side bearer (6) are through second motor (7) and support (8) swing joint, two second motor (7) difference fixed connection is at the both ends of support (8), the front and the equal fixedly connected with bracing piece in the back (9) of support (8), the bottom of bracing piece (9) and the lower surface of support (8) all with the last fixed surface of motor base (10) be connected, support (8) are located roll control panel (5) under.
2. The indoor flight attitude simulator of a fixed-wing drone of claim 1, wherein: the axis of the pitching control disc (1) and the axes of the two first motors (4) are positioned on the same straight line.
3. The indoor flight attitude simulator of a fixed-wing drone of claim 1, wherein: the axes of the two second motors (7) are positioned on the same straight line, the axes of the second motors (7) and the axis of the first motor (4) are positioned on the same horizontal plane, and the axes of the second motors (7) and the axis of the first motor (4) are mutually vertical.
4. The indoor flight attitude simulator of a fixed-wing drone of claim 1, wherein: the roll control panel (5) is in an elliptical ring shape, and the pitch control panel (1) is arranged at the position of the circle center corresponding to the roll control panel (5).
5. The indoor flight attitude simulator of a fixed-wing drone of claim 1, wherein: the motor base (10) comprises a chassis (1001), a rotating motor (1002) and a rotating disk (1003), wherein the rotating motor (1002) is embedded in the center of the upper surface of the chassis (1001), an output shaft of the rotating motor (1002) is fixedly connected with the lower surface of the rotating disk (1003), and the rotating disk (1003) is located right above the chassis (1001).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920391699.7U CN209972805U (en) | 2019-03-26 | 2019-03-26 | Indoor flight attitude simulator of fixed-wing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920391699.7U CN209972805U (en) | 2019-03-26 | 2019-03-26 | Indoor flight attitude simulator of fixed-wing unmanned aerial vehicle |
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| CN209972805U true CN209972805U (en) | 2020-01-21 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117058947A (en) * | 2023-09-12 | 2023-11-14 | 广州天海翔航空科技有限公司 | Half-simulation flight training system and method for fixed-wing unmanned aerial vehicle |
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2019
- 2019-03-26 CN CN201920391699.7U patent/CN209972805U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117058947A (en) * | 2023-09-12 | 2023-11-14 | 广州天海翔航空科技有限公司 | Half-simulation flight training system and method for fixed-wing unmanned aerial vehicle |
| CN117058947B (en) * | 2023-09-12 | 2024-03-15 | 广州天海翔航空科技有限公司 | Half-simulation flight training system and method for fixed-wing unmanned aerial vehicle |
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