CN218497671U - Fixed wing unmanned aerial vehicle controls real standard appearance - Google Patents
Fixed wing unmanned aerial vehicle controls real standard appearance Download PDFInfo
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- CN218497671U CN218497671U CN202123439085.8U CN202123439085U CN218497671U CN 218497671 U CN218497671 U CN 218497671U CN 202123439085 U CN202123439085 U CN 202123439085U CN 218497671 U CN218497671 U CN 218497671U
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Abstract
The utility model discloses a fixed wing unmanned aerial vehicle control practical training instrument, which comprises a practical training panel, an attitude control platform, a fixed wing teaching platform and an external display device, wherein the practical training panel, the attitude control platform and the fixed wing teaching platform are arranged in a box body; the attitude control platform mainly comprises a pitching servo mechanism, a rolling servo mechanism and a yawing servo mechanism, wherein the servo mechanisms can be controlled automatically or manually to realize attitude control of the unmanned aerial vehicle; the fixed wing teaching adopts a split installation mode for splicing; the empennage is fixed on the PCB of the fuselage in an inserting mode, so that various fixed wing layouts such as a conventional layout, a flying wing layout, a V-tail layout and the like can be realized; the platform universality is strong, and the teaching of various fixed wing layouts can be met by a single device; all teaching equipment are plugged through the interfaces, so that the connection of all the equipment is stable and correct, and the teaching equipment is more efficient when being applied to teaching.
Description
The technical field is as follows:
the utility model relates to a real standard appearance of fixed wing unmanned aerial vehicle control belongs to unmanned aerial vehicle teaching field.
Background art:
when the teaching of the fixed-wing unmanned aerial vehicle is carried out, at present, aiming at the content teaching of the assembly debugging of the fixed-wing airborne equipment, the control debugging of the fixed-wing unmanned aerial vehicle and the like before flight, the real fixed-wing unmanned aerial vehicle can only be used for carrying out the teaching, and because the real fixed-wing unmanned aerial vehicle is overlarge in size, single aircraft is single in structural layout, poor in universality and the like, a large space is required in the teaching; the assembly and control of the real unmanned aerial vehicle need to involve various devices and tools, which causes the teaching environment to be disordered; the connection circuit of the airborne equipment is complex in the teaching process; the airborne equipment can not be repeatedly installed and used; the layout of various fixed wings needs a large number of different airplanes to meet the teaching requirements and other outstanding problems.
The utility model has the following contents:
an object of the utility model is to provide a commonality is strong, and single equipment can satisfy the fixed wing unmanned aerial vehicle of multiple fixed wing overall arrangement teaching and control real standard appearance.
The utility model discloses implement by following technical scheme: the fixed-wing unmanned aerial vehicle control practical training instrument comprises a box body and a box cover arranged on the box body, wherein a practical training panel, an attitude control platform and a fixed-wing teaching platform are arranged in the box body;
the top of the box body is provided with the practical training panel, and the practical training panel is provided with a power supply interface, a power supply fuse, a safety switch, a servo mechanism control signal generator, an automatic control and manual control change-over switch and other components; the power supply interface is connected with the input end of a switching power supply arranged below the practical training panel, and the output end of the switching power supply is connected with the direct-current input interface of the practical training instrument;
the attitude control platform is arranged at the bottom of the box body and comprises a pitching servo mechanism, a rolling servo mechanism, a yawing servo motor and a supporting structure; the supporting structure comprises a vertical upright rod and a ball joint arranged on the upright rod; a motor shaft of the yaw servo motor is vertically arranged, and the vertical rod is coaxially and fixedly arranged on the motor shaft of the yaw servo motor; the pitching servo mechanism and the rolling servo mechanism are respectively arranged on the side part of the yaw servo motor, the pitching servo mechanism comprises a pitching servo motor, a pitching oscillating arm and a pitching transmission arm, the pitching oscillating arm is arranged on an output shaft of the pitching servo motor, and the pitching transmission arm is hinged to the pitching oscillating arm; the roll servo mechanism comprises a roll servo motor, a roll swing arm and a roll transmission arm, the roll swing arm is arranged on an output shaft of the roll servo motor, and the roll transmission arm is hinged on the roll swing arm;
the machine body PCB of the fixed wing teaching platform is fixedly arranged on a quick-mounting plate of the ball joint of the attitude control platform, the top end of the pitching transmission arm is hinged with the machine body PCB, and the top end of the rolling transmission arm is hinged with the machine body PCB; the head part of the PCB of the machine body is provided with a motor, and the tail part of the PCB of the machine body is provided with more than one empennage electrical connection pin header; a yaw electrical connection port electrically connected with the yaw servo motor, a pitching electrical connection port electrically connected with the pitching servo motor, a roll electrical connection port electrically connected with the roll servo motor, a flight control electrical connection port electrically connected with a flight control device and a motor electrical connection port electrically connected with the motor are arranged on the machine body PCB;
the plane at the top of the PCB board of the airplane body is fixedly provided with a flight control damping platform which comprises a flight control device, and the flight control device is electrically connected with the PCB board of the airplane body through the flight control electrical connection interface.
Preferably, the whole body PCB is a projection shape of the fixed wing unmanned aerial vehicle.
Preferably, a vertical tail wing electrical connection pin header is vertically arranged at the center of the tail part of the PCB of the machine body, and the vertical tail wing electrical connection pin header is separately inserted with the vertical tail wing PCB; the electric connection pin header is characterized in that horizontal tail wing electric connection pins arranged horizontally and V-shaped tail wing electric connection pins arranged in an upward inclined manner are arranged on the machine body PCB on two sides of the vertical tail wing electric connection pin header respectively, the horizontal tail wing PCB is inserted on the horizontal tail wing electric connection pins in a split manner, and the V-shaped tail wing PCB is inserted on the V-shaped tail wing electric connection pin header in a split manner.
Preferably, the flight control damping platform further comprises a flight control fixing plate and four damping support legs uniformly distributed at the bottom of the flight control fixing plate, the flight control damping platform is fixed on the top plate surface of the machine body PCB through the four damping support legs, and the flight control fixing plate is arranged in parallel with the machine body PCB; the top surface of the flight control fixing plate is fixedly provided with the flight control device in a split manner.
Preferably, a simulation umbrella cabin and an equipment cabin are arranged in the box body.
The utility model has the advantages that: the empennage is fixed on the PCB of the fuselage in an inserting mode, so that various fixed wing layouts such as a conventional layout, a flying wing layout, a V-tail layout and the like can be realized; the platform commonality is strong, and single equipment can satisfy the teaching of multiple stationary vane overall arrangement. All teaching equipment are plugged through the interfaces, so that the connection of all the equipment is stable and correct, and the teaching equipment is more efficient when being applied to teaching. The integrated level is high, can master unmanned aerial vehicle's flight control principle fast. The device commonality is strong, can carry on multiple unmanned aerial vehicle flight control system (compatible all fixed wing control system on the market). The equipment occupies small space, and is suitable for teaching of schools or training institutions for multiple times.
Description of the drawings:
fig. 1 is an overall schematic view of the present invention.
Fig. 2 is a bottom view of fig. 1.
Fig. 3 is a front view of the attitude control platform.
Fig. 4 is a side view of the attitude control platform.
Fig. 5 is a front view of the body PCB board.
Fig. 6 is a top view of the body PCB board.
Fig. 7 is a top view of a fuselage PCB board for a conventional fixed wing layout.
FIG. 8 is a front view of the fuselage PCB layout for a V-tail fixed wing layout.
FIG. 9 is a top view of the PCB board of the fuselage with a V-tail fixed wing layout.
The specific implementation mode is as follows:
the embodiment is as follows: the fixed-wing unmanned aerial vehicle operation training instrument shown in fig. 1-9 comprises a box body 1 and a box cover (not shown in the figure) arranged on the box body 1.
A training panel 7 is arranged in the box body 1, and a power distribution interface 71, a safety switch 72, a power fuse 73, a simulation umbrella cabin 74, a servo mechanism control signal generator 75 and an automatic control and manual control change-over switch 76 are arranged on the training panel 7; the safety switch 72 controls the on-off of the circuit of the whole device, the power distribution interface 71 is connected with the input end of a switch power supply arranged below the practical training panel 7, and the output end of the switch power supply is connected with the direct-current input interface of the practical training instrument.
The bottom of the box body 1 is provided with an attitude control platform 3, and the attitude control platform 3 comprises a yaw servo motor 31, a pitching servo mechanism 32, a rolling servo mechanism 33, a vertical rod 34 and a ball joint 35; a motor shaft of the yaw servo motor 31 is vertically arranged, a vertical rod 34 is coaxially and fixedly arranged on the motor shaft of the yaw servo motor 31, and a ball joint 35 is arranged at the top end of the vertical rod 34; a pitch servo mechanism 32 and a roll servo mechanism 33 are respectively arranged at the side part of the yaw servo motor 31, the pitch servo mechanism 32 comprises a pitch servo motor 321, a pitch and swing arm 322 and a pitch transmission arm 323, the output shaft of the pitch servo motor 321 is provided with the pitch and swing arm 322, and the pitch and swing arm 322 is hinged with the pitch transmission arm 323; the roll servo mechanism 33 includes a roll servo motor 331, a roll swing arm 332, and a roll transmission arm 333, the roll swing arm 332 is provided on an output shaft of the roll servo motor 331, and the roll transmission arm 333 is hinged to the roll swing arm 332.
The body PCB 4 is fixedly arranged on the quick-mounting plate 351 of the ball joint 35, and the whole shape of the body PCB is the projection shape of the fixed-wing unmanned aerial vehicle; the top end of the pitching transmission arm 323 is hinged with the PCB 4, the pitching transmission arm 323 is arranged in the 12-point direction or the 6-point direction of the PCB 4 of the body, and in the embodiment, the pitching transmission arm 323 is arranged in the 12-point direction of the PCB 4 of the body; the top end of the roller driving arm 333 is hinged to the PCB 4, the roller driving arm 333 is disposed in the 3 o ' clock direction or the 9 o ' clock direction of the body PCB 4, in this embodiment, the roller driving arm 333 is disposed in the 3 o ' clock direction of the body PCB 4.
A yaw electrical connection interface 408 electrically connected with the yaw servo motor 31, a pitch electrical connection interface 409 electrically connected with the pitch servo motor 321, a roll electrical connection interface 410 electrically connected with the roll servo motor 331 are arranged on the body PCB 4, and the body PCB 4 is driven to yaw by the rotation of the yaw servo motor 31; the pitching servo motor 321 rotates to drive the body PCB 4 to perform pitching motion; the body PCB 4 is driven by the rotation of the roll servo motor 331 to perform a roll motion.
The head of the body PCB 4 is connected with a motor 401 through a motor electrical connection interface 412; a vertically arranged vertical tail electrical connection pin header 402 is arranged at the center of the tail part of the machine body PCB 4, and a vertical tail PCB 403 is separately inserted on the vertical tail electrical connection pin header 402; a horizontal tail wing electrical connection pin header 404 arranged horizontally and a V-shaped tail wing electrical connection pin header 405 arranged obliquely upwards are respectively arranged on the machine body PCB 4 at two sides of the vertical tail wing electrical connection pin header 402, the horizontal tail wing PCB 406 is separately inserted on the horizontal tail wing electrical connection pin header 404, and the V-shaped tail wing PCB 407 is separately inserted on the V-shaped tail wing electrical connection pin header 405; the simulation of the conventional fixed wing layout is realized by inserting a vertical tail PCB 403 on the vertical tail electrical connection pin header 402 and inserting a horizontal tail PCB 406 on the horizontal tail electrical connection pin header 404; the layout of the V-tail fixed wing is simulated by inserting the V-tail PCB 407 on the V-tail electrical connection pin 405.
A flight control damping platform 5 is fixedly arranged on the top plate surface of the body PCB 4 to reduce the vibration of the unmanned aerial vehicle in the working process, the flight control damping platform 5 comprises a flight control device 6, and the flight control device 6 is electrically connected with the body PCB 4 through a flight control electrical connection interface 411; the flight control damping platform 5 further comprises a flight control fixing plate 51, four damping support legs 52 are uniformly distributed at the bottom of the flight control fixing plate 51, the flight control damping platform 5 is fixed on the top plate surface of the machine body PCB 4 through the four damping support legs 52, and the flight control fixing plate 51 is arranged in parallel with the machine body PCB 4; the flight control device 6 is fixed on the top surface of the flight control fixed plate 51 in a split manner.
When the servo mechanism is in an automatic working state, the flight control device 6 sends signals to control the yaw servo motor 31, the pitch servo motor 321 and the roll servo motor 331 to act, so that the PCB 4 of the fuselage performs corresponding yaw, pitch and roll actions; controlling the motor 401 to rotate forward and backward; controlling the aileron steering engine 413 and the flap steering engine 414 on the fuselage PCB 4 to act, and driving the corresponding ailerons 415 and the flaps 416 hinged on the wings of the fuselage PCB 4 to act; in the conventional fixed wing layout, a rudder steering engine 417 on the vertical tail wing PCB 403 is controlled to act to drive a hinged rudder 418 on the vertical tail wing PCB 403 to act; controlling an elevator steering engine 419 on the horizontal tail wing PCB 406 to act to drive an elevator 420 hinged on the horizontal tail wing PCB 406 to act; and in the layout of the V-shaped tail fixed wings, a tail rudder steering engine 421 on the V-shaped tail wing PCB 407 is controlled to act, and a tail rudder 422 hinged to the V-shaped tail wing PCB 407 is driven to act.
The working principle is as follows:
the simulation of the unmanned aerial vehicle with different wings can be realized by inserting corresponding empennage PCB boards on different empennage electrical connection pins at the tail part of the fuselage PCB board 4; and (5) switching on a power distribution interface 71 on the practical training panel 7 and closing a safety switch 72, so that the fixed-wing unmanned aerial vehicle controls the practical training instrument to start working.
The automatic control and manual control conversion switch 76 can be converted to realize the automatic control or manual control of the motion attitude of the unmanned aerial vehicle, and the controllable motion states comprise yaw, pitch and roll; when the switch is in a manual control state, the control information of the manual pull rod is transmitted to the servo mechanism control signal generator 75, and the yaw servo motor 31, the pitch servo mechanism 32 and the roll servo mechanism 33 of the attitude control platform 3 are further controlled to adjust the attitude of the unmanned aerial vehicle; when the switch is in an automatic control state, the flight control device 6 automatically controls the motion attitude of the unmanned aerial vehicle.
Claims (5)
1. The fixed-wing unmanned aerial vehicle control practical training instrument is characterized by comprising a box body and a box cover arranged on the box body, wherein a practical training panel, an attitude control platform and a fixed-wing teaching platform are arranged in the box body; the top of the box body is provided with the practical training panel, and the practical training panel is provided with a power supply interface, a power supply fuse, a safety switch, a servo mechanism control signal generator and an automatic control and manual control change-over switch; the power supply interface is connected with the input end of a switch power supply arranged below the practical training panel, and the output end of the switch power supply is connected with the direct-current input interface of the practical training instrument; the attitude control platform is arranged at the bottom of the box body and comprises a pitching servo mechanism, a rolling servo mechanism, a yawing servo motor and a supporting structure; the supporting structure comprises a vertical upright rod and a ball joint arranged on the upright rod; a motor shaft of the yaw servo motor is vertically arranged, and the vertical rod is coaxially and fixedly arranged on the motor shaft of the yaw servo motor; the pitching servo mechanism and the rolling servo mechanism are respectively arranged on the side part of the yaw servo motor, the pitching servo mechanism comprises a pitching servo motor, a pitching oscillating arm and a pitching transmission arm, the pitching oscillating arm is arranged on an output shaft of the pitching servo motor, and the pitching transmission arm is hinged to the pitching oscillating arm; the roll servo mechanism comprises a roll servo motor, a roll swing arm and a roll transmission arm, the roll swing arm is arranged on an output shaft of the roll servo motor, and the roll transmission arm is hinged to the roll swing arm; a machine body PCB of the fixed wing teaching platform is fixedly arranged on a quick-mounting plate of the ball joint of the attitude control platform, the top end of the pitching transmission arm is hinged with the machine body PCB, and the top end of the rolling transmission arm is hinged with the machine body PCB; the head of the PCB of the machine body is provided with a motor, and the tail of the PCB of the machine body is provided with more than one empennage electrical connection pin header; a yaw electrical connection port electrically connected with the yaw servo motor, a pitching electrical connection port electrically connected with the pitching servo motor, a roll electrical connection port electrically connected with the roll servo motor, a flight control electrical connection port electrically connected with a flight control device and a motor electrical connection port electrically connected with the motor are arranged on the machine body PCB; the plane at the top of the PCB board of the airplane body is fixedly provided with a flight control damping platform which comprises a flight control device, and the flight control device is electrically connected with the PCB board of the airplane body through the flight control electrical connection interface.
2. The fixed-wing drone operation practical training instrument according to claim 1, wherein the fuselage PCB board is in the shape of a projection of the fixed-wing drone as a whole.
3. The fixed-wing unmanned aerial vehicle control practical training instrument according to claim 1 or 2, wherein a vertical tail wing electrical connection pin header is vertically arranged at the center of the tail part of the fuselage PCB, and the vertical tail wing PCB is separately inserted into the vertical tail wing electrical connection pin header; the electric connection pin header is characterized in that horizontal tail wing electric connection pins arranged horizontally and V-shaped tail wing electric connection pins arranged in an upward inclined manner are arranged on the PCB of the machine body on two sides of the vertical tail wing electric connection pin header respectively, the horizontal tail wing PCB is spliced on the horizontal tail wing electric connection pins in a split manner, and the V-shaped tail wing PCB is spliced on the V-shaped tail wing electric connection pins in a split manner.
4. The fixed-wing unmanned aerial vehicle control practical training instrument as claimed in claim 1, wherein the flight control damping platform further comprises a flight control fixing plate and four damping legs uniformly distributed at the bottom of the flight control fixing plate, the flight control damping platform is fixed on the top plate surface of the body PCB plate through the four damping legs, and the flight control fixing plate is arranged in parallel with the body PCB plate; the top surface of the flight control fixing plate is fixedly provided with the flight control device in a split manner.
5. The fixed-wing unmanned aerial vehicle control practical training instrument as claimed in claim 1, wherein a simulation parachute cabin and an equipment cabin are arranged in the box body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123439085.8U CN218497671U (en) | 2021-12-30 | 2021-12-30 | Fixed wing unmanned aerial vehicle controls real standard appearance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123439085.8U CN218497671U (en) | 2021-12-30 | 2021-12-30 | Fixed wing unmanned aerial vehicle controls real standard appearance |
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| Publication Number | Publication Date |
|---|---|
| CN218497671U true CN218497671U (en) | 2023-02-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123439085.8U Active CN218497671U (en) | 2021-12-30 | 2021-12-30 | Fixed wing unmanned aerial vehicle controls real standard appearance |
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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 |
-
2021
- 2021-12-30 CN CN202123439085.8U patent/CN218497671U/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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