CN208705679U - UAV Flight Control analogue system - Google Patents
UAV Flight Control analogue system Download PDFInfo
- Publication number
- CN208705679U CN208705679U CN201821311290.1U CN201821311290U CN208705679U CN 208705679 U CN208705679 U CN 208705679U CN 201821311290 U CN201821311290 U CN 201821311290U CN 208705679 U CN208705679 U CN 208705679U
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- China
- Prior art keywords
- flight control
- guide rail
- plate
- steering engine
- sliding block
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Abstract
The utility model discloses UAV Flight Control analogue systems, it is related to UAV Flight Control simulation technical field, including body plate and pedestal, groove is arranged in the body plate bottom centre position, the body plate is square plate and four square positions are diagonally provided with four branches outward, guide rail-sliding block-steering engine subsystem is installed respectively in the branch, guide rail-sliding block-steering engine the subsystem includes steering engine, steering wheel, draw bar, sliding block, guide rail, connecting shaft one and connecting shaft two, the steering engine is mounted on the bifurcated upper face, the guide rail is fixed on the branches end, the sliding block is socketed on the guide rail.There is no high-speed rotating wing in system in the utility model, it carries out that danger will not be brought to personnel and aircraft when dynamic demonstration indoors, the flight control technology that can show unmanned plane during flying device well simultaneously, is highly suitable for the flight control principle of the various unmanned planes of indoor instruction.
Description
Technical field
The utility model relates to UAV Flight Control simulation technical fields, in particular to UAV Flight Control emulation system
System.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without cockpit on machine, but the equipment such as automatic pilot, presetting apparatus are installed.On ground, naval vessels or
Machine tool remote control station personnel track it, are positioned, are remotely controlled, telemetering and Digital Transmission by the equipment such as radar.It can be in radio
It takes off as conventional airplane under remote control or is launched with booster rocket, aerial launch can also be taken to by machine tool and flown.Recycling
When, the mode automatic Landing as conventional airplane landing mission can be used, can also be recycled by remote control parachute or block.It can
It is reused several times.It is widely used in aerial reconnaissance, monitoring, communication, antisubmarine, electronic interferences etc..
" UAV Flight Control " course is an important course of unmanned plane application technology profession, mainly learns various nothings
Man-machine flight control principle, including aircraft stability contorting and Navigation Control, need suitable instruments used for education to show nobody
The flight control technology of machine, but the course is mainly imparted knowledge to students indoors, with the more rotors of actual aircraft Dynamic Display and can not be consolidated
The control principle of wing unmanned plane is determined, so needing a kind of UAV Flight Control analogue system that can be shown indoors.
Utility model content
The utility model embodiment provides UAV Flight Control analogue system, existing in the prior art to solve
Problem.
UAV Flight Control analogue system, the Flight control simulation system of multi-rotor unmanned aerial vehicle: including body plate and bottom
Seat, the body plate bottom centre position are arranged groove, the body plate be square plate and four square positions diagonally to
It is provided with four branches outside, guide rail-sliding block-steering engine subsystem, the guide rail-sliding block-steering engine point are installed respectively in the branch
System includes steering engine, steering wheel, draw bar, sliding block, guide rail, connecting shaft one and connecting shaft two, and the steering engine is mounted on the branch
Upper surface, the guide rail are fixed on the branches end, and the sliding block is socketed on the guide rail, and the rudderpost on the steering engine is fixed
One end of the steering wheel is connected, the other end of the steering wheel is rotatablely connected one end of the draw bar by the connecting shaft one,
The other end of the draw bar is rotatablely connected the sliding block by the connecting shaft two, the body plate center installation fly control plate and
Inertial sensor, the wireless communication module and the power module are symmetrically mounted on the two sides of the body plate, the winged control
Plate is to be electrically connected with the steering engine, the inertial sensor, the wireless communication module and the power module, the power supply
Module is to be electrically connected with the winged control plate, the steering engine, the inertial sensor and the wireless communication module, described
Fixed mandril above pedestal, the top pointed cone of the mandril support the bottom groove of the body plate, the apex cone of the mandril
The sharp bottom groove with the body plate is point connection；
The Flight control simulation system of fixed-wing unmanned plane: including support base, being arranged fuselage above the support base,
The fuselage includes head and tail, and setting and the orthogonal main wing of the fuselage on the fuselage, the main wing includes a left side
A set of guide rail-sliding block-steering engine subsystem, the tail top are installed respectively above the wing and right flank, the left wing and the right flank
A set of guide rail-sliding block-steering engine subsystem is installed, increases appropriate counterweight on the head, the center of the fuselage is mounted on
In the support base.
Preferably, the intermediate position that the body plate is square plate four sides length vertically devises four branches outward.
Preferably, the body plate is that four square positions of square plate devise four branches along side length outward.
Preferably, the body plate is that circular slab devises four branches.
Preferably, micro computer is arranged in the winged control plate.
Preferably, setting wireless receiver and wireless transmitter in the wireless communication module, connect with experiment computer wireless
It connects.
Preferably, being made of inside the power module lithium battery and voltage transformation module.
Preferably, the pedestal is round or square plate.
The utility model is carried out indoors the utility model has the advantages that do not have high-speed rotating wing in system in the utility model
Will not personnel and aircraft be brought with danger when dynamic demonstration, while can show the flight control of unmanned plane during flying device well
Technology is highly suitable for the flight control principle of the various unmanned planes of indoor instruction.
Detailed description of the invention
Fig. 1 is the overlooking structure diagram of UAV Flight Control analogue system provided by the embodiment of the utility model；
Fig. 2 is the quadrotor drone Flight control simulation system side view for installing support base；
Fig. 3 is quadrotor drone analogue system fuselage plate shape.
Description of symbols:
1- steering engine, 2- steering wheel, 3- draw bar, 4- sliding block, 5- guide rail, 6- body plate, the winged control plate of 7-, 8- inertial sensor,
9- connecting shaft one, 10- connecting shaft two, 11- wireless communication module, 12- power module, 13- pedestal, 14- mandril.
Specific embodiment
Below with reference to the attached drawing in utility model embodiment, the technical scheme in the embodiment of the utility model is carried out clear
Chu, complete description, it is to be understood that the protection scope of the utility model is not limited by the specific implementation.
Referring to Fig.1-3, the utility model provides UAV Flight Control analogue system, the flight control of multi-rotor unmanned aerial vehicle
Analogue system processed: including body plate 6 and pedestal 13, groove is arranged in 6 bottom centre position of body plate, and the body plate 6 is
Square plate and four square positions are diagonally provided with four branches outward, install guide rail-sliding block-rudder respectively in the branch
Machine subsystem, the guide rail-sliding block-steering engine subsystem include steering engine 1, steering wheel 2, draw bar 3, sliding block 4, guide rail 5, connecting shaft one
9 and connecting shaft 2 10, the steering engine 1 be mounted on the bifurcated upper face, the guide rail 5 is fixed on the branches end, described
Be socketed the sliding block 4 on guide rail 5, the rudderpost on the steering engine 1 is fixedly connected with one end of the steering wheel 2, the steering wheel 2 it is another
One end is rotatablely connected one end of the draw bar 3 by the connecting shaft 1, and the other end of the draw bar 3 passes through the company
Spindle 2 10 is rotatablely connected the sliding block 4, and 6 center of the body plate installation flies control plate 7 and inertial sensor 8, the channel radio
Letter module 11 and the power module 12 are symmetrically mounted on the two sides of the body plate 6, the winged control plate 7 and the steering engine 1, institute
Stating inertial sensor 8, the wireless communication module 11 and the power module 12 is electrical connection, the power module 12 and institute
Stating the winged control plate 7, the steering engine 1, the inertial sensor 8 and the wireless communication module 11 is electrical connection, the bottom
13 top fixed mandrils 14 of seat, the top pointed cone of the mandril 14 support the bottom groove of the body plate 6, the mandril 14
The bottom groove of top cone and the body plate 6 is point connection；
The Flight control simulation system of fixed-wing unmanned plane: to fixed-wing unmanned plane, when realizing Flight control simulation system,
It does not need to remove original component, it is only necessary to install three sets of guide rail-sliding block-steering engine subsystems additional, and support base is installed.Tool
Body way is as follows: including support base, being arranged fuselage above the support base, the fuselage includes head and tail, described
Setting and the orthogonal main wing of the fuselage, the main wing include left wing and right flank on fuselage, the left wing and the right flank
A set of guide rail-sliding block-steering engine subsystem is installed in top respectively, and a set of guide rail-sliding block-steering engine point is installed above the tail and is
It unites, increases appropriate counterweight on the head, the center of the fuselage is mounted in the support base.
Wherein Fig. 3 (a) body plate 6 is that the intermediate position of square plate four sides length vertically devises four points outward
Branch.
Wherein Fig. 3 (b) body plate 6 is that four square positions of square plate are diagonally provided with four branches outward,
Wherein Fig. 3 (c) body plate 6 is that four square positions of square plate devise four branches along side length outward.
Wherein Fig. 3 (d) body plate 6 is that circular slab devises four branches.
Micro computer is set in the winged control plate 7.
Setting wireless receiver and wireless transmitter in the wireless communication module 11 are connect with experiment computer wireless.
It is made of inside the power module 12 lithium battery and voltage transformation module.
The pedestal 13 is round or square plate.
Working principle: UAV Flight Control analogue system provided by the utility model carries out flight control to unmanned plane
Including two aspects of stability contorting and Navigation Control, wherein Navigation Control mainly controls the flight path of aircraft, to complete
The aerial mission planned；Stability contorting mainly controls the balance of aircraft, can be certainly when by external action disequilibrium
Row restores balance or establishes new equalization point.The utility model is mainly used for showing the stability control techniques of aircraft, is suitable for
Multi-rotor aerocraft and Fixed Wing AirVehicle.
It is illustrated by taking quadrotor drone as an example, the unmanned plane of more rotors is only the quantitative difference of rotor, former
Reason is the same.There are four direct current generator, two motors to be mounted with that positive paddle, two motors are mounted with anti-paddle for quadrotor drone,
The lift and torsion of each rotor are controlled by accurately controlling the revolving speed of each motor, to control quadrotor drone itself
Posture and the position in flight space.The utility model is a quadrotor drone analogue system, which eliminates
All direct current generators and blade instead four sets of guide rail-sliding block-steering engine subsystems, the downward weight of sliding block in the system
Power is equivalent to the upward lift of blade, and sliding block moment variations caused by different location on guide rail are equivalent to blade in fixed bit
The lifting force moment variation under different rotating speeds is set, therefore the two has good similitude in terms of stability contorting, sliding block is in guide rail
On position controlled by steering engine, steering engine drives sliding block for linear motion on guide rail by steering wheel one, steering wheel two and draw bar,
The rotary motion of steering engine is converted into the reciprocating motion of sliding block.
Inertial sensor 8 needs to be mounted on the central location of whole system, and the installation site of other components is adjustable, makes
Whole system is obtained about supporting point energy kept in balance, the micro computer flown on control plate 7 is managed entire analogue system, is used to
Property sensor 8 effect be to measure the posture of analogue system, i.e. inclination angle；Wireless communication module 11 realizes the communication with host computer
Function carries out control parameter adjustment on host computer, can see influence of the different parameters to control effect in analogue system,
Power module 12 provides necessary work electricity consumption for entire analogue system.
After power, under the control for flying control 7 inner microcomputer of plate, system is in equilibrium state, such as uses finger when having to disturb
When gently the system of laying a finger on makes system tilt, system can measure tilt angle by inertial sensor 8, and control sliding block fortune
It moves to reduce tilt angle, until reaching balance again；Unmanned plane during flying analogue system is by radio-circuit and tests computer (such as
Desktop computer or laptop) communication, realize that PID dynamic state of parameters modifies function.
In conclusion there is no high-speed rotating wing in system in the utility model, when carrying out dynamic demonstration indoors
Personnel and aircraft will not be brought with danger, while can show the flight control technology of unmanned plane during flying device well, very
The flight control principle of suitable various unmanned planes of imparting knowledge to students indoors.
Disclosed above is only a specific embodiment of the utility model, and still, the utility model embodiment is not office
It is limited to this, the changes that any person skilled in the art can think of should all fall into the protection scope of the utility model.
Claims (8)
1. UAV Flight Control analogue system, which is characterized in that the Flight control simulation system of multi-rotor unmanned aerial vehicle: including machine
Groove is arranged in body (6) and pedestal (13), body plate (6) bottom centre position, and the body plate (6) is square plate and four
A square position is diagonally provided with four branches outward, installs guide rail-sliding block-steering engine subsystem respectively in the branch,
Guide rail-sliding block-steering engine the subsystem includes steering engine (1), steering wheel (2), draw bar (3), sliding block (4), guide rail (5), connecting shaft
One (9) and connecting shaft two (10), the steering engine (1) are mounted on the bifurcated upper face, and the guide rail (5) is fixed on the branch
End is socketed the sliding block (4) on the guide rail (5), and the rudderpost on the steering engine (1) is fixedly connected with the one of the steering wheel (2)
End, the other end of the steering wheel (2) are rotatablely connected one end of the draw bar (3), the traction by the connecting shaft one (9)
The other end of bar (3) is rotatablely connected the sliding block (4) by the connecting shaft two (10), and body plate (6) the center installation flies
Control plate (7) and inertial sensor (8), wireless communication module (11) and power module (12) are symmetrically mounted on the body plate (6)
Two sides, the winged control plate (7) and the steering engine (1), the inertial sensor (8), the wireless communication module (11) and institute
Stating power module (12) is electrical connection, the power module (12) and the winged control plate (7), the steering engine (1), the inertia
Sensor (8) and the wireless communication module (11) are electrical connection, fixed mandril (14), the top above the pedestal (13)
The top pointed cone of bar (14) supports the bottom groove of the body plate (6), the top cone of the mandril (14) and the fuselage
The bottom groove of plate (6) is point connection；
The Flight control simulation system of fixed-wing unmanned plane: including support base, being arranged fuselage above the support base, described
Fuselage includes head and tail, setting and the orthogonal main wing of the fuselage on the fuselage, the main wing include left wing and
A set of guide rail-sliding block-steering engine subsystem, installation above the tail are installed respectively above right flank, the left wing and the right flank
A set of guide rail-sliding block-steering engine subsystem, increases appropriate counterweight on the head, and the center of the fuselage is mounted on described
In support base.
2. UAV Flight Control analogue system as described in claim 1, which is characterized in that the body plate (6) is rectangular
The intermediate position of plate four sides length vertically devises four branches outward.
3. UAV Flight Control analogue system as described in claim 1, which is characterized in that the body plate (6) is rectangular
Four square positions of plate devise four branches along side length outward.
4. UAV Flight Control analogue system as described in claim 1, which is characterized in that the body plate (6) is circle
Plate devises four branches.
5. UAV Flight Control analogue system as described in claim 1, which is characterized in that setting in the winged control plate (7)
Micro computer.
6. UAV Flight Control analogue system as described in claim 1, which is characterized in that the wireless communication module (11)
Interior setting wireless receiver and wireless transmitter are connect with experiment computer wireless.
7. UAV Flight Control analogue system as described in claim 1, which is characterized in that the power module (12) is internal
It is made of lithium battery and voltage transformation module.
8. UAV Flight Control analogue system as described in claim 1, which is characterized in that the pedestal (13) be it is round or
Square plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821311290.1U CN208705679U (en) | 2018-08-14 | 2018-08-14 | UAV Flight Control analogue system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821311290.1U CN208705679U (en) | 2018-08-14 | 2018-08-14 | UAV Flight Control analogue system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208705679U true CN208705679U (en) | 2019-04-05 |
Family
ID=65943231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821311290.1U Expired - Fee Related CN208705679U (en) | 2018-08-14 | 2018-08-14 | UAV Flight Control analogue system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208705679U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108919674A (en) * | 2018-08-14 | 2018-11-30 | 正德职业技术学院 | UAV Flight Control analogue system |
-
2018
- 2018-08-14 CN CN201821311290.1U patent/CN208705679U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108919674A (en) * | 2018-08-14 | 2018-11-30 | 正德职业技术学院 | UAV Flight Control analogue system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190405 Termination date: 20200814 |