CN201729270U - Electric screw pitch changing device for screw propeller-driven unmanned aircraft - Google Patents
Electric screw pitch changing device for screw propeller-driven unmanned aircraft Download PDFInfo
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- CN201729270U CN201729270U CN201020264755XU CN201020264755U CN201729270U CN 201729270 U CN201729270 U CN 201729270U CN 201020264755X U CN201020264755X U CN 201020264755XU CN 201020264755 U CN201020264755 U CN 201020264755U CN 201729270 U CN201729270 U CN 201729270U
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Abstract
The utility model discloses an electric screw pitch changing device for a screw propeller-driven unmanned aircraft, which comprises an aircraft control computer (1) arranged on the aircraft and a ground station (4). The aircraft control computer (1) is connected with the ground station (4) in a wireless manner and connected with the input end of a screw propeller control box (2), and the output end of the screw propeller control box (2) is connected with a screw propeller control motor (3). The electric screw pitch changing device adopts open-loop control, so as to avoid instable power after abnormity occurrence during flight process of the aircraft. The flight control staff can send remote regulating instructions and select propeller blade angle required by the screw propeller according to the engine speed during flight and flight attitude, flight speed and flight altitude, resulting in more direct control of the ground flight control staff to the aircraft. The electric screw pitch changing device controls the propeller blade angle so as to achieve the optimum efficiency of the screw propeller.
Description
Technical field
The utility model relates to a kind of device of screw propeller unmanned plane electric variable pitch distance, belongs to the unmanned aerial vehicle (UAV) control technology.
Background technology
Still do not have at present and can supply with the screw propeller pulp distance varying mechanism that unmanned aerial vehicle uses.At the demand of the novel unmanned aerial vehicle of development, will manually control pulp distance varying mechanism and be improved to remote control control, to satisfy the specific (special) requirements of using the feather screw propeller on the unmanned aerial vehicle to the screw propeller variablepiston.
Summary of the invention
The purpose of this utility model is, a kind of device of screw propeller unmanned plane electric variable pitch distance is provided, and will manually control pulp distance varying mechanism and be improved to remote control control, realizes using on the unmanned aerial vehicle specific (special) requirements of electric variable pitch apart from screw propeller in the mode of numerical control transformation.
The technical solution of the utility model: the device of a kind of screw propeller unmanned plane electric variable pitch distance of the present utility model comprises the flight control computer on the machine and is located at ground station on the ground; Flight control computer and ground station's wireless connections, the control end of flight control computer is connected with the input end of screw propeller control capsule, and the mouth of screw propeller control capsule is connected with screw propeller control motor.
In the aforementioned means, be provided with relay J 1 and relay J 2 in the described screw propeller control capsule, the coil of relay J 1 and relay J 2 is connected with two control ends of flight control computer respectively, the moving contact of relay J 1 and relay J 2 is connected with screw propeller control motor respectively, and two break back contacies of relay J 1 and relay J 2 are connected with earth point with the 12V power supply respectively.
Owing to adopted technique scheme, compared with prior art, the utility model adopts open loop control, avoid might occurring in the aircraft flight process unusual after cause the situation of dynamic instability, flicon personnel are according to rotating speed, flight attitude, flying speed and the flying height etc. of driving engine are sent the remote regulating instruction in-flight, select the needed blade angle of screw propeller, make ground flying control personnel more direct the operation of aircraft.Control propeller blade angle size is brought into play the optimum efficiency of screw propeller with this.
Take two relays to realize the switching function of circuit in the circuit, and increase can realize that the open circuit protection switch of reset function is to guarantee the safety of motor under the state of overshoot in circuit.
The product design index
Rated voltage: 27VDC;
Voltage range: by 2. 2. class of 181-1986 " aviation power supply characteristic and to the requirement of consumer " of GJ;
Operating temperature :-50 ℃～+ 50 ℃;
Storage temperature :-45 ℃～+ 60 ℃;
Relative humidity: (95 ± 3) %;
Vibration: 5～500Hz (sine), acceleration/accel 7g;
Operating altitude :≤8000m (acyclic control system);
Weight :≤1Kg;
Control circuit received current: I 1.≤15m 1.;
Overall dimensions (unit: millimeter): 83 * 61 * 50.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the electrical schematic diagram of screw propeller control capsule on the machine of the present utility model.
Being labeled as in the accompanying drawing: 1-flight control computer, 2-ground station, 3-screw propeller control capsule, 4-screw propeller control motor.
The specific embodiment
The utility model is described in further detail below in conjunction with drawings and Examples.
Embodiment: structural principle of the present utility model as depicted in figs. 1 and 2, when implementing the device of screw propeller unmanned plane electric variable pitch distance of the present utility model, this device comprises the flight control computer 1 on the existing machine and is located at ground station 4 on the ground; Flight control computer 1 and ground station's 4 wireless connections, flight control computer 1 is connected with the input end of screw propeller control capsule 2, and the mouth of screw propeller control capsule 2 is connected with existing screw propeller control motor 3; In screw propeller control capsule 2, be provided with relay J 1 and relay J 2, the coil of relay J 1 and relay J 2 is connected with two control ends of flight control computer 1 respectively, the moving contact of relay J 1 and relay J 2 is connected with screw propeller control motor 3 respectively, and two break back contacies of relay J 1 and relay J 2 are connected with earth point with the 12V power supply respectively.
The method of screw propeller unmanned plane electric variable pitch distance of the present utility model is to adopt open loop control, promptly send telecommand by existing ground station 4, after receiving telecommand, flight control computer 1 on the aircraft sends control signal, control signal is by 3 work of the 2 control screw propeller drive motor of the screw propeller control capsule on the aircraft, the rotating and the anglec of rotation by screw propeller drive motor 3 change the propeller blade angle, reach the purpose of control state of flight.The angular rate signal that described open loop control is propeller blade does not feed back to flight control computer 1, and 1 of flight control computer is accepted the telecommand that ground station 4 sends.Described propeller blade from minimum angles change to maximum angle or propeller blade from the time that maximum angle changes to minimum angles be the total travel work-hours, the total travel work-hours is divided into N set time section controls; Whenever power up once, only move a set time section, propeller blade can only change fixed angle, determines the angle of current propeller blade by powering up number of times.Described total travel work-hours is 10 seconds, and each set time section equals 10/N second.Described powering up adopts click to power up mode, and an impulse singla is once only sent in every click, and the width of impulse singla equals the duration 10/N second of set time section.The control signal that described flight control computer 1 sends is a two path control signal; Be respectively signal 1. with signal 2.; Two path control signal is only exported high level or low level respectively, and high level is 1, and low level is 0; Determine the mode of operation of screw propeller drive motor 3 according to the logical relation of two path control signal.2.=1 o'clock described logical relation is as follows: when 1.=0,, the screw propeller drive motor just changes; When 1.=1,2.=0 o'clock, the counter-rotating of screw propeller drive motor; 2.=1 o'clock when 1.=1,, screw propeller drive motor 3 does not change.Described screw propeller control capsule 2 adopts relay on-off control circuit, the fugitiveness of avoiding complicated circuit to bring.
The utility model is in order to guarantee convenient, the safe use on unmanned aerial vehicle of electric variable pitch spacing mechanism, the utility model does not use closed loop control, open loop control is that the angular rate signal of propeller blade does not feed back to flight control computer 1, and 1 of flight control computer is accepted the telecommand that ground station 4 sends.Set relevant adjustment window on the flight operation interface and be selected at.Flicon personnel's foundation rotating speed, flight attitude, flying speed and flying height etc. of driving engine is in-flight sent the remote regulating instruction, and control propeller blade angle size is brought into play the optimum efficiency of screw propeller with this.The open loop controlling Design can be avoided might occurring in the aircraft flight process causes the situation of dynamic instability after unusual, after by the flicon personnel current state of flight being carried out anticipation, select the needed blade angle of screw propeller, make ground flying control personnel more direct the operation of aircraft.
During concrete enforcement, control signal can use the idle discrete magnitude of flight control computer 1 part, i.e. two path control signal link.The control signal that flight control computer sends is a two path control signal; Be respectively 1. signal and 2. signal; Two path control signal is only exported high level or low level respectively, and high level is 1, and low level is 0; Determine the mode of operation of motor according to the logical relation of two path control signal.2.=1 o'clock described logical relation is as follows: when 1.=0,, motor just changes; When 1.=1,2.=0 o'clock, the motor counter-rotating; 2.=1 o'clock when 1.=1,, motor does not change.Just can finish the control of this signal.
1. signal and 2. signal by powering up the movement travel that number of times comes the controlling and driving motor, specific practice is propeller blade to be changed to maximum angle or propeller blade change to minimum angles from maximum angle time from minimum angles be set at 10 seconds for the total travel work-hours, again 10 seconds total travel work-hourses are divided into 10 set time sections and control, each set time section is 1 second; If it is 90 degree from the angle changing that maximum angle changes to minimum angles that propeller blade changes to maximum angle or propeller blade from minimum angles, then each set time section can only make propeller blade that the variations of 9 degree are arranged.According to the rotating number of times of number of times that powers up and motor, just can learn the actual angle of current propeller blade, thereby counting machine can be set count, by the mode of operation of engine speed monitoring pulp distance varying mechanism to powering up number of times.
The whole propeller variable-pitch control system is made up of flight control computer and electric drive system, as shown in Figure 2.The drive control part of motor receives by two kinds of impulse singlas of flight control computer, a high level, a low level signal.
Take to use the impulse singla of regulation duration in control, whenever send the pulsatile once signal, electric drive system is carried out once action, and the duration of carrying out action is determined by pulse length.
The logic of concrete control as shown in Figure 2,1., 2. two-port connects flight control computer, sends impulse singla by flight control computer when needs increase (reducing) blade angle.Logical relation is as shown in table 1 below.
The regulation high level is 1 in the table 1, and low level is 0, and 1., 2. port is respectively two interfaces that insert flight control computer in the motor driving controling circuit.
| ? | Motor just changes | The motor counter-rotating | Motor does not change |
| |
0 | 1 | 1 |
| |
1 | 0 | 1 |
Table 1 drive motor control logic
Set the action of relevant control button control motor on the flight operation interface, whenever send the pulsatile once signal by button flight control computer next time, machine operation once.When needs increase (reducing) blade angle, click the control corresponding button.When if the one click button can't reach the blade angle that needs, the click by repeatedly can reach final demand.
The design of predetermined pulse duration can avoid in operating process because the manually operated error of operator, has influence on the accuracy of electric machine control.
Claims (2)
1. the device of a screw propeller unmanned plane electric variable pitch distance is characterized in that: this device comprises the flight control computer (1) on the machine and is located at ground station (4) on the ground; Flight control computer (1) and ground station (4) wireless connections, flight control computer (1) is connected with the input end of screw propeller control capsule (2), and the mouth of screw propeller control capsule (2) is connected with screw propeller control motor (3).
2. the device of screw propeller unmanned plane electric variable pitch distance according to claim 1, it is characterized in that: be provided with relay J 1 and relay J 2 in the described screw propeller control capsule (2), the coil of relay J 1 and relay J 2 is connected with two control ends of flight control computer (1) respectively, the moving contact of relay J 1 and relay J 2 is connected with screw propeller control motor (3) respectively, and two break back contacies of relay J 1 and relay J 2 are connected with earth point with the 12V power supply respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020264755XU CN201729270U (en) | 2010-07-21 | 2010-07-21 | Electric screw pitch changing device for screw propeller-driven unmanned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020264755XU CN201729270U (en) | 2010-07-21 | 2010-07-21 | Electric screw pitch changing device for screw propeller-driven unmanned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201729270U true CN201729270U (en) | 2011-02-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020264755XU Expired - Fee Related CN201729270U (en) | 2010-07-21 | 2010-07-21 | Electric screw pitch changing device for screw propeller-driven unmanned aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201729270U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102336266A (en) * | 2010-07-21 | 2012-02-01 | 贵州贵航无人机有限责任公司 | Method and device for propeller electric pitch control of unmanned aerial vehicle |
| GB2555194A (en) * | 2016-08-12 | 2018-04-25 | Safran Aircraft Engines | Turbopropeller control system with control saturation management |
-
2010
- 2010-07-21 CN CN201020264755XU patent/CN201729270U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102336266A (en) * | 2010-07-21 | 2012-02-01 | 贵州贵航无人机有限责任公司 | Method and device for propeller electric pitch control of unmanned aerial vehicle |
| GB2555194A (en) * | 2016-08-12 | 2018-04-25 | Safran Aircraft Engines | Turbopropeller control system with control saturation management |
| US10480423B2 (en) | 2016-08-12 | 2019-11-19 | Safran Aircraft Engines | Turbopropeller control system with control saturation management |
| GB2555194B (en) * | 2016-08-12 | 2021-03-24 | Safran Aircraft Engines | Turbopropeller control system with control saturation management |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110202 Termination date: 20120721 |