CN106483962A - A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control - Google Patents
A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control Download PDFInfo
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- CN106483962A CN106483962A CN201510523282.8A CN201510523282A CN106483962A CN 106483962 A CN106483962 A CN 106483962A CN 201510523282 A CN201510523282 A CN 201510523282A CN 106483962 A CN106483962 A CN 106483962A
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- unmanned aerial
- rotor wing
- aerial vehicles
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 13
- 230000007257 malfunction Effects 0.000 claims description 2
- 230000009977 dual effect Effects 0.000 description 2
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Abstract
The present invention discloses a kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control, including remote-control receiver, remote control, master controller, from controller, electron speed regulator, motor, many rotor wing unmanned aerial vehicles of remote control, screw, main GPS, from GPS, master controller be connected from controller by data/address bus, during normal work, the aerial mission of many rotor wing unmanned aerial vehicles of main controller controls remote control, when main controller system breaks down, from control of the controller system automatic seamless adapter to many rotor wing unmanned aerial vehicles of remote control.A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control, during efficiently solving unmanned plane during flying, problem when controller breaks down, make the operation of many rotor wing unmanned aerial vehicles of remote control more safe and reliable.
Description
Technical field
The present invention relates to many rotor wing unmanned aerial vehicles of unmanned plane, more particularly to remote control.
Background technology
In recent years, as the market of unmanned plane is increasing, whether professional unmanned plane and player's level unmanned plane, safety problem, are all centered around
Sixty-four dollar question between unmanned plane production firm and user, and there is problem in the flight control system that maximum of which problem is then unmanned plane, cause
Unmanned plane twinkling signal is lost, and air crash phenomenon occurs；So will be most important and must solve in the control system stable problem for solving unmanned plane
Problem.More than currently marketed unmanned plane in the form of a controller, so awing, as long as this controller failure, unmanned plane will
Out of hand, will carry for asking above, study a kind of remotely pilotless machine flight control system with dual controller.
Content of the invention
To achieve these goals, the technical scheme is that：
A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control, including remote-control receiver, remote control, master controller, from controller,
Electron speed regulator, motor, many rotor wing unmanned aerial vehicles of remote control, screw, main GPS, from GPS, master controller passes through data/address bus phase with from controller
Connection, during normal work, the aerial mission of many rotor wing unmanned aerial vehicles of main controller controls remote control, when main controller system breaks down, from controller
System automatic seamless takes over the control to many rotor wing unmanned aerial vehicles of remote control.
The master controller output PWM square-wave signal is to the electron speed regulator to control the electron speed regulator action.
The master controller is connected with the mission payload of many rotor wing unmanned aerial vehicles of remote control with control task load action.
The master controller is connected with the remote-control receiver of many rotor wing unmanned aerial vehicles of remote control.
The invention has the advantages that：
1：Safer.Using double On A Redundant Flight Control Systems, under normal circumstances, master controller is operated the present invention, stores from controller
All master controller information, in master controller failure, can be worked with seamless connection master controller from controller.
2：Multiple usages.When user thinks that dual controller is bothered, can be operated with separately installed master controller.
3：Simple to operate.Operating system is essentially identical at ordinary times with user for double redundant flight systems, and it is convenient that user operation is got up, convenient.
Description of the drawings
Technical advantage for the innovative principle of the clear explanation present invention and its compared to existing product, illustrates below by way of accompanying drawing.In in figure：
Fig. 1 is the flow chart of the present invention.
Fig. 2 is the whole machine design sketch of the present invention.
Specific embodiment
In order to better illustrate the present invention, it is described further in conjunction with accompanying drawing.
As shown in Figure 1 and Figure 2, a kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control, including remote-control receiver 1, remote control 2,
Master controller 3, from controller 4, electron speed regulator 5, many rotor wing unmanned aerial vehicles 7 of motor 6, remote control, screw 8, main GPS 9, from GPS 10,
Master controller 3 be connected from controller 4 by data/address bus, during normal work, master controller 3 controls the flight of many rotor wing unmanned aerial vehicles 7 of remote control
Task, when 3 system malfunctions of master controller, from control of 4 system automatic seamless of the controller adapter to many rotor wing unmanned aerial vehicles 7 of remote control.
The master controller 3 exports PWM square-wave signal to the electron speed regulator 5 to control 5 action of the electron speed regulator.
The master controller 3 is connected with the mission payload of many rotor wing unmanned aerial vehicles 7 of remote control with control task load action.
The master controller 3 is connected with the remote-control receiver 1 of many rotor wing unmanned aerial vehicles 7 of remote control.
Operation principle of the present invention is：Master controller is connected with remote-control receiver, and remote control is directly controlled to master controller；Master controller with from control
Being connected by data/address bus between device processed, under normal circumstances, only master controller is operated, flying while storing all of master controller from controller
Row information, when master controller breaks down, can be with seamless connection, so as to strengthen the safety guarantee during unmanned plane during flying from controller；Master control
Device processed is controlled to electron speed regulator by PWM square wave, and electron speed regulator controlled motor is rotated, and motor drives rotor wing rotation, so as to control aircraft
Flight attitude.
Claims (4)
1. a kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control, including remote-control receiver (1), remote control (2), master controller
(3), from controller (4), electron speed regulator (5), motor (6), many rotor wing unmanned aerial vehicles of remote control (7), screw (8), main GPS (9),
From GPS (10), master controller (3) be connected from controller (4) by data/address bus, during normal work, master controller (3) control is distant
The aerial mission of many rotor wing unmanned aerial vehicles (7) is controlled, when master controller (3) system malfunctions, is taken over from controller (4) system automatic seamless
Control to many rotor wing unmanned aerial vehicles of remote control (7).
2. double On A Redundant Flight Control Systems of many rotor wing unmanned aerial vehicles of remote control are used for as claimed in claim 1, it is characterised in that：Master controller (3)
Output PWM square-wave signal is to the electron speed regulator (5) to control the electron speed regulator (5) action.
3. double On A Redundant Flight Control Systems of many rotor wing unmanned aerial vehicles of remote control are used for as claimed in claim 1 or 2, it is characterised in that：The main control
Device (3) is connected with the mission payload of many rotor wing unmanned aerial vehicles of remote control (7) with control task load action.
4. double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control as described in claim 1-3, it is characterised in that：The master controller
(3) it is connected with the remote-control receiver (1) of many rotor wing unmanned aerial vehicles of remote control (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510523282.8A CN106483962A (en) | 2015-08-24 | 2015-08-24 | A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510523282.8A CN106483962A (en) | 2015-08-24 | 2015-08-24 | A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106483962A true CN106483962A (en) | 2017-03-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510523282.8A Pending CN106483962A (en) | 2015-08-24 | 2015-08-24 | A kind of double On A Redundant Flight Control Systems for many rotor wing unmanned aerial vehicles of remote control |
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| CN (1) | CN106483962A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110058585A (en) * | 2018-01-19 | 2019-07-26 | 通用电气航空系统有限责任公司 | Automatic driving control system for unmanned vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101799689A (en) * | 2010-04-08 | 2010-08-11 | 中国电子科技集团公司第三十八研究所 | Dual-redundancy steering engine controller |
| CN201796292U (en) * | 2010-04-28 | 2011-04-13 | 北京航空航天大学 | Double-redundancy posture control system of coaxial type unmanned helicopter |
| CN203786564U (en) * | 2014-04-22 | 2014-08-20 | 零度智控（北京）智能科技有限公司 | Dual-redundancy flight control system |
| CN204965188U (en) * | 2015-08-24 | 2016-01-13 | 武汉好奥航空技术有限公司 | A two remaining flight control for many rotor unmanned aerial vehicle of remote control |
-
2015
- 2015-08-24 CN CN201510523282.8A patent/CN106483962A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101799689A (en) * | 2010-04-08 | 2010-08-11 | 中国电子科技集团公司第三十八研究所 | Dual-redundancy steering engine controller |
| CN201796292U (en) * | 2010-04-28 | 2011-04-13 | 北京航空航天大学 | Double-redundancy posture control system of coaxial type unmanned helicopter |
| CN203786564U (en) * | 2014-04-22 | 2014-08-20 | 零度智控（北京）智能科技有限公司 | Dual-redundancy flight control system |
| CN204965188U (en) * | 2015-08-24 | 2016-01-13 | 武汉好奥航空技术有限公司 | A two remaining flight control for many rotor unmanned aerial vehicle of remote control |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110058585A (en) * | 2018-01-19 | 2019-07-26 | 通用电气航空系统有限责任公司 | Automatic driving control system for unmanned vehicle |
| US11966223B2 (en) | 2018-01-19 | 2024-04-23 | Ge Aviation Systems Llc | Autopilot control system for unmanned vehicles |
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Address after: 430073 1403, building E3, Guanggu Software Park, Guanshan Avenue, Donghu New Technology Development Zone, Wuhan City, Hubei Province Applicant after: HUBEI E-HAWK TECHNOLOGY CO.,LTD. Address before: 430073 1403, building E3, Guanggu Software Park, Guanshan Avenue, Donghu New Technology Development Zone, Wuhan City, Hubei Province Applicant before: WUHAN HAOAO AVIATION TECHNOLOGY Co.,Ltd. |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170308 |
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| WD01 | Invention patent application deemed withdrawn after publication |