CN109292090A - A redundant electronic flameout control system for unmanned helicopter - Google Patents
A redundant electronic flameout control system for unmanned helicopter Download PDFInfo
- Publication number
- CN109292090A CN109292090A CN201811297831.4A CN201811297831A CN109292090A CN 109292090 A CN109292090 A CN 109292090A CN 201811297831 A CN201811297831 A CN 201811297831A CN 109292090 A CN109292090 A CN 109292090A
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- CN
- China
- Prior art keywords
- solenoid valve
- valve module
- control circuit
- unmanned helicopter
- control system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0011—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots associated with a remote control arrangement
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Catching Or Destruction (AREA)
- Toys (AREA)
Abstract
本发明属于无人直升机技术领域，具体的说是一种无人直升机冗余电子熄火控制系统。包括通断控制电路及连接在通断控制电路中的电磁阀模块，其中电磁阀模块设置于无人直升机的发动机供油管路上，通断控制电路设置于无人直升机的机舱内，电磁阀模块包括电磁阀模块Ⅰ和\或电磁阀模块Ⅱ,电磁阀模块Ⅰ连接在通断控制电路中的通断控制电路Ⅰ中，通断控制电路Ⅰ与飞控系统连接，飞行控制系统通过地面站控制系统远程控制；电磁阀模块Ⅱ连接在通断控制电路中通断控制电路Ⅱ中，通断控制电路Ⅱ与遥控开关和\或有线开关连接。本发明实现无人直升机在地面开车试验中可靠的紧急熄火停车，避免因发动机超转速或其他故障导致的危险。
The invention belongs to the technical field of unmanned helicopters, in particular to an unmanned helicopter redundant electronic flameout control system. It includes an on-off control circuit and a solenoid valve module connected in the on-off control circuit, wherein the solenoid valve module is arranged on the engine oil supply pipeline of the unmanned helicopter, and the on-off control circuit is arranged in the cabin of the unmanned helicopter. Including solenoid valve module I and \ or solenoid valve module II, solenoid valve module I is connected to the on-off control circuit I in the on-off control circuit, the on-off control circuit I is connected with the flight control system, and the flight control system is controlled by the ground station. The system is remotely controlled; the solenoid valve module II is connected to the on-off control circuit II in the on-off control circuit, and the on-off control circuit II is connected with the remote control switch and/or the wired switch. The invention realizes reliable emergency stop of the unmanned helicopter in the ground driving test, and avoids the danger caused by the over-speed of the engine or other failures.
Description
Technical field
The invention belongs to unmanned helicopter technical field, the flame-out control of specifically a kind of unmanned helicopter redundant electronic
System.
Background technique
Unmanned helicopter can VTOL, hedgehopping, its intrinsic flight maneuver is strong in addition, kinematic dexterity
The features such as high, has boundless application prospect.500-800 kilograms of take-off weight of technical grade unmanned helicopter is (hereinafter referred to as
Light-duty industry unmanned helicopter) have net load ability more than hundred kilograms, other platforms can be played in more key areas
Irreplaceable role generates great economic and social benefit.
Ground debugging test is that unmanned helicopter develops indispensable development link, be may be implemented to whole system items
Comprehensive test of function is crucial verifying link before first-fly.Since ground debugging is that unmanned helicopter is completed to carry out after integrating
Joint test whole for the first time, need to detect and exclude it is integrated after the problem of depositing, therefore empirical risk with higher realizes
In case of emergency reliable and stable flame-out control is to ensure the important means of test safety.
Engine generally has electronic control system, can be started under normal circumstances by sending flame-out cutoff command realization
Machine is flame-out, but does not ensure that the control to engine reliable.By directly cutting off oil circuit except electronic control system
Method can stop the fuel feeding of engine, stop it, and be the reliable means for terminating engine operation, herein on basis
Increase Redundancy Design, it can be ensured that the safety of unmanned helicopter ground debugging test.This mode can be used for ensureing other
Debug safety in ground based on engine apparatus.
Summary of the invention
In view of the above-mentioned problems, the purpose of the present invention is to provide a kind of unmanned helicopter redundant electronic flameout control system,
It, can be to avoid to realize unmanned helicopter reliable urgent flame-out parking in the running experience of integrated engine dynamical system ground
Because dangerous caused by engine overrun speed or other failures, equipment and personnel safety is ensured.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of unmanned helicopter redundant electronic flameout control system, including on-off control circuit and it is connected to the on-off control
Solenoid valve module in circuit processed, wherein solenoid valve module is set on the oil feed line for engines of unmanned helicopter, described logical
Disconnected control circuit be set in the cabin of unmanned helicopter and with the flight control system of unmanned helicopter, remote control switch and or have
Wiretap connection.
The solenoid valve module include solenoid valve module I and or solenoid valve module II, the solenoid valve module I be connected to
In on-off control circuit I in the on-off control circuit, the on-off control circuit I is connect with the flight control system, described
Flight control system is remotely controlled by ground station control system；The solenoid valve module II is connected to the on-off control circuit
In middle on-off control circuit II, the on-off control circuit II and remote control switch and or cable switch connect.
The on-off control circuit I includes lithium battery I and relay switch I, and the lithium battery I and relay switch I are logical
Cross conducting wire connection, form closed circuit I, the solenoid valve module I connects in the closed circuit I, the relay switch I with
The flight control system connection.
In the closed circuit I, the both ends of the solenoid valve module I are parallel with freewheeling diode I and work light
Ⅰ。
In the closed circuit I, one end of the solenoid valve module I is in series with fuse.
The on-off control circuit II includes lithium battery II and relay switch II, the lithium battery II and relay switch
II is connected by conducting wire, forms closed circuit II, and the solenoid valve module II connects in the closed circuit II, the relay
Switch II is connect with remote control switch, and the remote control switch and remote controler wirelessly communicate.
The on-off control circuit II further includes the relay switch III being connected in parallel with relay switch II, the relay
Device switch III is connect by conducting wire with the cable switch.
In the on-off control circuit II, the both ends of the solenoid valve module II are parallel with freewheeling diode II and work
Indicator light II.
In the on-off control circuit II, one end of the solenoid valve module II is in series with fuse.
The solenoid valve module I and solenoid valve module II are installed in series in the oil feed line for engines of the unmanned helicopter
It is upper and connected with body rack.
The invention has the advantages and beneficial effects that:
1. the present invention realizes that unmanned helicopter is reliable in the driving of integrated engine dynamical system ground and flight test
Urgent flame-out parking can ensure equipment and personnel safety to avoid because dangerous caused by engine overrun speed or other failures.
2. the present invention increases emergency stop dual redundant switch, even if engine control system fails, fly the case where control is broken down
The lower parking that so can promptly stop working.
3. the present invention especially extends wired extension emergency stop switch in the ground running experience stage, security reliability is increased.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for being equipped with unmanned helicopter of the invention；
Fig. 2 is electric operation control circuit figure of the invention.
Wherein: 1 is unmanned helicopter, and 2 be oil feed line for engines, and 3 be solenoid valve I, and 4 be solenoid valve II, and 5 be to start
Machine, 6 be on-off control circuit, and 7 be fuel tank.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention clearer, right in the following with reference to the drawings and specific embodiments
The present invention is described in detail.
As shown in Figs. 1-2, a kind of unmanned helicopter redundant electronic flameout control system provided by the invention, including on-off control
Circuit 6 processed and the solenoid valve module being connected in on-off control circuit 6, wherein solenoid valve module is set to unmanned helicopter 1
On oil feed line for engines 2, on-off control circuit 6 be set in the cabin of unmanned helicopter 1 and with unmanned helicopter 1
Flight control system, remote control switch with or cable switch connect.
Solenoid valve module include solenoid valve module I 3 and or solenoid valve module II 4, solenoid valve module I 3 be connected to on-off control
In on-off control circuit I in circuit 6 processed, on-off control circuit I is connect with flight control system, and flight control system passes through earth station
Control system remotely controls；Solenoid valve module II 4 is connected in on-off control circuit 6 in on-off control circuit II, on-off control
Circuit II and remote control switch and or cable switch connect.
On-off control circuit I includes lithium battery I and relay switch I, and lithium battery I and relay switch I are connected by conducting wire
It connects, forms closed circuit I, solenoid valve module I 3 connects in closed circuit I, and relay switch I is connect with flight control system.
Further, in closed circuit I, the both ends of solenoid valve module I 3 are parallel with freewheeling diode I and work instruction
One end of lamp I, solenoid valve module I 3 is in series with fuse.
On-off control circuit II includes lithium battery II and relay switch II, and lithium battery II and relay switch II are by leading
Line connection forms closed circuit II, and solenoid valve module II 4 connects in closed circuit II, and relay switch II and remote control switch connect
It connects, remote control switch and remote controler wirelessly communicate.
On-off control circuit II further includes the relay switch III being connected in parallel with relay switch II, relay switch III
It is connect by conducting wire with cable switch.
Further, in on-off control circuit II, the both ends of solenoid valve module II 4 are parallel with freewheeling diode II and work
Make indicator light II, one end of solenoid valve module II 4 is in series with fuse.
In the embodiment of the present invention, solenoid valve module I 3 is identical with II 4 structure of solenoid valve module, solenoid valve module I 3 and electricity
Magnet valve module II 4 is installed in series on the oil feed line for engines 2 of unmanned helicopter 1 and is connected with body rack.
In on-off control circuit 6, the counter electromotive force damage of the powerful electromagnet inductive element of shutdown transient in order to prevent
Other electronic equipments are parallel with freewheeling diode at the both ends of solenoid valve module I 3 and solenoid valve module II 4.Solenoid valve module I 3
It is also parallel with indicator light with solenoid valve module II 4, by indicator light it is known that whether redundant electronic flameout control system is in
Normal operating conditions.
Redundant electronic flameout control system is remotely controlled by ground station control system, remote controler.Entire control circuit is logical
It crosses relay switch to connect with unmanned helicopter flight control system, the height exported by unmanned helicopter flight control system
Level controls opening and turning off for on-off control circuit, and this control command is from ground station control system or remote controler
It is sent to redundant electronic flameout control system, to remotely control the work of redundant electronic flameout control system.Entire on-off control
Circuit processed is by two 25V lithium battery power supplies.
On-off control circuit 6 is connected by the flight control system of relay switch and unmanned helicopter, is equivalent to two
A circuit is isolated, so the avionics system of unmanned helicopter 1 will not be by redundant electronic flameout control system control circuit
Influence, independently work.
Redundant electronic flameout control system provided by the invention, structure is simple, easy for installation, and entire redundant system can be independent
Work, will not influence the normal work of other electronic equipments.The present invention realizes unmanned helicopter in integrated engine dynamical system
Ground drive and flight test in reliable urgent flame-out parking, can be to avoid caused by because of engine overrun speed or other failures
Danger ensures equipment and personnel safety.
Mode the above is only the implementation of the present invention is not intended to limit the scope of the present invention.It is all in the present invention
Spirit and principle within any modification, equivalent replacement, improvement, extension etc., be all contained in protection scope of the present invention
It is interior.
Claims (10)
1. a kind of unmanned helicopter redundant electronic flameout control system, which is characterized in that including on-off control circuit (6) and connection
Solenoid valve module in the on-off control circuit (6), wherein solenoid valve module is set to the engine of unmanned helicopter (1)
On oil feed line (2), the on-off control circuit (6) is set in the cabin of unmanned helicopter (1) and and unmanned helicopter
(1) flight control system, remote control switch with or cable switch connect.
2. unmanned helicopter redundant electronic flameout control system according to claim 1, which is characterized in that the solenoid valve
Module include solenoid valve module I (3) and or solenoid valve module II (4), the solenoid valve module I (3) be connected to the on-off control
In on-off control circuit I in circuit (6) processed, the on-off control circuit I is connect with the flight control system, the flight control
System is remotely controlled by ground station control system；The solenoid valve module II (4) is connected in the on-off control circuit (6)
In on-off control circuit II, the on-off control circuit II and remote control switch and or cable switch connect.
3. unmanned helicopter redundant electronic flameout control system according to claim 2, which is characterized in that the on-off control
Circuit I processed includes lithium battery I and relay switch I, and the lithium battery I is connected with relay switch I by conducting wire, forms closure
Circuit I, the solenoid valve module I (3) connect in the closed circuit I, and the relay switch I connects with the flight control system
It connects.
4. unmanned helicopter redundant electronic flameout control system according to claim 3, which is characterized in that in the closure
In circuit I, the both ends of the solenoid valve module I (3) are parallel with freewheeling diode I and work light I.
5. unmanned helicopter redundant electronic flameout control system according to claim 3, which is characterized in that in the closure
In circuit I, one end of the solenoid valve module I (3) is in series with fuse.
6. unmanned helicopter redundant electronic flameout control system according to claim 2, which is characterized in that the on-off control
Circuit II processed includes lithium battery II and relay switch II, and the lithium battery II is connected with relay switch II by conducting wire, shape
At closed circuit II, the solenoid valve module II (4) is connected in the closed circuit II, and the relay switch II is opened with remote control
Connection connects, and the remote control switch and remote controler wirelessly communicate.
7. unmanned helicopter redundant electronic flameout control system according to claim 6, which is characterized in that the on-off control
Circuit II processed further includes the relay switch III being connected in parallel with relay switch II, the relay switch III by conducting wire with
The cable switch connection.
8. unmanned helicopter redundant electronic flameout control system according to claim 6 or 7, which is characterized in that described
In on-off control circuit II, the both ends of the solenoid valve module II (4) are parallel with freewheeling diode II and work light II.
9. unmanned helicopter redundant electronic flameout control system according to claim 6 or 7, which is characterized in that described
In on-off control circuit II, one end of the solenoid valve module II (4) is in series with fuse.
10. unmanned helicopter redundant electronic flameout control system according to claim 2, which is characterized in that the electromagnetism
Valve module I (3) and solenoid valve module II (4) be installed in series on the oil feed line for engines (2) of the unmanned helicopter (1),
And it is connected with body rack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811297831.4A CN109292090B (en) | 2018-11-01 | 2018-11-01 | Redundant electronic flameout control system of unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811297831.4A CN109292090B (en) | 2018-11-01 | 2018-11-01 | Redundant electronic flameout control system of unmanned helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109292090A true CN109292090A (en) | 2019-02-01 |
| CN109292090B CN109292090B (en) | 2024-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811297831.4A Active CN109292090B (en) | 2018-11-01 | 2018-11-01 | Redundant electronic flameout control system of unmanned helicopter |
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| Country | Link |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112278297A (en) * | 2020-11-09 | 2021-01-29 | 中国人民解放军总参谋部第六十研究所 | An emergency flameout control system for unmanned helicopter |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6393353B1 (en) * | 1999-03-18 | 2002-05-21 | Snecma Moteurs | Self-testable architecture for overspeed limitation and cutoff systems when the turbojet stops |
| CN2570473Y (en) * | 2002-07-29 | 2003-09-03 | 苏军锋 | Pipe line fuelling vehicle interlocking controlled engine stall apparatus |
| CN102092475A (en) * | 2010-12-30 | 2011-06-15 | 清华大学 | Landing automatic flameout system for unmanned helicopter |
| CN202448982U (en) * | 2012-01-12 | 2012-09-26 | 安徽铜冠机械股份有限公司 | Diesel engine flameout and parking brake interlock control device |
| US20180223785A1 (en) * | 2017-02-08 | 2018-08-09 | Pratt & Whitney Canada Corp. | Method and system for testing operation of solenoid valves |
| CN209023130U (en) * | 2018-11-01 | 2019-06-25 | 中国科学院沈阳自动化研究所 | Redundant electronic flameout control system for unmanned helicopter |
-
2018
- 2018-11-01 CN CN201811297831.4A patent/CN109292090B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6393353B1 (en) * | 1999-03-18 | 2002-05-21 | Snecma Moteurs | Self-testable architecture for overspeed limitation and cutoff systems when the turbojet stops |
| CN2570473Y (en) * | 2002-07-29 | 2003-09-03 | 苏军锋 | Pipe line fuelling vehicle interlocking controlled engine stall apparatus |
| CN102092475A (en) * | 2010-12-30 | 2011-06-15 | 清华大学 | Landing automatic flameout system for unmanned helicopter |
| CN202448982U (en) * | 2012-01-12 | 2012-09-26 | 安徽铜冠机械股份有限公司 | Diesel engine flameout and parking brake interlock control device |
| US20180223785A1 (en) * | 2017-02-08 | 2018-08-09 | Pratt & Whitney Canada Corp. | Method and system for testing operation of solenoid valves |
| CN209023130U (en) * | 2018-11-01 | 2019-06-25 | 中国科学院沈阳自动化研究所 | Redundant electronic flameout control system for unmanned helicopter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112278297A (en) * | 2020-11-09 | 2021-01-29 | 中国人民解放军总参谋部第六十研究所 | An emergency flameout control system for unmanned helicopter |
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| Publication number | Publication date |
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| CN109292090B (en) | 2024-03-12 |
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