CN106043715A - In-flight auto-ignition control method of engine of unmanned aerial vehicle - Google Patents
In-flight auto-ignition control method of engine of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106043715A CN106043715A CN201610366869.7A CN201610366869A CN106043715A CN 106043715 A CN106043715 A CN 106043715A CN 201610366869 A CN201610366869 A CN 201610366869A CN 106043715 A CN106043715 A CN 106043715A
- Authority
- CN
- China
- Prior art keywords
- engine
- aircraft
- aerial vehicle
- ignition
- unmanned vehicle
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
- B64D31/06—Initiating means actuated automatically
-
- 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
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D17/00—Controlling engines by cutting out individual cylinders; Rendering engines inoperative or idling
- F02D17/04—Controlling engines by cutting out individual cylinders; Rendering engines inoperative or idling rendering engines inoperative or idling, e.g. caused by abnormal conditions
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The invention discloses an in-flight auto-ignition control method of an engine of an unmanned aerial vehicle. The method comprises: (11), detecting whether a ground control station is out of control, or whether the engine of the aerial vehicle is subjected to accidental flameout and shut down; (12), if the ground control station is out of airplane control ability, or the engine of the aerial vehicle is subjected to accidental flameout and shut down, executing the step (13); (13), detecting whether the communication link between the unmanned aerial vehicle and the ground control station is normal, if the communication link between the unmanned aerial vehicle and the ground control station is normal, executing the step (14); (14), detecting whether the engine working condition information and the aerial vehicle flight state meet operation requirements, if the engine working condition information and the aerial vehicle flight state meet the operation requirements, executing the step (15); and (15), detecting whether a throttle servo, an accelerator servo and a task servo of the engine can work normally, if the throttle servo, the accelerator servo and the task servo of the engine can work normally, carrying out an ignition command, and restarting the engine; if the throttle servo, the accelerator servo and the task servo of the engine cannot work normally, stopping sending the ignition command. The method can be applied to reignition and starting of the unmanned aerial vehicle after fault recovery, the aerial vehicle can be effectively protected, and the flight cost is reduced.
Description
Technical field
The present invention relates to unmanned vehicle field, automatic ignition controlling party in specifically a kind of unmanned vehicle engine air
Method
Background technology
Unmanned vehicle is the not manned vehicle of the presetting apparatus manipulation utilizing radio robot with providing for oneself,
Such as unmanned aerial vehicle.Unmanned vehicle can be generally divided into unmanned Fixed Wing AirVehicle, unmanned vertical flight, nobody flies
Ship, depopulated helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..The range of application of unmanned vehicle is more and more extensive, bag
Include taking photo by plane, agricultural, plant protection, auto heterodyne, express transportation, disaster relief, observation wild animal, monitoring infectious disease, mapping, Xin Wen Bao
The application in road, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field, has greatly expanded the use of unmanned plane itself
On the way.
Unmanned vehicle awing it is possible that out of touch with ground control station thus cause ground control station without
Method controls the state of aircraft in real time, and the meeting out of control of this unmanned vehicle causes the more serious consequence of ratio, the most then aircraft and
The equipment carried smashes to be scrapped, and people or building may be brought injury time serious.Having a kind of mode at present is by automatically
Cutting off engine power is that aircraft is protected by the mode actively controlling engine misses, i.e. makes it by control electromotor
Flame-out, thus protect the uncertainty or damage that aircraft causes because uncontrolled power exists.It addition, another kind of situation
It is that unmanned vehicle is awing also possible to can be because system stability or otherwise failure and other reasons occur that electromotor is non-
The flame-out situation shut down under normal condition.Under this state, the most also it is to flying by the way of controlling aircraft emergency landing
Row device is protected.
But, would generally occur at present following situation, i.e. unmanned vehicle enter recover again after automatic defence program with
The contact of ground control station, ground control station can control again the state of aircraft the most in real time, or engine failure recovers,
But now because engine misses cannot be carried out restarting, even if aircraft is the most recovered normally also cannot continue executing with flight,
Flight cost is caused to be greatly improved.
At present, there is in the industry aerial automatic ignition and recover the scheme of flight, such as patent documentation CN102072063A is open
A kind of Encounter-starting airstart system of aircraft engine, it is by finding combustor to the monitoring of engine combustion room temperature
After Xi Huo, digitial controller controls oil supply system immediately and ignition system carries out electromotor airstart, it is ensured that electromotor exists
The success rate of high height airstart, improves the safety and reliability of aircraft to a great extent.The program uses complete
Authority digital controller achieves aero-engine and i.e. puts out the experience starting airstart working method i.e. put, it is ensured that engine air
The success rate of middle starting.
But, the program is only applicable to aero-engine in the case of aircraft operating mode is all normal after accident extinguishing
Restarting, its work-based logic is for i.e. putting out i.e. point, it is therefore an objective to shortening the time of restarting after stopping working as far as possible, it does not has judgement and flies
Row device fault occur condition whether eliminate or operating mode residing for aircraft if appropriate for ignition trigger again, i.e. such scheme without
Method adapts to control with the unmanned vehicle startup recovering igniting after a failure.
Summary of the invention
For disadvantages described above or the Improvement requirement of prior art, the present invention provides a kind of unmanned vehicle electromotor aloft
Method for controlling automatic ignition, it is by the control strategy optimized, for awing breaking down at unmanned vehicle and stopping working
And after fault recovery, carry out ignition trigger electromotor again, thus realize after unmanned vehicle aloft loses ground station control
Recover again control or electromotor accident extinguishing aloft can automatically send ignition order when shutting down and be again started up, the party
Method can be applicable to the ignition trigger again after unmanned vehicle fault recovery, it is possible to effectively realizes the protection to aircraft, joint
About flight cost.
For achieving the above object, it is proposed, according to the invention, provide a kind of unmanned vehicle electromotor automatic ignition aloft to control
Method, it is adaptable to awing break down at unmanned vehicle and stop working and carry out ignition trigger again after fault recovery,
It is characterized in that, the method includes:
(11) detection ground control station is the most out of hand, or aircraft engine whether accident extinguishing is shut down；
(12) if ground control station is to lose aircraft control ability or the shutdown of aircraft engine accident extinguishing, then step is performed
Suddenly (13), if it is not, then return step (11)；
(13) communication link between detection unmanned vehicle and ground control station is the most normal, the most then perform step
(14), if it is not, then stop sending ignition order；
(14) whether detection engine operating condition information and aircraft flight state reach job requirement, the most then perform step
Suddenly (15), if it is not, then stop sending ignition order,
Wherein said engine operating condition information and aircraft flight state include that engine coolant temperature, aircraft flight are high
Degree and airborne accumulator electric-quantity；
(15) can detection detection electromotor air door steering wheel, throttle steering wheel, task steering wheel normally work, the most then perform
Ignition order, is again started up electromotor；If it is not, then stop sending ignition order.
As present invention further optimization, the job requirement of described engine coolant temperature is 60 DEG C to 80 DEG C.
As present invention further optimization, the job requirement of described on-board batteries voltage is greater than equal to 12V.
As present invention further optimization, the job requirement of described aircraft terrain clearance is greater than equal to 30m.
In general, method for controlling automatic ignition in the unmanned vehicle engine air of the present invention, unmanned including detecting
When aircraft returns to ground station control, real-time reception engine operating condition information and unmanned vehicle state of flight information are carried out point
Analysis judges, judges whether to send firing command to electromotor with this.By the contemplated above technical scheme of the present invention with existing
Technology is compared, and has the advantages that
(1) in the method for the present invention, aloft lose for unmanned vehicle recover again after ground station control to control or
Electromotor accident extinguishing aloft shuts down this situation, utilizes the control strategy optimized, it is possible to automatically send ignition order and carry out
Being again started up, the method can be applicable to the ignition trigger again after unmanned vehicle fault recovery, it is possible to effectively realizes flying
The protection of row device, saves flight cost；
(2), in the method for the present invention, it is provided with engine operating condition judgement, aircraft flight condition adjudgement, ground station control
Multiple decision stage such as link judgement, so that the accuracy rate that igniting is again started up greatly improves, and can protect well
Protect aircraft, and save flight cost；
(3) in the method for the present invention, by arranging engine operating condition information and the actual conditions of aircraft flight state, can
To better assure that the terms and conditions that aircraft engine automatic ignition is restarted so that unmanned vehicle awing occurs event
Hinder and stop working and after fault recovery, carry out the control of ignition trigger electromotor again more accurately effectively.
Accompanying drawing explanation
Fig. 1 is the configuration diagram of the method for controlling automatic ignition according to the embodiment of the present invention；
Fig. 2 is the flow chart of the method for controlling automatic ignition according to the embodiment of the present invention；
Fig. 3 is sentencing according to the engine operating condition in the method for controlling automatic ignition of the embodiment of the present invention and flight state
Disconnected flow chart；
Fig. 4 is to release condition adjudgement side according to the automatic defence program in the method for controlling automatic ignition of the embodiment of the present invention
Method flow chart；
In all of the figs, identical reference is used for representing identical element or structure, wherein: 1-ignition switch,
2-flying vehicles control module, 3-sensor, 4-ignition module, 5-signal generator, 6-electromotor.
Detailed description of the invention
In order to make the purpose of the present invention, technical scheme and advantage clearer, below in conjunction with drawings and Examples, right
The present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, and
It is not used in the restriction present invention.If additionally, technical characteristic involved in each embodiment of invention described below
The conflict of not constituting each other just can be mutually combined.
As it is shown in figure 1, automatic ignition system in the unmanned vehicle engine air of one embodiment of the invention, mainly comprise
Ignition switch 1, flying vehicles control module 2, ignition module 4, sensor 3, electromotor 6, signal generator 5 in five parts.
As in figure 2 it is shown, flying vehicles control personnel have only to click on the button ignition switch 1 on ground control station, just can enter
The ignition module 4 of aircraft, ignition module 4 initializes.
In this programme, unmanned vehicle ignition module includes engine operating condition judgement, aircraft flight condition adjudgement, ground
Control link of standing judges three phases.
Specifically, this method for controlling automatic ignition includes detecting when unmanned vehicle returns to ground station control, logical
Many real-time reception engine operating condition information and unmanned vehicle state of flight information are analyzed judging, send igniting to electromotor
Instruction, it specifically includes following steps:
(11) detection ground control station is the most out of hand, and aircraft engine whether shut down by accident extinguishing；
(12) if ground control station is to lose aircraft control ability or the shutdown of aircraft engine accident extinguishing, then step is performed
Suddenly (13), if it is not, then return step (11)；
(13) communication link between detection unmanned vehicle and ground control station is the most normal, the most then perform step
(14), if it is not, then stop sending ignition order；
(14) whether detection engine operating condition and aircraft flight state reach job requirement, the most then perform step
(15), if it is not, then stop sending ignition order；
By judge ground control station to the link of flying vehicles control program be normal after, by ground level sensor
Sense aircraft terrain clearance, on-board batteries voltage sensor senses on-board batteries voltage, engine coolant temperature sensor is examined
Survey engine coolant temperature, collect data.
Wherein, engine operating condition information and aircraft flight state mainly include engine coolant temperature, aircraft flight
Highly, airborne accumulator electric-quantity etc..As it is shown on figure 3, engine operating condition judges and the step of aircraft flight condition adjudgement is concrete
Including following process:
(140) gear detects that aircraft overhead height >=30m, on-board batteries voltage >=12V, engine coolant temperature exist
Time between 60 DEG C to 80 DEG C, enter the next stage；
(141) when not reaching condition and requiring, for ensuring safety, flying vehicles control module stops lighting a fire to engine start
Instruction, returns data collection phase.
Engine operating condition information and aircraft flight state include engine coolant temperature, on-board batteries voltage, aircraft
Terrain clearance etc..The too low work efficiency that can reduce electromotor of engine coolant temperature, is unfavorable for that aircraft is drawn high rotating speed and completed
Climbing action, water temperature over-high then can affect engine cool；If aircraft terrain clearance≤30m, aircraft can not be the completeest
Become flight control action；If on-board voltage≤12V, then do not reach aircraft engine ignition voltage.
Engine operating condition information and aircraft flight status information being judged, if meeting Rule of judgment, preserving data
Entering the next stage, if not meeting judgement, the information of returning to judges the stage.
(15) can detection detection electromotor air door steering wheel, throttle steering wheel, task steering wheel normally work, if can, then perform
Ignition order, if it is not, then stop sending ignition order.
As shown in Figure 4, by engine operating condition with after the aircraft flight condition adjudgement stage, enter and automatically protect releasing
The judgement stage:
(150) defence program releasing detection-phase includes that the air door steering wheel of aircraft, throttle steering wheel, task steering wheel are automatically
No work
(151) normal, if normally, then flying vehicles control module sends firing command to electromotor, if abnormal, then returns
Automatically defence program releases detection-phase.
As it will be easily appreciated by one skilled in the art that and the foregoing is only presently preferred embodiments of the present invention, not in order to
Limit the present invention, all any amendment, equivalent and improvement etc. made within the spirit and principles in the present invention, all should comprise
Within protection scope of the present invention.
Claims (4)
1. a unmanned vehicle electromotor method for controlling automatic ignition aloft, it is adaptable to awing send out at unmanned vehicle
Give birth to fault and stop working and after fault recovery, carry out ignition trigger again, it is characterised in that the method includes:
(11) detection ground control station is the most out of hand, or aircraft engine whether accident extinguishing is shut down；
(12) if ground control station is to lose aircraft control ability or the shutdown of aircraft engine accident extinguishing, then step is performed
(13), if it is not, then return step (11)；
(13) communication link between detection unmanned vehicle and ground control station is the most normal, the most then perform step (14),
If it is not, then stop sending ignition order；
(14) whether detection engine operating condition information and aircraft flight state reach job requirement, the most then perform step
(15), if it is not, then stop sending ignition order,
Wherein said engine operating condition information and aircraft flight state include engine coolant temperature, aircraft altitude with
And airborne accumulator electric-quantity；
(15) can detection detection electromotor air door steering wheel, throttle steering wheel, task steering wheel normally work, the most then perform igniting
Order, is again started up electromotor；If it is not, then stop sending ignition order.
A kind of unmanned vehicle electromotor method for controlling automatic ignition aloft the most according to claim 1, wherein, described
The job requirement of engine coolant temperature is 60 DEG C to 80 DEG C.
A kind of unmanned vehicle electromotor method for controlling automatic ignition aloft the most according to claim 1 and 2, wherein,
The job requirement of described on-board batteries voltage is greater than equal to 12V.
4. according to the electromotor automatic ignition controlling party aloft of a kind of unmanned vehicle according to any one of claim 1-3
Method, wherein, the job requirement of described aircraft terrain clearance is greater than equal to 30m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610366869.7A CN106043715B (en) | 2016-05-27 | 2016-05-27 | A kind of aerial method for controlling automatic ignition of unmanned vehicle engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610366869.7A CN106043715B (en) | 2016-05-27 | 2016-05-27 | A kind of aerial method for controlling automatic ignition of unmanned vehicle engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106043715A true CN106043715A (en) | 2016-10-26 |
| CN106043715B CN106043715B (en) | 2018-03-27 |
Family
ID=57175685
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610366869.7A Active CN106043715B (en) | 2016-05-27 | 2016-05-27 | A kind of aerial method for controlling automatic ignition of unmanned vehicle engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106043715B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109703766A (en) * | 2018-12-14 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of remote starting system of piston engine unmanned plane |
| CN111099024A (en) * | 2018-10-29 | 2020-05-05 | 中科灵动航空科技成都有限公司 | Ignition restarting method, system and memory for oil-electricity hybrid power rotor unmanned aerial vehicle |
| CN111746806A (en) * | 2020-06-15 | 2020-10-09 | 西安爱生技术集团公司 | A kind of unmanned aerial vehicle inspiration system and integrated control method |
| CN111855220A (en) * | 2020-06-30 | 2020-10-30 | 成都飞机工业（集团）有限责任公司 | Method for verifying inertia starting capability of turbofan engines installed side by side |
| CN112832910A (en) * | 2020-11-04 | 2021-05-25 | 北京动力机械研究所 | Method for identifying air flameout and secondary starting success of turbofan engine |
| CN114962007A (en) * | 2021-02-23 | 2022-08-30 | 昆明桑达科技有限公司 | Emergent starting circuit of unmanned aerial vehicle engine |
| CN116398300A (en) * | 2023-04-12 | 2023-07-07 | 中国航发湖南动力机械研究所 | Control method and system for air stopping and restarting of turboshaft engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102072063A (en) * | 2011-01-04 | 2011-05-25 | 北京航空航天大学 | Encounter-starting airstart system of aircraft engine |
| US20140249694A1 (en) * | 2011-06-29 | 2014-09-04 | Geoffrey Paul Cathcart | Method of controlling operation of an unmanned aerial vehicle |
| CN204776041U (en) * | 2015-06-26 | 2015-11-18 | 周勤 | Aerial secondary starting drive of unmanned aerial vehicle engine |
| WO2015192177A1 (en) * | 2014-06-18 | 2015-12-23 | Orbital Australia Pty Limited | Ignition control and system for an engine of an unmanned aerial vehicle (uav) |
| CN105221318A (en) * | 2015-10-23 | 2016-01-06 | 四川测绘地理信息局测绘技术服务中心 | A kind of unmanned plane with remote activating device |
| CN205150244U (en) * | 2015-11-09 | 2016-04-13 | 襄阳宏伟航空器有限责任公司 | Unmanned aerial vehicle is scattered to intelligence |
-
2016
- 2016-05-27 CN CN201610366869.7A patent/CN106043715B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102072063A (en) * | 2011-01-04 | 2011-05-25 | 北京航空航天大学 | Encounter-starting airstart system of aircraft engine |
| US20140249694A1 (en) * | 2011-06-29 | 2014-09-04 | Geoffrey Paul Cathcart | Method of controlling operation of an unmanned aerial vehicle |
| WO2015192177A1 (en) * | 2014-06-18 | 2015-12-23 | Orbital Australia Pty Limited | Ignition control and system for an engine of an unmanned aerial vehicle (uav) |
| CN204776041U (en) * | 2015-06-26 | 2015-11-18 | 周勤 | Aerial secondary starting drive of unmanned aerial vehicle engine |
| CN105221318A (en) * | 2015-10-23 | 2016-01-06 | 四川测绘地理信息局测绘技术服务中心 | A kind of unmanned plane with remote activating device |
| CN205150244U (en) * | 2015-11-09 | 2016-04-13 | 襄阳宏伟航空器有限责任公司 | Unmanned aerial vehicle is scattered to intelligence |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111099024A (en) * | 2018-10-29 | 2020-05-05 | 中科灵动航空科技成都有限公司 | Ignition restarting method, system and memory for oil-electricity hybrid power rotor unmanned aerial vehicle |
| CN109703766A (en) * | 2018-12-14 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of remote starting system of piston engine unmanned plane |
| CN111746806A (en) * | 2020-06-15 | 2020-10-09 | 西安爱生技术集团公司 | A kind of unmanned aerial vehicle inspiration system and integrated control method |
| CN111746806B (en) * | 2020-06-15 | 2023-06-23 | 西安爱生技术集团公司 | Unmanned aerial vehicle heuristic system and integrated control method |
| CN111855220A (en) * | 2020-06-30 | 2020-10-30 | 成都飞机工业（集团）有限责任公司 | Method for verifying inertia starting capability of turbofan engines installed side by side |
| CN112832910A (en) * | 2020-11-04 | 2021-05-25 | 北京动力机械研究所 | Method for identifying air flameout and secondary starting success of turbofan engine |
| CN114962007A (en) * | 2021-02-23 | 2022-08-30 | 昆明桑达科技有限公司 | Emergent starting circuit of unmanned aerial vehicle engine |
| CN116398300A (en) * | 2023-04-12 | 2023-07-07 | 中国航发湖南动力机械研究所 | Control method and system for air stopping and restarting of turboshaft engine |
| CN116398300B (en) * | 2023-04-12 | 2024-08-02 | 中国航发湖南动力机械研究所 | Control method and system for air stopping and restarting of turboshaft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043715B (en) | 2018-03-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106043715A (en) | In-flight auto-ignition control method of engine of unmanned aerial vehicle | |
| US9551990B2 (en) | Unmanned aerial vehicle landing system | |
| EP3095705B1 (en) | System and method of flight termination for air vehicles | |
| CN100568137C (en) | A Judgment and Processing Method for UAV Remote Control Link Interruption | |
| US8504222B2 (en) | Emergency descent intervention system | |
| KR20140038495A (en) | The rotor blade drone safety landing pack | |
| CN203876988U (en) | Protection and control system of aircraft and aircraft | |
| CN205256682U (en) | Control system is retrieved in unmanned aerial vehicle parachuting | |
| CN111874256A (en) | Fault emergency treatment method and device for solar unmanned aerial vehicle | |
| CN102464108A (en) | Engine failure treating method for unmanned aerial vehicle | |
| CN103543652A (en) | Monitoring and controlling unit of engine of unmanned aerial vehicle | |
| CN113412217A (en) | Piloting device designed to be integrated into an existing aircraft | |
| CN109471453A (en) | UAV relay station cruise system | |
| CN113655812A (en) | Landing method for flameout of aerial engine of large-scale freight unmanned aerial vehicle | |
| CN112618992A (en) | Low-cost suicide type networking fire extinguishing method and unmanned aerial vehicle system | |
| CN110535232A (en) | A kind of high reliability captive unmanned aerial vehicle onboard power control system | |
| US20240152162A1 (en) | Control method and device of unmanned aerial vehicle system, unmanned aerial vehicle system and storage medium | |
| CN117151432B (en) | Unmanned aerial vehicle automatic airport allocation method for risk avoidance mode | |
| Luo et al. | An internet of things (lot) perspective of understanding the boeing 737 max crash | |
| CN105775142A (en) | Autonomous parachute opening safety protection method and system for small aircraft | |
| O'Donnell | Investigation of UAS accidents and incidents | |
| CN109573024B (en) | Unmanned aerial vehicle emergency recovery method based on power supply management equipment | |
| CN116395143A (en) | Pilot abnormal operation monitoring and emergency treatment method | |
| CN212829092U (en) | Intelligent standby parachute system for safe emergency slow landing of civil unmanned aerial vehicle | |
| CN103744285A (en) | Ground acquisition plane data backup system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |