CN110398977A - A kind of unmanned plane aileron deceleration system and method - Google Patents
A kind of unmanned plane aileron deceleration system and method Download PDFInfo
- Publication number
- CN110398977A CN110398977A CN201810379589.9A CN201810379589A CN110398977A CN 110398977 A CN110398977 A CN 110398977A CN 201810379589 A CN201810379589 A CN 201810379589A CN 110398977 A CN110398977 A CN 110398977A
- Authority
- CN
- China
- Prior art keywords
- aileron
- instruction
- unmanned plane
- drift angle
- deceleration
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 19
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 25
- 238000013467 fragmentation Methods 0.000 claims abstract description 7
- 238000006062 fragmentation reaction Methods 0.000 claims abstract description 7
- 230000000979 retarding effect Effects 0.000 claims description 9
- 239000000725 suspension Substances 0.000 claims description 4
- 230000005283 ground state Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 5
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- 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
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
-
- 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
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
The present invention discloses a kind of unmanned plane aileron deceleration system and method, after unmanned plane enters the deceleration sliding race stage, issues the instruction of aileron drift angle by aileron instruction generator；The aileron movement instruction that the instruction of aileron drift angle has coupled the aileron movement instruction of aileron deceleration system and flight control system control UAV Attitude issues；Including following two classes situation: normal condition: instruction that aileron instruction generator sends out aileron drift angle preset；Case of emergency: aileron instruction generator sends out the instruction of aileron sail angle；After Aileron control system receives the instruction of aileron drift angle, control aileron movement to designated state.Preset aileron drift angle instruction are as follows: the different aileron drift angle of different speed fragmentation values.The present invention is suitable for various unmanned aerial vehicle platform, and versatility is stronger, and programmed logic is clear, strong operability, it is easy to accomplish, at low cost, slowing effect is significant, can effectively reduce sliding race time and ground run distance, reduce risk.
Description
Technical field
The invention belongs to the methods of flying vehicles control technical field, especially aircraft down.
Background technique
In the prior art, the Landing Control mode of most of unmanned plane is, by flight control computer after UAV Landing ground connection
Autonomous control is completed to slow down and be stopped；The deceleration measure or deceleration system that unmanned plane generallys use at present are following equipment or following
The combination of equipment: drag parachute, brake, flap；Current deceleration system, deceleration measure is simple, remaining is less, in a certain deceleration
Its slowing effect will be greatly reduced when equipment cannot use, to increase deceleration time, prolonged deceleration distance, influence peace of landing
Entirely；Aileron deceleration system increases retarding device on the basis of existing conventional deceleration system, improves unmanned plane slowing down power(SDP), increases
Acceleration and deceleration measure remaining improves landing safety；The system applies also for unmanned plane suspension takeoff procedure simultaneously, increases pneumatic
Resistance effectively improves the slowing down power(SDP) of unmanned plane, ensures that unmanned plane stops safety of taking off.In addition, aileron deceleration system is directed to nothing
Man-machine landing mission or the unusual slowdown situation for stopping to occur in take-off process can carry out emergency maneuver, by aileron control surface deflection
To maximum rating, maximum aerodynamic drag is obtained with this, the increasing for sufficiently excavating aileron hinders slowing down power(SDP), reduces in case of emergency
Risk.Currently, not yet occurring alighting run using aileron deceleration system the case of deceleration, also have no about aileron reduction train
The report for design of uniting.
Summary of the invention
The task of the present invention is the blank for developing field for current aileron deceleration system, by the process of alightinging run or
Stop to use unmanned plane aileron in take-off process, enrich unmanned plane deceleration means, improve slowing down power(SDP), increases more than slowing down power(SDP)
Degree improves the safety under unmanned plane deceleration abnormal conditions.
The technical solution of the present invention is as follows:
A kind of unmanned plane aileron deceleration system, which is characterized in that including aileron instruction generator, aileron deceleration system, flight control
System processed, sensing system, Aileron control system；Wherein,
Aileron control system realizes aileron movement according to aileron drift angle instruction control steering engine；
Sensing system detects the status information of unmanned plane；
Flight control system issues control unmanned aerial vehicle (UAV) control instruction according to the status information of sensing system；
Aileron deceleration system issues aileron movement instruction after unmanned plane ground connection, to realize that increasing resistance slows down；
Aileron instruction generator issues the instruction of aileron drift angle, and the aileron movement that the instruction of aileron drift angle has coupled aileron deceleration system refers to
It enables and the aileron movement of flight control system control UAV Attitude sending instructs.
A kind of unmanned plane aileron retarding method, step are as follows:
S1 flight control system judges whether UAV system enters the sliding race stage of slowing down:
S11 judges whether unmanned plane is grounded according to the information that sensing system provides, and thereby determines that unmanned plane ground state, accordingly
Decision instruction judges whether unmanned plane enters and alightings run the stage；If carrying out subsequent operation, otherwise into the stage of alightinging run
Rejudge whether unmanned plane enters the sliding race stage of slowing down；
S12 judges whether unmanned plane enters the sliding race stage of slowing down according to whether flight control system issues suspension and take off to instruct；If
Into the stage of alightinging run, then subsequent operation is carried out, otherwise rejudges whether unmanned plane enters the sliding race stage of slowing down；
After S2 unmanned plane enters the deceleration sliding race stage, the instruction of aileron drift angle is issued by aileron instruction generator；The instruction of aileron drift angle
The aileron movement that the aileron movement instruction and flight control system control UAV Attitude for having coupled aileron deceleration system issue refers to
It enables；Including following two classes situation:
S21 normal condition: instruction that aileron instruction generator sends out aileron drift angle preset；
S22 case of emergency: aileron instruction generator sends out the instruction of aileron sail angle；
After S3 Aileron control system receives aileron movement instruction, control aileron movement to designated state.
Instruction that aileron instruction generator described in the step S21 sends out aileron drift angle preset are as follows: the speed of unmanned plane is set
Spend number of stages n and speed fragmentation value V1、V2……Vn, value is sequentially reduced, and corresponding, different aileron drift angles is arranged with this.
The preset aileron drift angle instruction are as follows: as the speed of unmanned plane reduces, aileron drift angle is gradually increased.
Case of emergency is in the step S22, when the failure of the deceleration systems such as unmanned plane drag parachute, brake, flap, flies
After row control system determines unmanned plane deceleration exception, aileron instruction generator directly issues the instruction of aileron sail angle.
The present invention is suitable for various unmanned aerial vehicle platform, and versatility is stronger, and programmed logic is clear, strong operability, it is easy to accomplish,
At low cost, slowing effect is significant, can effectively reduce sliding race time and ground run distance, reduce risk.
Detailed description of the invention
Fig. 1 is present system flow chart.
Fig. 2 is the flow chart of aileron instruction generator in deceleration system under normal circumstances.
Fig. 3 is aileron instruction generator coupling flow chart.
Specific embodiment
In order to further illustrate above-mentioned implementation, present invention will be further explained below with reference to the attached drawings and examples.
Embodiment 1
A kind of unmanned plane aileron deceleration system, including aileron instruction generator, aileron deceleration system, flight control system, sensing
Device system, Aileron control system；Wherein, Aileron control system realizes aileron movement according to instruction control steering engine；Sensor system
System, detects the status information of unmanned plane；Flight control system issues control unmanned plane control according to the status information of sensing system
System instruction；Aileron deceleration system issues aileron movement instruction after unmanned plane ground connection, to realize that increasing resistance slows down；Aileron instruction life
It grows up to be a useful person and issues the instruction of aileron drift angle, the instruction of aileron drift angle has coupled aileron movement instruction and the flight control system of aileron deceleration system
The aileron movement instruction that system control UAV Attitude issues.
Embodiment 2
A kind of unmanned plane aileron retarding method, step are as follows:
S1 flight control system judges whether UAV system enters the sliding race stage of slowing down:
S11 judges whether unmanned plane is grounded according to the information that sensing system provides, and thereby determines that unmanned plane ground state, accordingly
Decision instruction judges whether unmanned plane enters and alightings run the stage；If carrying out subsequent operation, otherwise into the stage of alightinging run
Rejudge whether unmanned plane enters the sliding race stage of slowing down；
S12 judges whether unmanned plane enters the sliding race stage of slowing down according to whether flight control system issues suspension and take off to instruct；If
Into the stage of alightinging run, then subsequent operation is carried out, otherwise rejudges whether unmanned plane enters the sliding race stage of slowing down；
After S2 unmanned plane enters the deceleration sliding race stage, the instruction of aileron drift angle is issued by aileron instruction generator；The instruction of aileron drift angle
The aileron movement that the aileron movement instruction and flight control system control UAV Attitude for having coupled aileron deceleration system issue refers to
It enables；Including following two classes situation:
S21 normal condition: instruction that aileron instruction generator sends out aileron drift angle preset；
S22 case of emergency: aileron instruction generator sends out the instruction of aileron sail angle；
After S3 Aileron control system receives aileron movement instruction, control aileron movement to designated state.
Embodiment 3
A kind of unmanned plane aileron retarding method, after flight control system judges that UAV system enters the deceleration sliding race stage, aileron
Instruction generator issues the instruction of aileron drift angle, and aileron instruction generator send out preset aileron drift angle and instructed are as follows: unmanned plane is arranged
Speed stage number n and corresponding speed fragmentation value V1、V2……Vn, velocity amplitude is sequentially reduced, and different speed fragmentation values is corresponding not
Same aileron drift angle；After Aileron control system receives aileron movement instruction, control aileron movement to designated state.One kind is default
Aileron drift angle instruction selection are as follows: with unmanned plane speed reduce, aileron drift angle is gradually increased.
Embodiment 3
A kind of unmanned plane aileron retarding method, after flight control system judges that UAV system enters the deceleration sliding race stage, emergency
Situation is, when the failure of the deceleration systems such as unmanned plane drag parachute, brake, flap, flight control system determines that unmanned plane slows down
After exception, aileron instruction generator directly issues the instruction of aileron sail angle；Aileron control system receives aileron movement instruction
Afterwards, aileron movement is controlled to designated state.
Embodiment 4
Fig. 1 describes each information conveying flow relationship of the present invention, controls computer using decision instruction as foundation, is instructed and given birth to aileron
As control means are implemented, it is finally reached aileron movement, increase aerodynamic drag, the purpose for improving slowing down power(SDP).Wherein:
Decision instruction includes two parts:
A) ground signalling, unmanned plane is during touchdown, the unmanned plane main wheel wheel load that is collected according to sensing system
Data or main wheel wheel speed data judge ground contact state, while can also be several after being transferred to course alignment stage according to aircraft
Second, judge whether aircraft is grounded on this basis.If aircraft meets this condition, then it can determine that aircraft is grounded, it can be with
Execute down-stream；As if not satisfied, if exit the program.
B) stop instruction of taking off, unmanned plane is in taxiing procedures, and either unmanned plane lets inventory fly away according to minimum and independently determines
Fixed to stop to take off, also or manually disposition stops to take off, after control computer, which issues, stops to take off instruction, i.e., executable aileron
Increase resistance deceleration program.
Aileron instruction generator: when upper one layer of decision instruction is true, aileron instruction generator can be controlled according to setting
Strategy, while the aileron instruction for coupling control UAV Attitude generates aileron control instruction manipulation aileron.
A) under normal circumstances, unmanned plane drag parachute, brake, flap stabilization working properly, aileron instruction generator is by pre-
If program issues the instruction of aileron drift angle, drift angle degree is determined by steering engine performance and slowing effect synthesis.
B) under case of emergency, when the failure of the deceleration systems such as unmanned plane drag parachute, brake, flap, flight control system
After determining unmanned plane deceleration exception, aileron instruction generator directly issues the instruction of aileron sail angle, by unmanned plane aileron movement
Limiting value determines.
Aileron control system, the system realize aileron movement according to instruction control steering engine, achieve the purpose that increasing resistance slows down.
Embodiment 5
Fig. 2 gives the process instruction figure of normal condition lower aileron instruction generator.The aileron instruction generator is passed according to table speed
Sensor information Vb, corresponding aileron drift angle, which is generated, according to the different tables fast stage instructs.Based on steering engine for unmanned plane performance and deceleration
Reasonable table speed number of stages n and table speed fragmentation value V is arranged in effect1、V2……Vn(value is sequentially reduced) thus generates different pairs
Wing drift angle reaches as table speed reduces, and the effect that aileron drift angle is gradually increased realizes the maximized target of aerodynamic drag.
The table speed V collected with table speed sensorbReduce, aileron instruction generator receives table speed information Vb, comparison
VbWith table speed fragmentation value Vi(i=1、2……n)。
If Vb<ViAnd continuous 5 clap satisfaction, then judge V into next stageb<Vi+1;
If being unsatisfactory for above-mentioned condition, corresponding aileron drift angle instruction is generated；
And so on, aileron instruction generator generates the corresponding aileron drift angle instruction of different tables fast stage, different tables fast stage pair
The aileron drift angle value answered can refer to the division rule of following table.
The aileron drift angle value in different tables fast stage
| The table speed stage | Aileron drift angle δ |
| Vn-1 <Vb<Vn | δmax(maximum aileron drift angle) |
| … | … |
| Vi-1 <Vb<Vi | i*δmax /n |
| … | … |
| Vb<V1 | δmax/n |
Embodiment 6
Fig. 3 gives aileron instruction generator coupling flow chart.After unmanned plane, which enters deceleration, slides the race stage, according to nobody
The flight parameter data of machine Real-time Feedback, aileron instruction generator couple the aileron movement signal that aileron deceleration system generates and fly
The aileron movement signal for controlling computer control UAV Attitude ultimately generates the instruction of aileron drift angle, manipulates aileron movement, realizes nothing
Man-machine deceleration.
Claims (5)
1. a kind of unmanned plane aileron deceleration system, which is characterized in that including aileron instruction generator, aileron deceleration system, flight
Control system, sensing system, Aileron control system；Wherein,
Aileron control system realizes aileron movement according to aileron drift angle instruction control steering engine；
Sensing system detects the status information of unmanned plane；
Flight control system issues the instruction of control unmanned plane according to the status information of sensing system；
Aileron deceleration system issues aileron movement instruction after unmanned plane ground connection, to realize that increasing resistance slows down；
Aileron instruction generator issues the instruction of aileron drift angle, and the aileron movement that the instruction of aileron drift angle has coupled aileron deceleration system refers to
It enables and the aileron movement of flight control system control UAV Attitude sending instructs.
2. a kind of unmanned plane aileron retarding method, step are as follows:
S1 flight control system judges whether UAV system enters the sliding race stage of slowing down:
S11 judges whether unmanned plane is grounded according to the information that sensing system provides, and thereby determines that unmanned plane ground state, accordingly
Decision instruction judges whether unmanned plane enters and alightings run the stage；If carrying out subsequent operation, otherwise into the stage of alightinging run
Rejudge whether unmanned plane enters the sliding race stage of slowing down；
S12 judges whether unmanned plane enters the sliding race stage of slowing down according to whether flight control system issues suspension and take off to instruct；If
Into the stage of alightinging run, then subsequent operation is carried out, otherwise rejudges whether unmanned plane enters the sliding race stage of slowing down；
After S2 unmanned plane enters the deceleration sliding race stage, the instruction of aileron drift angle is issued by aileron instruction generator；The instruction of aileron drift angle
The aileron movement that the aileron movement instruction and flight control system control UAV Attitude for having coupled aileron deceleration system issue refers to
It enables；Including following two classes situation:
S21 normal condition: instruction that aileron instruction generator sends out aileron drift angle preset；
S22 case of emergency: aileron instruction generator sends out the instruction of aileron sail angle；
After S3 Aileron control system receives the instruction of aileron drift angle, control aileron movement to designated state.
3. a kind of unmanned plane aileron retarding method according to claim 2, which is characterized in that aileron described in step S21
Instruction that instruction generator sends out aileron drift angle preset are as follows: the speed stage number n and speed fragmentation value V of unmanned plane are set1、V2……
Vn, value is sequentially reduced, and corresponding, different aileron drift angles is arranged with this.
4. a kind of unmanned plane aileron retarding method according to claim 3, which is characterized in that the preset aileron drift angle
Instruction are as follows: as the speed of unmanned plane reduces, aileron drift angle is gradually increased.
5. a kind of unmanned plane aileron retarding method according to claim 2, which is characterized in that meet an urgent need in the step S22
Situation is, when the failure of the deceleration systems such as unmanned plane drag parachute, brake, flap, flight control system determines that unmanned plane slows down
After exception, aileron instruction generator directly issues the instruction of aileron sail angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810379589.9A CN110398977A (en) | 2018-04-25 | 2018-04-25 | A kind of unmanned plane aileron deceleration system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810379589.9A CN110398977A (en) | 2018-04-25 | 2018-04-25 | A kind of unmanned plane aileron deceleration system and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110398977A true CN110398977A (en) | 2019-11-01 |
Family
ID=68319763
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810379589.9A Pending CN110398977A (en) | 2018-04-25 | 2018-04-25 | A kind of unmanned plane aileron deceleration system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110398977A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113204186A (en) * | 2021-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Safe power supply method for throwing of unmanned aerial vehicle drag parachute |
| CN114560095A (en) * | 2022-03-18 | 2022-05-31 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle landing method and device |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101678894A (en) * | 2007-06-15 | 2010-03-24 | 波音公司 | The automatic resistance function that is used for slideway control |
| CN102592007A (en) * | 2011-12-30 | 2012-07-18 | 成都飞机工业（集团）有限责任公司 | Method for modeling unmanned aerial vehicle object model for parameter adjustment of flight control law design |
| US20150102166A1 (en) * | 2013-09-24 | 2015-04-16 | The Boeing Company | System and method for reducing the stopping distance of an aircraft |
| US20160031554A1 (en) * | 2014-07-30 | 2016-02-04 | Siniger LLC | Control system for an aircraft |
| CN105786009A (en) * | 2016-04-07 | 2016-07-20 | 中国航空工业集团公司西安飞机设计研究所 | Flight control method in airplane asymmetric mounting mode |
| CN105786020A (en) * | 2016-04-28 | 2016-07-20 | 深圳飞马机器人科技有限公司 | Short-distance slide landing method of unmanned aerial vehicle |
| CN106444793A (en) * | 2016-08-31 | 2017-02-22 | 北京控制工程研究所 | RLV auto-landing segment speed control method based on nominal speed compensation idea |
| CN106542083A (en) * | 2016-11-25 | 2017-03-29 | 北京理工大学 | A kind of SUAV is slided and runs augmentation control method |
| CN106628163A (en) * | 2017-01-13 | 2017-05-10 | 厦门大学 | Supersonic unmanned combat air vehicle capable of achieving large-resistance deceleration and vertical take-off and landing |
| CN106697263A (en) * | 2016-12-28 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Rolling aileron reversal control method |
| CN106741954A (en) * | 2017-03-10 | 2017-05-31 | 佛山市神风航空科技有限公司 | The landing-gear and its mode of a kind of aircraft |
| CN106864730A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业第六八研究所 | A kind of unpowered vehicle speed accurate tracking control method |
| CN107264813A (en) * | 2017-05-24 | 2017-10-20 | 南京理工大学 | A kind of tailstock vertical takeoff and landing vehicle flight control system |
-
2018
- 2018-04-25 CN CN201810379589.9A patent/CN110398977A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101678894A (en) * | 2007-06-15 | 2010-03-24 | 波音公司 | The automatic resistance function that is used for slideway control |
| CN102592007A (en) * | 2011-12-30 | 2012-07-18 | 成都飞机工业（集团）有限责任公司 | Method for modeling unmanned aerial vehicle object model for parameter adjustment of flight control law design |
| US20150102166A1 (en) * | 2013-09-24 | 2015-04-16 | The Boeing Company | System and method for reducing the stopping distance of an aircraft |
| US20160031554A1 (en) * | 2014-07-30 | 2016-02-04 | Siniger LLC | Control system for an aircraft |
| CN106864730A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业第六八研究所 | A kind of unpowered vehicle speed accurate tracking control method |
| CN105786009A (en) * | 2016-04-07 | 2016-07-20 | 中国航空工业集团公司西安飞机设计研究所 | Flight control method in airplane asymmetric mounting mode |
| CN105786020A (en) * | 2016-04-28 | 2016-07-20 | 深圳飞马机器人科技有限公司 | Short-distance slide landing method of unmanned aerial vehicle |
| CN106444793A (en) * | 2016-08-31 | 2017-02-22 | 北京控制工程研究所 | RLV auto-landing segment speed control method based on nominal speed compensation idea |
| CN106542083A (en) * | 2016-11-25 | 2017-03-29 | 北京理工大学 | A kind of SUAV is slided and runs augmentation control method |
| CN106697263A (en) * | 2016-12-28 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Rolling aileron reversal control method |
| CN106628163A (en) * | 2017-01-13 | 2017-05-10 | 厦门大学 | Supersonic unmanned combat air vehicle capable of achieving large-resistance deceleration and vertical take-off and landing |
| CN106741954A (en) * | 2017-03-10 | 2017-05-31 | 佛山市神风航空科技有限公司 | The landing-gear and its mode of a kind of aircraft |
| CN107264813A (en) * | 2017-05-24 | 2017-10-20 | 南京理工大学 | A kind of tailstock vertical takeoff and landing vehicle flight control system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113204186A (en) * | 2021-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Safe power supply method for throwing of unmanned aerial vehicle drag parachute |
| CN113204186B (en) * | 2021-03-31 | 2022-08-12 | 成都飞机工业（集团）有限责任公司 | Safe power supply method for throwing of unmanned aerial vehicle drag parachute |
| CN114560095A (en) * | 2022-03-18 | 2022-05-31 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle landing method and device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3136197B1 (en) | Aircraft stall protection system | |
| CN109917812B (en) | High-altitude high-speed unmanned aerial vehicle landing state control method | |
| US9043050B2 (en) | Programmable reverse thrust detent system and method | |
| CA2785692C (en) | Control system of aircraft, method for controlling aircraft, and aircraft | |
| US9405295B2 (en) | Flight control system | |
| CN107870629B (en) | Enhanced takeoff system | |
| EP3444692A1 (en) | Methods and systems for intelligent predictive aircraft takeoff rejection decision making | |
| EP3037345B1 (en) | A method of automatically controlling the descent phase of an aircraft using aircraft avionics executing a descent algorithm | |
| US9272770B2 (en) | Method and apparatus for improved lateral control of an aircraft on the ground during takeoff | |
| JPH04331698A (en) | Method of aircraft landing control | |
| EP3159767B1 (en) | Zoom climb prevention system for enhanced performance | |
| US9815561B2 (en) | Device for regulating the speed of rotation of a rotorcraft rotor, a rotorcraft fitted with such a device, and an associated regulation method | |
| CN110398977A (en) | A kind of unmanned plane aileron deceleration system and method | |
| US7850125B2 (en) | Method and device for reducing the wake vortices of an aircraft in the approach/landing phase | |
| EP3450304B1 (en) | Automatic command for lift control devices | |
| EP3929073A1 (en) | Longitudinal trim control movement during takeoff rotation | |
| CN113050690A (en) | Airplane ground comprehensive control system and control method | |
| JP2024028203A (en) | Method and apparatus for controlling aircraft ground maneuvers | |
| US20180134371A1 (en) | Air brake system for aircraft | |
| CN108033025B (en) | Thrust control system of aircraft engine | |
| Ohme | A model-based approach to aircraft takeoff and landing performance assessment | |
| CN115959286A (en) | Civil aircraft landing automatic brake control system and control method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191101 |