CN105857581A - Airplane cockpit control system and method - Google Patents
Airplane cockpit control system and method Download PDFInfo
- Publication number
- CN105857581A CN105857581A CN201610339257.9A CN201610339257A CN105857581A CN 105857581 A CN105857581 A CN 105857581A CN 201610339257 A CN201610339257 A CN 201610339257A CN 105857581 A CN105857581 A CN 105857581A
- Authority
- CN
- China
- Prior art keywords
- optical displacement
- pedals
- remaining optical
- displacement sensor
- side lever
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention relates to the technical field of flying control, and provides an airplane cockpit control system. The system comprises side rods, rudder pedals and an air brake handle. Each side rod is connected with four dual-redundancy optical displacement sensors, each dual-redundancy optical displacement sensor is connected with two ACEs (data concentrators), and each side rod is connected with four ACEs through eight optical cables. Each rudder pedal is connected with one dual-redundancy optical displacement sensor, each dual-redundancy optical displacement sensor is connected with two ACEs, and each rudder pedal is connected with two ACEs through two optical cables. The air brake handle is connected with two dual-redundancy optical displacement sensors, each dual-redundancy optical displacement sensor is connected with two ACEs, and the air brake handle is connected with four ACEs through four optical cables. The airplane cockpit control system has the advantages that system deployment is simple, efficient and modular, and integration is easy; redundancy configuration is reasonable, and the number of the cables is small; the optical displacement sensors are used, so that signal collecting real-time performance is better, and anti-interference performance is higher.
Description
Technical field
The present invention relates to aircraft flight and control technical field, particularly to a kind of aircraft cockpit steerable system and manipulation
Method.
Background technology
The flight control system of aircraft typically by driving cabin steerable system, fly to control electronics and actuator and form, driving cabin
Steerable system mainly realizes the control command input of driver, flies to control electronics and mainly realizes the instruction according to driver in fact
The resolving of existing control law, and export to actuator execution；Actuator system carries out aircraft according to the instruction flying to control electronics
The deflection of rudder face, it is achieved the closed loop control of rudder face.
Traditional driving cabin steerable system is made up of side lever, pedal, flap handle, driver-operated input by
The RVDT sensor installing each operating mechanism realizes, and flying to control electronics provides the resolving of control signal, it is provided that drive
Member handles the quantized data of input.
Fig. 1 is traditional driving cabin steerable system structural representation, and the problem that this implementation is brought is system collection
Become complexity: 1, pilot control component sensors is by flying control electronic power, fly to control electronics and reoffer the solution of signal
Calculating, system crosslinking is strong, and coupling is strong, and integrated difficulty is big.2, RVDT sensor complex, each sensor
It is made up of 5 lines, and in order to ensure remaining, each operating mechanism is equipped with multiple RVDT sensor, band
Having carried out the complexity realized, wiring quantity increases, and weight increases.
In prior art with the application closest to technical scheme as follows:
As in figure 2 it is shown, as a example by side lever, single side lever uses 8 single remaining RVDT sensors, each two
RVDT completes the collection of pitching and rolling signal, a corresponding data concentrator or flight control computer or actuator control
Electronics processed (ACE), each RVDT is made up of 5 lines, totally 40 lines, two RVDT inside side lever
Integrated at side lever end, formed 4 strands totally 20 lines cross-link with data concentrator.
Single pedals use 2 single remaining RVDT sensors, the corresponding data set of each sensor
Middle device, each RVDT is made up of 5 lines, formed 2 strands totally 10 lines cross-link with data concentrator.
Single flap handle uses 4 single remaining RVDT sensors, the corresponding data set of each sensor
Middle device or flight control computer or actuator control electronics, and each RVDT is made up of 5 lines, form 4 strands totally 20
Root line cross-links with data concentrator.
Prior art has the disadvantages that
1, integration complexity is high；Handle the collection of signal in order to realize driving cabin, need between each control member
Dispose multiple sensor, the most also need to be simulated signals collecting and resolving, the system degree of cross linking flying to control in electronics
Greatly, coupling is strong, and interface definition is high with the complexity realized, and integrated difficulty is big；
2, number of cables is many, and volume is big with weight；Each operating mechanism, in order to ensure remaining, is equipped with multiple
RVDT sensor, each sensor just can be completed function by 5 lines, and the number of cables causing system is many, body
Long-pending big with weight；
3, system restructural degree is low.
Summary of the invention
The purpose of the present invention overcomes the deficiencies in the prior art exactly, it is provided that a kind of aircraft cockpit steerable system and behaviour
Vertical method.
One aircraft cockpit steerable system of the present invention, including side lever, pedals, flap handle, throttle
Platform, described side lever, pedals, flap handle are all by double remaining Optical displacement sensors and data concentrator
Connecting, described data concentrator controls electronics with flight control computer or actuator and is connected.
Further, this aircraft cockpit steerable system includes 2 side levers, 2 pedals.
Further, each side lever and 4 double remaining Optical displacement sensors connect, each pair of remaining light displacement sensing
Device and 2 data concentrators connect, and each side lever is connected by 8 optical cables and 4 data concentrators.
Further, each pedals and 1 double remaining Optical displacement sensor connect, each pair of remaining light position
Displacement sensor and 2 data concentrators connect, and each pedals pass through 2 optical cables and 2 data concentrators
Connect.
Further, described flap handle and 2 double remaining Optical displacement sensors connect, each pair of remaining light position
Displacement sensor and 2 data concentrators connect, and described flap handle passes through 4 optical cables and 4 data concentrators
Connect.
Further, described pair of remaining Optical displacement sensor includes the subassembly set that 2 sets are identical, every subcomponents
Set includes optical signal generator, optical signal acquisition device, optical signal modulator, optical fiber cable, photo-detector, often
Subcomponents set can complete independently optical signal generation, gather, measure, modulate, demodulate, it is achieved by physical quantity
Signal to digital quantity is changed.
Present invention also offers a kind of integrated physical interface being applied to above-mentioned aircraft cockpit steerable system, described 2
Individual side lever, 2 pedals, the manipulation signal transport vehicle physical integrations of flap handle are integrated, described
Integrated physical interface includes 8 physical interfaces corresponding to single described side lever, corresponding to single described rudder foot
2 physical interfaces pedaling, 4 physical interfaces corresponding to described flap handle；Wherein, each pair of remaining light
Displacement transducer corresponds respectively to 2 physical interfaces.
Present invention also offers a kind of method handling above-mentioned aircraft cockpit steerable system, including:
Side lever is connected with data concentrator by double remaining Optical displacement sensors, so that the manipulation signal of each side lever leads to
Cross 4 double remaining Optical displacement sensors and be transferred to the step of 4 data concentrators；
Pedals are connected with data concentrator by double remaining Optical displacement sensors, so that each pedals
Handle signal and be transferred to the step of 2 data concentrators by 1 double remaining Optical displacement sensor；And
Flap handle is connected with data concentrator by double remaining Optical displacement sensors, so that flap stick control
Signal is transferred to the step of 4 data concentrators by 2 double remaining Optical displacement sensors.
The invention have the benefit that
1, flight control system dispose simple, efficiently, modularity, be easily integrated；
2, rational redundant configurations scheme so that driving cabin operating mechanism i.e. meets wanting of flight control system entirety remaining
Ask, realize again the minimizing of the number of cables of system, the reduction of volume, alleviating of weight；
3, using Optical displacement sensor, the collection real-time of signal is higher, and anti-interference is higher.
Accompanying drawing explanation
Fig. 1 show tradition driving cabin steerable system schematic diagram.
Fig. 2 show side lever connection diagram in tradition driving cabin steerable system.
Fig. 3 show embodiment of the present invention one driving cabin steerable system schematic diagram.
Fig. 4 show side lever connection diagram in the embodiment of the present invention.
In figure: bar, 2-right-hand rod, 3-pedals, 4-flap handle on the left of 1-.
Detailed description of the invention
The specific embodiment of the invention is described in detail below in conjunction with concrete accompanying drawing.It should be noted that, following embodiment
Described in technical characteristic or the combination of technical characteristic be not construed as isolating, they can be by mutual group
Close thus reach superior technique effect.In the accompanying drawing of following embodiment, the identical label generation that each accompanying drawing is occurred
Feature that table is identical or parts, can be applicable in different embodiment.
As it is shown on figure 3, embodiment of the present invention one aircraft cockpit steerable system, including side lever 1,2 (respectively
For left side bar 1, right-hand rod 2, it is possibility to have other side lever arrangement), pedals 3, flap
Handle 4, throttle platform, described side lever 1,2, pedals 3, flap handle 4 is all by double remaining light positions
Displacement sensor is connected with data concentrator, and described data concentrator controls electronics even with flight control computer or actuator
Connect.
Preferably, aircraft cockpit steerable system includes 2 side levers 1,2,2 pedals 3.
Preferably, each side lever (1 or 2) is connected with 4 double remaining Optical displacement sensors, each pair of remaining light
Displacement transducer and 2 data concentrators connect, and each side lever (1 or 2) passes through 8 optical cables and 4 data
Concentrator connects.Fig. 4 shows that double remaining Optical displacement sensors of single side lever are connected with the concrete of data concentrator
Relation.
Preferably, each pedals 3 are connected with 1 double remaining Optical displacement sensor, each pair of remaining light position
Displacement sensor and 2 data concentrators connect, and each pedals 3 are concentrated by 2 optical cables and 2 data
Device connects.
Preferably, described flap handle 4 is connected with 2 double remaining Optical displacement sensors, each pair of remaining light position
Displacement sensor and 2 data concentrators connect, and described flap handle 4 is concentrated by 4 optical cables and 4 data
Device connects.
Preferably, described pair of remaining Optical displacement sensor includes the subassembly set that 2 sets are identical, every subcomponents collection
Conjunction includes optical signal generator, optical signal acquisition device, optical signal modulator, optical fiber cable, photo-detector, often overlaps
Subassembly set can complete independently optical signal generation, gather, measure, modulate, demodulate, it is achieved by physical quantity to
The signal conversion of digital quantity.
The embodiment of the present invention is for the integrated physical interface of above-mentioned aircraft cockpit steerable system, described 2 side levers
(1,2), 2 pedals 3, the manipulation signal transport vehicles of flap handle 4 are physically integrated into one
Body, described integrated physical interface includes 8 physical interfaces, correspondences corresponding to single described side lever (1 or 2)
2 physical interfaces in single described pedals 3,4 physics corresponding to described flap handle 4 connect
Mouthful；Wherein, each pair of remaining Optical displacement sensor corresponds respectively to 2 physical interfaces.
A kind of method handling above-mentioned aircraft cockpit steerable system, including:
Side lever (1 or 2) is connected with data concentrator by double remaining Optical displacement sensors, so that each side lever (1
Or 2) signal of handling be transferred to the step of 4 data concentrators by 4 pair remaining Optical displacement sensors；
Pedals 3 are connected with data concentrator by double remaining Optical displacement sensors, so that each rudder foot
Pedal 3 manipulation signals and be transferred to the step of 2 data concentrators by 1 double remaining Optical displacement sensor；And
Flap handle 4 is connected with data concentrator by double remaining Optical displacement sensors, so that flap handle 4
Handle signal and be transferred to the step of 4 data concentrators by 2 double remaining Optical displacement sensors.
In embodiments of the present invention, side lever 1,2 mainly realize pilot manipulation input, including fore-and-aft control,
Lateral control and Autopilot Disengage Switch, the manipulation of pilot is inputted to gather and uses double remaining light displacement by the present invention
Sensor, is sent to data concentrator after signal condition, it is achieved the vertical and horizontal operating function of pilot.
Pedals 3 mainly provide the manipulation on pilot course to input, it is achieved the input to rudder control,
And then realizing Heading control, the manipulation of pilot is inputted to gather and uses double remaining Optical displacement sensor, letter by the present invention
Number conditioning after be sent to data concentrator, it is achieved the operating function in pilot course.
Flap handle 4 mainly provides the manipulation of pilot's Air slowdown to input, and the present invention is defeated to the manipulation of pilot
Enter to gather the mode using double remaining Optical displacement sensors, be sent to data concentrator after signal condition, it is achieved fly
The operating function of the Air slowdown of office staff.
Optical displacement sensor uses double redundancy design, each pair of remaining Optical displacement sensor to have the light letter that two sets are identical
Number generator, optical signal acquisition device, optical signal modulator, optical fiber cable and photo-detector, it is achieved sensor
Backup functionality.
The invention have the benefit that
1, flight control system dispose simple, efficiently, modularity, be easily integrated；
2, rational redundant configurations scheme so that driving cabin operating mechanism i.e. meets wanting of flight control system entirety remaining
Ask, realize again the minimizing of the number of cables of system, the reduction of volume, alleviating of weight；
3, using Optical displacement sensor, the collection real-time of signal is higher, and anti-interference is higher.
Although having been presented for several embodiments of the present invention herein, it will be appreciated by those of skill in the art that
Without departing from the spirit of the invention, the embodiments herein can be changed.Above-described embodiment simply shows
Example, should be using the embodiments herein as the restriction of interest field of the present invention.
Claims (8)
1. an aircraft cockpit steerable system, including side lever, pedals, flap handle, throttle
Platform, it is characterised in that described side lever, pedals, flap handle are all by double remaining Optical displacement sensors
Being connected with data concentrator, described data concentrator controls electronics with flight control computer or actuator and is connected.
2. aircraft cockpit steerable system as claimed in claim 1, it is characterised in that include 2 side levers, 2
Individual pedals.
3. aircraft cockpit steerable system as claimed in claim 2, it is characterised in that each side lever and 4
Double remaining Optical displacement sensors connect, and each pair of remaining Optical displacement sensor and 2 data concentrators connect, each
Side lever is connected by 8 optical cables and 4 data concentrators.
4. aircraft cockpit steerable system as claimed in claim 2, it is characterised in that each pedals
Being connected with 1 double remaining Optical displacement sensor, each pair of remaining Optical displacement sensor and 2 data concentrators are even
Connecing, each pedals are connected by 2 optical cables and 2 data concentrators.
5. aircraft cockpit steerable system as claimed in claim 2, it is characterised in that described flap handle
Being connected with 2 double remaining Optical displacement sensors, each pair of remaining Optical displacement sensor and 2 data concentrators are even
Connecing, described flap handle is connected by 4 optical cables and 4 data concentrators.
6. the aircraft cockpit steerable system as described in any one of claim 1-5, it is characterised in that described double
Remaining Optical displacement sensor includes that the subassembly set that 2 sets are identical, every subcomponents set include that optical signal occurs
Device, optical signal acquisition device, optical signal modulator, optical fiber cable, photo-detector, every subcomponents set can be independent
Complete the generation of optical signal, gather, measure, modulate, demodulate, it is achieved turned by the signal of physical quantity to digital quantity
Change.
7. it is applied to an integrated physical interface for aircraft cockpit steerable system as claimed in claim 2, its
It is characterised by, described 2 side levers, 2 pedals, the manipulation signal transport vehicle physics of flap handle
Becoming one, described integrated physical interface includes 8 physical interfaces corresponding to single described side lever, corresponds to
2 physical interfaces of single described pedals, 4 physical interfaces corresponding to described flap handle；Its
In, each pair of remaining Optical displacement sensor corresponds respectively to 2 physical interfaces.
8. the method handling aircraft cockpit steerable system as claimed in claim 2, it is characterised in that
Including:
Side lever is connected with data concentrator by double remaining Optical displacement sensors, so that the manipulation signal of each side lever leads to
Cross 4 double remaining Optical displacement sensors and be transferred to the step of 4 data concentrators；
Pedals are connected with data concentrator by double remaining Optical displacement sensors, so that each pedals
Handle signal and be transferred to the step of 2 data concentrators by 1 double remaining Optical displacement sensor；And
Flap handle is connected with data concentrator by double remaining Optical displacement sensors, so that flap stick control
Signal is transferred to the step of 4 data concentrators by 2 double remaining Optical displacement sensors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610339257.9A CN105857581B (en) | 2016-05-19 | 2016-05-19 | A kind of aircraft cockpit steerable system and method for operating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610339257.9A CN105857581B (en) | 2016-05-19 | 2016-05-19 | A kind of aircraft cockpit steerable system and method for operating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105857581A true CN105857581A (en) | 2016-08-17 |
| CN105857581B CN105857581B (en) | 2018-10-02 |
Family
ID=56635564
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610339257.9A Active CN105857581B (en) | 2016-05-19 | 2016-05-19 | A kind of aircraft cockpit steerable system and method for operating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105857581B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107357175A (en) * | 2017-07-26 | 2017-11-17 | 中国航空工业集团公司西安飞机设计研究所 | A kind of plane nose physical prototyping demonstration and verification platform |
| CN107450358A (en) * | 2017-07-21 | 2017-12-08 | 上海航空电器有限公司 | Aviation driving cabin control panel and dimming control system based on optical fiber transmission |
| CN108639313A (en) * | 2018-05-22 | 2018-10-12 | 南京航空航天大学 | A kind of high-precision stick force control method of aircraft master end lever system |
| CN108674634A (en) * | 2018-05-22 | 2018-10-19 | 南京航空航天大学 | A kind of friction compensation method suitable for the control of aircraft master end lever system position |
| CN108706094A (en) * | 2018-05-22 | 2018-10-26 | 南京航空航天大学 | A kind of stick force anti-shaking method of aircraft master end lever system near neutral position |
| CN108891578A (en) * | 2018-05-22 | 2018-11-27 | 南京航空航天大学 | A kind of trimming control method of aircraft master end lever system |
| CN110766930A (en) * | 2019-10-23 | 2020-02-07 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Distributed control system of civil owner flight control system direct mode |
| CN111532418A (en) * | 2020-05-20 | 2020-08-14 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN112415979A (en) * | 2020-10-30 | 2021-02-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control test system, method, equipment and storage medium |
| CN114743430A (en) * | 2022-03-15 | 2022-07-12 | 哈尔滨莱特兄弟科技开发有限公司 | Pedal mechanism with adjustable simulated aircraft position |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104192300A (en) * | 2014-04-22 | 2014-12-10 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A flight control system and a method |
| CN205837175U (en) * | 2016-05-19 | 2016-12-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft cockpit steerable system and the physical interface being applied thereon |
-
2016
- 2016-05-19 CN CN201610339257.9A patent/CN105857581B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104192300A (en) * | 2014-04-22 | 2014-12-10 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A flight control system and a method |
| CN205837175U (en) * | 2016-05-19 | 2016-12-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft cockpit steerable system and the physical interface being applied thereon |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107450358A (en) * | 2017-07-21 | 2017-12-08 | 上海航空电器有限公司 | Aviation driving cabin control panel and dimming control system based on optical fiber transmission |
| CN107357175A (en) * | 2017-07-26 | 2017-11-17 | 中国航空工业集团公司西安飞机设计研究所 | A kind of plane nose physical prototyping demonstration and verification platform |
| CN108639313B (en) * | 2018-05-22 | 2021-07-13 | 南京航空航天大学 | High-precision rod force control method of airplane driving side rod system |
| CN108639313A (en) * | 2018-05-22 | 2018-10-12 | 南京航空航天大学 | A kind of high-precision stick force control method of aircraft master end lever system |
| CN108706094A (en) * | 2018-05-22 | 2018-10-26 | 南京航空航天大学 | A kind of stick force anti-shaking method of aircraft master end lever system near neutral position |
| CN108891578A (en) * | 2018-05-22 | 2018-11-27 | 南京航空航天大学 | A kind of trimming control method of aircraft master end lever system |
| CN108674634A (en) * | 2018-05-22 | 2018-10-19 | 南京航空航天大学 | A kind of friction compensation method suitable for the control of aircraft master end lever system position |
| CN108891578B (en) * | 2018-05-22 | 2021-06-15 | 南京航空航天大学 | Trimming control method of airplane active side lever system |
| CN108674634B (en) * | 2018-05-22 | 2021-03-30 | 南京航空航天大学 | Friction compensation method suitable for position control of airplane active side lever system |
| CN108706094B (en) * | 2018-05-22 | 2021-03-30 | 南京航空航天大学 | Rod force anti-shaking method for airplane active side rod system near neutral position |
| CN110766930A (en) * | 2019-10-23 | 2020-02-07 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Distributed control system of civil owner flight control system direct mode |
| CN111532418A (en) * | 2020-05-20 | 2020-08-14 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN111532418B (en) * | 2020-05-20 | 2021-09-24 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN112415979A (en) * | 2020-10-30 | 2021-02-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control test system, method, equipment and storage medium |
| CN112415979B (en) * | 2020-10-30 | 2021-11-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control test system, method, equipment and storage medium |
| CN114743430A (en) * | 2022-03-15 | 2022-07-12 | 哈尔滨莱特兄弟科技开发有限公司 | Pedal mechanism with adjustable simulated aircraft position |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105857581B (en) | 2018-10-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105857581A (en) | Airplane cockpit control system and method | |
| CN101117155B (en) | Aircraft electrical brake control system architecture | |
| US8078340B2 (en) | Active user interface haptic feedback and linking control system using either force or position data | |
| CN109147467B (en) | Helicopter control load system based on actual-mounted control lever system and simulation implementation method | |
| CN104616561B (en) | Large transport airplane control loading simulator | |
| US20160376003A1 (en) | Aircraft | |
| US8565939B2 (en) | Distributed pedal system for aircraft | |
| CN204965053U (en) | Telex flight control system | |
| US10239633B2 (en) | System and method to interchange flight control inceptors in an aircraft flight control system and cockpit | |
| CN208233348U (en) | A kind of unmanned plane during flying steerable system | |
| CN208731225U (en) | Take-off system | |
| CN206210171U (en) | A kind of new flight control system manipulates load device | |
| CN113093618B (en) | Brake controller hardware architecture and control method | |
| US20190382101A1 (en) | Electric pedal control device for aircraft | |
| CN109606630A (en) | A kind of intelligence wing composite material rear system | |
| RU2472672C1 (en) | Aircraft with remote control system | |
| CN205837175U (en) | A kind of aircraft cockpit steerable system and the physical interface being applied thereon | |
| CN106828884A (en) | The method that amphibious aircraft flight control system installs control augmentation stability system additional | |
| EP3333069A1 (en) | Systems and methods for aircraft emergency and park brakes | |
| US10829211B2 (en) | Local digital conversion for force and position signals for electric actuation control | |
| CN209118544U (en) | A kind of simulation operations device of aircraft | |
| CN209388518U (en) | Simple load simulation device based on airplane steering column control | |
| CN116449874A (en) | Modularized unmanned control refitting kit of piloted plane and construction method | |
| EP3428022A1 (en) | Brake handle for emergency electric braking | |
| RU2630030C1 (en) | Multifunctional single-seat aircraft with integrated control 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 |