CN110450940A - A kind of elevator trimming control circuit of aircraft - Google Patents
A kind of elevator trimming control circuit of aircraft Download PDFInfo
- Publication number
- CN110450940A CN110450940A CN201910547487.8A CN201910547487A CN110450940A CN 110450940 A CN110450940 A CN 110450940A CN 201910547487 A CN201910547487 A CN 201910547487A CN 110450940 A CN110450940 A CN 110450940A
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- China
- Prior art keywords
- relay
- trim
- switch
- control circuit
- hand drive
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Classifications
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- 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
- B64C13/18—Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Elevator Control (AREA)
Abstract
The invention belongs to technical field of aerospace, the elevator trimming control circuit of specially a kind of aircraft.It is switched including change-over switch, left-hand drive person's trim, right driver's trim switch, relay B, two group relay A, Tiao Xiao mechanisms, trimmer motor drive mechanism.Tiao Xiao mechanism and trimmer steerable system Electric Control Design use Integrated design, and by change-over switch, conversion and control between realization system, electrical control is simple, route is few, light-weight.By the control of relay, left-hand drive trim permission may be implemented higher than right driving trim, be convenient for system operatio.
Description
Technical field
The invention belongs to technical field of aerospace, be about a kind of aircraft control stick trimming system, realized to aircraft handling
The artificial trim function of stick force, is mainly used in large and medium-sized transporter and civil aircraft.Specially a kind of elevator of aircraft is matched
Level control circuit.
Background technique
In a kind of irreversible powered control system of aircraft, the artificial trim operating mode of elevator Tiao Xiao mechanism is for matching
Flat pilot control control stick compresses elevator spring-loaded mechanism and the steering force of generation, the work for mitigating driver are tired
Labor.
When the winged control hydraulic system and left General hydraulic system simultaneous faults that fly control booster or fly control hydraulic system and the right side
When General hydraulic system simultaneous faults, elevator trimmer steerable system is thrown as the spare trimmer of pilot control stick force
Enter to use.
Currently, traditional elevator Tiao Xiao mechanism and elevator trimmer steerable system major defect have: ①Tiao Xiao mechanism and
Trimmer steerable system electrical control is individually designed, and Electric Control Design is complicated, and route is more, and weight is big.2. can not achieve left/right
The interlocking of driver behavior priority, is unfavorable for system operatio.
Summary of the invention
The present invention overcomes deficiencies in the prior art, provide a kind of novel elevating rudder trimming control circuit
Technical solution
A kind of elevator trimming control circuit of aircraft, including change-over switch 1, left-hand drive person's trim switch 3, right driver
Trim switch 6, relay B5, two group relay A2, Tiao Xiao mechanisms, trimmer motor drive mechanism.The change-over switch 1 is opened for double-pole
It closes, wherein the tip side of one group of connection power supply and left-hand drive person's trim switch 3, relay A2, another group of connection power supply and relay
The control coil hot end of device B5；Left-hand drive person's trim switch 3 connects the tip side and difference of change-over switch 1, relay B5
Connect the tip side of two relay A2；Right driver's trim switch 6 is separately connected the tip side and relay of two relay A2
The tip side of device B5；The control coil hot end connection change-over switch 1 of relay B5, tip side connection Tiao Xiao mechanism, adjustment
Piece motor drive mechanism, left-hand drive person's trim switch 3, right driver's trim switch 6；After two group relay A2 tip sides are connected, and point
It is not connect with change-over switch 1 and right driver's trim switch 6, the touching of control terminal and left-hand drive person's trim switch 3 and relay B5
Point end is connected.
The circuit further includes diode 4, four groups of diodes 4 respectively with left-hand drive person's trim switch 3 and relay B5
Tip side connection.
The diode 4 is four groups.
The trim permission of left-hand drive person's trim switch 3 is higher than right driver's trim switch 6.
Left-hand drive person's trim switch 3 is single knife switch.
Right driver's trim switch 6 is single knife switch.
Relay B5 is four contact relay of unicoil.
Relay A2 is unicoil single-contact relay.
Technical effect
Compared with prior art, the beneficial effects of the present invention are: Tiao Xiao mechanism and trimmer steerable system electric-controlled are set up
Meter uses Integrated design, and by change-over switch, conversion and control between realization system, electrical control is simple, route is few, weight
Gently.By the control of relay, left-hand drive trim permission may be implemented higher than right driving trim, be convenient for system operatio.
Detailed description of the invention
Fig. 1 is elevator trimming control circuit diagram；
Fig. 2 elevator tune effect/trimmer electric control theory block diagram.
Specific embodiment
It elaborates in conjunction with elevator trimming control circuit of the attached drawing to a kind of aircraft of the invention:
Elevator trimming control circuit integration design are as follows: when operating change-over switch 1, relay B5 work is realized and adjusts effect
Mechanism/trimmer system work switching.
Left-hand drive trim permission is designed higher than right driving trim are as follows: when operating left steering wheel trim switch (upper and lower) 3,
The power supply of relay A2 work, right steering wheel trim switch 6 is cut off, and is operated right steering wheel trim switch 6 simultaneously at this time, is not changed
Become the direction of motion of trimmer.
Tiao Xiao mechanism and trimmer steerable system electrical control Integrated design are as shown in Figure 1, 2, including 1. Tiao Xiao mechanism/tune
Full wafer change-over switch, 2,5. relays, 3. left-hand drive person's trims switch, 6. right driver's trim switches, 4. diodes.
Left-hand drive trim permission is designed higher than right driving trim are as follows: when operating 3. left steering wheel trims switch (upper and lower),
2. relay works, the power supply of 6. right steering wheel trims switch is cut off, and operates 6. right steering wheel trims switch simultaneously at this time, no
Change the direction of motion of trimmer.
Tiao Xiao mechanism/trimmer electrical control Integrated design are as follows: when operating 1. Tiao Xiao mechanisms/trimmer change-over switch,
5. relay works, Tiao Xiao mechanism/trimmer system work switching is realized.
Elevator Tiao Xiao mechanism automatic trim Functional Design are as follows:, when manual or automatic vector aircraft to new posture or boat
On mark or certain reason destroys the equilibrium state of aircraft, and autopilot servo drives 7. operating system leverages to move, and 8.
Elevator control feel simulator is mobile and amount of movement is transferred to 9. tune effect mechanism controls box, forwards after 9. tune effect mechanism controls box processing
To 10. automatic flight-control computers, if 10. automatic flight-control computers identify displacement, displacement is more than
Automatic trim threshold value adjusts effect mechanism controls box to issue automatic trim instruction to 9., and 9. adjust effect mechanism controls box control 11. to adjust effect
The work of mechanism actuator.
Claims (8)
1. a kind of elevator trimming control circuit of aircraft, it is characterised in that: match including change-over switch (1), left-hand drive person and be opened flat
It closes (3), right driver's trim switchs (6), relay B (5), two group relay A (2), Tiao Xiao mechanism, trimmer motor drive mechanism；
The change-over switch (1) is double-pole switch, wherein one group of connection power supply and left-hand drive person's trim switch (3), relay A (2)
Tip side, the control coil hot end of another group of connection power supply and relay B (5)；Left-hand drive person's trim switchs (3) connection and turns
Change switch (1), relay B (5) tip side and be separately connected the tip sides of two relay A (2)；Right driver's trim switch
(6) tip side of two relay A (2) and the tip side of relay B (5) are separately connected；The control coil of relay B (5) is high
Potential end connect change-over switch (1), tip side connection Tiao Xiao mechanism, trimmer motor drive mechanism, left-hand drive person's trim switch (3),
Right driver's trim switchs (6)；Two group relay A (2) tip sides be connected after, and respectively with change-over switch (1) and right driver
Trim switchs (6) connection, and control terminal is connected with the tip side of left-hand drive person's trim switch (3) and relay B (5).
2. a kind of elevator trimming control circuit of aircraft according to claim 1, it is characterised in that: the circuit is also
Including diode (4), diode (4) is connect with left-hand drive person's trim switch (3) and relay B (5) tip side respectively.
3. a kind of elevator trimming control circuit of aircraft according to claim 2, it is characterised in that: the diode
It (4) is four groups.
4. a kind of elevator trimming control circuit of aircraft according to claim 1, it is characterised in that: the left-hand drive person
The trim permission that trim switchs (3) is higher than right driver's trim switch (6).
5. a kind of elevator trimming control circuit of aircraft according to claim 1, it is characterised in that: left-hand drive person's trim
Switching (3) is single knife switch.
6. a kind of elevator trimming control circuit of aircraft according to claim 1, it is characterised in that: right driver's trim
Switching (6) is single knife switch.
7. a kind of elevator trimming control circuit of aircraft according to claim 1, it is characterised in that: relay B (5) is
Four contact relay of unicoil.
8. a kind of elevator trimming control circuit of aircraft according to claim 1, it is characterised in that: relay A (2) is
Unicoil single-contact relay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910547487.8A CN110450940B (en) | 2019-06-24 | 2019-06-24 | Aircraft elevator trim control circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910547487.8A CN110450940B (en) | 2019-06-24 | 2019-06-24 | Aircraft elevator trim control circuit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110450940A true CN110450940A (en) | 2019-11-15 |
| CN110450940B CN110450940B (en) | 2022-09-20 |
Family
ID=68480800
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910547487.8A Active CN110450940B (en) | 2019-06-24 | 2019-06-24 | Aircraft elevator trim control circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110450940B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110989660A (en) * | 2019-11-19 | 2020-04-10 | 哈尔滨飞机工业集团有限责任公司 | Automatic flight control system's balancing adapter |
| CN112666929A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Automatic balancing system for airplane state switching |
| CN112727902A (en) * | 2020-12-25 | 2021-04-30 | 兰州飞行控制有限责任公司 | Balancing mechanism and method for flexible connecting assembly transmission |
| CN112918660A (en) * | 2021-03-26 | 2021-06-08 | 陕西飞机工业有限责任公司 | Device is imitated to elevator |
| CN113184168A (en) * | 2021-05-14 | 2021-07-30 | 陕西飞机工业有限责任公司 | Elevator adjustment sheet control system |
Citations (5)
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|---|---|---|---|---|
| US5913492A (en) * | 1996-05-17 | 1999-06-22 | Aerospatiale Societe Nationale Industrielle | System for controlling an aircraft control surface tab |
| CN103303467A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Electrical control method and system for airplane trimmer |
| CN104616561A (en) * | 2014-12-05 | 2015-05-13 | 中国人民解放军空军航空大学军事仿真技术研究所 | Large transport airplane control loading simulator |
| US20160152323A1 (en) * | 2014-10-13 | 2016-06-02 | Gulfstream Aerospace Corporation | Aircraft, systems, and methods for trim control in fly-by-wire aircraft systems |
| CN106184715A (en) * | 2015-04-29 | 2016-12-07 | 陕西飞机工业（集团）有限公司 | A kind of aircraft control stick trimming system |
-
2019
- 2019-06-24 CN CN201910547487.8A patent/CN110450940B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5913492A (en) * | 1996-05-17 | 1999-06-22 | Aerospatiale Societe Nationale Industrielle | System for controlling an aircraft control surface tab |
| CN103303467A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Electrical control method and system for airplane trimmer |
| US20160152323A1 (en) * | 2014-10-13 | 2016-06-02 | Gulfstream Aerospace Corporation | Aircraft, systems, and methods for trim control in fly-by-wire aircraft systems |
| CN104616561A (en) * | 2014-12-05 | 2015-05-13 | 中国人民解放军空军航空大学军事仿真技术研究所 | Large transport airplane control loading simulator |
| CN106184715A (en) * | 2015-04-29 | 2016-12-07 | 陕西飞机工业（集团）有限公司 | A kind of aircraft control stick trimming system |
Non-Patent Citations (1)
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| 孙勇: "《基于FPGA的升降舵调效机构控制盒设计》", 《甘肃科技纵横》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110989660A (en) * | 2019-11-19 | 2020-04-10 | 哈尔滨飞机工业集团有限责任公司 | Automatic flight control system's balancing adapter |
| CN112727902A (en) * | 2020-12-25 | 2021-04-30 | 兰州飞行控制有限责任公司 | Balancing mechanism and method for flexible connecting assembly transmission |
| CN112666929A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Automatic balancing system for airplane state switching |
| CN112918660A (en) * | 2021-03-26 | 2021-06-08 | 陕西飞机工业有限责任公司 | Device is imitated to elevator |
| CN113184168A (en) * | 2021-05-14 | 2021-07-30 | 陕西飞机工业有限责任公司 | Elevator adjustment sheet control system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110450940B (en) | 2022-09-20 |
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