CN112591076A - Airplane control surface trimmer control system with rod force follow-up compensation - Google Patents
Airplane control surface trimmer control system with rod force follow-up compensation Download PDFInfo
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- CN112591076A CN112591076A CN202011612757.8A CN202011612757A CN112591076A CN 112591076 A CN112591076 A CN 112591076A CN 202011612757 A CN202011612757 A CN 202011612757A CN 112591076 A CN112591076 A CN 112591076A
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- 230000001360 synchronised effect Effects 0.000 claims description 64
- 230000007246 mechanism Effects 0.000 claims description 14
- 229910000831 Steel Inorganic materials 0.000 claims description 9
- 239000010959 steel Substances 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000009347 mechanical transmission Effects 0.000 description 3
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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
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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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
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
Abstract
The invention belongs to the technical field of control system design in the field of airplane design, and discloses an airplane control surface adjustment sheet control system with rod force follow-up compensation. The technical scheme has the advantages of simple and easy realization of the structure, no special processing, manufacturing or assembly, and realization of the airplane auxiliary control system which is reliable, easy to use, light in weight and low in cost through the combination of conventional mechanical components.
Description
Technical Field
The invention belongs to the technical field of control system design in the field of airplane design, and particularly relates to an airplane control surface trimmer control system with rod force follow-up compensation.
Background
In the field of airplane design, in particular to the field of design of a mechanically-operated small and medium-sized airplane operated by people, an auxiliary control surface operation system, namely an adjusting sheet operation system, is arranged on the basis of a main control surface operation system of the airplane, the adjusting sheet operation system is generally used in the airplane cruising process, and an aerodynamic moment is generated on the control surface of the airplane in the opposite direction through active deflection of an adjusting sheet, so that the main control surface generates deflection in a certain range, the attitude adjustment of the airplane is further realized, the airplane can keep the airplane in the flying attitude, a pilot can not need to operate an airplane steering column in a short time, the driving fatigue is reduced, and the driving comfort is increased. When a pilot normally controls the airplane to land and land, the adjusting sheet moves along with the main rudder surface, the main rudder surface control system and the rudder surface adjusting sheet control system jointly realize coarse adjustment and fine adjustment of the flight attitude of the airplane, and further, under the condition that the main rudder surface control system of the airplane fails, the rudder surface adjusting sheet control system can control the attitude of the airplane under certain conditions, so that the airplane can safely return.
In the design of small and medium-sized airplanes, the cost and the weight of the airplane are important factors for determining the economy and the range of the airplane, and meanwhile, the airplane control system is required to have very high reliability. Simple mechanical steering systems have the advantages of simple structure, low cost, light weight and high reliability, and are difficult to replace in a short time by other types of systems, especially auxiliary steering systems for aircraft, in which aspects they are more typical.
Disclosure of Invention
The invention aims to provide an aircraft control surface adjustment sheet control system with the follow-up compensation of the rod force, which has the characteristics of mechanical driving, mechanical transmission, mechanical actuation and mechanical indication, has a simple structure, is easy to realize, and is particularly suitable for auxiliary control systems of small and medium-sized aircraft.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
An aircraft control surface tab steering system with stick force following compensation, the system comprising: the hand wheel control device 1, the transmission rope device 2, the lead screw actuating device 3 and the control connecting rod 6, wherein the transmission rope device 2 comprises a front end synchronous cable 201, a transmission rope 202, a guide wheel 203 and a rear end synchronous cable 204 which are sequentially connected, the hand wheel control device 1 comprises a dial wheel 101 and an output synchronous wheel 102, and the lead screw actuating device 3 comprises an input synchronous wheel 301, a lead screw nut mechanism 302 and an output end 303;
the output synchronizing wheel 102 of the handwheel control device 1 is connected with the front synchronizing cable 202 of the transmission rope device 2, the rear synchronizing cable 204 of the transmission rope device 2 is connected with the input synchronizing wheel 301 of the screw rod actuating device 3, the output end 303 of the screw rod actuating device 3 is connected with an adjusting sheet control point by the control connecting rod 6, the adjusting sheet is arranged on the rear edge of the airplane control surface, and the output end of the screw rod actuating device 3, the control surface rotating shaft, the adjusting sheet rotating shaft and the adjusting sheet control point are sequentially connected to form a quadrangle.
The technical scheme of the invention has the characteristics and further improvements that:
(1) the system further comprises a trimmer indicator, wherein the trimmer indicator comprises a pointer 112 and a shifting rod 113, a dial wheel 101 of the hand wheel operating device is provided with a spiral groove feature, the shifting rod 113 is embedded in the groove feature of the dial wheel 101, and the rotating shaft of the pointer 112 is not coincident with the rotating shaft of the dial wheel 101.
(2) The transmission rope device further comprises a connecting threaded sleeve 205, the connecting threaded sleeve 205 has internal thread characteristics, stud characteristics are arranged on the end heads of the front-end synchronous rope 201, the transmission rope 202 and the rear-end synchronous rope 204, and the connecting threaded sleeve 205 is respectively connected with the stud of the corresponding end heads of the front-end synchronous rope 201, the transmission rope 202 and the rear-end synchronous rope 204 in a matched mode.
(3) The transmission rope device 2 further comprises a stopping device, the stopping device comprises a forward stopping block 206, an intermediate stopping block 207 and a reverse stopping block 208 which are arranged in sequence, the forward stopping block 206, the reverse stopping block 208 and the intermediate stopping block 207 are respectively provided with a fixing feature and a through hole feature, the forward stopping block 206 and the reverse stopping block 208 are fixedly connected with a first driving edge of the transmission rope device through the fixing features, a second driving edge of the transmission rope device penetrates through the through hole features of the forward stopping block 206 and the reverse stopping block 208, the intermediate stopping block 207 is fixedly connected with a second driving edge of the transmission rope device through the fixing features, and the first driving edge of the transmission rope device penetrates through the through hole feature of the intermediate stopping block 207.
(4) The lead angle alpha of the lead screw actuating device and the friction coefficient mu of the nut material meet tan alpha < mu.
(5) The output synchronizing wheel 102 of the hand wheel control device 1 is a chain wheel, the front synchronizing cable 01 of the transmission cable device 2 is a chain, the transmission cable 202 is a steel wire rope, the guide wheel 203 is a pulley, the rear synchronizing cable 204 is a chain, the input synchronizing wheel (301) of the lead screw actuating device is a chain wheel, the lead screw in the lead screw actuating device is a T-shaped lead screw with two, three or four ends, and the nut is a nut with corresponding number of ends and thread shape.
(6) The front end synchronous cable and the rear end synchronous cable are a section of roller chain, the end heads of the roller chain are connected with threaded joints through hinge pin shaft mechanisms, the transmission cable is a steel wire rope, two ends of the steel wire rope are respectively connected with the threaded joints in a compression joint fastening mode, one end of each of the front end synchronous cable, the transmission cable and the rear end synchronous cable threaded joints is a left-handed thread, the other end of each of the front end synchronous cable, the transmission cable and the rear end synchronous cable threaded joints is a right-handed thread, internal threads of the connection threaded sleeve are divided into two sections, one section of the internal threads is a left-handed thread, the other section of the internal threads is a right-handed thread, and when the.
(7) The forward stop 206, the middle stop block 207 and the reverse stop block 208 are formed by oppositely combining and fastening two groups of clamping plates, the opposite surfaces of the clamping plates are respectively provided with a half-hole characteristic and a shallow slot characteristic, the two groups of clamping plates are oppositely combined to form a flat hole and a round hole, the sectional area of the flat hole is smaller than that of a transmission rope, and the transmission rope penetrating through the flat hole is clamped under the clamping force of a fastener to form a fixed connection characteristic; the diameter of the circular hole is larger than the maximum outline of the transmission rope passing through the circular hole, and a through hole characteristic is formed.
The technical scheme of the invention realizes the mechanical control function of the control surface adjusting sheet by arranging a hand wheel device with a dial wheel and an output synchronizing wheel, realizes the mechanical transmission function of the control surface adjusting sheet by arranging a transmission rope device with a front end synchronizing cable, a transmission rope, a guide wheel and a rear end synchronizing cable, realizes the mechanical driving function of the control surface adjusting sheet by arranging a lead screw actuating device with an input synchronizing wheel and a lead screw nut mechanism, realizes the mechanical indication function of the control surface adjusting sheet by matching a spiral groove of the dial wheel with a shift lever of an indicator, and realizes the limit position locking function of the control surface adjusting sheet by combining 3 groups of stop blocks. The output end of the screw actuating device, the control surface rotating shaft, the adjusting sheet rotating shaft and the adjusting sheet control point are sequentially connected to form a quadrangle, the adjusting sheet can reversely deflect relative to the control surface when the control surface moves, the control surface is pushed to reversely move through the aerodynamic force of the adjusting sheet, the moment compensation function of the adjusting sheet on the main control surface is realized, and the control force compensation function is further realized. The auxiliary control system for the airplane is simple in structure, easy to achieve, free of special processing manufacturing or assembling, reliable, easy to use, light in weight and low in cost and has wide market popularization and use values.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft control surface tab steering system with stick force follow-up compensation according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a forward stop block, a reverse stop block and an intermediate stop block provided in an embodiment of the present invention;
wherein, 1-handwheel control device; 2-a transmission rope device; 3-a screw actuation device; 4-aircraft control surface; 5-an adjustment sheet; 6-operating the connecting rod; 101-a thumb wheel; 102-output synchronizing wheel; 111-trench features; 112-a pointer; 113-a deflector rod; 201-front synchronous cable; 202-a drive rope; 203-a guide wheel; 204-a rear synchronous cable; 205-connecting thread insert; 206-positive stop; 207-intermediate stop block; 208-reverse stop; 211 clamping plates; 212-a fastener; 213-round hole; 214-flat hole; 301-input sync wheel; 302-a lead screw nut mechanism; 303-an output terminal; 401-aircraft rudder surface rotating shaft; 501-adjustment of sheet handling points; 502-tab rotation axis.
Detailed Description
The following description refers to the accompanying drawings, which illustrate in greater detail the implementation of the present application of the system for manipulating the elevator trim of a piston engine trainer.
Referring to fig. 1, an embodiment of the present invention provides an aircraft control surface adjustment sheet control system with stick force follow-up compensation, including a handwheel device, a transmission rope device, a lead screw actuating device and a control link, where the transmission rope device includes a front-end synchronous cable, a transmission rope, a guide wheel and a rear-end synchronous cable connected in sequence, the handwheel device includes a dial wheel and an output synchronous wheel, the lead screw actuating device includes an input synchronous wheel, a lead screw nut mechanism and an output end, the output synchronous wheel of the handwheel device is connected with the front-end synchronous cable of the transmission rope device, the rear-end synchronous cable of the transmission rope device is connected with the input synchronous wheel of the lead screw actuating device, the control link connects the output end of the lead screw actuating device with an adjustment sheet point, the adjustment sheet is installed at the rear edge of a left elevator of an aircraft, and the output end of the lead screw actuating device (3, The control points of the adjusting sheets are connected in sequence to form a quadrangle.
The aircraft control surface adjustment sheet control system further comprises an adjustment sheet indicator, the indicator comprises a pointer and a shifting rod, a shifting wheel of the hand wheel device is provided with a spiral groove feature, the shifting rod is embedded in the groove feature of the shifting wheel, and a rotating shaft of the pointer is not coincident with a rotating shaft of the shifting wheel. When the dial wheel is dialed, the dial rod moves close to and away from the dial wheel rotating shaft relative to the groove characteristic of the dial wheel to drive the pointer to rotate, and the position indication function is realized.
The transmission rope device of the aircraft control surface trimmer control system further comprises a connecting threaded sleeve, the connecting threaded sleeve is provided with internal threads, stud features are arranged on the ends of the front-end synchronous cable, the transmission rope and the rear-end synchronous cable, and the connecting threaded sleeve is respectively connected with the stud features of the corresponding ends of the front-end synchronous cable, the transmission rope and the rear-end synchronous cable in a matched mode.
The transmission rope device of the aircraft control surface tab control system further comprises a stopping device, as shown in fig. 2, the stopping device comprises a forward stopping block, a middle stopping block and a reverse stopping block which are sequentially arranged, the forward stopping block, the reverse stopping block and the middle stopping block are respectively provided with a fixed connection characteristic and a via hole characteristic, the forward stopping block and the reverse stopping block are fixedly connected with a first driving edge of the transmission rope device through the fixed connection characteristic, a second driving edge of the transmission rope device penetrates through the via hole characteristics of the forward stopping block and the reverse stopping block, the middle stopping block is fixedly connected with a second driving edge of the transmission rope device through the fixed connection characteristic, and the first driving edge of the transmission rope device penetrates through the via hole characteristic of the middle stopping block. When the thumb wheel rotates to the positive limit position, the middle stop block is contacted with the positive stop block to realize the stop of the movement of the transmission rope device, and further realize the movement stop of the adjustment sheet control system; when the thumb wheel rotates to the positive limit position, the middle stop block contacts with the reverse stop block to realize the stop of the movement of the transmission rope device and further realize the movement stop of the adjustment sheet control system, and further: to facilitate the arrangement of the forward, intermediate and reverse stops on the aircraft, the intermediate stops may be provided in two sets, one set for use in pairs with the forward stops and the other set for use in pairs with the reverse stops.
The lead angle alpha of a lead screw actuating device of the aircraft lifting control surface adjusting sheet operating system and the friction coefficient mu of a nut material meet tan alpha < mu, when the aerodynamic force of the adjusting sheet is transmitted to the output end of the lead screw actuating device through an operating connecting rod, a lead screw nut mechanism can be self-locked in the opposite direction, namely the aerodynamic force of the adjusting sheet cannot drive the adjusting sheet operating system to move in the opposite direction.
The output synchronizing wheel of the hand wheel device of the aircraft lifting control surface adjustment sheet control system is a chain wheel, the front end synchronizing wheel of the transmission rope device is a chain, the transmission rope is a steel wire rope, the guide wheel is a pulley, the rear end synchronizing cable is a chain, and the input synchronizing wheel of the lead screw actuating device is a chain wheel. The front end synchronous cable and the rear end synchronous cable are a section of roller chain, the end heads of the roller chain are connected with threaded joints through hinge pin shaft mechanisms, the transmission cable is a steel wire rope, two ends of the steel wire rope are respectively connected with the threaded joints in a compression joint fastening mode, one end of each of the front end synchronous cable, the transmission cable and the rear end synchronous cable threaded joint is a left-hand thread, the other end of each of the front end synchronous cable, the transmission cable and the rear end synchronous cable threaded joint is a right-hand thread, internal threads of the connection threaded sleeve are divided into two sections, one section is a left-hand thread, the other section is a right-hand thread, when the connection threaded sleeve and the threaded joint connected with the connection threaded sleeve rotate relatively, the tension adjustment of the transmission cable device can be realized, and after the tension of the. The screw rod in the screw rod actuating device is a T-shaped screw rod with two ends to four ends, the nut is a nut with the number corresponding to the number of the heads and the shape of threads, and the T-shaped screw rod and the T-shaped nut with two ends to four ends are arranged, so that the positive transmission efficiency of the adjusting sheet control system is improved.
The forward stop block, the middle stop block and the reverse stop block are formed by oppositely combining and fastening two groups of clamping plates, the opposite surfaces of the clamping plates are respectively provided with a half-hole characteristic and a shallow slot characteristic, the two groups of clamping plates are oppositely combined to form a flat hole and a round hole, the sectional area of the flat hole is smaller than that of a transmission rope, and the transmission rope passing through the flat hole is clamped under the clamping force of a fastener to form a fixedly-connected characteristic; the diameter of the circular hole is larger than the maximum outline of the transmission rope passing through the circular hole, and a through hole characteristic is formed.
The adjusting sheet operating system of the technical scheme of the invention is also suitable for a rudder adjusting sheet operating system and a flap adjusting sheet operating system.
When the adjusting device is used for a rudder adjusting sheet control system, the adjusting device comprises a hand wheel device, a transmission rope device, a lead screw actuating device and a control connecting rod, wherein the transmission rope device comprises a front end synchronous cable, a transmission rope, a guide wheel and a rear end synchronous cable which are sequentially connected, the hand wheel device comprises a dial wheel and an output synchronous wheel, the lead screw actuating device comprises an input synchronous wheel, a lead screw nut mechanism and an output end, the output synchronous wheel of the hand wheel device is connected with the front end synchronous cable of the transmission rope device, the rear end synchronous cable of the transmission rope device is connected with the input synchronous wheel of the lead screw actuating device, the control connecting rod connects the output end of the lead screw actuating device with an adjusting sheet control point, the adjusting sheet is installed on the rear edge of an airplane rudder, and the initial position of the output.
When the adjusting mechanism is used for an aileron adjusting sheet control system, the adjusting mechanism comprises a hand wheel device, a transmission rope device, a lead screw actuating device and a control connecting rod, wherein the transmission rope device comprises a front end synchronous cable, a transmission rope, a guide wheel and a rear end synchronous cable which are sequentially connected, the hand wheel device comprises a dial wheel and an output synchronous wheel, the lead screw actuating device comprises an input synchronous wheel, a lead screw nut mechanism and an output end, the output synchronous wheel of the hand wheel device is connected with the front end synchronous cable of the transmission rope device, the rear end synchronous cable of the transmission rope device is connected with the input synchronous wheel of the lead screw actuating device, the control connecting rod connects the output end of the lead screw actuating device with an adjusting sheet control point, the adjusting sheet is arranged at the left aileron trailing edge of an airplane, and the initial.
The technical scheme of the invention realizes the mechanical control function of the control surface adjusting sheet by arranging a hand wheel device with a dial wheel and an output synchronizing wheel, realizes the mechanical transmission function of the control surface adjusting sheet by arranging a transmission rope device with a front end synchronizing cable, a transmission rope, a guide wheel and a rear end synchronizing cable, realizes the mechanical driving function of the control surface adjusting sheet by arranging a lead screw actuating device with an input synchronizing wheel and a lead screw nut mechanism, realizes the mechanical indication function of the control surface adjusting sheet by matching a spiral groove of the dial wheel with a shift lever of an indicator, and realizes the limit position locking function of the control surface adjusting sheet by combining 3 groups of stop blocks. The output end of the screw actuating device, the control surface rotating shaft, the adjusting sheet rotating shaft and the adjusting sheet control point are sequentially connected to form a quadrangle, the adjusting sheet can reversely deflect relative to the control surface when the control surface moves, the control surface is pushed to reversely move through the aerodynamic force of the adjusting sheet, the moment compensation function of the adjusting sheet on the main control surface is realized, and the control force compensation function is further realized.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (8)
1. An aircraft control surface tab steering system with stick force follow up compensation, the system comprising: the device comprises a hand wheel operating device (1), a transmission rope device (2), a lead screw actuating device (3) and an operating connecting rod (6), wherein the transmission rope device (2) comprises a front end synchronous cable (201), a transmission rope (202), a guide wheel (203) and a rear end synchronous cable (204) which are sequentially connected, the hand wheel operating device (1) comprises a shifting wheel (101) and an output synchronous wheel (102), and the lead screw actuating device (3) comprises an input synchronous wheel (301), a lead screw nut mechanism (302) and an output end (303);
an output synchronizing wheel (102) of a hand wheel control device (1) is connected with a front synchronizing cable (202) of a transmission rope device (2), a rear synchronizing cable (204) of the transmission rope device (2) is connected with an input synchronizing wheel (301) of a lead screw actuating device (3), an output end (303) of the lead screw actuating device (3) is connected with an adjusting sheet control point through an operating connecting rod (6), the adjusting sheet is installed on the rear edge of an airplane control surface, and the output end of the lead screw actuating device (3), the control surface rotating shaft, the adjusting sheet rotating shaft and the adjusting sheet control point are sequentially connected to form a quadrangle.
2. An aircraft rudder surface trimmer steering system with stick force follow compensation according to claim 1, characterized in that the system further comprises a trimmer indicator, the trimmer indicator comprises a pointer (112) and a shift lever (113), the dial wheel (101) of the hand wheel steering device has a spiral groove feature, the shift lever (113) is embedded in the groove feature of the dial wheel (101), and the rotation axis of the pointer (112) is not coincident with the rotation axis of the dial wheel (101).
3. The aircraft control surface tab control system with the stick force follow-up compensation function according to claim 1, wherein the transmission rope device further comprises a connection threaded sleeve (205), the connection threaded sleeve (205) has an internal thread feature, stud features are arranged on the ends of the front end synchronous cable (201), the transmission rope (202) and the rear end synchronous cable (204), and the connection threaded sleeve (205) is respectively in fit connection with studs of the corresponding ends of the front end synchronous cable (201), the transmission rope (202) and the rear end synchronous cable (204).
4. An aircraft control surface tab steering system with stick force following compensation according to claim 1, characterized in that the transmission rope device (2) also comprises a stopping device, the stopping device comprises a forward stopping block (206), a middle stopping block (207) and a reverse stopping block (208) which are arranged in sequence, the forward stop block (206), the reverse stop block (208) and the middle stop block (207) are respectively provided with a fixed connection feature and a through hole feature, the forward stop block (206) and the reverse stop block (208) are fixedly connected with a first driving edge of the transmission rope device through the fixed connection feature, a second driving edge of the transmission rope device penetrates through the through hole features of the forward stop block (206) and the reverse stop block (208), the middle stop block (207) is fixedly connected with a second driving edge of the transmission rope device through the fixed connection feature, and the first driving edge of the transmission rope device penetrates through the through hole feature of the middle stop block (207).
5. An aircraft control surface tab steering system with stick force follow-up compensation according to claim 1, characterized in that the lead angle α of the screw actuating means and the coefficient of friction μ of the nut material satisfy tan α < μ.
6. The aircraft control surface tab control system with stick force follow-up compensation according to claim 1, wherein the output synchronizing wheel (102) of the hand wheel control device (1) is a chain wheel, the front end synchronizing cable (101) of the transmission cable device (2) is a chain, the transmission cable (202) is a steel wire rope, the guide wheel (203) is a pulley, the rear end synchronizing cable (204) is a chain, the input synchronizing wheel (301) of the lead screw actuating device is a chain wheel, the lead screw in the lead screw actuating device is a two-end, three-end or four-end T-shaped lead screw, and the nut is a nut corresponding to the number of heads and the shape of the thread.
7. The aircraft control surface adjustment sheet control system with the stick force follow-up compensation function as claimed in claim 1, wherein the front end synchronous cable and the rear end synchronous cable are a section of roller chain, the ends of the roller chain are connected with threaded joints through hinge pin shaft mechanisms, the transmission cable is a steel wire rope, two ends of the steel wire rope are respectively connected with the threaded joints in a compression fastening mode, one end of the front end synchronous cable, one end of the transmission cable and one end of the rear end synchronous cable threaded joint are left-handed threads, the other end of the front end synchronous cable, the other end of the transmission cable and the other end of the rear end synchronous cable threaded joint are right-handed threads, the internal threads of the connection threaded sleeve are divided into two sections, one section is left-handed threads, the other section is right-handed threads, and when the connection threaded sleeve and the.
8. The aircraft control surface tab control system with the stick force follow-up compensation function as claimed in claim 1, wherein the forward stop block (206), the middle stop block (207) and the reverse stop block (208) are formed by oppositely combining and fastening two groups of clamping plates, the opposite surfaces of the clamping plates are respectively provided with a half-hole characteristic and a shallow-groove characteristic, the two groups of clamping plates are oppositely combined to form a flat hole and a round hole, the cross-sectional area of the flat hole is smaller than that of the transmission rope, and the transmission rope passing through the flat hole is clamped under the clamping force of the fastening piece to form a fixed connection characteristic; the diameter of the circular hole is larger than the maximum outline of the transmission rope passing through the circular hole, and a through hole characteristic is formed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011612757.8A CN112591076A (en) | 2020-12-29 | 2020-12-29 | Airplane control surface trimmer control system with rod force follow-up compensation |
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| CN202011612757.8A CN112591076A (en) | 2020-12-29 | 2020-12-29 | Airplane control surface trimmer control system with rod force follow-up compensation |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113968348A (en) * | 2021-11-03 | 2022-01-25 | 西安羚控电子科技有限公司 | Fault processing method and device for servo actuation system of unmanned aerial vehicle |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107840258A (en) * | 2017-09-21 | 2018-03-27 | 北京机械设备研究所 | A kind of bidirectional driving apparatus |
| CN108204782A (en) * | 2017-12-08 | 2018-06-26 | 西安飞机工业（集团）有限责任公司 | A kind of angle measurement and instruction device based on Archimedian screw disk |
| CN208233346U (en) * | 2018-05-31 | 2018-12-14 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of aircraft horizontal tail trimming tab manipulation device |
| CN208325608U (en) * | 2018-06-11 | 2019-01-04 | 通航国际（西安）飞机技术有限公司 | A kind of airplane operation system suitable for trainer aircraft |
| CN110065621A (en) * | 2019-04-12 | 2019-07-30 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft evelvator trimmer deflection indicating means |
| CN209396030U (en) * | 2018-12-29 | 2019-09-17 | 福建野马飞机制造有限公司 | A kind of Aileron control system of light-duty sport plane |
| CN110920868A (en) * | 2019-11-19 | 2020-03-27 | 哈尔滨飞机工业集团有限责任公司 | Steering engine mounting device of automatic pilot |
| CN211685586U (en) * | 2019-11-25 | 2020-10-16 | 西安庆安电气控制有限责任公司 | Flexible control steel cable device used on airplane |
-
2020
- 2020-12-29 CN CN202011612757.8A patent/CN112591076A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107840258A (en) * | 2017-09-21 | 2018-03-27 | 北京机械设备研究所 | A kind of bidirectional driving apparatus |
| CN108204782A (en) * | 2017-12-08 | 2018-06-26 | 西安飞机工业（集团）有限责任公司 | A kind of angle measurement and instruction device based on Archimedian screw disk |
| CN208233346U (en) * | 2018-05-31 | 2018-12-14 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of aircraft horizontal tail trimming tab manipulation device |
| CN208325608U (en) * | 2018-06-11 | 2019-01-04 | 通航国际（西安）飞机技术有限公司 | A kind of airplane operation system suitable for trainer aircraft |
| CN209396030U (en) * | 2018-12-29 | 2019-09-17 | 福建野马飞机制造有限公司 | A kind of Aileron control system of light-duty sport plane |
| CN110065621A (en) * | 2019-04-12 | 2019-07-30 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft evelvator trimmer deflection indicating means |
| CN110920868A (en) * | 2019-11-19 | 2020-03-27 | 哈尔滨飞机工业集团有限责任公司 | Steering engine mounting device of automatic pilot |
| CN211685586U (en) * | 2019-11-25 | 2020-10-16 | 西安庆安电气控制有限责任公司 | Flexible control steel cable device used on airplane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113968348A (en) * | 2021-11-03 | 2022-01-25 | 西安羚控电子科技有限公司 | Fault processing method and device for servo actuation system of unmanned aerial vehicle |
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Application publication date: 20210402 |