CN104503483B - Controllable strake wing/canard wing pitching angle movement system of airplane wind tunnel test model - Google Patents
Controllable strake wing/canard wing pitching angle movement system of airplane wind tunnel test model Download PDFInfo
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- CN104503483B CN104503483B CN201410765736.8A CN201410765736A CN104503483B CN 104503483 B CN104503483 B CN 104503483B CN 201410765736 A CN201410765736 A CN 201410765736A CN 104503483 B CN104503483 B CN 104503483B
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Abstract
The invention discloses a controllable strake wing/canard wing pitching angle movement system of an airplane wind tunnel test model. The controllable strake wing/canard wing pitching angle movement system comprises a headpiece and frame component, an airplane model shafting vertical axis, left and right connecting shafts, left and right strake wings/canard wings as well as rotary shafts thereof, left and right bearings, left and right bearing seats, left and right reversing bevel gear pairs, left and right motor installation bases, left and right motors and a coder, left and right main wings, a computer and left and right motor drivers, wherein the right strake wing/canard wing is fixed with the right strake wing/canard wing rotary shaft, the right strake wing/canard wing rotary shaft is connected with the right end of the right connecting shaft, the left end of the right connecting shaft is connected with lower gears of the right reversing bevel gear pair, the same connecting mode is adopted at the left side; the left strake wing/canard wing rotary shaft axis and the right strake wing/canard wing rotary shaft axis are symmetrically arranged along longitudinal symmetrical surfaces of the airplane model shafting vertical axis. The controllable strake wing/canard wing pitching angle movement system can be used for realizing controllable yaw motion of the strake wing/canard wing pitching angle, and changing the mode of regulating the strake wing/canard wing pitching angle through a fixed angle plate in a static mode in the conventional wind tunnel test.
Description
Technical field
The present invention relates to a kind of aircraft model in wind tunnel strake wing/canard angle of pitch controlled motion system.
Background technology
In traditional airplane design, strake wing is relatively fixed with aircraft as a fixed component, and in layout type selecting
When, in order to determine the relativeness between strake wing and aircraft, some are designed in wind tunnel test simulation and fix gusset plate, for solid
Fixed and connection strake wing and model aircraft, but these gusset plates can only realize the angle of existing design, it is impossible to continuous adjustment or dynamic
Change.
In traditional airplane design, canard is a primary control surface.Some are designed in wind tunnel test simulation and fix gusset plate,
For fixing and connecting canard and model aircraft, these gusset plates can only realize the angle of existing design, it is impossible to which continuous adjustment is dynamic
State changes.
With the lifting of aircraft topology, new use demand is proposed to strake wing/canard：Need in some cases
Strake wing/canard angle consecutive variations, for realizing static cost control；Strake wing/canard dynamic is needed to change shape in some cases
State, plays rudder face effect or active Flow Control effect.Therefore, traditional fixed gusset plate connected mode can not meet this
Demand.
The content of the invention
For problem above, the present invention discloses a kind of aircraft model in wind tunnel strake wing/canard angle of pitch controlled motion
System, including body joint component, model aircraft longitudinal body axis, the first left lock-screw, left connecting shaft, left strake wing/duck
The wing, left strake wing/canard rotating shaft, left bearing, left shaft holder, the second left lock-screw, left commutation bevel gear are to, the 3rd left locking
Screw, left motor mount, left motor and encoder, left main wing, the first right lock-screw, right connecting shaft, right strake wing/duck
The wing, right strake wing/canard rotating shaft, right bearing, right axle bearing, right motor mount, right motor and encoder, the 3rd right locking screw
Nail, right commutation bevel gear to, the second right lock-screw, right main wing, computer, left motor driver and right motor driver；It is left
Main wing, right main wing, left shaft holder, left motor mount, right axle bearing and right motor mount are each attached to body joint component
On；Left strake wing/canard is fixed with left strake wing/canard rotating shaft, and left strake wing/canard rotating shaft is connected with left connecting shaft left end,
And fixed by two the first left lock-screws, left connecting shaft right-hand member is connected with the lower gear of left commutation bevel gear pair, and is passed through
Two the second left lock-screws are fixed, and are supported by left bearing in the middle part of left connecting shaft, and left bearing is arranged on left shaft holder；Left motor
And encoder is threaded connection on left motor mount, the output shaft of left motor and encoder and left commutation bevel gear
To gear connection, and fixed by two the 3rd left lock-screws；Right strake wing/canard and right strake wing/canard rotating shaft
Fixed, right strake wing/canard rotating shaft is connected with right connecting shaft right-hand member, and is fixed by two the first right lock-screws, right connection
Axle left end is connected with the lower gear of right commutation bevel gear pair, and is fixed by two the second right lock-screws, in the middle part of right connecting shaft
Supported by right bearing, right bearing is arranged in right axle bearing；Right motor and encoder are threaded connection pacifies installed in right motor
On dress seat, it is fixed on body joint component, the output shaft of right motor and encoder is connected with the gear of right commutation bevel gear pair
Connect, and fixed by two the 3rd right lock-screws；Left strake wing/canard rotating shaft cloth vertical with the axis of left motor and encoder
Put in a plane, right strake wing/canard rotating shaft is arranged vertically in a plane with the axis of right motor and encoder；It is left
Strake wing/canard shaft axis and right strake wing/canard shaft axis are faced along the longitudinally asymmetric of model aircraft longitudinal body axis
Claim arrangement.
Computer is connected by the signal of telecommunication with left motor driver and right motor driver, and computer is by left Motor drive
Motor and encoder and right motor and encoder send control instruction to the left respectively for device and right motor driver, control left motor and
Encoder and right motor and encoder realize controllable deflection；Left motor and encoder are by left connecting shaft and are fixed on left connecting shaft
On left commutation bevel gear to driving left strake wing/canard rotating shaft and left strake wing/canard around left strake wing/canard shaft axis
Deflection, realizes left strake wing/canard angle of pitch controlled motion；Right motor and encoder are by right connecting shaft and are fixed on right connection
Right commutation bevel gear on axle is to driving right strake wing/canard rotating shaft and right strake wing/canard around right strake wing/canard rotating shaft axle
Line is deflected, and realizes right strake wing/canard angle of pitch controlled motion；Left motor and encoder and right motor and encoder can be electricity
The real time position feedback of machine gives left electric machine controller and right electric machine controller, then feeds back to computer accurately to determine real-time position
Put, realize that position is fed back.
The present invention also has following technical characteristic：
1st, a kind of aircraft model in wind tunnel strake wing/canard angle of pitch controlled motion system as above, its control
And feedback specific implementation step is：
The first step, motor driver and right motor driver send deflection control instruction and synchronous/asynchronous to computer to the left
Control instruction；
Second step, left motor driver and right motor driver are respectively transmitted instruction to left motor and encoder and right electricity
Machine and encoder；
3rd step, left motor and encoder and right motor and encoder drive left strake wing/canard rotating shaft and the right respectively
The bar wing/canard rotating shaft realizes that mandatory rotation, left strake wing/canard rotating shaft and right strake wing/canard rotating shaft drive the left side respectively
The bar wing/canard and right strake wing/canard realize mandatory rotation；
4th step, left motor and encoder and right motor and encoder real-time position information are fed back to left motor respectively and are driven
Dynamic device and right motor driver, and then computer is fed back to again, for feedback control.
2nd, the deflection control instruction of left and right edge strip as above has three kinds of modes, and respectively staged deflection control refers to
Make, uniform motion control instruction harmonic oscillating movement control instruction；Wherein, staged deflection control instruction can realize edge strip
The step variation of the wing/canard angle of pitch, i.e., it is static to adjust angle of pitch angle；Uniform motion control instruction can adjust left side bar
The displacement of the wing/canard and left strake wing/canard rotating shaft uniform motion and speed, realize that strake wing/canard angle of pitch at the uniform velocity changes；
Harmonic oscillation motion control instruction can adjust the amplitude of left strake wing/canard and left strake wing/canard pivot, frequency and
Starting phase angle.
3rd, the synchronous/asynchronous control instruction of left strake wing/canard as above and right strake wing/canard has five kinds of sides
Formula, respectively individually deflects control instruction, homophase bit synchronization deflection control instruction, antiphase i.e. 180 ° phase contrasts synchronously deflection control
Synchronously deflection control instruction and the asynchronous controlling instruction of system instruction, random phase difference；Wherein, individually deflection control instruction is used to realize
Left strake wing/canard or the individually controllable deflection of right strake wing/canard, homophase bit synchronization deflection control instruction are used to realize left side bar
The controllable deflection of homophase bit synchronization of the wing/canard and right strake wing/canard, i.e. 180 ° phase contrasts of antiphase synchronously deflect control instruction
For realizing the controllable deflection of anti-phase bit synchronization of left strake wing/canard and right strake wing/canard, random phase difference synchronously deflection control
For realizing the synchronous deflection of left strake wing/canard and right strake wing/canard random phase difference, asynchronous controlling instruction is used for system instruction
In the asynchronous controllable deflection for realizing left strake wing/canard and right strake wing/canard.
Advantages and advantages of the invention：
The present invention changes biography by a kind of aircraft model in wind tunnel strake wing/canard angle of pitch controlled motion system
The wind tunnel test of system can either realize static test institute by the way of the static adjustment strake wing/canard angle of pitch of fixed gusset plate
The stepped change of the strake wing of requirement/canard angle of pitch, can realize the strake wing/canard angle of pitch required by dynamic test again
Dynamic change, while the kinematic parameter of strake wing/canard angle of pitch can be controlled, realize strake wing/canard aerodynamic
The favourable interference of vortex system and main wing aerodynamic vortex system, so as to realize rudder face effect or active Flow Control.
Description of the drawings
Fig. 1 strake wings/canard angle of pitch controlled motion aircraft model in wind tunnel overall construction drawing；
Fig. 2 strake wings/canard angle of pitch controlled motion aircraft model in wind tunnel partial enlarged drawing one；
Fig. 3 strake wings/canard angle of pitch controlled motion aircraft model in wind tunnel partial enlarged drawing two；
Fig. 4 strake wings/canard angle of pitch controlled motion control system schematic diagram；
Specific embodiment
Further illustrate below according to accompanying drawing citing：
Embodiment 1
As shown in figure 1, a kind of aircraft model in wind tunnel strake wing/canard angle of pitch controlled motion system, including fuselage
Nose assembly 1, model aircraft longitudinal body axis 2, the first left lock-screw 3, left connecting shaft 4, left strake wing/canard 5, left side bar
The wing/canard rotating shaft 6, left bearing 8, left shaft holder 9, the second left lock-screw 10, left commutation bevel gear are to the 11, the 3rd left locking screw
Nail 12, left motor mount 13, left motor and encoder 14, left main wing 15, the first right lock-screw 16, right connecting shaft 17, the right side
Strake wing/canard 18, right strake wing/canard rotating shaft 19, right bearing 21, right axle bearing 22, right motor mount 23, right motor and
Encoder 24, the 3rd right lock-screw 25, right commutation bevel gear are to the 26, second right lock-screw 27, right main wing 28, computer
29th, left motor driver 30 and right motor driver 31；Left main wing 15, right main wing 28, left shaft holder 9, left motor mount 13,
Right axle bearing 22 and right motor mount 23 are each attached on body joint component 1；Left strake wing/canard 5 and left strake wing/duck
Wing rotating shaft 6 is fixed, and left strake wing/canard rotating shaft 6 is connected with 4 left end of left connecting shaft, and solid by two the first left lock-screws 3
Fixed, 4 right-hand member of left connecting shaft is connected to 11 lower gear with left commutation bevel gear, and solid by two the second left lock-screws 10
It is fixed, supported by left bearing 8 in the middle part of left connecting shaft 4, left bearing 8 is arranged on left shaft holder 9；Left motor and encoder 14 pass through spiral shell
Stricture of vagina connection on the left motor mount 13, the output shaft of left motor and encoder 14 and left commutation upper tooth of the bevel gear to 11
Wheel connection, and fixed by two the 3rd left lock-screws 12；Right strake wing/canard 18 is solid with right strake wing/canard rotating shaft 19
Fixed, right strake wing/canard rotating shaft 19 is connected with 17 right-hand member of right connecting shaft, and is fixed by two the first right lock-screws 16, right
17 left end of connecting shaft is connected to 26 lower gear with right commutation bevel gear, and is fixed by two the second right lock-screws 27, right
Supported by right bearing 21 in the middle part of connecting shaft 17, right bearing 21 is arranged in right axle bearing 22；Right motor and encoder 24 pass through spiral shell
Stricture of vagina connection is fixed on body joint component 1 on the right motor mount 23, the output shaft of right motor and encoder 24 with
Right commutation bevel gear connects to 26 gear, and is fixed by two the 3rd right lock-screws 25；Left strake wing/canard rotating shaft
6 are arranged vertically in a plane with the axis of left motor and encoder 14, right strake wing/canard rotating shaft 19 and right motor and volume
The axis of code device 24 is arranged vertically in a plane；Left strake wing/canard shaft axis 7 and right strake wing/canard rotating shaft axle
Line 20 is arranged symmetrically along the longitudinally asymmetric face of model aircraft longitudinal body axis 2.
Computer 29 is connected by the signal of telecommunication with left motor driver 30 and right motor driver 31, and computer 29 is by a left side
Motor and encoder 14 and right motor and the transmission control of encoder 24 to the left respectively of motor driver 30 and right motor driver 31
Instruction, controls left motor and encoder 14 and right motor and encoder 24 realizes controllable deflection；Left motor and encoder 14 pass through
Left connecting shaft 4 and the left commutation bevel gear being fixed in left connecting shaft 4 drive left strake wing/canard rotating shaft 6 and left side bar to 11
The wing/canard 5 is deflected around left strake wing/canard shaft axis 7, realizes 5 angle of pitch controlled motion of left strake wing/canard, deflection angle
Degree scope is adjustable, and angle can be with consecutive variations；Deflection can be stepped, for static test, or dynamic；
Right motor and encoder 24 drive the right to 26 by right connecting shaft 17 and the right commutation bevel gear being fixed in right connecting shaft 17
The bar wing/canard rotating shaft 19 and right strake wing/canard 18 are deflected around right strake wing/canard shaft axis 20, realize right strake wing/duck
18 angle of pitch controlled motion of the wing, range of deflection angles is adjustable, and angle can be with consecutive variations；Deflection can be stepped, use
In static test, or dynamically；Left motor and encoder 14 and right motor and encoder 24 can be the real-time of motor
Position feeds back to left electric machine controller and right electric machine controller, then feeds back to computer 29 accurately to determine real time position, realizes
Feed back position.
Embodiment 2
The deflection control instruction of left and right edge strip has three kinds of modes：
(1) staged deflection control instruction, can realize the step variation of strake wing/canard angle of pitch, i.e., static to adjust
Section angle of pitch angle, for static test；
(2) uniform motion control instruction, can adjust displacement and the speed of motion, can realize strake wing/canard pitching
The at the uniform velocity change at angle, both can be used for dynamic deflection test to test dynamic effect, the i.e. dynamic regulation angle of pitch of edge strip deflection
Angle, can obtain the favourable interference of strake wing/canard aerodynamic vortex system and main wing aerodynamic vortex system, again so as to reality
Show active Flow Control or act on, improve the air dynamic behaviour of aircraft equivalent to rudder face；Above-mentioned strake wing/canard contains the left side
The bar wing/canard 5 and right strake wing/canard 18, main wing contain left main wing 15 and right main wing 28；
(3) harmonic oscillation motion control instruction, can adjust amplitude, frequency and the starting phase angle of motion, for obtaining
The favourable interference of strake wing/canard aerodynamic vortex system and main wing aerodynamic vortex system, so as to realizing active Flow Control
Or the air dynamic behaviour of aircraft is acted on, is improved equivalent to rudder face；Above-mentioned strake wing/canard contains left strake wing/canard 5 and the right side
Strake wing/canard 18, main wing contain left main wing 15 and right main wing 28.
Embodiment 3
The synchronous/asynchronous control instruction of left strake wing/canard 5 and right strake wing/canard 18 has five kinds of modes：
(1) the independent deflection control instruction of left strake wing/canard 5 or right strake wing/canard 18, for realize left strake wing/
The 18 individually controllable deflection of canard 5 or right strake wing/canard；
(2) the homophase bit synchronization deflection control instruction of left strake wing/canard 5 and right strake wing/canard 18, for realizing a left side
The controllable deflection of homophase bit synchronization of strake wing/canard 5 and right strake wing/canard 18；
(3) synchronously deflection control refers to i.e. 180 ° phase contrasts of the antiphase of left strake wing/canard 5 and right strake wing/canard 18
Order, for realizing the controllable deflection of anti-phase bit synchronization of left strake wing/canard 5 and right strake wing/canard 18；
(4) random phase difference of left strake wing/canard 5 and right strake wing/canard 18 synchronously deflects control instruction, for reality
The synchronous deflection of existing left strake wing/canard 5 and right 18 random phase difference of strake wing/canard；
(5) the asynchronous controlling instruction of left strake wing/canard 5 and right strake wing/canard 18, for realizing left strake wing/duck
The asynchronous controllable deflection of the wing 5 and right strake wing/canard 18.
Embodiment 4
Control and feedback specific implementation step are：
The first step, motor driver 30 and right motor driver 31 send deflection control instruction and same to computer 29 to the left
Step/asynchronous controlling is instructed；
Second step, left motor driver 30 and right motor driver 31 are respectively transmitted instruction to left motor and encoder 14
With right motor and encoder 24；
3rd step, left motor and encoder 14 and right motor and encoder 24 drive left strake wing/6 He of canard rotating shaft respectively
Right strake wing/canard rotating shaft 19 realizes that mandatory rotation, left strake wing/canard rotating shaft 6 and right strake wing/canard rotating shaft 19 are distinguished
Left strake wing/canard 5 and right strake wing/canard 18 is driven to realize mandatory rotation；
Real-time position information is fed back to left electricity respectively for 4th step, left motor and encoder 14 and right motor and encoder 24
Machine driver 30 and right motor driver 31, and then computer 29 is fed back to again, for feedback control.
Claims (4)
- A kind of 1. aircraft model in wind tunnel strake wing/canard angle of pitch controlled motion system, including body joint component (1), Model aircraft longitudinal body axis (2), the first left lock-screw (3), left connecting shaft (4), left strake wing/canard (5), left side bar The wing/canard rotating shaft (6), left bearing (8), left shaft holder (9), the second left lock-screw (10), left commutation bevel gear to (11), the Three left lock-screws (12), left motor mount (13), left motor and encoder (14), left main wing (15), the first right locking screw Nail (16), right connecting shaft (17), right strake wing/canard (18), right strake wing/canard rotating shaft (19), right bearing (21), right bearing Seat (22), right motor mount (23), right motor and encoder (24), the 3rd right lock-screw (25), right commutation bevel gear pair (26), the second right lock-screw (27), right main wing (28), computer (29), left motor driver (30) and right motor driver (31)；Left main wing (15) and right main wing (28) are fixed on body joint component (1)；Characterized in that, left shaft holder (9), a left side Motor mount (13), right axle bearing (22) and right motor mount (23) are each attached on body joint component (1)；Left side bar The wing/canard (5) is fixed with left strake wing/canard rotating shaft (6), and left strake wing/canard rotating shaft (6) is connected with left connecting shaft (4) left end Connect, and by two the first left lock-screws (3) fixations, left connecting shaft (4) right-hand member and left commutation lower tooth of the bevel gear to (11) Wheel connection, and it is fixed by two the second left lock-screws (10), supported by left bearing (8) in the middle part of left connecting shaft (4), left bearing (8) on left shaft holder (9)；Left motor and encoder (14) are fixed on left motor mount (13), left motor and volume The output shaft of code device (14) is connected to the gear of (11) with left commutation bevel gear, and passes through two the 3rd left lock-screws (12) It is fixed；Right strake wing/canard (18) and right strake wing/canard rotating shaft (19) fixation, right strake wing/canard rotating shaft (19) and right company Spindle (17) right-hand member connects, and fixed by two the first right lock-screws (16), and right connecting shaft (17) left end and right commutation are bored The lower gear connection of gear mesh (26), and it is fixed by two the second right lock-screws (27), by the right side in the middle part of right connecting shaft (17) Bearing (21) is supported, and right bearing (21) is in right axle bearing (22)；Right motor and encoder (24) are fixed on right motor peace On dress seat (23), the output shaft of right motor and encoder (24) is connected to the gear of (26) with right commutation bevel gear, and is passed through Two the 3rd right lock-screws (25) are fixed；Left strake wing/canard rotating shaft (6) is vertical with the axis of left motor and encoder (14) It is arranged in a plane, right strake wing/canard rotating shaft (19) is arranged vertically on one with the axis of right motor and encoder (24) In individual plane；Left strake wing/canard shaft axis (7) and right strake wing/canard shaft axis (20) are along model aircraft body shafting The longitudinally asymmetric face of the longitudinal axis (2) is arranged symmetrically；Computer (29) is logical with left motor driver (30) and right motor driver (31) Signal of telecommunication connection is crossed, computer (29) distinguishes motor and volume to the left by left motor driver (30) and right motor driver (31) Code device (14) and right motor and encoder (24) send control instruction, control left motor and encoder (14) and right motor and coding Device (24) realizes controllable deflection；Left motor and encoder (14) is by left connecting shaft (4) and is fixed in left connecting shaft (4) Left commutation bevel gear drives left strake wing/canard rotating shaft (6) and left strake wing/canard (5) to turn around left strake wing/canard to (11) Axle axis (7) is deflected, and realizes left strake wing/canard (5) angle of pitch controlled motion；Right motor and encoder (24) are by right connection Axle (17) and the right commutation bevel gear being fixed in right connecting shaft (17) drive right strake wing/canard rotating shaft (19) and the right side to (26) Around right strake wing/canard shaft axis (20) deflection, strake wing/canard (18) realizes that right strake wing/canard (18) angle of pitch can Control motion；Left motor and encoder (14) and right motor and encoder (24) can give left motor the real time position feedback of motor Driver and right motor driver, then feed back to computer (29) accurately to determine real time position, realize that position is fed back.
- 2. a kind of aircraft model in wind tunnel strake wing according to claim 1/canard angle of pitch controlled motion system, its It is characterised by, its control and feedback specific implementation step are：The first step, motor driver (30) and right motor driver (31) send deflection control instruction and same to computer (29) to the left Step/asynchronous controlling is instructed；Second step, left motor driver (30) and right motor driver (31) are respectively transmitted instruction to left motor and encoder And right motor and encoder (24) (14)；3rd step, left motor and encoder (14) and right motor and encoder (24) drive left strake wing/canard rotating shaft (6) respectively Mandatory rotation, left strake wing/canard rotating shaft (6) and right strake wing/canard rotating shaft are realized with right strake wing/canard rotating shaft (19) (19) left strake wing/canard (5) and right strake wing/canard (18) is driven to realize mandatory rotation respectively；Real-time position information is fed back to left electricity respectively for 4th step, left motor and encoder (14) and right motor and encoder (24) Machine driver (30) and right motor driver (31), and then computer (29) is fed back to again, for feedback control.
- 3. a kind of aircraft model in wind tunnel strake wing according to claim 1/canard angle of pitch controlled motion system, its It is characterised by, the deflection control instruction of described left strake wing/canard (5) and left strake wing/canard rotating shaft (6) there are three kinds of sides Formula, respectively staged deflection control instruction, uniform motion control instruction harmonic oscillating movement control instruction；Wherein, ladder Formula deflection control instruction can realize the step variation of strake wing/canard angle of pitch, i.e., static to adjust angle of pitch angle；At the uniform velocity Motion control instruction can adjust displacement and the speed of left strake wing/canard (5) and left strake wing/canard rotating shaft (6) uniform motion Degree, realizes that strake wing/canard angle of pitch at the uniform velocity changes；Harmonic oscillation motion control instruction can adjust left strake wing/canard (5) Amplitude, frequency and the starting phase angle moved with left strake wing/canard rotating shaft (6).
- 4. a kind of aircraft model in wind tunnel strake wing according to claim 1/canard angle of pitch controlled motion system, its It is characterised by, the synchronous/asynchronous control instruction of described left strake wing/canard (5) and right strake wing/canard (18) there are five kinds of sides Formula, respectively individually deflects control instruction, homophase bit synchronization deflection control instruction, antiphase i.e. 180 ° phase contrasts synchronously deflection control Synchronously deflection control instruction and the asynchronous controlling instruction of system instruction, random phase difference；Wherein, individually deflection control instruction is used to realize Left strake wing/canard (5) or the individually controllable deflection of right strake wing/canard (18), homophase bit synchronization deflection control instruction are used for real Existing left strake wing/canard (5) and the controllable deflection of homophase bit synchronization of right strake wing/canard (18), antiphase is 180 ° of phase contrasts Synchronous deflection control instruction is controllable partially for the anti-phase bit synchronization for realizing left strake wing/canard (5) and right strake wing/canard (18) Turn, synchronously deflection control instruction is used to realize left strake wing/canard (5) and right strake wing/canard (18) arbitrarily random phase difference The synchronous deflection of phase contrast, asynchronous controlling are instructed for realizing the different of left strake wing/canard (5) and right strake wing/canard (18) Walk controllable deflection.
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| CN105628327B (en) * | 2015-12-24 | 2018-06-01 | 中国航天空气动力技术研究院 | A kind of two axis rudder of wire rope gearing formula controls device for measuring force partially |
| CN107416157B (en) * | 2017-07-13 | 2020-05-19 | 华中科技大学 | Deformable observation device of deep sea underwater observation platform |
| CN107830987B (en) * | 2017-12-04 | 2024-04-12 | 中国航空工业集团公司沈阳空气动力研究所 | Six-degree-of-freedom mechanism store strut for capture track test based on bevel gear transmission |
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