CN105857580A - Fixing device of aircraft control system - Google Patents
Fixing device of aircraft control system Download PDFInfo
- Publication number
- CN105857580A CN105857580A CN201610323090.7A CN201610323090A CN105857580A CN 105857580 A CN105857580 A CN 105857580A CN 201610323090 A CN201610323090 A CN 201610323090A CN 105857580 A CN105857580 A CN 105857580A
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- Prior art keywords
- pedal
- fixing device
- fixture block
- control wheel
- auricle
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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
- B64C13/04—Initiating means actuated personally
-
- 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
- B64C13/14—Initiating means actuated personally lockable
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
- Finger-Pressure Massage (AREA)
Abstract
The invention relates to a fixing device of an aircraft control system, and belongs to the technical field of aeroelastic effect tests. The device comprises pedal fixing units (1), steering wheel fixing units (2), a basis (3) and support bar systems (4), wherein one end of each pedal fixing unit is connected with the basis, and a clamping end is arranged at the other end of each pedal fixing unit and is used for clamping a pedal connecting tube of an aircraft pedal; one end of each support bar system is connected to the basis, and the other end extends toward an aircraft steering wheel to form a hollow tube; each hollow tube is used for muff-coupling and fixing an end part of the corresponding steering wheel fixing unit; a second clamping end is arranged at the other end of each steering wheel fixing unit, and is used for clamping a steering wheel control handle of the aircraft steering wheel. Through the device, whole aircraft control system fixation can be realized in the process of an aircraft ground resonance test, each part is prevented from relative displacement in the fixation process, and measurement of each control surface rotating frequency in the resonance test is ensured.
Description
Technical field
The invention belongs to aeroelastic effect test technical field, especially relate to a kind of flight control system solid
Determine device.
Background technology
Universal aircraft generally uses rope driven reversible steerable system, is carrying out the examination of full machine ground resonance
When testing, if each rudder face is not fixed, then it is difficult to measure the speed of rudder face.It is thus desirable to it is right
The each control surface of aircraft is fixed in neutral position, and this support requires to be fixed at manipulatable end, except making
Obtain control wheel and pedal can not have outside relative motion under the limited External Force Acting of rudder face, also should ensure that whole manipulation
The manipulation rigidity of system circuit is unaffected, simultaneously the most not the control wheel of wrap up and the outward appearance of pedal and knot
Structure.In prior art, universal aircraft full machine ground resonance test generally by aircraft itself carry simple
Detent mechanism realizes control surface fixing in neutral position, or uses screw rod dieback control stick and the side of pedal
Formula, it is difficult to accomplish stable, all the time, gapless fixing, it is also possible to destroy control wheel and pedal
Outward appearance and structure, simultaneously when in process of the test, rudder face is encouraged by external force, easily disengage, fixed effect
Undesirable, the error of test data obtained in the case is the biggest.
Summary of the invention
In order to solve the problems referred to above, the invention provides a kind of flight control system fixing device, for flying
Fix steerable system during machine ground resonance test, play holding each control surface effect in neutral position.
Described device includes pedal fixing device, control wheel fixing device, sole plate and braced bar system,
Wherein, one end of pedal fixing device connects described sole plate, and the other end is provided with the first bare terminal end, institute
Stating the first bare terminal end for clamping the pedal connecting tube of airplane tread, one end of described braced bar system is connected to base
On plinth base, the other end extends to control wheel direction and forms hollow pipe, and described hollow pipe is for socket also
The end of fixing described control wheel fixing device, the other end of control wheel fixing device is provided with the second clamping
End, described second bare terminal end is for clamping the control of the yoke handle of control wheel.
Preferably, described first bare terminal end includes the pedal fixture block base being arranged on pedal fixing device end
And the pedal fixture block auricle being detachably connected on pedal fixture block base, pedal fixture block base and pedal fixture block
During the fixing connection of auricle, forming the first columnar through holes, pedal connecting tube adaptation can be arranged on described first post
In shape through hole.
In such scheme preferably, between the inwall of described pedal connecting tube and described first columnar through holes
It is provided with pedal fixture block cushion pad.
In such scheme preferably, pedal fixture block cushion pad is the ring-type cushion block of rubber.
Preferably, described second bare terminal end includes the control wheel fixture block being arranged on control wheel fixing device end
Base and the control wheel fixture block auricle being detachably connected on control wheel fixture block base, control wheel fixture block base
Fixing with control wheel fixture block auricle when being connected, form the second columnar through holes, control of the yoke handle can adaptation
It is arranged in described second columnar through holes.
In such scheme preferably, between the inwall of control of the yoke handle and described second columnar through holes
It is provided with control wheel fixture block cushion pad.
In such scheme preferably, control wheel fixture block cushion pad is the ring-type cushion block of rubber.
Preferably, described sole plate includes front-axle beam, the back rest and for connecting the connection of front-axle beam and the back rest
Side plate, front-axle beam extends to the direction of pedal fixing device and forms forward direction auricle, is used for connecting described pedal and fixes
Device, the back rest extends to the direction of braced bar system and forms auricle base, is used for connecting described braced bar system.
, described front-axle beam being additionally provided with backward auricle, described braced bar system exists in such scheme preferably
One end away from auricle base is provided with switching auricle, and backward auricle is mutual by oblique drawbar with switching auricle
Connect.
Preferably, one end being connected with hollow pipe of control wheel fixing device is column structure, hollow pipe
Inside pipe wall diameter is not less than the end face diameter of described column structure, and is provided with on the sidewall of described hollow pipe certainly
The notch that hollow pipe end face extends in the middle part of hollow pipe, when the column structure end face of described control wheel fixing device
When being positioned at hollow pipe, indicator clip clamps described hollow pipe, and can make the inside pipe wall of described hollow pipe
Compress the column structure end face of described control wheel fixing device.
Preferably, after connecting lateral plate is connected with front-axle beam and the back rest respectively, then it is fixedly mounted on aircraft cockpit
On the basis of, based on generally choosing the slide rail of pilot set.
The universal flight control system fixing device of present invention design, can be in aircraft floor resonance test mistake
Journey realizes full machine steerable system fix, so that each control surface is maintained at neutral position, in fixation procedure
In each parts will not produce relative displacement, outward appearance and the structure of flight control system will not be destroyed simultaneously, permissible
Ensure the measurement of resonance test each control surface speed.
Accompanying drawing explanation
Fig. 1 be a preferred embodiment of flight control system fixing device of the present invention and equipment connection structure
Schematic diagram.
Fig. 2 is the steerable system fixture structure schematic diagram of embodiment illustrated in fig. 1.
Fig. 3 is the pedal fixture structure schematic diagram of embodiment illustrated in fig. 1.
Fig. 4 is the control wheel fixture structure schematic diagram of embodiment illustrated in fig. 1.
Fig. 5 is the braced bar system structural representation of embodiment illustrated in fig. 1.
Wherein, 1 is pedal fixing device, and 2 is control wheel fixing device, base based on 3, and 4 for supporting
Leverage, 5 is pedal connecting tube, and 6 is control of the yoke handle；
11 is pedal fixture block base, and 12 is pedal fixture block auricle, and 13 is pedal fixture block cushion pad；
21 is control wheel fixture block base, and 22 is control wheel fixture block auricle, and 23 is control wheel fixture block cushion pad；
31 is front-axle beam, and 32 is the back rest, and 33 is connecting lateral plate, and 34 is forward direction auricle, and 35 is backward auricle,
36 is auricle base；
41 is hollow pipe, and 42 is switching auricle, and 43 is oblique drawbar, and 44 is indicator clip.
Detailed description of the invention
Clearer, below in conjunction with the present invention for the purpose making the present invention implement, technical scheme and advantage
Accompanying drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the present invention.Attached
In figure, the most same or similar label represents same or similar element or has same or like
The element of function.Described embodiment is a part of embodiment of the present invention rather than whole enforcement
Example.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for explaining the present invention, and
It is not considered as limiting the invention.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under not making creative work premise, broadly falls into present invention protection
Scope.Below in conjunction with the accompanying drawings embodiments of the invention are described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " horizontal stroke
To ", "front", "rear", "left", "right", " vertically ", " level ", " top ",
Orientation or the position relationship of the instruction such as " end " " interior ", " outward " are based on orientation shown in the drawings or position
Put relation, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that
Limiting the scope of the invention.
Below by embodiment, the present invention is described in further details.
The invention provides a kind of flight control system fixing device, in aircraft floor resonance test process
In fix steerable system, play holding the effect in neutral position of each control surface.
Described device is as it is shown in figure 1, mainly include pedal fixing device 1, control wheel fixing device 2, base
Plinth base 3 and braced bar system 4, wherein, one end of pedal fixing device 1 connects described sole plate 3,
The other end is provided with the first bare terminal end, and described first bare terminal end is for clamping the pedal connecting tube of airplane tread
5, one end of described braced bar system 4 is connected on sole plate 3, and the other end prolongs to control wheel direction
Stretching formation hollow pipe, described hollow pipe, for being socketed and fix the end of described control wheel fixing device 2, is driven
The other end sailing tray fixing device 2 is provided with the second bare terminal end, and described second bare terminal end is used for clamping aircraft and drives
Sail the control of the yoke handle 6 of dish.
It is understood that pedal fixing device 1 quantity is two, structure is identical, is separately fixed at two
In pedal connecting tube 5, the quantity of braced bar system 4 is two, and structure is identical, vertical is arranged on sole plate
On 3, for connecting the control wheel fixing device 2 that two structures are identical, control of the yoke handle 6 includes two
Individual tubulose bindiny mechanism, Liang Ge tubulose bindiny mechanism adaptation respectively is arranged on above-mentioned two control wheel fixing device
On 2.
In the present embodiment, as it is shown on figure 3, described first bare terminal end includes being arranged on pedal fixing device 1
The pedal fixture block base 11 of end and the pedal fixture block auricle being detachably connected on pedal fixture block base 11
12, pedal fixture block base 11 is fixed with pedal fixture block auricle 12 when being connected, and forms the first columnar through holes, foot
Pedal connecting tube 5 can adaptation be arranged in described first columnar through holes.
It is understood that pedal fixture block base 11 and pedal fixture block auricle 12 are provided with semicolumn structure
Groove, when by modes such as bolts above-mentioned two assembly merged install time, two semicolumn structures recessed
Groove docks mutually, forms the through hole of column structure, the i.e. first columnar through holes.
It should be noted that the first columnar through holes size adapts to pedal connecting tube 5, the such as first column is led to
The hole internal diameter in hole is slightly less than the diameter of pedal connecting tube 5, so, when by pedal fixture block base 11 and foot
Pedal fixture block auricle 12 time pedal connecting tube 5 is clamped in centre, pedal fixture block base 11 and pedal fixture block ear
Sheet 12 interface will leave a fixed gap, now, pedal fixing device 1 can be made to have by tighting a bolt
Effect clamping pedal connecting tube 5.
In the present embodiment, between the inwall of described pedal connecting tube 5 and described first columnar through holes, it is provided with foot
Pedal fixture block cushion pad 13, thus the effect of protection pedal connecting tube 5 can be played, pedal can be increased again even
Friction between adapter 5 and described first columnar through holes, meanwhile, pedal fixture block cushion pad is set by the present embodiment
Being set to the ring-type cushion block of rubber, it also has certain elasticity, it is possible to connecting pedal fixture block base 11 and foot
The bolt pedaling fixture block auricle 12 plays locking effect, and in alternate embodiment, the bolt at this can also make
Use self-locking screw.
Needing further exist for explanation, in concrete installation process, left side pedal fixture block cushion pad is connected to
After on left side pedal fixture block base and left side pedal fixture block auricle, then it is arranged on the pedal below the pedal of left side even
In adapter, then it is connected with the forward direction auricle 34 on sole plate 3, right side pedal fixture block base, right side
Pedal fixture block auricle, right side pedal fixture block cushion pad is similar with the connected mode in left side.Due to the fixing dress of pedal
Putting 1 to be connected by bolt assembly with pedal connecting tube 5, pedal fixing device 1 can be along pedal connecting tube 5
Axis direction move, in preferred forms, pedal fixing device 1 and pedal connecting tube 5 link position
Middle part for pedal connecting tube 5.
Forward direction auricle 34 with continued reference to Fig. 3, pedal fixing device 1 and sole plate 3 is connected, than
As being bolted, can readjust by a small margin at link position before bolt is tightened, after bolt is tightened
Must not there is any relative displacement, play the effect of fastening aircraft pedal steerable system, additionally need explanation,
The auricle structure that the present invention mentions is the structure of the formation that stretches out from auricle connection main body, and this structure is far
The one end connecting main body from auricle is provided with the adaptive bolt hole with bolt or circular hole.
Similar with the first bare terminal end structure, as shown in Figure 4, described second bare terminal end includes being arranged on control wheel
The control wheel fixture block base 21 of fixing device 2 end and be detachably connected on control wheel fixture block base 21
On control wheel fixture block auricle 22, control wheel fixture block base 21 and control wheel fixture block auricle 22 is fixing to be connected
Time, forming the second columnar through holes, control of the yoke handle 6 adaptation can be arranged on described second columnar through holes
In.
It is understood that control wheel fixture block base 21 and control wheel fixture block auricle 22 are provided with semicolumn
The groove of structure, when above-mentioned two assembly being merged installation by modes such as bolts, two semicolumn structures
Groove dock mutually, formed column structure through hole, the i.e. second columnar through holes.
It should be noted that the second columnar through holes size adapts to control of the yoke handle 6, the such as second post
The hole internal diameter of shape through hole is slightly less than the diameter of control of the yoke handle 6, so, at the bottom of by control wheel fixture block
When control of the yoke handle 6 is clamped in centre by seat 21 and control wheel fixture block auricle 22, at the bottom of control wheel fixture block
Seat 21 and control wheel fixture block auricle 22 interface will leave a fixed gap, now, by tighting a bolt energy
Control wheel fixing device 2 is made effectively to clamp control of the yoke handle 6.
In the present embodiment, arrange between the inwall of described control of the yoke handle 6 and described second columnar through holes
There is control wheel fixture block cushion pad 23, thus the effect of protection control of the yoke handle 6 can be played, again can
Increasing the friction between control of the yoke handle 6 and described second columnar through holes, meanwhile, the present embodiment will be driven
Sailing disk folder block buffering pad 23 and be set to the ring-type cushion block of rubber, it also has certain elasticity, it is possible to connection
Control wheel fixture block base 21 plays locking effect, alternate embodiment with the bolt of control wheel fixture block auricle 22
In, the bolt at this can also use self-locking screw.
Need further exist for explanation, in concrete installation process, left handle drive disk folder block base, left side
Control wheel fixture block auricle is sailed disk folder block buffering pad and is coordinated and be arranged in control wheel left side handle with left side, then will
On the left of the bottom insertion of left handle drive disk folder block base in vertical connection hollow pipe, then use left side indicator clip
It is connected hollow circular-tube fixes vertical to itself and left side, right hand drive disk folder block base, right hand drive disk folder block
The installation that auricle, right side sail disk folder block buffering pad and right side indicator clip is similar with left side.Control wheel is solid
The fixture block cushion pad determining device 2 is installed on control wheel fixture block base 21, then passes through fixture block auricle 22 and drive
Sailing dish handle to be connected, control wheel fixture block cushion pad 23 uses elastomeric material, the outward appearance of protection handle and knot
Structure is not damaged when clamping, before bolt is tightened, can readjust by a small margin clip position, and bolt is twisted
After Jin, must not there is any relative displacement, play fastening aircraft control-stick assembly in the effect specifying position.
It should be noted that left and right side clamp springs chip architecture is as shown in Figure 4, before it is explained,
First it is necessary braced bar system 4 is described further, as it is shown in figure 5, be braced bar system structural representation,
It includes hollow pipe 41, switching auricle 42, oblique drawbar 43 and indicator clip 44, wherein clamps
Spring leaf 44 is the most a part of, and it adapts to hollow pipe 41.Concrete, control wheel fixing device 2
The one end being connected with hollow pipe 41 is column structure, and the inside pipe wall diameter of hollow pipe 41 is not less than described column
It is provided with on the end face diameter of structure, and the sidewall of described hollow pipe 41 from hollow pipe 41 end face to hollow pipe
The notch extended in the middle part of in the of 41, when the column structure end face of described control wheel fixing device is positioned at hollow pipe 41
Time, indicator clip 44 clamps described hollow pipe 41, in conjunction with reference Fig. 5 and Fig. 4, and can be able to make
The inside pipe wall of described hollow pipe 41 compresses the column structure end face of described control wheel fixing device 2.
So, the lower end of the control wheel fixture block base 21 of control wheel fixing device 2 may be inserted into vertical connection
At the upper end open of hollow pipe 41, it is possible to move up and down and regulate the degree of depth of entrance.And indicator clip
Control wheel fixture block base 21 can be connected hollow pipe 41 phase with vertical in the way of being bolted by 44
Connect so that it is relative displacement does not occur.
In the present embodiment, by sole plate 3, above-mentioned pedal fixing device 1 is interconnected with braced bar system 4 phase
Connect, as in figure 2 it is shown, described sole plate 3 includes front-axle beam 31, the back rest 32 and for connecting front-axle beam 31
And the connecting lateral plate 33 of the back rest 32, front-axle beam 31 extends to the direction of pedal fixing device and forms forward direction auricle
34, it is used for connecting described pedal fixing device 1, the back rest 32 extends to the direction of braced bar system 4 and forms ear
Sheet base 36, is used for connecting described braced bar system 4.
In an alternate embodiment, described front-axle beam 31 is additionally provided with backward auricle 35, described support
Leverage 4 is provided with switching auricle 42, backward auricle 35 and switching ear in the one end away from auricle base 36
Sheet 42 is connected with each other by oblique drawbar 43, can be in conjunction with reference to Fig. 5.This design makes braced bar system 4
Arrive that the whole device of reinforcement is vertical, the effect of vertical and horizontal support stiffness, prevented full machine ground resonance test
Time, the situation that the free clearance caused due to excitation rudder face increases.
In the present embodiment, the upper end of hollow pipe 41 is connected with control wheel fixing device 2, and spiral shell is passed through in lower end
Bolt is connected with the auricle base 36 of sole plate 3, before bolt is not tightened, hollow pipe 41 can around under
The junction point of end rotates, and can not have any rotation after tightening, and plays and provides fixing device firm in longitudinal support
The effect of degree.
Forward direction auricle 34 and backward auricle 35 are arranged on front-axle beam 31, and auricle base 36 is arranged on the back rest
On 32, connected mode is welding.
In the present embodiment, after the connecting lateral plate 33 at two ends is connected with front-axle beam 31 and the back rest 32 respectively more solid
On the basis of Dingan County is contained in aircraft cockpit.Preferred forms is: the slide rail generally choosing pilot set is made
Based on.
The universal flight control system fixing device of present invention design, can be in aircraft floor resonance test mistake
Journey realizes full machine steerable system fix, so that each control surface is maintained at neutral position, in fixation procedure
In each parts will not produce relative displacement, outward appearance and the structure of flight control system will not be destroyed simultaneously, permissible
Ensure the measurement of resonance test each control surface speed.
Last it is noted that above example is only in order to illustrate technical scheme, rather than right
It limits.Although the present invention being described in detail with reference to previous embodiment, the common skill of this area
Art personnel it is understood that the technical scheme described in foregoing embodiments still can be modified by it,
Or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, do not make corresponding
The essence of technical scheme departs from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (10)
1. a flight control system fixing device, it is characterised in that: include pedal fixing device (1),
Control wheel fixing device (2), sole plate (3) and braced bar system (4), wherein, the fixing dress of pedal
The one end putting (1) connects described sole plate (3), and the other end is provided with the first bare terminal end, and described first
Bare terminal end is for clamping the pedal connecting tube (5) of airplane tread, and one end of described braced bar system (4) connects
On sole plate (3), the other end extends to control wheel direction and forms hollow pipe (41), described sky
Heart pipe (41) is used for being socketed and fixing the end of described control wheel fixing device (2), the fixing dress of control wheel
The other end putting (2) is provided with the second bare terminal end, and described second bare terminal end is for clamping control wheel
Control of the yoke handle (6).
2. flight control system fixing device as claimed in claim 1, it is characterised in that: described first
Pedal fixture block base (11) that bare terminal end includes being arranged on pedal fixing device (1) end and detachable
Pedal fixture block auricle (12) being connected on pedal fixture block base (11), pedal fixture block base (11) with
During the fixing connection of pedal fixture block auricle (12), forming the first columnar through holes, pedal connecting tube (5) can
Adaptation is arranged in described first columnar through holes.
3. flight control system fixing device as claimed in claim 2, it is characterised in that: described pedal
Pedal fixture block cushion pad (13) it is provided with between the inwall of connecting tube (5) and described first columnar through holes.
4. flight control system fixing device as claimed in claim 3, it is characterised in that: pedal fixture block
Cushion pad (13) is the ring-type cushion block of rubber.
5. flight control system fixing device as claimed in claim 1, it is characterised in that: described second
Bare terminal end includes control wheel fixture block base (21) being arranged on control wheel fixing device (2) end and can
Control wheel fixture block auricle (22) that dismounting is connected on control wheel fixture block base (21), at the bottom of control wheel fixture block
Seat (21) is fixed with control wheel fixture block auricle (22) when being connected, and forms the second columnar through holes, and control wheel is grasped
Vertical handle (6) can adaptation be arranged in described second columnar through holes.
6. flight control system fixing device as claimed in claim 5, it is characterised in that: control wheel is grasped
Indulge and between handle (6) and the inwall of described second columnar through holes, be provided with control wheel fixture block cushion pad (23).
7. flight control system fixing device as claimed in claim 6, it is characterised in that: drive disk folder
Block buffering pad (23) is the ring-type cushion block of rubber.
8. flight control system fixing device as claimed in claim 1, it is characterised in that: described basis
Base (3) includes front-axle beam (31), the back rest (32) and is used for connecting front-axle beam (31) and the back rest (32)
Connecting lateral plate (33), front-axle beam (31) to the direction of pedal fixing device (1) extend formed forward direction auricle
(34), being used for connecting described pedal fixing device (1), the back rest (32) is to the direction of braced bar system (4)
Extend and form auricle base (36), be used for connecting described braced bar system (4).
9. flight control system fixing device as claimed in claim 8, it is characterised in that: described front-axle beam
On be additionally provided with backward auricle (35), described braced bar system (4) is in the one end away from auricle base (36)
Being provided with switching auricle (42), backward auricle (35) and switching auricle (42) are by oblique drawbar (43)
It is connected with each other.
10. flight control system fixing device as claimed in claim 1, it is characterised in that: control wheel is solid
The one end being connected with hollow pipe (41) determining device (2) is column structure, in the pipe of hollow pipe (41)
Wall diameter is not less than the end face diameter of described column structure, and is provided with on the sidewall of described hollow pipe (41)
The notch extended to hollow pipe (41) middle part from hollow pipe (41) end face, when described control wheel fixing device
(2), when column structure end face is positioned at hollow pipe (41), indicator clip (44) clamps described sky
Heart pipe (41), and the inside pipe wall of described hollow pipe (41) can be made to compress described control wheel fixing device (2)
Column structure end face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610323090.7A CN105857580B (en) | 2016-05-16 | 2016-05-16 | A kind of flight control system fixing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610323090.7A CN105857580B (en) | 2016-05-16 | 2016-05-16 | A kind of flight control system fixing device |
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| Publication Number | Publication Date |
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| CN105857580A true CN105857580A (en) | 2016-08-17 |
| CN105857580B CN105857580B (en) | 2018-10-09 |
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| CN201610323090.7A Active CN105857580B (en) | 2016-05-16 | 2016-05-16 | A kind of flight control system fixing device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741864A (en) * | 2016-11-30 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of mechanical integrated motion of three functions |
| CN110510107A (en) * | 2018-05-22 | 2019-11-29 | 空中客车运营简化股份公司 | The pedals for aircraft with single-piece and detachable main module |
| CN110525685A (en) * | 2019-07-16 | 2019-12-03 | 中国特种飞行器研究所 | A kind of aircraft primary control circuit experimental method and device |
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| US6250589B1 (en) * | 2000-02-10 | 2001-06-26 | Richard T. Russ | Apparatus for locking control surfaces of stick controlled aircraft |
| CN202144049U (en) * | 2011-06-14 | 2012-02-15 | 湖州高林不锈钢管制造有限公司 | Nondestructive fixture for steel pipe |
| CN202987524U (en) * | 2012-11-16 | 2013-06-12 | 哈尔滨飞机工业集团有限责任公司 | Foot plate limiting device of fixed-wing aircraft |
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| CN106741864A (en) * | 2016-11-30 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of mechanical integrated motion of three functions |
| CN106741864B (en) * | 2016-11-30 | 2021-05-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Three-function mechanical comprehensive movement mechanism |
| CN110510107A (en) * | 2018-05-22 | 2019-11-29 | 空中客车运营简化股份公司 | The pedals for aircraft with single-piece and detachable main module |
| CN110525685A (en) * | 2019-07-16 | 2019-12-03 | 中国特种飞行器研究所 | A kind of aircraft primary control circuit experimental method and device |
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