CN109625247A - A kind of adjustable aircraft side lever arm support - Google Patents
A kind of adjustable aircraft side lever arm support Download PDFInfo
- Publication number
- CN109625247A CN109625247A CN201811449305.5A CN201811449305A CN109625247A CN 109625247 A CN109625247 A CN 109625247A CN 201811449305 A CN201811449305 A CN 201811449305A CN 109625247 A CN109625247 A CN 109625247A
- Authority
- CN
- China
- Prior art keywords
- support
- supporting plate
- hole
- side lever
- lever arm
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/06—Initiating means actuated personally adjustable to suit individual persons
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The application belongs to field of airplane structure, in particular to a kind of adjustable aircraft side lever arm support.It include: support (1), support arm (2), supporting plate (3) and supporting plate height adjustment assembly (4).One end and support (1) of support arm (2) are hinged, interconnecting piece is set on supporting plate height adjustment assembly (4) side wall, interconnecting piece and the other end of support arm (2) are connected, and supporting plate height adjustment assembly (4) upper end is connect with supporting plate (3).The adjustable aircraft side lever arm support support arm of the application carries out adaptability adjusting using pilot's own wt, when adjusting blade position without unclamping control stick, can experience adjustment immediately as a result, so as to quickly adjust Support Position；Band is decontroled from locking ability and adjusts i.e. holding current location, support reliable；Can fast folding pack up, stowed position also lockable；It is high reliablity, small in size, light-weight.
Description
Technical field
The application belongs to field of airplane structure, in particular to a kind of adjustable aircraft side lever arm support.
Background technique
Relative to conventional central control stick, side lever device is placed on pilot's body side, can improve downward view before pilot, and
There is chair tilting angle to increase, so that improving pilot shoulders motor-driven overload capacity.The country is for side lever manipulation device
Research is required in exploration and conceptual phase, handling characteristic and ergonomic by a large number of experiments and accumulation.Drive bar side
It postpones, steering force is relatively large, grasps so that usual control stick is designed as structure space constraint and the requirement of itself handling characteristic in cockpit
Pilot's arm need to be utilized bracket in this case to improve accurate manipulation characteristic by the relatively small force-displacement behavior of vertical displacement
Carry out Auxiliary support.It can be described as fupport arm, ancon or wrist support according to the position of support frame relative flight person's arm.
Sidebar mechanism is more complicated, usually guarantees that mounting characteristics will not design size adjustment mechanism, then fupport arm is driven
The relative position for sailing bar, which then becomes an important design element, influences manipulation impression.Since side lever ergonomic itself has been in
Conceptual phase is walked, pilot's scale of construction individual sex differernce yet objective reality can not between the fupport arm and control stick grip of fixed position
Adapt to the requirement of different pilots.Meanwhile if fupport arm only can ground crew using tool adjust, can not quickly according to fly
The requirement of office staff adapts in time.Even if can be adjusted by pilot, also need to adjust repeatedly and find optimum position, adjustment is difficult
It spends larger.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided a kind of adjustable aircraft side lever arm supports for the purpose of the application, to solve of the existing technology at least one
A problem.
The technical solution of the application is:
A kind of adjustable aircraft side lever arm support, comprising:
Support；
Support arm, one end of the support arm and the support are hinged；
Supporting plate；
Supporting plate height adjustment assembly is provided with interconnecting piece, the interconnecting piece on the side wall of the supporting plate height adjustment assembly
It is connected with the other end of the support arm, supporting plate height adjustment assembly upper end is connect with the supporting plate.
It optionally, further include the first in command, the first in command is connect by the first connection component with the support；Its
In,
The first in command offers through-hole；
First connection component includes: pin barrel shell, spiral cover, locking pin and the first spring, wherein
The pin barrel shell is connected by the first bolt and the support, and the pin barrel shell is provided with external screw thread, and bottom is opened
Equipped with through-hole；
The spiral cover is provided with internal screw thread, and the spiral cover forms inner cavity, and the rotation after being threadedly coupled with the pin barrel shell
Lid is provided with through-hole；
Limiting section is provided on the locking pin；
First spring is arranged in the inner cavity, and one end abuts the limiting section of the locking pin, and the other end abuts institute
State spiral cover；
By the locking pin pass through the through-hole of the first in command, the through-hole of the spiral cover, first spring and
The through-hole of the pin barrel shell, attaching nut fix the first in command.
Optionally, the support is provided with ears structure, and axis hole is provided on the support arm, and the support arm passes through bolt axle
Attaching nut and the support are hinged.
Optionally, one end that the support arm is connect with the support is provided with side ear projection shape structure, the master of the support arm
Form installation bushing is threadedly coupled in body and side ear projection shape structure respectively, forms two dowel holes, two linings
It covers and is equidistant with the axis hole of the support arm.
Optionally, the supporting plate height adjustment assembly includes shell, rack shaft and second spring, wherein
The upper end of the shell is provided with the first cover board, and lower end is provided with the second cover board, offers on first cover board
Through-hole, second cover board are provided with cylindrical bump；
The through-hole that the lower end of the rack shaft passes through first cover board is disposed in the housing, and the rack shaft is in institute
It states the part in shell and is provided with cyclic annular tooth-shape structure, the lower end of the ring-type tooth-shape structure is provided with limiting section；
The second spring is set on the rack shaft, and one end abuts the limiting section of the rack shaft, and the other end abuts
The cylindrical bump of second cover board.
Optionally, the interconnecting piece on the side wall of the supporting plate height adjustment assembly is two bolts hole, the support arm
It is connected by the second bolt and the supporting plate height adjustment assembly.
Optionally, further include second handle, the second handle by the second connection component be arranged on the housing with
On the opposite side wall of the interconnecting piece.
Optionally, the second handle offers through-hole；
Second connection component includes: segmental support, third spring and third cover board, wherein
One end of the segmental support is disposed in the housing by third cover board, which is provided with cylindrical grooves, institute
It states third spring to be arranged in the cylindrical grooves, and the end at the end is provided with trapezoidal lobe, the trapezoidal lobe and institute
The cyclic annular tooth-shape structure for stating rack shaft is mutually twisted；
The through-hole attaching nut that the other end of the segmental support passes through the second handle is fixed.
Optionally, the upper end of the supporting plate height adjustment assembly is connect with the supporting plate by third connection component；
The third connection component includes pallet stand, handwheel lead screw and split pin, and the bottom end of the pallet stand is set
It is equipped with longitudinal through-hole, the upper end of the rack shaft passes through the through-hole attaching nut and fixes, and the pallet stand is provided with cross
To supporting circular holes, the handwheel lead screw is arranged in the supporting circular holes of the pallet stand by split pin, the handwheel silk
Thick stick is provided with threads of lead screw；
The lower end of the supporting plate is provided with protrusion with threaded hole, and the supporting plate passes through the protrusion and the handwheel lead screw
It is threadedly coupled.
Optionally, the upper end of the supporting plate is provided with sponge soft structures, and the sponge soft structures are wrapped with cortex
It wraps up in.
At least there are following advantageous effects in invention:
The adjustable aircraft side lever arm support of the application carries out adaptability adjusting using pilot's own wt, in holder for regulating
Without unclamping control stick when Board position, adjustment can be experienced immediately as a result, so as to quickly adjust Support Position；With it is self-locking surely
Power is decontroled and adjusts i.e. holding current location, supports reliable；Can fast folding pack up, stowed position also lockable；High reliablity,
It is small in size, light-weight.
Detailed description of the invention
Fig. 1 is the adjustable aircraft side lever arm support unfolded state schematic diagram of one embodiment of the application；
Fig. 2 is that the adjustable aircraft side lever arm collection of one embodiment of the application plays status diagram；
Fig. 3 is the adjustable aircraft side lever arm support main view of one embodiment of the application；
Fig. 4 is adjustable aircraft side lever arm support the first connection component cross-sectional view of one embodiment of the application；
Fig. 5 is the adjustable aircraft side lever arm support supporting plate height adjustment assembly cross-sectional view of one embodiment of the application；
Fig. 6 is the A-A view of Fig. 5；
Fig. 7 is the adjustable aircraft side lever arm support third connection component cross-sectional view of one embodiment of the application；
Fig. 8 is the adjustable aircraft side lever arm support support arm front view of one embodiment of the application；
Fig. 9 is the adjustable aircraft side lever arm support support arm bottom view of one embodiment of the application；
Figure 10 is the B-B view of Fig. 8.
Wherein:
1- support；2- support arm；3- supporting plate；4- supporting plate height adjustment assembly；The 5- first in command；6- second handle；7- second
Bolt；The first bolt of 8-；9- rack shaft；10- segmental support；11- third spring；12- third cover board；13- shell；The first spiral shell of 14-
Nail；15- second spring；The second cover board of 16-；The first cover board of 17-；The second screw of 18-；19- pallet stand；20- handwheel lead screw；
21- split pin；22- boss；23- bolt axle；24- nut；25- sells barrel shell；26- spiral cover；27- locking pin；The first spring of 28-；
29- bushing；30- pilot's forearm.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Figure 10 the application is described in further details with reference to the accompanying drawing.
The application provides a kind of adjustable aircraft side lever arm support, comprising: support 1, support arm 2, supporting plate 3 and supporting plate height tune
Save component 4.
Specifically, one end of support arm 2 and support 1 are hinged, interconnecting piece is set on 4 side wall of supporting plate height adjustment assembly, is connected
The other end of portion and support arm 2 is connected, and 4 upper end of supporting plate height adjustment assembly is connect with supporting plate 3.
In the embodiment of the application, ears structure is set in one end of support 1, axis is arranged in one end of support arm 2
Hole, it is by 23 attaching nut 24 of bolt axle that support arm 2 and support 1 is hinged.Mounting hole there are three opening up on support 1, can be pacified
It is attached in cabin interior structure.
As shown in figure 4, being equipped with the first in command 5 on support 1, the first in command 5 is connected by the first connection component and support 1
It connects, offers through-hole on the first in command 5.In the present embodiment, the first connection component includes pin barrel shell 25, spiral cover 26, locking pin 27
And first spring 28.Pin barrel shell 25 is fastenedly connected by two the first bolts 8 with support 1, and pin barrel shell 25 is provided with external screw thread,
And bottom offers through-hole；Spiral cover 26 offers internal screw thread, and inner cavity is formed after being threadedly coupled with pin barrel shell 25, and spiral cover 26 is same
Offer through-hole；27 upper end of locking pin is the stem knob with chamfering, and lower end is the end threaded cylindrical structure of heading tape, locking pin
Limiting section is additionally provided on 27, the upper end of locking pin 27 is pierced by from the through-hole of pin barrel shell 25, and limiting section support outbound barrel shell 25 is logical
The inside in hole, after being pierced by the through-hole of spiral cover 26, the through-hole that threaded cylindrical structure passes through the first in command 5 utilizes spiral shell for lower end
Mother is fixed；First spring 28 is set on locking pin 27, and in pin barrel shell 25 in the inner cavity that spiral cover 26 is formed, one end abuts locking
The limiting section of pin 27, the other end are compressed by spiral cover 26.
As shown in figure 5, supporting plate height adjustment assembly 4 may include shell 13, tooth in the embodiment of the application
Axis 9 and second spring 15.13 upper end of shell be arranged the first cover board 17, lower end be arranged the second cover board 16, the first cover board 17 with
And second cover board 16 be fixedly connected with shell 13 by four the second screws 18, offer through-hole on the first cover board 17, second
Cover board 16 is provided with cylindrical bump；The through-hole that the lower end of rack shaft 9 passes through the first cover board 17 is arranged in shell 13, rack shaft
9 part in shell 13 is provided with multiple cyclic annular tooth-shape structures, and the lower end of cyclic annular tooth-shape structure is provided with limiting section, the second bullet
Spring 15 is set on rack shaft 9, and one end abuts the limiting section of rack shaft 9, and the other end abuts the cylindrical bump of the second cover board 16.
In the embodiment of the application, the interconnecting piece on the side wall of supporting plate height adjustment assembly 4 is to be arranged in shell
Two bolts hole on body 13, again with two bolts hole on support arm 2, support arm 2 passes through the second bolt 7 and supporting plate height adjustment
Component 4 is connected.
As shown in fig. 6, being additionally provided with second handle 6, second handle 6 in the adjustable aircraft side lever arm support of the application
It is arranged on side wall opposite with interconnecting piece on shell 13 by the second connection component, offers through-hole on second handle 6.Second
Connection component may include segmental support 10, third spring 11 and third cover board 12.In the present embodiment, one end of segmental support 10 is logical
It crosses third cover board 12 to be arranged in shell 13, which is provided with symmetrical cylindrical grooves at two, and third spring 11 is arranged in circle
In cylindrical recesses, and the end at the end is provided with trapezoidal lobe, and the cyclic annular tooth-shape structure of trapezoidal lobe and rack shaft 9 is mutually stung
It closes；The other end of segmental support 10 is provided with screw thread, and the through-hole attaching nut which passes through second handle 6 is fixed.It is understood that
It is that in the present embodiment, third cover board 12 is fixed on shell 13 by two the first screws 14, is had at two on third cover board 12
Cylindrical projection, for positioning two third springs 11 of suit.
As shown in fig. 7,4 upper end of supporting plate height adjustment assembly and supporting plate 3 are logical in the adjustable aircraft side lever arm support of the application
The connection of third connection component is crossed, third connection component may include pallet stand 19, handwheel lead screw 20 and split pin 21.Its
In, the bottom end of pallet stand 19 is provided with longitudinal through-hole, which is stair-stepping through-hole, and the upper end of rack shaft 9 is provided with
Boss 22 and helicitic texture, 9 upper end of rack shaft pass through through-hole attaching nut and fix, and pallet stand 19 is additionally provided with lateral branch
Hold round hole；Handwheel lead screw 20 has discoid hand wheel structure, and cylinder lead screw passes through the supporting circular holes of pallet stand 19, and leads to
The positioning of split pin 21 is crossed, prevents handwheel lead screw 20 from deviating from from the supporting circular holes of pallet stand 19 and free to rotate.
In the present embodiment, handwheel lead screw 20 is provided with threads of lead screw, and the lower end of supporting plate 3 is provided with protrusion with threaded hole,
Supporting plate 3 is threadedly engaged with handwheel lead screw 20 by protrusion and is connect.It is understood that the upper end of supporting plate 3 is arranged in the present embodiment
There are sponge soft structures, sponge soft structures are wrapped up with cortex.
Further, as shown in Figure 8,9, 10, the adjustable aircraft side lever arm support of the application further includes two bushings 29, and two
Bushing 29 is threadedly coupled form and is installed in the main body and side ear projection shape structure of support arm 2, forms two dowel holes, and two
The axis hole of a bushing 29 and support arm 2 is equidistant.
In the adjustable aircraft side lever arm support of the application, locking pin 27 is protruded into the agent localization pin hole of support arm 2 as arm
Hold in the palm unfolded state.When needing to pack up fupport arm, pulls downward on the first in command 5 and compress the first spring 28 and drive locking pin 27 from support arm
Deviate from 2 agent localization pin hole, at this time rotatable support arm 2, keeps dowel hole in its ear projection shape structure and locking pin 27 right
Positive to unclamp the first in command 5, locking pin 27 projects upwardly under the restoring force effect of the first spring 28 to be determined in ear projection shape structure
In the pin hole of position, so that support arm 2 be made to be fixed on collapsed state.When use state is unfolded in fupport arm, segmental support 10 is by third spring 11
Rebound effect, the cyclic annular tooth-shape structure of trapezoidal lobe and rack shaft 9 is mutually closely engaged, and makes rack shaft 9 can not be in shell
It is moved up and down in 13, to fix the height and position state of supporting plate 3；Handwheel lead screw 20 and the formation of supporting plate 3 thread lead screw are self-locking
State, supporting plate 3 also can not be moved forward and backward freely.The position of supporting plate 3 is uniquely fixed at this time, and pilot's forearm 30 can be by branch
It supports on supporting plate 3, stablizing the movement of its forearm, to carry out accurate manipulation to control stick.
When pilot thinks that 3 position of supporting plate is not satisfied enough, when needing to be adjusted.3 height of adjustment supporting plate: it can keep holding
Bar state is driven, pilot's forearm 30 is applied pressure to naturally on supporting plate 3, dynamic second handle 6 is pulled with another, to drive bow
Shape frame 10 moves out, and compresses two third springs 11 simultaneously.Segmental support 10 moves a certain distance and the cyclic annular tooth form of rack shaft 9
Structure is detached from occluding relation, can not continue the up and down motion for locking rack shaft 9, rebound masterpiece of the rack shaft 9 in second spring 15
Has the tendency that bullet back up under.The lower pressure initiation resultant force of the screen resilience and pilot's forearm 30 of second spring 15, can control support
The upper and lower position of plate 3.When pilot arrives proper height using forearm adjustment supporting plate 3, second handle 6 is unclamped, segmental support 10 exists
It is mutually twisted under the rebound effect of two third springs 11 with 9 another location ring-type tooth-shape structure of rack shaft, and to rack shaft 9
Upper and lower position lock state is formed, thus the upper and lower position of fixed pallet 3.Adjustment 3 front-rear position of supporting plate: it can keep holding driving
Bar state applies pressure to pilot's forearm 30 on supporting plate 3 naturally, rotates handwheel lead screw 20 with another hand, utilizes threads of lead screw
The principle adjustment supporting plate 3 of rotary motion moves forward and backward, and when 3 position of supporting plate, which meets use, to be needed, stop operating handwheel lead screw 20,
The front-rear position of supporting plate 3 is locked naturally.
The adjustable aircraft side lever arm support support arm of the application carries out adaptability adjusting using pilot's own wt, is adjusting
Without unclamping control stick when saving blade position, adjustment can be experienced immediately as a result, so as to quickly adjust Support Position；Band locks certainly
Ability is decontroled and adjusts i.e. holding current location, supports reliable；Can fast folding pack up, stowed position also lockable；Reliability
It is high, small in size, light-weight.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of adjustable aircraft side lever arm support characterized by comprising
Support (1)；
Support arm (2), one end and the support (1) of the support arm (2) are hinged；
Supporting plate (3)；
Supporting plate height adjustment assembly (4) is provided with interconnecting piece, the connection on the side wall of the supporting plate height adjustment assembly (4)
The other end of portion and the support arm (2) is connected, and supporting plate height adjustment assembly (4) upper end is connect with the supporting plate (3).
2. adjustable aircraft side lever arm support according to claim 1, which is characterized in that it further include the first in command (5), it is described
The first in command (5) is connect by the first connection component with the support (1)；Wherein,
The first in command (5) offers through-hole；
First connection component includes: pin barrel shell (25), spiral cover (26), locking pin (27) and the first spring (28), wherein
The pin barrel shell (25) is connected by the first bolt (8) and the support (1), and the pin barrel shell (25) is provided with outer spiral shell
Line, and bottom offers through-hole；
The spiral cover (26) is provided with internal screw thread, and the spiral cover (26) forms inner cavity after being threadedly coupled with the pin barrel shell (25),
And the spiral cover (26) is provided with through-hole；
Limiting section is provided on the locking pin (27)；
First spring (28) is arranged in the inner cavity, and one end abuts the limiting section of the locking pin (27), and the other end supports
Connect the spiral cover (26)；
The through-hole of the first in command (5), the through-hole of the spiral cover (26), first bullet are passed through by the locking pin (27)
The through-hole of spring (28) and the pin barrel shell (25), attaching nut are fixed by the first in command (5).
3. adjustable aircraft side lever arm support according to claim 2, which is characterized in that the support (1) is provided with ears
Structure, axis hole is provided on the support arm (2), and the support arm (2) passes through bolt axle (23) attaching nut (24) and the support
(1) hinged.
4. adjustable aircraft side lever arm support according to claim 3, which is characterized in that the support arm (2) and the support
(1) one end connected is provided with side ear projection shape structure, in the main body and side ear projection shape structure of the support arm (2) respectively with
Threaded form installs bushing (29), forms two dowel holes, the axis hole of two bushings (29) and the support arm (2)
It is equidistant.
5. adjustable aircraft side lever arm support according to claim 4, which is characterized in that the supporting plate height adjustment assembly
It (4) include shell (13), rack shaft (9) and second spring (15), wherein
The upper end of the shell (13) is provided with the first cover board (17), and lower end is provided with the second cover board (16), first cover board
(17) through-hole is offered on, second cover board (16) is provided with cylindrical bump；
The through-hole that the lower end of the rack shaft (9) passes through first cover board (17) is arranged in the shell (13), the tooth
Part of the axis (9) in the shell (13) is provided with cyclic annular tooth-shape structure, and the lower end of the ring-type tooth-shape structure is provided with
Limiting section；
The second spring (15) is set on the rack shaft (9), and one end abuts the limiting section of the rack shaft (9), another
End abuts the cylindrical bump of second cover board (16).
6. adjustable aircraft side lever arm support according to claim 5, which is characterized in that the supporting plate height adjustment assembly
(4) interconnecting piece on side wall is two bolts hole, and the support arm (2) passes through the second bolt (7) and the supporting plate height
Component (4) are adjusted to be connected.
7. adjustable aircraft side lever arm support according to claim 6, which is characterized in that it further include second handle (6), it is described
Second handle (6) is arranged on side wall opposite with the interconnecting piece on the shell (13) by the second connection component.
8. adjustable aircraft side lever arm support according to claim 7, which is characterized in that the second handle (6) offers
Through-hole；
Second connection component includes: segmental support (10), third spring (11) and third cover board (12), wherein
One end of the segmental support (10) is arranged in the shell (13) by third cover board (12), which is provided with cylindric
Groove, the third spring (11) is arranged in the cylindrical grooves, and the end at the end is provided with trapezoidal lobe, the ladder
Shape lobe and the cyclic annular tooth-shape structure of the rack shaft (9) are mutually twisted；
The through-hole attaching nut that the other end of the segmental support (10) passes through the second handle (6) is fixed.
9. adjustable aircraft side lever arm support according to claim 8, which is characterized in that the supporting plate height adjustment assembly
(4) upper end is connect with the supporting plate (3) by third connection component；
The third connection component includes pallet stand (19), handwheel lead screw (20) and split pin (21), the pallet stand
(19) bottom end is provided with longitudinal through-hole, and the upper end of the rack shaft (9) passes through the through-hole attaching nut and fixes, the support
Board mount (19) is provided with lateral supporting circular holes, and the handwheel lead screw (20) is arranged by split pin (21) in the supporting plate branch
In the supporting circular holes of frame (19), the handwheel lead screw (20) is provided with threads of lead screw；
The lower end of the supporting plate (3) is provided with protrusion with threaded hole, and the supporting plate (3) passes through the protrusion and the handwheel silk
Thick stick (20) is threadedly coupled.
10. adjustable aircraft side lever arm support according to claim 9, which is characterized in that the upper end of the supporting plate (3) is arranged
There are sponge soft structures, the sponge soft structures are wrapped up with cortex.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811449305.5A CN109625247A (en) | 2018-11-30 | 2018-11-30 | A kind of adjustable aircraft side lever arm support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811449305.5A CN109625247A (en) | 2018-11-30 | 2018-11-30 | A kind of adjustable aircraft side lever arm support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109625247A true CN109625247A (en) | 2019-04-16 |
Family
ID=66070210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811449305.5A Pending CN109625247A (en) | 2018-11-30 | 2018-11-30 | A kind of adjustable aircraft side lever arm support |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109625247A (en) |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4674713A (en) * | 1984-09-28 | 1987-06-23 | Falcon Jet Corporation | Double airplane seats |
| US5393124A (en) * | 1992-12-08 | 1995-02-28 | Neil; Gary K. | Armrest assembly |
| JPH10187263A (en) * | 1996-12-20 | 1998-07-14 | Commuter Herikoputa Senshin Gijutsu Kenkyusho:Kk | Side stick type control device |
| RU2164878C2 (en) * | 1999-04-30 | 2001-04-10 | Титов Андрей Анатольевич | Flying vehicle lateral wrist control stick |
| CN101020428A (en) * | 2007-02-23 | 2007-08-22 | 成都市宇中梅科技有限责任公司 | Arm rest for driver |
| US20110303039A1 (en) * | 2007-08-08 | 2011-12-15 | Kopp John D | Control stick adapted for use in a fly-by-wire flight control system, and linkage for use therein |
| CN203970563U (en) * | 2014-07-31 | 2014-12-03 | 苗红星 | A kind of arm support for neurosurgery |
| CN204507245U (en) * | 2015-03-05 | 2015-07-29 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft side lever operation elbow rest device |
| CN105240353A (en) * | 2015-09-21 | 2016-01-13 | 北京精密机电控制设备研究所 | Fast clamping locking device |
| CN105711818A (en) * | 2014-12-03 | 2016-06-29 | 中国直升机设计研究所 | Helicopter pedal operating mechanism |
| FR3031083A1 (en) * | 2014-12-31 | 2016-07-01 | Ratier Figeac Soc | ADJUSTABLE PALONNIER |
| CN205428281U (en) * | 2016-03-25 | 2016-08-03 | 中国飞行试验研究院 | Four degree of freedom arms hold in palm suitable for side lever control system |
| CN106697264A (en) * | 2016-11-30 | 2017-05-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-range position regulating mechanism |
| CN107097935A (en) * | 2017-04-18 | 2017-08-29 | 河北天启通宇航空器材科技发展有限公司 | Rudder angle position governor motion and aircraft |
| EP3248868A1 (en) * | 2016-05-27 | 2017-11-29 | Fly By Wire Systems France | Force feedback mechanism for an aircraft control mini-stick and aircraft control device having such a mechanism |
| CN108116674A (en) * | 2016-11-30 | 2018-06-05 | 空客直升机 | Control member, rotor craft and method |
-
2018
- 2018-11-30 CN CN201811449305.5A patent/CN109625247A/en active Pending
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4674713A (en) * | 1984-09-28 | 1987-06-23 | Falcon Jet Corporation | Double airplane seats |
| US5393124A (en) * | 1992-12-08 | 1995-02-28 | Neil; Gary K. | Armrest assembly |
| JPH10187263A (en) * | 1996-12-20 | 1998-07-14 | Commuter Herikoputa Senshin Gijutsu Kenkyusho:Kk | Side stick type control device |
| RU2164878C2 (en) * | 1999-04-30 | 2001-04-10 | Титов Андрей Анатольевич | Flying vehicle lateral wrist control stick |
| CN101020428A (en) * | 2007-02-23 | 2007-08-22 | 成都市宇中梅科技有限责任公司 | Arm rest for driver |
| US20110303039A1 (en) * | 2007-08-08 | 2011-12-15 | Kopp John D | Control stick adapted for use in a fly-by-wire flight control system, and linkage for use therein |
| CN203970563U (en) * | 2014-07-31 | 2014-12-03 | 苗红星 | A kind of arm support for neurosurgery |
| CN105711818A (en) * | 2014-12-03 | 2016-06-29 | 中国直升机设计研究所 | Helicopter pedal operating mechanism |
| FR3031083A1 (en) * | 2014-12-31 | 2016-07-01 | Ratier Figeac Soc | ADJUSTABLE PALONNIER |
| CN204507245U (en) * | 2015-03-05 | 2015-07-29 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft side lever operation elbow rest device |
| CN105240353A (en) * | 2015-09-21 | 2016-01-13 | 北京精密机电控制设备研究所 | Fast clamping locking device |
| CN205428281U (en) * | 2016-03-25 | 2016-08-03 | 中国飞行试验研究院 | Four degree of freedom arms hold in palm suitable for side lever control system |
| EP3248868A1 (en) * | 2016-05-27 | 2017-11-29 | Fly By Wire Systems France | Force feedback mechanism for an aircraft control mini-stick and aircraft control device having such a mechanism |
| CN106697264A (en) * | 2016-11-30 | 2017-05-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-range position regulating mechanism |
| CN108116674A (en) * | 2016-11-30 | 2018-06-05 | 空客直升机 | Control member, rotor craft and method |
| CN107097935A (en) * | 2017-04-18 | 2017-08-29 | 河北天启通宇航空器材科技发展有限公司 | Rudder angle position governor motion and aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 王欢，孙永荣，孙旭东，赵伟: "飞机主动侧杆系统的杆力控制方法研究", 《测控技术》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20140147104A1 (en) | Camera stabilizer | |
| CN105980250B (en) | Undercarriage and the unmanned vehicle for using the undercarriage | |
| CN108533909B (en) | Vehicle-mounted bracket | |
| CN108032919A (en) | A kind of hopping robot with posture balancing adjusting mechanism | |
| CN106882391B (en) | Spherical triaxial allies oneself with accuse vector motor cabinet that unmanned aerial vehicle used | |
| CN109720555A (en) | A kind of servo-actuated hatch door of large size undercarriage | |
| CN109625247A (en) | A kind of adjustable aircraft side lever arm support | |
| US20190060144A1 (en) | Mid-wheel tilt-in-space manual wheelchair with constant shoulder position | |
| JP6420737B2 (en) | Work aid | |
| CN108190037A (en) | A kind of electronic flight data bag support of adjustable-angle and height | |
| CN109878738A (en) | A kind of aero seat angle adjustment device | |
| CN208559486U (en) | One kind can gradient adjusting steering column | |
| JPH07270163A (en) | Lift mechanism of surveying tripod | |
| CN110434837A (en) | A kind of upper limb assistance device | |
| CN210130612U (en) | Chair armrest | |
| CN207860491U (en) | A kind of electronic flight data bag support of adjustable-angle and height | |
| US2920841A (en) | Helicopter with body attaching means | |
| CN215821217U (en) | Ultrasonic auxiliary arm support | |
| CN107692618B (en) | Tilt force adjusting device of office chair | |
| CN109533292A (en) | A kind of helicopter pedal regulating mechanism | |
| CN217074802U (en) | Three-shaft adjusting steering rod toggle support device | |
| CN213299524U (en) | Monitoring mounting bracket | |
| CN218063613U (en) | Spare hand wheel device of valve actuator | |
| CN218112973U (en) | Locking adjusting device of helicopter control rod | |
| CN211258827U (en) | Tester for ballistic parameters in rocket engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190416 |
|
| RJ01 | Rejection of invention patent application after publication |