CN105775163B - A kind of test simulator of aircraft flap motion - Google Patents
A kind of test simulator of aircraft flap motion Download PDFInfo
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- CN105775163B CN105775163B CN201610302146.0A CN201610302146A CN105775163B CN 105775163 B CN105775163 B CN 105775163B CN 201610302146 A CN201610302146 A CN 201610302146A CN 105775163 B CN105775163 B CN 105775163B
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Abstract
The invention discloses a kind of test simulator of aircraft flap motion, it includes forward part and rear part, and forward part includes：Wing flap slide assemblies in end rib bogusware, torsion tube assembly, first group of joint bogusware and first group at the preceding skeleton of aircraft flap, torque tube；Rear portion point includes：The back skeleton for the aircraft flap being connected with preceding skeleton and second group of joint bogusware and second group of outer wing flap slide assemblies, wherein, wing flap slide assemblies in this first group are connected to preceding skeleton by first group of joint bogusware, and this second group outer wing flap slide assemblies are connected to back skeleton by second group of joint bogusware.Moved by 4 motions of present invention simulation aircraft flap and the total tune of inside and outside wing flap, each motion and inside and outside wing flap interference situation are checked in simulation process, the harmony linked between each motion is checked, is easy to analyze and coordinates the various problems that solve to occur during assembling and setting.
Description
Technical field
The invention belongs to the test simulator of Fixture Design technical field, more particularly to a kind of motion of aircraft flap.
Background technology
The country carries out the debugging analogue means that airplane flap test is used, for individually being retreated or rotary motion in wing flap
When simulate, or simulated when wing flap puts down, is retracted into special angle.This debugging apparatus can not to aircraft flap retreat and
Rotary motion will also carry out being servo-actuated to wing flap of the LRO Lateral Runout with Comlex-locus simultaneously, real-time Simulation, can not be
Change the position for simulating point during simulative debugging with flap kinematics.
Therefore, it is necessary to design a kind of test simulator of new aircraft flap motion.
The content of the invention
The problem of existing for prior art, meets aircraft flap motion it is an object of the invention to provide one kind and tests
Receive the test simulator of the aircraft flap motion of technical conditions.
To achieve the above object, the test simulator of a kind of aircraft flap motion of the invention, including forward part and rear portion
Point, the forward part includes：End rib bogusware at the preceding skeleton of aircraft flap, torque tube, it is connected with end rib bogusware at the torque tube
Torsion tube assembly, wing flap slide assemblies in first group of joint bogusware of preceding skeleton connection and first group；The rear part
Including：The back skeleton for the aircraft flap being connected with preceding skeleton and second group of joint bogusware, Yi Ji being connected with the back skeleton
Two groups of outer wing flap slide assemblies, wherein, wing flap slide assemblies in this first group are connected to described by first group of joint bogusware
This second group outer wing flap slide assemblies are connected to the back skeleton by preceding skeleton, second group of joint bogusware.
Further, wing flap slide assemblies include the interior slide track component of wing flap first and the slide rail of interior wing flap second in described first group
With pulley yoke component, first group of joint bogusware includes joint bogusware, the cunning relative with joint bogusware after the slide rail after slide rail
Connect after rail front connector bogusware, rocking arm hanging before joint bogusware and the rocking arm hanging relative with joint bogusware after rocking arm hanging
Joint bogusware and slide rail front connector bogusware connect the interior slide track component of wing flap first to the prebone after head bogusware, the slide rail
Frame, joint bogusware and rocking arm hanging front connector bogusware connect the interior slide rail of wing flap second and pulley yoke group after the rocking arm hanging
Part is to the preceding skeleton.
Further, the forward part also includes preceding driving bearing bogusware, and the interior slide track component of wing flap first is by the cunning
Joint bogusware, slide rail front connector bogusware and the driving bearing bogusware are connected on the preceding skeleton after rail.
Further, the forward part also includes the front reduction gear component of wing flap number one slide track component motion in driving.
Further, the front reduction gear component is set and interior the first slide track component of wing flap upper end.
Further, the rear part also includes the preceding driving bearing bogusware by the front reduction gear Component driver.
Further, described second group outer wing flap slide assemblies include the outer slide rail of wing flap the 3rd and pulley yoke component and outer wing flap
4th slide rail and pulley yoke component, second group of joint bogusware include bogusware joint after outer wing flap the 3rd, with the outer wing flap the
After three before the relative outer wing flap the 3rd of bogusware joint after bogusware joint, outer wing flap the 4th bogusware joint and with the outer wing flap
Bogusware joint and outer wing flap the 3rd after bogusware joint before the relative outer wing flap the 4th of bogusware joint after four, the described outer wing flap the 3rd
Preceding bogusware joint connects the outer slide rail of wing flap the 3rd with pulley yoke component to the back skeleton, bogusware after the outer wing flap the 4th
Bogusware joint connects the outer slide rail of wing flap the 4th and pulley yoke component to the back skeleton before joint and outer wing flap the 4th.
Further, the rear part also includes the rear reducer assemblies for driving the outer slide rail of wing flap the 3rd and pulley yoke component.
Further, the rear part is also included by the rear driving bearing bogusware of the rear reducer assemblies driving.
Further, the forward part also includes the first tooling platform positioned at bottom, and the rear part also includes being located at bottom
Second tooling platform in portion, the forward part is integrally attached on first tooling platform, it is described after be partly integrally attached to
On second tooling platform.
Moved, simulated by 4 motions of present invention simulation aircraft flap and the total tune of inside and outside wing flap
Each motion and inside and outside wing flap interference situation are checked in journey, the harmony linked between each motion is checked, is easy to analysis
And coordinate to solve the various problems that occur during assembling and setting, and determine the extreme position of motion to ensure the product energy delivered
Meet flap kinematics mechanism inspection specifications.
Brief description of the drawings
Fig. 1 is the structural representation for the test simulator that aircraft flap of the present invention is moved；
Fig. 2 is another angled arrangement schematic diagram for the test simulator that aircraft flap shown in Fig. 1 is moved；
Fig. 3 be after the slide rail of test simulator described in Fig. 1 joint bogusware and slide rail front connector bogusware with interior wing flap the
The structural representation of one slide track component connection；
The structural representation of joint bogusware after Fig. 4 hangs for the rocking arm of test simulator described in Fig. 1；
Fig. 5 hangs the structural representation of front connector bogusware for the rocking arm of test simulator described in Fig. 1；
Fig. 6 is the preceding driving bearing bogusware and the interior slide rail of wing flap second and pulley yoke component of test simulator described in Fig. 1
The structural representation of assembling；
Fig. 7 is the structural representation that end rib bogusware is connected with torsion tube assembly at the torque tube of test simulator described in Fig. 1
Figure；
Fig. 8 is the rear driving bearing bogusware and the outer slide rail of wing flap the 4th and pulley yoke component of test simulator described in Fig. 1
With the structural representation of torque tube assembling components；
Fig. 9 is the structural representation of the rear driving bearing bogusware of test simulator described in Fig. 1.
Figure number explanation：
Joint bogusware, 5- shake after joint bogusware, 3- slide rail front connectors bogusware, the hanging of 4- rocking arms after skeleton, 2- slide rails before 1-
Arm hangs driving bearing bogusware before front connector bogusware, 6-, end rib bogusware, 8- front reduction gears component, the outer wing flaps of 9- at 7- torque tubes
Bogusware joint, the outer wing flaps the 4th of 16- after the outer wing flap the 4th of bogusware joint, 15- before the outer wing flap the 3rd of bogusware joint, 10- after 3rd
Reducer assemblies, 14- tooling platforms, 31- torque tubes after bearing bogusware, 12- back skeletons, 13- are driven after preceding bogusware joint, 11-
The slide track component of wing flap first in component, 21-, in 22- the slide rail of wing flap second and the outer slide rail of wing flap the 3rd of pulley yoke component, 23- with
The outer slide rail of wing flap the 4th of pulley yoke component, 24- and pulley yoke component 24.
Embodiment
Below, refer to the attached drawing, is more fully illustrated to the present invention, shown in the drawings of the exemplary implementation of the present invention
Example.However, the present invention can be presented as a variety of multi-forms, the exemplary implementation for being confined to describe here is not construed as
Example.And these embodiments are to provide, so that the present invention is fully and completely, and it will fully convey the scope of the invention to this
The those of ordinary skill in field.
For ease of explanation, space relative terms such as " on ", " under " " left side " " right sides " can be used herein, for saying
The element or feature shown in bright figure is relative to another element or the relation of feature.It should be understood that except in figure
Outside the orientation shown, spatial terminology is intended to include the different azimuth of device in use or operation.If for example, in figure
Device is squeezed, be stated as being located at other elements or feature " under " element will be located into other elements or feature " on ".Cause
This, exemplary term " under " both upper and lower orientation can be included.Device, which can be positioned otherwise, (to be rotated by 90 ° or is located at
Other orientation), can correspondingly it be explained used herein of the relative explanation in space.
The invention discloses a kind of test simulator of aircraft flap motion, aircraft is simulated by this test simulator
The outer wing flap bogusware of interior wing flap bogusware and aircraft, the simulating test device retains the skeleton of aircraft flap, simulates the end of aircraft flap
Each joint of simulation aircraft flap, the gross weight of the simulating test device in the middle of ribbed belt skin shape, the simulating test device
Amount and the weight of aircraft flap are basically identical, center of gravity of its center of gravity close to aircraft flap.
As depicted in figs. 1 and 2, the test simulator of this aircraft flap motion includes forward part and rear part, forward part
Including：End rib bogusware 7, the torque tube group being connected with end rib bogusware 7 at the torque tube at the preceding skeleton 1 of aircraft flap, torque tube
Joint bogusware 2, the slide rail front connector relative with joint bogusware 2 after the slide rail after part 31, the first slide track component of interior wing flap 21, slide rail
Joint bogusware 4 after bogusware 3, rocking arm hanging, hung with the rocking arm after the relative rocking arm of joint bogusware 4 hang front connector bogusware 5, it is interior
The slide rail of wing flap second and pulley yoke component 22 and preceding driving bearing bogusware 11.
Connect after slide rail after joint bogusware 2, slide rail front connector bogusware 3, rocking arm hanging before joint bogusware 4 and rocking arm hanging
Head bogusware 5 is referred to as first group of joint bogusware；Interior the first slide track component of wing flap 21 and the slide rail of interior wing flap second and pulley yoke component
22 are referred to as wing flap slide assemblies in first group.
Before interior the first slide track component of wing flap 21 and the slide rail of interior wing flap second are both connected to pulley yoke component 22 on skeleton 1.
Please refer to shown in Fig. 3 to Fig. 7, end rib bogusware 7 and torsion tube assembly 31 connect preceding skeleton 1 and interior at torque tube
The first slide track component of wing flap 21, i.e. the preceding skeleton 1 is realized and the interior flap by end rib bogusware 7 at torque tube and torsion tube assembly 31
The first slide track component of the wing 21 is connected, and interior first slide track component of wing flap 21 is by joint bogusware 2, slide rail front connector bogusware 3 after slide rail
Before being connected to driving bearing bogusware 6 on skeleton 1.Before joint bogusware 4 and rocking arm hanging front connector bogusware 5 are connected after rocking arm hanging
Skeleton 1 and the slide rail of interior wing flap second and pulley yoke component 22, i.e.,：Connect after being hung by rocking arm before joint bogusware 4 and rocking arm hanging
The interior slide rail of wing flap second is connected by head bogusware 5 with pulley yoke component 22 with preceding skeleton 1.
By above-mentioned connected mode, the forward part of an independent overall test simulator is constituted.
The forward part of simulating test device is additionally provided with the front reduction gear component 8 being connected with preceding skeleton 1, the front reduction gear component
8 are set and the interior upper end of the first slide track component of wing flap 21.
Before moving and then drive using wing flap number one slide track component 21 in the front reduction gear component 8 input drive force
Part overall operation, and it is servo-actuated to drive at preceding driving bearing bogusware 11.
Please refer to shown in Fig. 8 and Fig. 9, the rear portion point of test simulator includes：Back skeleton 12, outer wing flap the 3rd are slided
Rail and bogusware joint 9 and the outer flap after pulley yoke component 23, the slide rail of outer wing flap the 4th and pulley yoke component 24, outer wing flap the 3rd
Bogusware joint 15 after bogusware joint 10, outer wing flap the 4th before the relative outer wing flap the 3rd of bogusware joint 9 after the wing the 3rd, with the outer flap
Bogusware joint 16 before the relative outer wing flap the 4th of bogusware joint 15, rear driving bearing bogusware 11 and rear decelerator after the wing the 4th
Component 13.
Bogusware joint 15 after bogusware joint 10, outer wing flap the 4th before bogusware joint 9, outer wing flap the 3rd after outer wing flap the 3rd,
And bogusware joint 16 is referred to as second group of joint bogusware before outer wing flap the 4th；The outer slide rail of wing flap the 3rd and pulley yoke component 23 and
The outer slide rail of wing flap the 4th is referred to as second group of outer wing flap slide assemblies with pulley yoke component 24.
Back skeleton 12 is connected with preceding skeleton 11.
After the outer slide rail of wing flap the 3rd is both connected to pulley yoke component 23 and the slide rail of outer wing flap the 4th with pulley yoke component 24
On skeleton 12.
After outer wing flap the 3rd before bogusware joint 9 and outer wing flap the 3rd bogusware joint 10 by the outer slide rail of wing flap the 3rd and pulley yoke
Component 23 is connected on back skeleton 12；After outer wing flap the 4th before bogusware joint 15 and outer wing flap the 4th bogusware joint 16 by outer wing flap
4th slide rail is connected on back skeleton 12 with pulley yoke component 24.
By above-mentioned connected mode, the rear part of an independent overall test simulator is constituted.
The rear part of simulating test device is additionally provided with the rear reducer assemblies 13 being connected with back skeleton 12, the front reduction gear group
Part 8 is set and the interior upper end of the first slide track component of wing flap 21.
Moved, entered with pulley yoke component 23 using the slide rail of wing flap the 3rd outside the rear input of reducer assemblies 13 drive force
And it is servo-actuated to be driven after part overall operation after driving, and driving at bearing bogusware 11.
Forward part also includes the first tooling platform 14 positioned at bottom, and the second frock that rear part also includes positioned at bottom is put down
Platform 17, forward part is integrally attached on the first tooling platform 14, is partly integrally attached to afterwards on the second tooling platform 17, substantial amounts of
Tool locating part assembles mutually integral with product, preferably to simulate actual product state.
Moved, simulated by 4 motions of present invention simulation aircraft flap and the total tune of inside and outside wing flap
Each motion and inside and outside wing flap interference situation are checked in journey, the harmony linked between each motion is checked, is easy to analysis
And coordinate to solve the various problems that occur during assembling and setting, and determine the extreme position of motion to ensure the product energy delivered
Meet flap kinematics mechanism inspection specifications.
Claims (10)
1. a kind of test simulator of aircraft flap motion, it is characterised in that including forward part and rear part, the forward part
Including：End rib bogusware at the preceding skeleton of aircraft flap, torque tube, the torsion tube assembly being connected with end rib bogusware at the torque tube,
Wing flap slide assemblies in first group of joint bogusware of preceding skeleton connection and first group；The rear portion point includes：With preceding skeleton
The back skeleton of the aircraft flap of connection and second group of joint bogusware being connected with the back skeleton, second group of outer wing flap Slide Group
Part, wherein, wing flap slide assemblies in first group are connected to the preceding skeleton by first group of joint bogusware, and described second group connects
This second group outer wing flap slide assemblies are connected to the back skeleton by head bogusware.
2. the test simulator of aircraft flap motion according to claim 1, it is characterised in that：The flap in described first group
Wing slide assemblies include the interior slide track component of wing flap first and the slide rail of interior wing flap second and pulley yoke component, and first group of joint is false
It is false that part includes joint after joint bogusware after slide rail, the slide rail front connector bogusware relative with joint bogusware after the slide rail, rocking arm hanging
Part and the rocking arm relative with joint bogusware after rocking arm hanging hang joint bogusware and cunning after front connector bogusware, the slide rail
Rail front connector bogusware connects the interior slide track component of wing flap first to the preceding skeleton, joint bogusware and is shaken after the rocking arm hanging
Arm hanging front connector bogusware connects the interior slide rail of wing flap second and pulley yoke component to the preceding skeleton.
3. the test simulator of aircraft flap motion according to claim 2, it is characterised in that：The forward part is also wrapped
Driving bearing bogusware before including, the interior slide track component of wing flap first by joint bogusware after the slide rail, slide rail front connector bogusware, with
And the driving bearing bogusware is connected on the preceding skeleton.
4. the test simulator of aircraft flap motion according to claim 2, it is characterised in that：The forward part is also wrapped
Include the front reduction gear component of the slide track component of wing flap first motion in driving.
5. the test simulator of aircraft flap motion according to claim 4, it is characterised in that：The front reduction gear group
Part is arranged at the first slide track component of interior wing flap upper end.
6. the test simulator of aircraft flap motion according to claim 4, it is characterised in that：Part is also wrapped after described
Include the preceding driving bearing bogusware by the front reduction gear Component driver.
7. the test simulator of aircraft flap motion according to claim 1, it is characterised in that：Second group of outer flap
Wing slide assemblies include the outer slide rail of wing flap the 3rd and pulley yoke component and the slide rail of outer wing flap the 4th and pulley yoke component, described second
Group joint bogusware is included after outer wing flap the 3rd before bogusware joint, the outer wing flap the 3rd relative with bogusware joint after the outer wing flap the 3rd
After bogusware joint, outer wing flap the 4th before bogusware joint and the outer wing flap the 4th relative with bogusware joint after the outer wing flap the 4th
The bogusware joint connection outer wing flap the 3rd is slided before bogusware joint and outer wing flap the 3rd after bogusware joint, the described outer wing flap the 3rd
Rail and pulley yoke component are to the back skeleton, and bogusware joint is connected before bogusware joint and outer wing flap the 4th after the outer wing flap the 4th
The slide rail of outer wing flap the 4th and pulley yoke component to the back skeleton.
8. the test simulator of aircraft flap motion according to claim 7, it is characterised in that：Part is also wrapped after described
Include the rear reducer assemblies for driving the outer slide rail of wing flap the 3rd and pulley yoke component.
9. the test simulator of aircraft flap motion according to claim 8, it is characterised in that：Part is also wrapped after described
Include by the rear driving bearing bogusware of the rear reducer assemblies driving.
10. the test simulator of aircraft flap motion according to claim 1, it is characterised in that：The forward part is also
Including the first tooling platform positioned at bottom, the rear portion point includes the second tooling platform positioned at bottom, and the forward part is whole
Body is fixed on first tooling platform, it is described after be partly integrally attached on second tooling platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610302146.0A CN105775163B (en) | 2016-05-06 | 2016-05-06 | A kind of test simulator of aircraft flap motion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610302146.0A CN105775163B (en) | 2016-05-06 | 2016-05-06 | A kind of test simulator of aircraft flap motion |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105775163A CN105775163A (en) | 2016-07-20 |
| CN105775163B true CN105775163B (en) | 2017-10-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610302146.0A Active CN105775163B (en) | 2016-05-06 | 2016-05-06 | A kind of test simulator of aircraft flap motion |
Country Status (1)
| Country | Link |
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| CN (1) | CN105775163B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1064176A1 (en) * | 1983-01-04 | 1983-12-30 | Московский Ордена Трудового Красного Знамени Автомобильно-Дорожный Институт | Self-propelled vessel joint moment of inertia determination method |
| JP3694742B2 (en) * | 2002-02-12 | 2005-09-14 | 防衛庁技術研究本部長 | Dynamic wind test model with control surface drive mechanism |
| JP4969492B2 (en) * | 2008-02-28 | 2012-07-04 | 三菱重工業株式会社 | Test load loading method and test load loading mechanism |
| GB201214952D0 (en) * | 2012-08-22 | 2012-10-03 | Moog Wolverhampton Ltd | Control surface actuation assembly |
| CN103558019B (en) * | 2013-11-05 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of three slide rail wing flap test methods simulating wing distortion |
-
2016
- 2016-05-06 CN CN201610302146.0A patent/CN105775163B/en active Active
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| Publication number | Publication date |
|---|---|
| CN105775163A (en) | 2016-07-20 |
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