CN109573100A - Iron bird testing stand - Google Patents
Iron bird testing stand Download PDFInfo
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- CN109573100A CN109573100A CN201811586779.4A CN201811586779A CN109573100A CN 109573100 A CN109573100 A CN 109573100A CN 201811586779 A CN201811586779 A CN 201811586779A CN 109573100 A CN109573100 A CN 109573100A
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- section rack
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention proposes a kind of iron bird testing stands.The testing stand includes: head section rack, for installing analog capsule cabin and nose-gear system；Forebody bridging table, for connecting head section rack and middle fuselage section rack, as personnel and device channels；Middle fuselage section rack, for installing main landing gear system and hydraulic system；Middle rear body bridging table, for connecting middle fuselage section rack and empennage section rack；Empennage section rack, for installing elevator, rudder rudder face and actuating system；Port wing section rack, for installing left side aileron, spoiler, wing flap rudder face and actuating system；Starboard wing section rack, for installing right side aileron etc..The embodiment of the present invention can reduce the relevance of iron bird test-bed structure design, to the design requirement of rack integral strength and rigidity, improve the intrinsic frequency of iron bird test-bed, production and processing, installation convenient for iron bird test-bed are fixed and dismounting maintenance, and can reduce the production of iron bird test-bed, change cost.
Description
Technical field
The present invention relates to the technical fields of Aviation Test, more particularly, to a kind of iron bird testing stand.
Background technique
In aircraft iron bird multi-function test stand development process, iron bird rack is that the main carrying of iron bird multi-function test stand carries
Body, the effects of carry installation, support by test system and testing equipment, workbench, service aisle are provided.
Due to carry out undercarriage in iron bird multi-function test stand, fly the tests such as control rudder face load test, rudder face frequency sweep test
Project, iron bird rack is as support platform, it is necessary to have enough rigidity, intensity, when preventing load or rudder face frequency sweep test,
Rack is deformed, vibrates or destroys, and this requires iron bird rack intrinsic frequency meets certain requirement, to avoid rudder face
Resonance is generated when frequency sweep.Therefore, iron bird horse structure intensity and natural frequency design often become the master of test-bed development
Want technological difficulties.
When country's iron bird rack is developed at present, unitary design is generallyd use, rack each section, which passes through, the side such as welds, is spirally connected
Formula is connected with each other, and entire iron bird horse structure is made to be connected.Meanwhile iron bird gantry designs are separated with development of test equipment, rack is ground
System is preferential to be carried out, and after the processing of iron bird rack is installed, considers further that the peace of testing equipment erection support, workbench, working stand
Dress demand.
The iron bird rack of this form, although structure design is simple, disadvantage is also fairly obvious.Each portion of iron bird rack is mutual
Connection has led to each portion of iron bird rack and is connected with each other as entirety, and each rack intercouples.In order to reduce the coupling between rack
Effect is closed, rack construction must just use larger sized profile, and the structure for allowing for iron bird rack in this way is more thick and heavy, reduces
The intrinsic frequency of iron bird rack, to have an adverse effect to frequency sweep test.It is not examined sufficiently when additionally, due to gantry designs
Consider testing equipment, workbench, working stand arrangement to require, testing equipment, workbench, working stand is caused to arrange, is difficult to install.Especially
It is the installation for loading pressurized strut, generally requires to change iron bird rack again.
Summary of the invention
The technical problem to be solved by the present invention is solve in traditional design, each portion of iron bird rack is interrelated, phase mutual coupling
Conjunction, iron bird rack rigidity, intensity requirement height, testing equipment, workbench and working stand are not easy the problem of arranging, realize to iron bird platform
The optimization design of frame.
The technical scheme is that
Testing stand is modular iron bird testing stand comprising: mutually independent head section rack, forebody transition bench
Frame, middle fuselage section rack, middle rear body bridging table, empennage section rack, port wing section rack, starboard wing section rack, right EDP platform
Frame, left EDP rack, in which:
Head section rack, empennage section rack, port wing section rack, starboard wing section rack, right EDP rack, left EDP rack are equal
It include: base frame and top rack；
Port wing section rack, starboard wing section rack all include mutually independent aileron rack, outer wing flap and spoiler rack
With interior wing flap rack；
Empennage section rack includes mutually independent left elevator rack, right elevator rack and rudder rack；
Head section rack, for installing analog capsule cabin and nose-gear system；
Forebody bridging table, for connecting head section rack and middle fuselage section rack, as personnel and device channels；
Middle fuselage section rack, for installing main landing gear system and hydraulic system；
Middle rear body bridging table, for connecting middle fuselage section rack and empennage section rack, as personnel and device channels；
Empennage section rack, for installing elevator, rudder rudder face and actuating system；
Port wing section rack, for installing left side aileron, spoiler, wing flap rudder face and actuating system；
Starboard wing section rack, for installing right side aileron, spoiler, wing flap rudder face and actuating system；
Right EDP rack is used for right engine transfer tube and driving device；
Left EDP rack is used for lefthand engine transfer tube and driving device.
Technical effect of the invention may is that
According to the layout of flight control system, hydraulic system, Landing Gear System and rudder face aboard, so that it is determined that iron bird rack
The division of module.The relevance of iron bird test-bed structure design can be reduced using such modular iron bird test-bed,
The design requirement to rack integral strength and rigidity is reduced simultaneously, improves the intrinsic frequency of iron bird test-bed, is convenient for iron
Production and processing, the installation of bird test-bed are fixed and dismounting is safeguarded, and can reduce the production of iron bird test-bed, change cost.
Left and right sides wing rack uses asymmetrical design, and left side wing rack can realize the exchange of rudder face bogusware Yu airborne part, to mention
The high flexibility of test.Right side wing rack installs rudder face simulating piece, has carried out aerodynamic force load, can ensure that examination in this way
The authenticity tested, and the cost of iron bird platform development can be reduced.EDP denoising device is installed on EDP rack, can effectively reduce EDP work
As when the noise that generates, provide good working environment for test test personnel.Working stand, workbench and guardrail only with basic platform
Frame connection, ensure that the independence of top rack.Modular iron bird test-bed can save development cost to the maximum extent,
Flexible design is easy to implement, and has very high universal value in Aviation Industry test.
Detailed description of the invention
In order to illustrate more clearly of the technical solution implemented of the present invention, below by it is of the invention be said in need using
Attached drawing make simple resolve.It is clear that drawings described below is only some embodiments of the present invention, for ability
For the technical staff in domain, without creative efforts, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the principle schematic diagram of the iron bird testing stand of one embodiment of the invention；
Fig. 2 (the 2 width figures including a and b) is the head section horse structure schematic illustration of one embodiment of the invention；
Fig. 3 (the 2 width figures including a and b) is the forebody bridging table principle schematic diagram of one embodiment of the invention；
Fig. 4 (the 2 width figures including a and b) is the middle fuselage section horse structure schematic illustration of one embodiment of the invention；
Fig. 5 (the 2 width figures including a and b) is the middle rear body bridging table principle schematic diagram of one embodiment of the invention；
Fig. 6 (the 2 width figures including a and b) is the empennage section horse structure schematic illustration of one embodiment of the invention；
Fig. 7 (the 2 width figures including a and b) is the port wing section horse structure schematic illustration of one embodiment of the invention；
Fig. 8 (the 2 width figures including a and b) is the starboard wing section horse structure schematic illustration of one embodiment of the invention；
Fig. 9 (the 2 width figures including a and b) is the left EDP horse structure schematic illustration of one embodiment of the invention；
Figure 10 (the 2 width figures including a and b) is the left EDP horse structure schematic illustration of one embodiment of the invention.
Wherein, 1- head section rack, 2- forebody bridging table, 3- middle fuselage section rack, rear body bridging table in 4-,
5- empennage section rack, 6- port wing section rack, 7- starboard wing section rack, the left EDP rack of 8-, the right EDP rack of 9-；
1-1 analog capsule cabin, 1-2 base frame, 1-3 base frame；
2-1 workbench and guardrail, 2-2 base frame, 2-3 working stand, 2-4 working stand；
3-1 workbench and guardrail, 3-2 base frame, 3-3 base frame；
4-1 workbench and guardrail, 4-2 base frame, 4-3 working stand, 4-4 working stand；
The top 5-1 rack, the top 5-2 rack, the top 5-3 rack, 5-4 base frame, 5-5 base frame, the basis 5-6 platform
Frame, 5-7 workbench and guardrail, 5-8 workbench and guardrail；
The top 6-1 rack, the top 6-2 rack, the top 6-3 rack, 6-4 working stand, 6-5 working stand, 6-6 base frame,
6-7 base frame, 6-8 base frame, 6-9 workbench and guardrail；
The top 7-1 rack, the top 7-2 rack, the top 7-3 rack, 7-4 workbench and guardrail, 7-5 working stand, 7-6 work
Ladder, 7-7 base frame, 7-8 base frame, 7-9 base frame；
8-1 denoising device, 8-2 workbench and guardrail, 8-3 base frame, 8-4 working stand；
9-1 denoising device, 9-2 working stand, 9-3 workbench and guardrail, 9-4 base frame.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described.Obviously, described embodiment is
A part of the embodiments of the present invention, rather than whole embodiments.Based on the embodiments of the present invention, the ordinary skill people of this field
Without making creative work, every other embodiment obtained shall fall within the protection scope of the present invention member.
The feature of the various aspects of the embodiment of the present invention is described more fully below.In the following detailed description, it proposes
Many concrete details, so as to complete understanding of the present invention.But for those of ordinary skill in the art, very bright
Aobvious, the present invention can also be implemented in the case where not needing these details.Below to the description of embodiment
Just for the sake of being better understood by showing example of the invention to the present invention.The present invention is not limited to presented below any
Specific setting and method, but cover all product structures covered without departing from the spirit of the invention, method
Any improvement, replacement etc..In each attached drawing and following description, well known structure and technology is not shown, to avoid right
The present invention causes unnecessary fuzzy.
It should be noted that in the absence of conflict, the feature in the embodiment of the present invention and embodiment can be tied mutually
It closes, each embodiment mutually can be referred to and be quoted.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the principle schematic diagram of the iron bird testing stand of one embodiment of the invention.
As shown in Figure 1, modular iron bird test-bed, according to flight control system, hydraulic system, Landing Gear System and flies control
Iron bird rack is divided into 9 modules by the arrangement of rudder face aboard, respectively head section rack 1, forebody bridging table 2,
Middle fuselage section rack 3, middle rear body bridging table 4, empennage section rack 5, port wing section rack 6, starboard wing section rack 7, left EDP
9,9 rack 8, right EDP rack modules are mutually indepedent, are mutually not attached to.Except forebody bridging table 2, middle fuselage section rack 3 and in
Outside rear body bridging table 4, along aircraft portrait direction, based on remaining 6 individual iron bird test-bed modules are divided
Rack and top rack two parts.
In some embodiments, iron bird testing stand may include: mutually independent head section rack 1, forebody transition bench
Frame 2, middle fuselage section rack 3, middle rear body bridging table 4, empennage section rack 5, port wing section rack 6, starboard wing section rack 7,
Right EDP rack 8, left EDP rack 9.Wherein: head section rack 1, empennage section rack 5, port wing section rack 6, starboard wing section rack
7, right EDP rack 8, left EDP rack 9 include: base frame and top rack；Port wing section rack 6, starboard wing section rack 7
It all include mutually independent aileron rack, outer wing flap and spoiler rack and interior wing flap rack；Empennage section rack 5 includes mutual
Independent left elevator rack, right elevator rack and rudder rack.
In some embodiments, head section rack 1 can be used for installing analog capsule cabin and nose-gear system；
Forebody bridging table 2 is logical as personnel and equipment for connecting head section rack 1 and middle fuselage section rack 3
Road；Middle fuselage section rack 3 can be used for installing main landing gear system and hydraulic system；Middle rear body bridging table 4 can be used for
Middle fuselage section rack 3 and empennage section rack 5 are connected, as personnel and device channels；Empennage section rack 5 can be used for installing lifting
Rudder, rudder rudder face and actuating system；Port wing section rack 6 can be used for installing left side aileron, spoiler, wing flap rudder face and work
Dynamic system；Starboard wing section rack 7 can be used for installing right side aileron, spoiler, wing flap rudder face and actuating system；Right EDP rack 8
It can be used for right engine transfer tube and driving device；Left EDP rack 9 can be used for lefthand engine transfer tube and driving dress
It sets.
In some embodiments, port wing section rack 6 includes: port wing section top rack 6-1,6-2,6-3.Starboard wing section
Rack 7 includes: starboard wing section top rack 7-1,7-2,7-3.On port wing section top rack 6-1,6-2,6-3 and starboard wing section
Portion rack 7-1,7-2,7-3 are asymmetric；Port wing section top rack 6-1,6-2,6-3 are equipped with airborne rudder face or airborne rudder face is false
Part, for being simulated without aerodynamic loading；Starboard wing section top rack 7-1,7-2,7-3 are equipped with airborne rudder face simulating piece, use
It is simulated in aerodynamic loading.
In some embodiments, rudder top rack 5-1 is equipped with rudder face simulating piece, for carrying out aerodynamic loading mould
It is quasi-；Alternatively, rudder top rack 5-1 is equipped with airborne rudder face, for simulating without aerodynamic loading.
In some embodiments, left EDP rack 8 and left EDP rack 9 are mounted on denoising device 8-1,9-1.Head section platform
Analog capsule cabin 2-1 is installed on frame 1.Base frame is bolted on test room floor.Base frame and upper stage
Frame is bolted, and mounting plate is reserved on base frame.It is pneumatic that right side rudder face top rack 7-1,7-2,7-3 are reserved with rudder face
Load loads pressurized strut and installs interface.
Fig. 2 (the 2 width figures including a and b) is the head section horse structure schematic illustration of one embodiment of the invention.
As shown in Fig. 2, the realization of head section rack can be as follows: head section rack 1 includes analog capsule cabin 1-1 and two
Base frame 1-2,1-3, base frame 1-2 are analog capsule cabin support stand, and base frame 1-3 nose-gear installs rack.Mould
Quasi- cockpit 1-1 is head section top rack.Two base frames 1-2,1-3 are mutually indepedent.
Base frame 1-2 is the mounting platform of analog capsule cabin 1-1, guarantees being reliably connected, installing for analog capsule cabin.Basic platform
Frame 1-2 is welded by 100 × 100 square steel, and there is mounting plate in lower end, is bolted on ground.The upper end base frame 1-2
Reserved mounting plate, is connect by bolt with analog capsule cabin 1-1.Base frame 1-2 intensity is able to bear install thereon all and sets
Weight when standby and 10 people 1000kg are worked at the same time.
Analog capsule cabin 1-1 is for installing, arranging that visual system, cockpit shell, operating mechanism, console, signal occur
The components such as device, exerciser.Its lower end is connect by bolt with base frame 1-2 there are installation interface.Analog capsule cabin 1-1 room body
Using glass steel making, cockpit floor is consistent with its airborne part.Analog capsule cabin 1-1 can provide operating interactive for testing crew
The visual displays such as interface and runway, weather.Visual system uses column curtain, is capable of providing fine day, the cloudy day, rains, snows, hail etc.
Weather condition is shown.Cockpit shell, operating mechanism, console are consistent with airborne part.
Base frame 1-3 is nose-gear mounting platform, guarantees to complete nose-gear folding and unfolding, turning on iron bird testing stand
Deng test.Base frame 1-3 and base frame 1-2 are mutually indepedent.Base frame 1-3 is welded by 200 × 200 square steel,
Intensity should be able to meet shock loading requirement when nose-gear folding and unfolding.Reserved nose-gear aerodynamic force when base frame 1-3 is designed
It loads pressurized strut and interface is installed, there is mounting plate in lower end, is bolted on ground.
Fig. 3 (the 2 width figures including a and b) is the forebody bridging table principle schematic diagram of one embodiment of the invention.
As shown in figure 3, the realization of forebody bridging table can be as follows: forebody bridging table 2 does not have top rack,
Include workbench and guardrail 2-1, base frame 2-2, working stand 2-3,2-4 three parts.Forebody bridging table 2 is for connecting machine
Head section rack 1 and middle fuselage section rack 3.
Base frame 2-2 is welded by 100 × 100 square steel, and height is consistent with analog capsule cabin 1-1 floor level.Before
2 antero-posterior pathway width of fuselage changeover portion rack is not less than 2600mm, when intensity is able to bear 10 people 1000kg and works at the same time
Weight.
Forebody bridging table 2 arranges workbench and guardrail 2-1, working stand 2-3,2-4 above, passes through welding and basis
Rack 2-2 is connected.Base frame 2-2 arranges two sides that working stand, right, right two sides working stand width are all not less than 1500mm.Base
There is mounting plate in the lower end plinth rack 2-2, is bolted on ground.
Forebody bridging table 2 reserves testing equipment and personnel channel, facilitates personnel and equipment around iron bird rack
Mobile, channel width is not less than 2000mm, is highly not less than 2000mm.
Fig. 4 (the 2 width figures including a and b) is the middle fuselage section horse structure schematic illustration of one embodiment of the invention.
As shown in figure 4, in some embodiments, the realization of middle fuselage section rack can be as follows: middle fuselage section rack 3 does not have
There is top rack, includes workbench and guardrail 3-1, two base frame 3-2,3-3 three parts.Two base frames 3-2,3-3,
Symmetric design, independently of each other, height are consistent with base frame 2-2 height.Middle fuselage section rack 3 is led for installing left and right
Fall frame and 1#, 2# hydraulic system.
Two base frames 3-2,3-3 are welded by 200 × 200 square steel, and intensity should be able to meet main landing gear receipts
Shock loading requirement when putting.Interface is installed in reserved main landing gear aerodynamic force load pressurized strut when base frame 3-2,3-3 are designed,
There is mounting plate in its lower end, is bolted on ground.Workbench and guardrail 3-1 are arranged above base frame 3-2,3-3,
It is connected by welding and left frame sections rack.
Fig. 5 (the 2 width figures including a and b) is the middle rear body bridging table principle schematic diagram of one embodiment of the invention.
As shown in figure 5, middle rear body bridging table realization can be as follows: middle rear body bridging table 4 does not have top
Rack includes workbench and guardrail 4-1, base frame 4-2, working stand 4-3,4-4 three parts.Base frame 4-2 be in after machine
The support stand of body bridging table 4.Base frame 4-2 height is consistent with two base frame 3-2,3-3 height.Middle rear body mistake
Rack 4 is crossed for connecting middle fuselage rack 3 and empennage section rack 5.
Base frame 4-2 is welded by 100 × 100 square steel, and height is consistent with 3 height of middle fuselage section rack.In after
4 antero-posterior pathway width of fuselage bridging table is not less than 2600mm, and intensity is able to bear when 10 people 1000kg are worked at the same time
Weight.
Middle rear body bridging table 4 arranges workbench and guardrail 4-1, working stand 4-3,4-4 above, through welding in
Rear body bridging table 4 is connected.Right, right two sides working stand width is not less than 1000mm.There is mounting plate in the lower end base frame 4-2,
It is bolted on ground.
Middle rear body bridging table 4 reserves testing equipment and personnel channel, facilitates personnel and equipment around iron bird rack
Movement, channel width be not less than 2000mm, highly be not less than 2000mm.
Fig. 6 (the 2 width figures including a and b) is the empennage section horse structure schematic illustration of one embodiment of the invention.
As shown in fig. 6, the realization of empennage section rack can be as follows: empennage section rack 5 is for installing 3# hydraulic system, rising
Drop the flight control systems components such as rudder, rudder actuator and fly control rudder face, 3# hydraulic system etc..Empennage section rack 5 includes on three
Portion rack 5-1,5-2,5-3, three base frames 5-4,5-5,5-6 and workbench and guardrail 5-7,5-8.Wherein, top rack
5-1 and base frame 5-4 constitutes rudder rack, and top rack 5-2 and base frame 5-5 constitute right elevator rack, top
Rack 5-3 and base frame 5-6 constitutes left elevator rack.Three parts rack is mutually indepedent.
5 base frame of empennage section rack is mainly used for support, installation, fixed 5 top rack of empennage section rack.Empennage section platform
Frame 5 base frame 5-4,5-5,5-6 are welded by 200 × 200 square steel.There is mounting plate in the lower end base frame 5-4,5-5,5-6,
It is bolted on test room floor, upper end bolt is by having reserved mounting plate and top rack 5-1,5-2,5-3
Connection.5 base frame of empennage section rack arranges workbench and guardrail 5-7,5-8, working stand, passes through welding and empennage section rack
5 base frames are connected.Since 5 height of empennage section rack is different, the workbench arranged on rack is designed using two layers, wherein lower layer
Height of table and 4 height of middle rear body bridging table are consistent.There is working stand to be connected between upper layer and lower layer workbench.
Left elevator top rack 5-3 is used for the true part of installation direction rudder or simulating piece.Top rack 5-3 is by profiles such as square steel
It is welded, rigidity should be 4~6 times of rudder actuating system rigidity.The top lower end rack 5-3 leads to there are installation interface
Bolt is crossed to connect with base frame 5-6.
Rudder top rack 5-1 is furnished with two sets of rudder face erection joints.One bell and spigot joint be used for installation direction rudder simulating piece, one
Bell and spigot joint is used for the true part of installation direction rudder.According to test demand, rudder face erection joint and rudder face form are replaced.Installation direction rudder mould
When quasi- part, aerodynamic force load can be carried out, load pressurized strut installation interface and rudder top rack 5-1 are integrally designed.Installation side
When part true to rudder, loaded without aerodynamic force.
Right elevator top rack 5-2 install right elevator simulating piece, top rack 5-2 by the profiles such as square steel weld and
At rigidity should be 4~6 times of elevator actuating system rigidity.The top lower end rack 5-2 passes through bolt there are installation interface
It is connect with base frame 5-5.Right elevator simulating piece simulates the rotary inertia of true rudder face, rotating shaft position.Right elevator simulation
Installation form of the part in the top upper end rack 5-2 is simplified, and is installed using bearing block.It is enterprising in right elevator simulating piece
The load of promoting the circulation of qi power, right elevator top rack 5-2 and aerodynamic force load pressurized strut installation are integrally designed, and are added with reserved aerodynamic force
It carries pressurized strut and interface is installed.
Left elevator top rack 5-3 is also welded by profiles such as square steel, but it and right elevator top rack 5-2 are adopted
Use asymmetrical design.It is different from right elevator top rack 5-2 installation right elevator simulating piece, left elevator top rack 5-3
Upper control surface suspension connector and airborne consistent, installation left elevator bogusware or true part.Left elevator bogusware rotary inertia, rudder face installation
Connector is consistent with true part.The rudder face bogusware or true part installed on the rack 5-3 of left elevator top are all loaded without aerodynamic force.
Fig. 7 (the 2 width figures including a and b) is the port wing section horse structure schematic illustration of one embodiment of the invention.
As shown in fig. 7, the realization of port wing section rack can be as follows: port wing section rack 6 is for installing left side wing
Active face, flight control system component and fluid pressure line etc..Port wing section rack 6 includes three top rack 6-1,6-2,6-3, three
Base frame 6-6,6-7,6-8, workbench and guardrail 6-9 and working stand 6-4,6-5.Wherein, top rack 6-1 and base frame
6-8 constitutes left side aileron rack, and top rack 6-2 and base frame 6-7 constitute the outer wing flap in left side and spoiler rack, upper stage
Frame 6-3 and base frame 6-6 constitutes wing flap rack in left side.Left side aileron rack, outer wing flap and spoiler rack and interior wing flap
Rack is mutually indepedent.
Port wing section rack 6 base frame 6-6,6-7,6-8 are mainly used for support, installation, fix on port wing section rack 6
Portion rack 6-1,6-2,6-3, are welded by 200 × 200 square steel.The lower end base frame 6-6,6-7,6-8 is bolted
On test room floor, upper end bolt is by there is reserved mounting plate to connect with top rack 6-1,6-2,6-3.Port wing section
6 base frame of rack arranges workbench and guardrail 6-9, working stand 6-4,6-5, passes through welding and base frame 6-6,6-7,6-
8 are connected.Workbench width is not less than 3600mm.There are connection port wing section rack 6 and middle fuselage section rack 3 on base frame 6-6
Working stand 6-4,6-5, to facilitate movement of the testing crew between two racks, the width of this working stand is not less than 800mm.
Left side aileron rack top rack 6-1 is for installing left side aileron bogusware or true part, by profiles such as square steel, channel steels
It is welded, there is mounting plate in lower end, is connect by bolt with base frame 6-8.The rotary inertia of left side aileron bogusware, rudder face peace
Joint is consistent with airborne part, control surface suspension connector and airborne consistent on the rack 6-1 of top, to guarantee left side aileron bogusware or true
Part can be mounted on the rack 6-1 of top.Aileron bogusware or true part are all without aerodynamic force on the left of the dress pacified on the rack 6-1 of top
Load.
Wing flap and spoiler rack top rack 6-2 are for installing outside left side spoiler bogusware/true part and left side outside left side
The true part of wing flap, is welded by profiles such as square steel, channel steels, and there is mounting plate in lower end, is connect by bolt with base frame 6-7.
Left side spoiler includes left inside spoiler and two pieces of left outside spoiler.Wing flap outside left side spoiler and left side shares a rack.
The rotary inertia of left side spoiler bogusware, rudder face erection joint are consistent with airborne part, spoiler suspension joint on the rack 6-2 of top
With it is airborne consistent, to guarantee that left side spoiler bogusware or true part can be mounted on the rack 6-2 of top.Pacify on the rack 6-2 of top
Wing flap is airborne part outside the left side of dress, and control surface suspension point is consistent with airborne part.The left side spoiler installed on the rack 6-2 of top
The true part of wing flap is all loaded without aerodynamic force outside bogusware/true part and left side.
Wing flap rack top rack 6-3 is welded for installing the true part of left inside wing flap by profiles such as square steel, channel steels in left side
It forms., there is mounting plate in lower end, is connect by bolt with base frame 6-6.Control surface suspension point is consistent with airborne part thereon.It is left inside
The true part of wing flap is loaded without aerodynamic force.
Fig. 8 (the 2 width figures including a and b) is the starboard wing section horse structure schematic illustration of one embodiment of the invention.
As shown in figure 8, the realization of starboard wing section rack can be as follows: starboard wing section rack 7 is adopted with port wing section rack 6
With asymmetrical design, it is used to install right side wing active face, flight control system component and fluid pressure line etc..Starboard wing section rack 6 wraps
Containing three top rack 7-1,7-2,7-3, three base frame 7-7,7-8,7-9, workbench and guardrail 7-4 and working stand 7-5,
7-6.Wherein, top rack 7-1 and base frame 7-7 constitutes wing flap rack in right side, top rack 7-2 and base frame 7-8
The outer wing flap in right side and spoiler rack are constituted, top rack 7-3 and base frame 7-9 constitute right side aileron rack.Right side aileron
Rack, outer wing flap and spoiler rack and interior wing flap rack are mutually indepedent.
Starboard wing section rack 7 base frame 7-7,7-8,7-9 be mainly used for support, installation, fixed upper right quarter rack 7-1,
7-2,7-3 are welded by 200 × 200 square steel.The lower end base frame 7-7,7-8,7-9 is bolted on laboratory
On ground, upper end bolt is by there is reserved mounting plate to connect with top rack 7-1,7-2,7-3.Base frame 7-7,7-8,
7-9 arranges workbench and guardrail 7-4, working stand 7-5,7-6, is connected by welding and base frame 7-7,7-8,7-9.Work
Platform width is not less than 3600mm.There is the working stand of connection starboard wing section rack 6 and middle fuselage section rack 3 on base frame 7-7, with
Facilitate movement of the testing crew between two racks.The width of this working stand is not less than 800mm.
Right side aileron rack top rack 7-3 is welded for aileron simulating piece on the right side of installing by profiles such as square steel,
There is mounting plate in lower end, is connect by bolt with base frame 7-9.The rotary inertia of right side aileron simulating piece, rudder surface rotation axis position
With it is airborne consistent.Installation form of the starboard aileron simulating piece in the top upper end rack 7-3 is simplified, and is pacified using bearing block
Dress.Aileron simulating piece carries out aerodynamic force load on the right side of the dress pacified on the rack 7-3 of top.It loads pressurized strut and starboard aileron section top
Rack 7-3 integrated design guarantees disassembly, installation of the load pressurized strut on the rack 7-3 of top.
Wing flap and spoiler rack top rack 7-2 are for installing wing flap outside right side spoiler simulating piece and right side outside right side
Simulating piece is welded by profiles such as square steel, and there is mounting plate in lower end, is connect by bolt with base frame 7-8.Right side flow-disturbing
Plate includes spoiler and outer two pieces of spoiler of the right side in the right side.Wing flap outside right side spoiler and right side shares a rack.Right side flow-disturbing
The rotary inertia of plate simulating piece, rudder surface rotation axis position and airborne consistent.Wing flap is false outside the right side installed on the rack 7-2 of top
Part, rotary inertia, the hitch point of wing flap bogusware are consistent with airborne part outside right side.The right side spoiler installed on the rack 7-2 of top
Wing flap bogusware all carries out aerodynamic force load outside simulating piece and right side.It loads pressurized strut and rack 7-2 in top is integrally designed, and guarantees
Load disassembly, installation of the pressurized strut on the rack 7-2 of top.
Wing flap rack top rack 7-1 is used to install wing flap bogusware in the right side in right side, is welded by profiles such as square steel,
There is mounting plate in lower end, is connect by bolt with base frame 7-7.The rotary inertia of wing flap bogusware, control surface suspension point and machine in the right side
Holder is consistent.Wing flap bogusware carries out aerodynamic force load in the right side.It loads pressurized strut and rack 7-1 in top is integrally designed, and guarantees to add
Carry disassembly, installation of the pressurized strut on the rack 7-1 of top.
Fig. 9 (the 2 width figures including a and b) is the left EDP horse structure schematic illustration of one embodiment of the invention.
As shown in figure 9, the left realization of EDP rack 8 can be as follows: left EDP rack 8 includes denoising device 8-1, workbench
And guardrail 8-2, base frame 8-3 and working stand 8-4.Base frame 8-3 is support stand, is equipped with working stand thereon.Noise reduction
Device 8-1 is the top rack of left EDP rack 8.Denoising device 8-1 is closing cabin, is connected by bolt and base frame 8-3
It connects, EDP and EDP driving device is installed inside denoising device.
Base frame 8-3 is welded by 200 × 200 square steel.The lower end base frame 8-3 is bolted on laboratory
On ground, upper end bolt is by there is reserved mounting plate to connect with denoising device 8-1.Base frame 8-3 intensity is able to bear
The weight when all devices and 10 people 1000kg installed thereon work at the same time.Base frame 8-3 arranges workbench and guardrail 8-
2, working stand 8-4 is connected by welding and base frame 8-3.There are the left EDP rack 8 of connection and middle fuselage on base frame 8-3
The working stand of section rack 3, to facilitate movement of the testing crew between two racks.The width of this working stand is not less than 800mm.
The height of denoising device 8-1 is not less than 1500mm, to guarantee enough operating spaces.Denoising device 8-1 is close
Rack side is equipped with door, and to facilitate testing crew to enter, denoising device 8-1 can make EDP and its driving device work bring
Noise is down to 80dB or less.
Figure 10 (the 2 width figures including a and b) is the left EDP horse structure schematic illustration of one embodiment of the invention.
As shown in Figure 10, the right realization of EDP rack 9 can be as follows: right EDP rack 9 and left 8 symmetric design of EDP rack,
Include denoising device 9-1, working stand 9-2, workbench and guardrail 9-3, base frame 9-4.
Foregoing invention embodiment can be according to flight control system, hydraulic system, Landing Gear System and rudder face aboard as a result,
Layout, so that it is determined that the division of iron bird rack module.Iron bird examination can be reduced using such modular iron bird test-bed
The relevance of horse structure design is tested, while reducing the design requirement to rack integral strength and rigidity, improves iron bird examination
The intrinsic frequency of rack is tested, production and processing, the installation convenient for iron bird test-bed are fixed and dismounting is safeguarded, and can reduce iron bird
Test-bed production, change cost.Left and right sides wing rack uses asymmetrical design, and left side wing rack can realize rudder face bogusware
With the exchange of airborne part, to improve the flexibility of test.Right side wing rack installs rudder face simulating piece, has carried out aerodynamic force
Load, can ensure that the authenticity of test in this way and reduce the cost of iron bird platform development.EDP noise reduction is installed on EDP rack
Device, can effectively reduce the noise generated when EDP work, provide good working environment for test test personnel.Working stand, work
Make platform and guardrail is only connect with base frame, ensure that the independence of top rack.Modular iron bird test-bed can be maximum
Development cost is saved to limit, flexible design is easy to implement, and has very high universal value in Aviation Industry test.
It should be noted that above-mentioned flow operations can carry out different degrees of combined application, for simplicity, repeating no more
Various combined implementations.Those skilled in the art can by actual conditions by above-mentioned method the step of sequence (or
The position of the component of person's product) it is adjusted flexibly, or the operation such as combination.
In addition, the implementation of functional unit shown in above-described embodiment can be the group of hardware, software or the two
It closes.When realizing in hardware, electronic circuit, specific integrated circuit (ASIC), plug-in unit, function card etc. can be made.When with
When software mode is realized, the program or code segment of required task can be used to carry out with thing.Program or code segment can be with
Be stored in out machine perhaps in readable medium or its can by data-signal entrained in carrier wave in transmission medium or
Communication links are sent.
Finally it should be noted that: the above embodiments are merely illustrative of the technical solutions of the present invention, but protection of the invention
Range is not limited thereto, and anyone skilled in the art in the technical scope disclosed by the present invention, can be thought easily
It is modified or replaceed to various equivalent, these, which are modified or replaceed, should all be included within the scope of the present invention.
Claims (8)
1. a kind of iron bird testing stand characterized by comprising
Mutually independent head section rack (1), forebody bridging table (2), middle fuselage section rack (3), middle rear body transition bench
Frame (4), empennage section rack (5), port wing section rack (6), starboard wing section rack (7), right EDP rack (8), left EDP rack
(9), in which:
Head section rack (1), empennage section rack (5), port wing section rack (6), starboard wing section rack (7), right EDP rack (8),
Left EDP rack (9) includes: base frame and top rack；
Port wing section rack (6), starboard wing section rack (7) all include mutually independent aileron rack, outer wing flap and flow-disturbing pallet
Frame and interior wing flap rack；
(5 include mutually independent left elevator rack, right elevator rack and rudder rack to empennage section rack；
Head section rack (1), for installing analog capsule cabin and nose-gear system；
Forebody bridging table (2) is logical as personnel and equipment for connecting head section rack (1) and middle fuselage section rack (3)
Road；
Middle fuselage section rack (3), for installing main landing gear system and hydraulic system；
Middle rear body bridging table (4), for connecting middle fuselage section rack (3) and empennage section rack (5), as personnel and equipment
Channel；
Empennage section rack (5), for installing elevator, rudder rudder face and actuating system；
Port wing section rack (6), for installing left side aileron, spoiler, wing flap rudder face and actuating system；
Starboard wing section rack (7), for installing right side aileron, spoiler, wing flap rudder face and actuating system；
Right EDP rack (8) is used for right engine transfer tube and driving device；
Left EDP rack (9) is used for lefthand engine transfer tube and driving device.
2. testing stand according to claim 1, which is characterized in that wherein:
Port wing section rack (6) includes: port wing section top rack (6-1,6-2,6-3),
Starboard wing section rack (7) includes: starboard wing section top rack (7-1,7-2,7-3),
Port wing section top rack (6-1,6-2,6-3) and starboard wing section top rack (7-1,7-2,7-3) are asymmetric；
Port wing section top rack (6-1,6-2,6-3) is equipped with airborne rudder face or airborne rudder face bogusware, for without pneumatic
It is load simulated；
Starboard wing section top rack (7-1,7-2,7-3) is equipped with airborne rudder face simulating piece, simulates for aerodynamic loading.
3. testing stand according to claim 1, which is characterized in that wherein:
Rudder top rack (5-1) is equipped with rudder face simulating piece, for carrying out aerodynamic loading simulation；
Alternatively,
Rudder top rack (5-1) is equipped with airborne rudder face, for simulating without aerodynamic loading.
4. testing stand according to claim 1, which is characterized in that wherein:
Left EDP rack (8) and left EDP rack (9) are mounted on denoising device (8-1,9-1).
5. testing stand according to claim 1, which is characterized in that wherein:
Analog capsule cabin (2-1) is installed on head section rack (1).
6. testing stand according to claim 1, which is characterized in that wherein:
Base frame is bolted on test room floor.
7. testing stand according to claim 6, which is characterized in that wherein:
Base frame is bolted with top rack, and mounting plate is reserved on base frame.
8. the testing stand according to any one of claim 2-7, it is characterized in that:
Right side rudder face top rack (7-1,7-2,7-3) is reserved with rudder face aerodynamic loading load pressurized strut installation interface.
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| CN201811586779.4A CN109573100B (en) | 2018-12-24 | 2018-12-24 | Iron bird test stand |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811586779.4A CN109573100B (en) | 2018-12-24 | 2018-12-24 | Iron bird test stand |
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| CN109573100B CN109573100B (en) | 2021-11-02 |
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| CN113071704A (en) * | 2021-03-30 | 2021-07-06 | 中国商用飞机有限责任公司 | Test method and system for simulating wing deformation |
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| CN109573100B (en) | 2021-11-02 |
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