CN109581314A - The device of aircraft RCS test - Google Patents
The device of aircraft RCS test Download PDFInfo
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- CN109581314A CN109581314A CN201811539152.3A CN201811539152A CN109581314A CN 109581314 A CN109581314 A CN 109581314A CN 201811539152 A CN201811539152 A CN 201811539152A CN 109581314 A CN109581314 A CN 109581314A
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- heavily loaded
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- 238000012360 testing method Methods 0.000 title claims abstract description 28
- 230000033001 locomotion Effects 0.000 claims abstract description 28
- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 230000003028 elevating effect Effects 0.000 claims abstract description 6
- 238000013461 design Methods 0.000 claims abstract description 5
- 239000000725 suspension Substances 0.000 claims description 7
- 230000008859 change Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 17
- 238000000034 method Methods 0.000 description 9
- 230000006870 function Effects 0.000 description 8
- 238000001514 detection method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
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- 230000005540 biological transmission Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000003032 molecular docking Methods 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
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- 238000007689 inspection Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000011017 operating method Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/41—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using analysis of echo signal for target characterisation; Target signature; Target cross-section
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- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention proposes a kind of devices of aircraft RCS test.It include: hangar system, lifting rope support rod, parallel moving mechanism, heavily loaded turntable, support jacking system, lifting sliding table, in which: the countertop segment of heavily loaded turntable is concordant with ground；Support jacking system hangs on the table top lower part of heavily loaded turntable；The two sides of support jacking system are respectively arranged with the lifting sliding table for capableing of independent linkage control；Lifting sliding table is equipped with parallel moving mechanism；Design has support rod on parallel moving mechanism；Support rod is used for elevating movement or translational motion；Hangar system includes lifting rope；Lifting rope is overlapped with the centre of gyration of heavily loaded turntable, is moved up and down for towing aircraft, and do 360 degree of rotary motions around lifting rope.The embodiment of the present invention be located at the erecting by overhang that is overlapped of turntable center and form " two one are hung " system, in the case where the integrality that aircraft can not be destroyed, the RCS of airplane complete machine is tested, flight attitude is not influenced, with higher kinematic accuracy and bearing capacity.
Description
Technical field
The present invention relates to the technical fields of aircraft test, more particularly, to a kind of device of aircraft RCS test.
Background technique
Radar Cross Section (Radar Cross Section, RCS) is the important of one frame invisbile plane of evaluation and measurement
Technical parameter.In recent years, the development that country has carried out stealthy aircraft has carried out the stealthy of aircraft configuration in development process
Performance test carries out the test of RCS performance using low scatterer (LRCS) support aircraft.
Fig. 1 is that low scatterer supports aircraft to test structure chart.Such as Fig. 1, current techniques need the setting of airframe abdomen with
The interface and pose_adjuster of low scatterer.This destroys the integralities of aircraft, can not achieve the RCS test of airplane complete machine.At present
Technology cannot carry out the RCS test of airplane complete machine, can not solve the detection of RCS of the aircraft entity under complete machine state, because this
The use state of aircraft can be had an impact, be unable to ensure aircraft RCS technical parameter and meet technique and tactics index.
Summary of the invention
The technical issues of embodiment of the present invention solves are as follows:
RCS test can not be integrally carried out for aircraft in the case where not destroying integrality, the use state of aircraft, it can not
Ensure that aircraft RCS technical parameter meets technique and tactics index.
The technical solution of the embodiment of the present invention are as follows:
A kind of device of aircraft RCS test, comprising:
Hangar system, lifting rope support rod, parallel moving mechanism, heavily loaded turntable, support jacking system, lifting sliding table, in which:
Heavily loaded turntable includes: main part and countertop segment；
Main part is located inside ground well, and countertop segment is concordant with ground；
Support jacking system hangs on the table top lower part of heavily loaded turntable；
The two sides of support jacking system are respectively arranged with the lifting sliding table for capableing of independent linkage control
Lifting sliding table is equipped with parallel moving mechanism；
Design has support rod on parallel moving mechanism；
Support rod is used for elevating movement or translational motion；
Hangar system includes lifting rope；
Lifting rope is overlapped with the centre of gyration of heavily loaded turntable, is moved up and down for towing aircraft, and do 360 around lifting rope
Spend rotary motion.
The technical effect of the embodiment of the present invention are as follows:
The interface of aircraft in the fabrication process is utilized using the test device of " two one are hung ", solves aircraft entity in complete machine
The detection that 360 ° of revolutions and the RCS under wide-angle pitch attitude are carried out under state, will not have an impact the use state of aircraft,
Have the characteristics that carrying, kinematic accuracy are high greatly.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it is therefore apparent that drawings described below is only some embodiments of the present invention, for this
For the technical staff in field, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is that low scatterer supports aircraft to test structure chart；
Fig. 2 is that " two one are hung " of one embodiment of the invention supports aircraft to test structural schematic diagram；
Fig. 3 is " two one are hung " apparatus system composition schematic diagram of one embodiment of the invention；
Fig. 4 is the support jacking system structural schematic diagram of one embodiment of the invention；
Fig. 5 is the parallel moving mechanism structural schematic diagram of one embodiment of the invention；
Fig. 6 is the large-scale heavy duty turntable structure schematic diagram of one embodiment of the invention；
Fig. 7 is the target transport vehicle structural schematic diagram of one embodiment of the invention；
Fig. 8 is that two one of one embodiment of the invention hang schematic elevation view；
Fig. 9 is the aircraft horizontal checkout status diagram of one embodiment of the invention；
Figure 10 is the aircraft angle of depression degree test mode schematic diagram of one embodiment of the invention；
Figure 11 is the aircraft elevation angle degree test mode schematic diagram of one embodiment of the invention.
In figure: 1 is aircraft, and 2 be low scatterer, and 3 be hangar system, and 4 be lifting rope, and 5 be support rod, and 6 be parallel moving mechanism, 7
It is support jacking system for large-scale heavy duty turntable, 8,9 be lifting sliding table, and 10 be load-bearing frame, and 11 be center positioning system, and 12 are
Wheel group, 13 be bracket, and 14 be micromatic setting, 15 target carriages.
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 embodiment of the present invention, rather than whole embodiments.Based on the embodiments of the present invention, those skilled in the art
Without making creative work, every other embodiment obtained, shall fall within the protection scope of the present invention.
The feature and illustrative examples of various aspects of the invention is described more fully below.In following detailed description
In, many details are proposed, in order to provide complete understanding of the present invention.But come for those skilled in the art
It says it will be apparent that the present invention can be implemented in the case where not needing some details in these details.Below to reality
The description of example is applied just for the sake of providing and better understanding to of the invention by showing example of the invention.The present invention is never
It is limited to any specific setting and method set forth below, but covering finishes under the premise of without departing from the spirit of the present invention
Structure, method, any improvement of device, substitutions and modifications.In the the accompanying drawings and the following description, well known structure and skill is not shown
Art is unnecessary fuzzy to avoid causing to the present invention.
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. 2 is that " two one are hung " of one embodiment of the invention supports aircraft to test structural schematic diagram；Fig. 3 is that the present invention one is real
Apply " two one are hung " apparatus system composition schematic diagram of example；Fig. 4 is the support jacking system structural representation of one embodiment of the invention
Figure；Fig. 5 is the parallel moving mechanism structural schematic diagram of one embodiment of the invention；Fig. 6 is the large-scale heavy duty turntable of one embodiment of the invention
Structural schematic diagram；Fig. 7 is the target transport vehicle structural schematic diagram of one embodiment of the invention；Fig. 8 is the two of one embodiment of the invention
Branch one hangs schematic elevation view；Fig. 9 is the aircraft horizontal checkout status diagram of one embodiment of the invention；Figure 10 is that the present invention one is real
Apply the aircraft angle of depression degree test mode schematic diagram of example；Figure 11 is that the aircraft elevation angle degree test mode of one embodiment of the invention is illustrated
Figure.
Referring to figs. 2 to Figure 11, in order to meet aircraft RCS testing requirement, the erection, support, lifting, tune of airplane complete machine are realized
The postures function of motion such as appearance and rotation, " two one are hung " system include large-scale heavy duty turntable, support jacking system and hangar system.
Heavily loaded turntable 7 (also referred to as: large-scale heavy duty turntable 7) is one 20.5 meters of diameter, 550 tons of load-carrying, can do 360 degree of companies
The one-dimensional turntable of continuous revolution, is docked on large-scale heavy duty turntable 7 for the ease of aircraft 1.7 main part of large-scale heavy duty turntable is located at
Inside ground well, the table top of large-scale heavy duty turntable 7 is concordant with ground, and design thereon has support jacking system 8, hangs on large-scale heavy duty
The table top lower part of turntable 7, support be provided on jacking system 82 sets can the control of independent linkage lifting sliding table 9, separate from branch
The two sides of jacking system 8 are supportted, each lifting sliding table 9 is equipped with parallel moving mechanism 6, and design has support rod 5 on every set parallel moving mechanism 6,
So that support rod 5 both can be moved up and down or do translational motion in this way；Hangar system 3 is a set of hoisting mechanism, lifting rope 4 and big
The centre of gyration of type heavy duty turntable 7 is overlapped, can towing aircraft 1 move up and down, 360 degree of revolutions can also be done around lifting rope 4
Movement.
The end of suspension centre and the lifting rope 4 of hangar system 3 on aircraft 1 is attached, and aircraft 2 is located at 2 thousand on wing
Jin vertex carries out with 5 top of support rod of support jacking system 8 hinged respectively, by this connection at 3, makes aircraft 1 and " two
One hangs " device forms connection.
When aircraft 1 moves up and down, the lifting of 2 support rods 5 of the lifting rope 4 and support jacking system 8 of hangar system 3
Movement mechanism synchronization lifting makes aircraft 1 be raised to test height or be down on large-scale heavy duty turntable table top.
When aircraft 1 does pitching movement, because hangar system 3 lifting rope 4 always with the centre of gyration weight of large-scale heavy duty turntable 7
It closes, when aircraft 1 does pitching movement, the spacing needs of suspension centre and fulcrum change, therefore complete the tune of pitch angle in aircraft 1
When whole, the lifting rope 4 of hangar system 3 and the parallel moving mechanism 6 of 2 support rods 5 of support jacking system 8 is needed to do cooperative motion.
When aircraft 1 completes the pitching motion posture of some angle, large-scale heavy duty turntable 7 carries out 360 ° of rotary motion,
So that the state of aircraft 1 in this case is shown completely, is tested convenient for the RCS of aircraft, in this way, complete multiple pitch angles
The test of degree can cover the entire shape of aircraft 1 comprehensively.
It should be noted that above-mentioned flow operations can carry out different degrees of combined application, for simplicity, repeating no more
The sequence of above-mentioned operating procedure can be carried out spirit according to actual needs by various combined implementations, those skilled in the art
Adjustment living, or above-mentioned steps are subjected to the operation such as flexible combination.
Fig. 7 is the target transport vehicle structural schematic diagram of one embodiment of the invention.
As shown in fig. 7, target transport vehicle 15 may include bracket 13 and micromatic setting 14.
Innovative point of the invention known to above-mentioned can be as follows:
1. " two one are hung " system includes large-scale heavy duty turntable, supports jacking system, hangar system and target transport vehicle, real
Docking, support, lifting and the pose adjustment function of airplane complete machine are showed.Large-scale heavy duty turntable, feature use large-scale high-precision
Setting element centered on cylinder roller bearing enables turntable to do high-precision rotary around center；Devise 8 groups of edge drivings
The extremely slow movement of large-scale heavy duty turntable can be converted into high speed by support and driving unit of the wheel group as large-scale heavy duty turntable
The high-speed motion of edge driving motor avoids creeping for turntable conducive to the motion control accuracy of large-scale heavy duty turntable.Support rises
Drop system, it is characterized in that being respectively provided with 2 sets of support rods in load-bearing frame two sides, the straight line by being arranged in load frame two sides is led
Rail guidance system and gear-rack drive system make 2 sets of support rods can either self-movement, be also able to carry out and move synchronously, meet
The elevating function for docking and supporting aircraft of supporting bar top and " push rod enters position " of aircraft fulcrum；It is set in the lower end of support rod
Parallel moving mechanism is set, support rod can be made to obtain translation function, meet the functional requirement that aircraft does pitch attitude.Hangar system,
It is characterized in that using hoist engine structure, the lifting rope being fixed on reel by one end is connected with aircraft suspension centre, controls the rotation of reel
Precision implements the lifting of aircraft suspension centre.Target transport vehicle, it is characterized in that can be by itself elevating function and fine adjustment function
Aircraft is transferred on target transport vehicle under jack holding state, and is transported on large-scale heavy duty turntable.
2. aircraft is docked with " two one are hung " device, moved by the independent-lifting of 1 support rod micro- with transport vehicle
Power Regulation is able to achieve supporting bar top with " push rod enters position " of aircraft fulcrum to connection function.
3. hangar system can pull aircraft suspension centre, support 2 support rods of jacking system that can support aircraft fulcrum, this
Test height is docked and risen to set system synchronization lifting, realization with aircraft.
4. hangar system lifting rope is overlapped with large-scale heavy duty turntable center, turntable does 360 degree of revolutions and support rod is driven to make aircraft
It is rotated in test height around turntable center, realizes the RCS detection of airplane complete machine circumferential profile.
5. the co-operating of hangar system and 2 sets of support jacking system parallel moving mechanisms makes aircraft always around large-scale weight
In the case that idling platform center is constant, the pitching motion of multi-angle is carried out, realizes the RCS inspection of airplane complete machine or more shape
It surveys.
The invention has the benefit that using the test device of " two one are hung " using aircraft connecing in the fabrication process
Mouthful, the detection that aircraft entity carries out 360 ° of revolutions and the RCS under wide-angle pitch attitude under complete machine state is solved, it will not be to winged
The use state of machine has an impact, and has the characteristics that carrying, kinematic accuracy are high greatly.
It should be noted that the implementation of functional unit shown in above-described embodiment can be hardware, software, firmware
Or their combination.When realizing in hardware, it may, for example, be electronic circuit, specific integrated circuit (ASIC), fit
When firmware, plug-in unit, function card etc..When being realized with software mode, element of the invention is used to execute required task
Program or code segment.Perhaps code segment can store in machine readable media or by carrying in carrier wave program
Data-signal is sent in transmission medium or communication links." machine readable media " may include being capable of storage or transmission information
Any medium.The example of machine readable media includes electronic circuit, semiconductor memory devices, ROM, flash memory, erasable ROM
(EROM), floppy disk, CD-ROM, CD, hard disk, fiber medium, radio frequency (RF) link, etc..Code segment can via such as because
The computer network of special net, Intranet etc. is downloaded.
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 device of aircraft RCS test characterized by comprising
Hangar system (3), lifting rope (4) support rod (5), parallel moving mechanism (6), heavily loaded turntable (7), support jacking system (8), lifting
Slide unit (9), in which:
The heavy duty turntable (7) includes: main part and countertop segment；
The main part is located inside ground well, and the countertop segment is concordant with ground；
Support jacking system (8) hangs on the table top lower part of heavily loaded turntable (7)；
The two sides of support jacking system (8) are respectively arranged with the lifting sliding table (9) for capableing of independent linkage control；
The lifting sliding table 9 is equipped with parallel moving mechanism (6)；
Design has support rod (5) on the parallel moving mechanism (6)；
The support rod (5) is used for elevating movement or translational motion；
The hangar system (3) includes lifting rope (4)；
The lifting rope 4 is overlapped with the centre of gyration of heavily loaded turntable 7, is moved up and down for towing aircraft 1, and surrounds lifting rope 4
Do 360 degree of rotary motions.
2. the apparatus according to claim 1, which is characterized in that wherein:
The lifting rope (4) of the hangar system (3) with 1 suspension centre on aircraft (1) for being attached；
The support rod (5) of support jacking system (8) is respectively used to the fulcrum with 2 jack on the wing of aircraft (1)
It is attached.
3. the apparatus of claim 2, which is characterized in that wherein:
When aircraft (1) moves up and down, the lifting rope (4) of hangar system (3) and 2 support rods (5) of support jacking system (8)
Elevating movement mechanism synchronization lifting, so that aircraft (1) is raised to test height or is down on the table top of the heavily loaded turntable (7).
4. the apparatus of claim 2, which is characterized in that wherein:
When aircraft (1) does pitching movement, the lifting rope (4) of hangar system (3) centre of gyration with the heavily loaded turntable (7) always
It is overlapped.
5. the apparatus of claim 2, which is characterized in that wherein:
When aircraft (1) does pitching movement, the spacing needs of the suspension centre and the fulcrum change.
6. the apparatus of claim 2, which is characterized in that wherein:
When aircraft (1) completes the adjustment of pitch angle, 2 of the lifting rope (4) of hangar system (3) and support jacking system (8)
The parallel moving mechanism (6) of support rod (5) does cooperative motion.
7. the apparatus of claim 2, which is characterized in that wherein:
When aircraft (1) completes the pitching motion posture of some angle, heavily loaded turntable (7) carries out 360 ° of rotary motion, makes to fly
The state of machine (1) in this case can be shown completely, and complete the RCS test of multiple pitch angles.
8. device according to any one of claims 1-7, which is characterized in that wherein:
The heavy duty turntable (7) is one 20.5 meters of diameter, 550 tons of load-carrying, can make the one-dimensional turntable of 360 degree of continuous rotaries.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811539152.3A CN109581314A (en) | 2018-12-14 | 2018-12-14 | The device of aircraft RCS test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811539152.3A CN109581314A (en) | 2018-12-14 | 2018-12-14 | The device of aircraft RCS test |
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| CN109581314A true CN109581314A (en) | 2019-04-05 |
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ID=65930400
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| CN201811539152.3A Pending CN109581314A (en) | 2018-12-14 | 2018-12-14 | The device of aircraft RCS test |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110001328A (en) * | 2019-03-05 | 2019-07-12 | 上海宇航系统工程研究所 | A kind of spacecraft simulator |
| CN111562792A (en) * | 2019-12-24 | 2020-08-21 | 中国航空工业集团公司北京航空精密机械研究所 | Airplane pitch angle adjusting control device and working method thereof |
| CN111912453A (en) * | 2020-06-15 | 2020-11-10 | 成都飞机工业（集团）有限责任公司 | Device for simultaneously obtaining target three-dimensional moment and angle for RCS test |
| CN112356761A (en) * | 2020-09-22 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Aircraft transportation method based on whole machine erection |
| CN112591139A (en) * | 2020-12-25 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Low-scattering supporting system of mounting aircraft |
| CN112720386A (en) * | 2020-12-25 | 2021-04-30 | 中国航空工业集团公司北京航空精密机械研究所 | Compatible rotatory revolving stage of jumbo size fecund article |
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| CN112720386B (en) * | 2020-12-25 | 2023-05-30 | 中国航空工业集团公司北京航空精密机械研究所 | Large-size multi-product compatible rotary turntable |
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Application publication date: 20190405 |
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