CN107036783A - A kind of carrier aircraft support prepared for captive trajectory testing ground - Google Patents
A kind of carrier aircraft support prepared for captive trajectory testing ground Download PDFInfo
- Publication number
- CN107036783A CN107036783A CN201611237473.9A CN201611237473A CN107036783A CN 107036783 A CN107036783 A CN 107036783A CN 201611237473 A CN201611237473 A CN 201611237473A CN 107036783 A CN107036783 A CN 107036783A
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- carrier aircraft
- poppet
- hinge component
- normal direction
- support arm
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- 238000012360 testing method Methods 0.000 title claims abstract description 30
- 238000013519 translation Methods 0.000 claims abstract description 14
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 3
- 238000002474 experimental method Methods 0.000 description 4
- 230000005611 electricity Effects 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Current-Collector Devices For Electrically Propelled Vehicles (AREA)
Abstract
The invention belongs to aviation aerodynamic force wind-tunnel technique field, it is related to a kind of carrier aircraft support prepared for captive trajectory testing ground.It is characterized in that：It includes door shape support frame, translation mechanism and guide rod cranking block mechanism；Translation mechanism includes spiral lift 5, line slideway 6, sliding block installing plate 7 and after-poppet 9；Guide rod cranking block mechanism includes servo electric jar 1, electronic jar 2, pitching support arm 4, after-poppet 9, the 1st hinge component 10, the 2nd hinge component 11 and the 3rd hinge component 12.The present invention proposes a kind of carrier aircraft support prepared for captive trajectory testing ground, solve the problem that carrier aircraft can not be supported when captive trajectory testing ground prepares, shorten the preparation for carrying out captive trajectory testing state and check the test period taken, improve the service efficiency of wind-tunnel.
Description
Technical field
The invention belongs to aviation aerodynamic force wind-tunnel technique field, it is related to a kind of captive trajectory testing ground that is used for and prepares
Carrier aircraft support.Experiment posture of the carrier aircraft in wind-tunnel can specifically be simulated, prepared for captive trajectory testing ground
Carrier aircraft support meanss.
Background technology
Captive trajectory testing is a kind of extraordinary wind tunnel test for studying store Combinations and carrier separation security feature, experiment China and foreign countries
The separation for hanging thing and carrier aircraft is realized by a kind of six-freedom motion mechanism.Wherein, carrier aircraft supports real using wind tunnel model support
Existing its angle of pitch change, store Combinations use six-freedom motion mechanism supports.Adjusted by controlling mechanism in six degree of freedom plug-in
The initial relative position of thing and carrier aircraft, is the necessary condition that guarantee test is smoothed out.According to test requirements document to store Combinations with carrying
Machine relative position relation carries out static simulation, can check the running status of six degree of freedom, and asking of being likely to occur is investigated out in time
Topic.Currently, the preparation of captive trajectory testing state and review time occupy the test period of wind-tunnel, reduce the use of wind-tunnel
Efficiency.It is more and more with wind tunnel test, take wind-tunnel facilities and carry out experiment and prepare meet experiment demand.It need to grind
Make the ground supports structure of a carrier aircraft to simulate holding state of the carrier aircraft in wind-tunnel, while realizing the phase of wind tunnel model support
Close function.Current wind tunnel test ground preparation model support is all fixed static, it is impossible to carry out pitching and normal direction motion, nothing
Method meets the ground preparation requirement of captive trajectory testing.
The content of the invention
The purpose of the present invention is：A kind of carrier aircraft support prepared for captive trajectory testing ground is proposed, to solve to catch
The problem that carrier aircraft can not be supported when trajectory tests ground prepares is obtained, the preparation and inspection for shortening progress captive trajectory testing state are accounted for
Test period, improves the service efficiency of wind-tunnel.
The technical scheme is that：A kind of carrier aircraft support prepared for captive trajectory testing ground, it is characterised in that：
It includes door shape support frame, translation mechanism and guide rod cranking block mechanism；
Door shape support frame is made up of 2 column 8a, 1 long beam 8b, 2 normal direction columns 3 and 4 tail trimmer 8c, and 2 are stood
Post 8a upper end is vertical with long beam 8b two ends respectively to be connected as under entirety, the upper end of 2 normal direction columns 3 and long beam 8b
Surface is vertically connected as entirety, positioned at the middle part and lower end of the normal direction column 3 on the left side by 2 tail trimmer 8c with being located at the left side
Column 8a is connected as entirety, and 2 tail trimmer 8c and standing positioned at the right are passed through positioned at the middle part and lower end of the normal direction column 3 on the right
The space that post 8a is connected as between entirety, 2 normal direction columns 3 turns into the installing space of translation mechanism and guide rod cranking block mechanism；
Translation mechanism includes spiral lift 5, line slideway 6, sliding block installing plate 7 and after-poppet 9；Spiral lift 5 one
End is arranged on the leading flank of long beam 8b in door shape support frame, and the other end is linked together with after-poppet 9, and after-poppet 9 is fixed on
On sliding block installing plate 7, the both sides of sliding block installing plate 7 are separately mounted on 2 line slideways 6, and line slideway 6 is separately fixed at a shape
The trailing flank of 2 normal direction columns 3 of support frame or so；It is spiral lift 5 and long beam 8b, line slideway 6 and normal direction column 3, straight
It is bolted between line guide rail 6 and after-poppet 9, spiral lift 5 and after-poppet 9；
Guide rod cranking block mechanism includes servo electric jar 1, electronic jar 2, pitching support arm 4, after-poppet 9, the 1st hinge component
10th, the 2nd hinge component 11 and the 3rd hinge component 12；Electronic jar 2 is bolted on after-poppet 9, servo electric jar
1 is fixed together by the 3rd hinge component 12 and electronic jar 2, and pitching support arm 4 passes through the 2nd hinge component 11 and servo electricity
Dynamic cylinder 1 is fixed together, and after-poppet 9 is fixed together by the 1st hinge component 10 and pitching support arm 4；1st hinge component 10,
2nd hinge component 11 and the 3rd hinge component 12 are rotary gemel, and two parts that can limit its connection can only be along hinge axes
Carry out relative rotary motion.
The running of translation mechanism and guide rod cranking block mechanism is：The carrier aircraft angle of attack as needed, controls servo electric jar 1
Stroke, 1st hinge component 10 of the pitching support arm 4 around the lower section of normal direction girder 3 is rotated and is reached the given carrier aircraft angle of attack；According to
Carrier aircraft change in angle of attack amount calculates carrier aircraft high variable quantity, and control spiral lift 5 makes after-poppet 9 and sliding block installing plate 7 along installation
Line slideway 6 on normal direction column 3 is moved；Because pitching support arm 4 is fixed together with after-poppet 9, therefore installed in pitching branch
The carrier aircraft of the front end of arm 4 carries out vertical motion with pitching support arm 4, compensate for because of the Normal Displacement amount that carrier aircraft change in angle of attack is produced.
It is an advantage of the invention that：A kind of carrier aircraft support prepared for captive trajectory testing ground is proposed, solves and catches
The problem that carrier aircraft can not be supported when trajectory tests ground prepares is obtained, the preparation and inspection for carrying out captive trajectory testing state is shortened
The test period of occupancy, improves the service efficiency of wind-tunnel.
Brief description of the drawings
Fig. 1 is the partial structural diagram of the present invention.
Fig. 2 is Fig. 1 right view, illustrate only the drawing of center section.
Fig. 3 is the axonometric drawing of monnolithic case of the present invention.
Embodiment
The present invention is described in further details below.Referring to Fig. 1 to Fig. 3, it is accurate that one kind is used for captive trajectory testing ground
Standby carrier aircraft support, it is characterised in that：It includes door shape support frame, translation mechanism and guide rod cranking block mechanism；
Door shape support frame is made up of 2 column 8a, 1 long beam 8b, 2 normal direction columns 3 and 4 tail trimmer 8c, and 2 are stood
Post 8a upper end is vertical with long beam 8b two ends respectively to be connected as under entirety, the upper end of 2 normal direction columns 3 and long beam 8b
Surface is vertically connected as entirety, positioned at the middle part and lower end of the normal direction column 3 on the left side by 2 tail trimmer 8c with being located at the left side
Column 8a is connected as entirety, and 2 tail trimmer 8c and standing positioned at the right are passed through positioned at the middle part and lower end of the normal direction column 3 on the right
The space that post 8a is connected as between entirety, 2 normal direction columns 3 turns into the installing space of translation mechanism and guide rod cranking block mechanism；
Translation mechanism includes spiral lift 5, line slideway 6, sliding block installing plate 7 and after-poppet 9；Spiral lift 5 one
End is arranged on the leading flank of long beam 8b in door shape support frame, and the other end is linked together with after-poppet 9, and after-poppet 9 is fixed on
On sliding block installing plate 7, the both sides of sliding block installing plate 7 are separately mounted on 2 line slideways 6, and line slideway 6 is separately fixed at a shape
The trailing flank of 2 normal direction columns 3 of support frame or so；It is spiral lift 5 and long beam 8b, line slideway 6 and normal direction column 3, straight
It is bolted between line guide rail 6 and after-poppet 9, spiral lift 5 and after-poppet 9；
Guide rod cranking block mechanism includes servo electric jar 1, electronic jar 2, pitching support arm 4, after-poppet 9, the 1st hinge component
10th, the 2nd hinge component 11 and the 3rd hinge component 12；Electronic jar 2 is bolted on after-poppet 9, servo electric jar
1 is fixed together by the 3rd hinge component 12 and electronic jar 2, and pitching support arm 4 passes through the 2nd hinge component 11 and servo electricity
Dynamic cylinder 1 is fixed together, and after-poppet 9 is fixed together by the 1st hinge component 10 and pitching support arm 4；1st hinge component 10,
2nd hinge component 11 and the 3rd hinge component 12 are rotary gemel, and two parts that can limit its connection can only be along hinge axes
Carry out relative rotary motion.
The running of translation mechanism and guide rod cranking block mechanism is：The carrier aircraft angle of attack as needed, controls servo electric jar 1
Stroke, 1st hinge component 10 of the pitching support arm 4 around the lower section of normal direction girder 3 is rotated and is reached the given carrier aircraft angle of attack；According to
Carrier aircraft change in angle of attack amount calculates carrier aircraft high variable quantity, and control spiral lift 5 makes after-poppet 9 and sliding block installing plate 7 along installation
Line slideway 6 on normal direction column 3 is moved；Because pitching support arm 4 is fixed together with after-poppet 9, therefore installed in pitching branch
The carrier aircraft of the front end of arm 4 carries out vertical motion with pitching support arm 4, compensate for because of the Normal Displacement amount that carrier aircraft change in angle of attack is produced.
The present invention operation principle be：The carrier aircraft angle of attack as needed, controls the stroke of servo electric jar 1, makes pitching
1st hinge component 10 of the support arm 4 around the lower section of normal direction girder 3 rotates and reaches the given carrier aircraft angle of attack；According to carrier aircraft change in angle of attack amount
Carrier aircraft high variable quantity is calculated, control spiral lift 5 makes after-poppet 9 and sliding block installing plate 7 along on normal direction column 3
Line slideway 6 is moved；Because pitching support arm 4 is fixed together with after-poppet 9, thus installed in the front end of pitching support arm 4 carrier aircraft with
Pitching support arm 4 and carry out vertical motion, compensate for because of the Normal Displacement amount that carrier aircraft change in angle of attack is produced.
Embodiment：Carrier aircraft is arranged on the front end of pitching support arm 4, the carrier aircraft and the relative position of store Combinations simulated as needed
And posture, control servo electric jar 1 and spiral lift 5, carrier aircraft is reached corresponding position and posture, you can to enter captive trajectory
Test the preparation and bug check on ground.
Claims (1)
1. a kind of carrier aircraft support prepared for captive trajectory testing ground, it is characterised in that：It includes door shape support frame, translation
Mechanism and guide rod cranking block mechanism；
Door shape support frame is made up of 2 columns (8a), 1 long beam (8b), 2 normal direction columns (3) and 4 tail trimmers (8c), and 2
The upper end of individual column (8a) is vertical with the two ends of long beam (8b) respectively to be connected as entirety, the upper end of 2 normal direction columns (3) and length
The lower surface of crossbeam (8b) is vertically connected as entirety, and the middle part and lower end positioned at the normal direction column (3) on the left side pass through 2 tail trimmers
(8c) is connected as entirety with the column (8a) positioned at the left side, and the middle part and lower end positioned at the normal direction column (3) on the right are short by 2
Crossbeam (8c) and the column (8a) positioned at the right be connected as space between entirety, 2 normal direction columns (3) turn into translation mechanism and
The installing space of guide rod cranking block mechanism；
Translation mechanism includes spiral lift (5), line slideway (6), sliding block installing plate (7) and after-poppet (9)；Spiral lift
(5) one end is arranged on the leading flank of long beam (8b) in door shape support frame, and the other end links together with after-poppet (9), rear branch
Frame (9) is fixed on sliding block installing plate (7), and sliding block installing plate (7) both sides are separately mounted on 2 line slideways (6), and straight line is led
Rail (6) is separately fixed at the trailing flank of 2 normal direction columns (3) of shape support frame or so；Spiral lift (5) and long beam
(8b), line slideway (6) and normal direction column (3), line slideway (6) and after-poppet (9), spiral lift (5) and after-poppet (9)
Between be bolted；
Guide rod cranking block mechanism includes servo electric jar (1), electronic jar (2), pitching support arm (4), after-poppet (9), the 1st hinge
Component (10), the 2nd hinge component (11) and the 3rd hinge component (12)；Electronic jar (2) is bolted on after-poppet
(9) on, servo electric jar (1) is fixed together by the 3rd hinge component (12) and electronic jar (2), and pitching support arm (4) leads to
Cross the 2nd hinge component (11) to be fixed together with servo electric jar (1), after-poppet (9) passes through the 1st hinge component (10) and pitching
Support arm (4) is fixed together；1st hinge component (10), the 2nd hinge component (11) and the 3rd hinge component (12) are rotary hinge
Chain, can limit two parts of its connection can only carry out relative rotary motion along hinge axes.
The running of translation mechanism and guide rod cranking block mechanism is：The carrier aircraft angle of attack as needed, control servo electric jar (1)
Stroke, makes 1st hinge component (10) of the pitching support arm (4) below normal direction girder (3) rotate and reach the given carrier aircraft angle of attack；
Carrier aircraft high variable quantity is calculated according to carrier aircraft change in angle of attack amount, control spiral lift (5) makes after-poppet (9) and sliding block installing plate
(7) along line slideway (6) motion being arranged on normal direction column (3)；Because pitching support arm (4) and after-poppet (9) are connected in one
Rise, therefore the carrier aircraft for being arranged on pitching support arm (4) front end compensate for because of the carrier aircraft angle of attack as pitching support arm (4) carries out vertical motion
Change the Normal Displacement amount produced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611237473.9A CN107036783A (en) | 2016-12-28 | 2016-12-28 | A kind of carrier aircraft support prepared for captive trajectory testing ground |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611237473.9A CN107036783A (en) | 2016-12-28 | 2016-12-28 | A kind of carrier aircraft support prepared for captive trajectory testing ground |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107036783A true CN107036783A (en) | 2017-08-11 |
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ID=59530829
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611237473.9A Pending CN107036783A (en) | 2016-12-28 | 2016-12-28 | A kind of carrier aircraft support prepared for captive trajectory testing ground |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107830987A (en) * | 2017-12-04 | 2018-03-23 | 中国航空工业集团公司沈阳空气动力研究所 | Captive trajectory testing mechanism in six degree of freedom store Combinations pole based on Bevel Gear Transmission |
| CN107860545A (en) * | 2017-12-04 | 2018-03-30 | 中国航空工业集团公司沈阳空气动力研究所 | The six degree of freedom system of large-scale transonic wind tunnel big load model captive trajectory testing |
| CN107991054A (en) * | 2017-11-08 | 2018-05-04 | 江西洪都航空工业集团有限责任公司 | A kind of captive trajectory experimental method |
| CN109297665A (en) * | 2018-08-16 | 2019-02-01 | 中国航空工业集团公司沈阳空气动力研究所 | Use the online test method of the captive trajectory of high accurancy and precision Aerodynamic Model |
| CN111289209A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model pitch angle motion supporting device suitable for wind tunnel test of wing-body fusion aircraft |
| CN116296225A (en) * | 2023-05-18 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel large-attack-angle test device based on arc-shaped curved knife attack-angle mechanism |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107991054A (en) * | 2017-11-08 | 2018-05-04 | 江西洪都航空工业集团有限责任公司 | A kind of captive trajectory experimental method |
| CN107991054B (en) * | 2017-11-08 | 2019-10-18 | 江西洪都航空工业集团有限责任公司 | A kind of captive trajectory experimental method |
| CN107830987A (en) * | 2017-12-04 | 2018-03-23 | 中国航空工业集团公司沈阳空气动力研究所 | Captive trajectory testing mechanism in six degree of freedom store Combinations pole based on Bevel Gear Transmission |
| CN107860545A (en) * | 2017-12-04 | 2018-03-30 | 中国航空工业集团公司沈阳空气动力研究所 | The six degree of freedom system of large-scale transonic wind tunnel big load model captive trajectory testing |
| CN107860545B (en) * | 2017-12-04 | 2024-04-12 | 中国航空工业集团公司沈阳空气动力研究所 | Six-degree-of-freedom system for large transonic wind tunnel large load model capture track test |
| CN107830987B (en) * | 2017-12-04 | 2024-04-12 | 中国航空工业集团公司沈阳空气动力研究所 | Six-degree-of-freedom mechanism store strut for capture track test based on bevel gear transmission |
| CN109297665A (en) * | 2018-08-16 | 2019-02-01 | 中国航空工业集团公司沈阳空气动力研究所 | Use the online test method of the captive trajectory of high accurancy and precision Aerodynamic Model |
| CN111289209A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model pitch angle motion supporting device suitable for wind tunnel test of wing-body fusion aircraft |
| CN116296225A (en) * | 2023-05-18 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel large-attack-angle test device based on arc-shaped curved knife attack-angle mechanism |
| CN116296225B (en) * | 2023-05-18 | 2023-07-21 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel large-attack-angle test device based on arc-shaped curved knife attack-angle mechanism |
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Application publication date: 20170811 |