CN102564727A - Wind resistance simulation test device for aviation photoelectric measuring device - Google Patents
Wind resistance simulation test device for aviation photoelectric measuring device Download PDFInfo
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- CN102564727A CN102564727A CN201110449236XA CN201110449236A CN102564727A CN 102564727 A CN102564727 A CN 102564727A CN 201110449236X A CN201110449236X A CN 201110449236XA CN 201110449236 A CN201110449236 A CN 201110449236A CN 102564727 A CN102564727 A CN 102564727A
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- aviation photoelectric
- measurement equipment
- photoelectric measurement
- electromagnetic exciter
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Abstract
A wind resistance simulation test device for an aviation photoelectric measuring device relates to the field of aviation test and solves the problem that during the existing wind resistance wind tunnel test performed by an aviation photoelectric measuring device, the device can only get the data information of wind resistance and wind resistance imposed position, and the dynamic performance of the device cannot be measured. The device comprises an aviation photoelectric measuring device, an electromagnetic exciter, a signal generator, a torque imposing lever and a test bed; the aviation photoelectric measuring device, the electromagnetic exciter and the signal generator are sequentially fixed on the test stand, the aviation photoelectric measuring device and the electromagnetic exciter are connected by the torque imposing lever, and the electromagnetic exciter and the signal generator are connected via a cable. The wind resistance simulation test device disclosed by the invention is simple in structure, is easy to use, is precise in test, and can improve the reliability of the aviation photoelectric measuring device.
Description
Technical field
The present invention relates to the aeromechanics field of measuring technique, be specifically related to the device of the indoor measurement of a kind of aviation photoelectric measurement equipment windage resistance disturbance experiments.
Background technology
Along with the development of contemporary aircraft technology, carrying the aircraft of aviation photoelectric measurement equipment, its flying speed is more and more faster, hangs over the moment of wind resistance that the aviation photoelectric measurement equipment of aircraft exterior born outward and also increases thereupon.Because the windage force measurement is the important ring of development aviation photoelectric measurement equipment; Need accurately simulation so that the calculating initial value of necessity is provided for the design of aviation photoelectric measurement equipment and detection of dynamic; So in the laboratory to ground wind moment simulated experiment; Can effectively assess photoelectric measurement equipment opposing windage resistance disturbance ability, prepare for formal flight provides necessary test.The best practice of surface wind resistance test is the aviation photoelectric measurement equipment to be put into wind-tunnel do test in kind.Because aviation photoelectric measurement equipment volume is bigger, receives the wind-tunnel condition restriction, generally adopts the scale down model to carry out test both at home and abroad.The wind tunnel test of scale down model windage resistance generally can only obtain the data that windage resistance and windage resistance apply the position, and under such windage resistance effect, how its dynamic property then can't detect as for the aviation photoelectric measurement equipment.
Summary of the invention
The present invention carries out in the windage resistance wind tunnel test process for solving the existing aviation photoelectric measurement equipment that adopts; Can only obtain the windage resistance of equipment and data message that windage resistance applies the position and can't record the problem of the dynamic property of equipment, a kind of device that is used for aviation photoelectric measurement equipment windage resistance simulation test is provided.
A kind of device that is used for the windage resistance simulation test of aviation photoelectric measurement equipment, this device comprises that moment applies bar, electromagnetic exciter, cable, signal generator and testing table; Aviation photoelectric measurement equipment, electromagnetic exciter and signal generator are fixed on the testing table successively, and said aviation photoelectric measurement equipment applies bar with electromagnetic exciter through moment and is connected, and electromagnetic exciter is connected through cable with signal generator.
Principle of work of the present invention: the invention provides a kind of device of simulating windage resistance; The wind-resistance test data that drawn according to the scale down model wind tunnel test; Send corresponding signal by signal generator; Electromagnetic exciter drives the signal that moment applies the pole-footing number of it is believed that generator and carries out stretching motion, touches the shell of aviation photoelectric measurement equipment, and then the moment thrust that applies bar is the suffered windage resistance of aviation photoelectric measurement equipment.The data that the electromagnetic exciter point of application and the power numerical values recited that applies can adopt the wind tunnel test of aviation photoelectric measurement equipment equal proportion minimodel to draw realize; Adopt the size and the frequency of signal generator, electromagnetic exciter simulation windage resistance; Be applied on the aviation photoelectric measurement equipment, can detect the dynamic property of aviation photoelectric measurement equipment when bearing windage resistance.Aviation this moment photoelectric measurement equipment is opened electricity, its dynamic property tested, as: apply the power of 100N along equipment perpendicular bisector 5mm place below its symcenter, diameter is the windage resistance that 300mm equipment is born in the time of can simulating 300km/h flight.(wherein B is the windage resistance undulating quantity to the situation that influences of aviation photoelectric measurement equipment when the power that will apply changes 100N+Bsin (2 π ft) N into, just can to simulate windage fluctuation; F is the windage resistance vibration frequency), optoelectronic device can be used index evaluations such as disturbance isolation to the influence of this windage.Entire test is carried out on a firm testing table.
Beneficial effect of the present invention: proving installation of the present invention adopts the size and the frequency of signal generator, electromagnetic exciter simulation windage resistance; Be applied on the aviation photoelectric measurement equipment, can detect the dynamic property of aviation photoelectric measurement equipment when bearing windage resistance.
Description of drawings
Fig. 1 is a kind of structural representation that is used for the device of aviation photoelectric measurement equipment windage resistance simulation test of the present invention.
Among the figure: 1, aviation photoelectric measurement equipment, 2, fixing base, 3, moment applies bar, 4, nut, 5, electromagnetic exciter, 6, pressing plate, 7, cable, 8, signal generator, 9, testing table.
Embodiment
In conjunction with Fig. 1 this embodiment is described, a kind of device that is used for aviation photoelectric measurement equipment windage resistance simulation test, this device comprise that fixing base 2, moment apply bar 3, electromagnetic exciter 5, pressing plate 6, cable 7, signal generator 8 and testing table 9; Aviation photoelectric measurement equipment 1 is fixed on the testing table 9 through fixing base 2; Electromagnetic exciter 5 is fixed on testing table 9 through pressing plate 6; And place the aviation photoelectric measurement equipment anterior; The distance of the two can touch aviation photoelectric measurement equipment 1 with the boosting-rod 3 that links to each other with electromagnetic exciter through nut 4 and be advisable, and signal generator 8 links to each other with electromagnetic exciter 5 through cable 7.
The described moment of this embodiment applies the standard nut 4 of bar 3 through a M6 and links into an integrated entity with electromagnetic exciter 5, and its front end is close to the shell of aviation photoelectric measurement equipment 1.
Claims (3)
1. device that is used for the windage resistance simulation test of aviation photoelectric measurement equipment, this device comprises that moment applies bar (3), electromagnetic exciter (5), cable (7), signal generator (8) and testing table (9); It is characterized in that; Aviation photoelectric measurement equipment (1), electromagnetic exciter (5) and signal generator (8) are fixed on the testing table (9) successively; Said aviation photoelectric measurement equipment (1) applies bar (3) with electromagnetic exciter (5) through moment and is connected, and electromagnetic exciter (5) is connected through cable (7) with signal generator (8).
2. a kind of device that is used for the windage resistance simulation test of aviation photoelectric measurement equipment according to claim 1; It is characterized in that; This device also comprises fixing base (2) and pressing plate (6); Said aviation photoelectric measurement equipment (1) is fixed on the testing table (9) through fixing base (2), and electromagnetic exciter (5) is fixed on the testing table (9) through pressing plate (6).
3. a kind of device that is used for the windage resistance simulation test of aviation photoelectric measurement equipment according to claim 1; It is characterized in that; The end that said moment applies bar (3) is close to the shell of aviation photoelectric measurement equipment (1); The other end that moment applies bar (3) is connected with electromagnetic exciter (5) through nut (4), and the shell that the end that the requirement of the distance of said aviation photoelectric measurement equipment (1) and electromagnetic exciter (5) applies bar (3) with moment is close to aviation photoelectric measurement equipment (1) is a standard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110449236XA CN102564727A (en) | 2011-12-29 | 2011-12-29 | Wind resistance simulation test device for aviation photoelectric measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110449236XA CN102564727A (en) | 2011-12-29 | 2011-12-29 | Wind resistance simulation test device for aviation photoelectric measuring device |
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| Publication Number | Publication Date |
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| CN102564727A true CN102564727A (en) | 2012-07-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110449236XA Pending CN102564727A (en) | 2011-12-29 | 2011-12-29 | Wind resistance simulation test device for aviation photoelectric measuring device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104501802A (en) * | 2015-01-09 | 2015-04-08 | 中国人民解放军63961部队 | Earth target capturing and identifying method used for high-speed aircraft |
| CN105424310A (en) * | 2015-11-05 | 2016-03-23 | 临沂金铭机械有限公司 | Grain layer air-inducing resistance test device |
| 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 |
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- 2011-12-29 CN CN201110449236XA patent/CN102564727A/en active Pending
Patent Citations (5)
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| CN1260481A (en) * | 2000-01-19 | 2000-07-19 | 山西省气象局 | Method and device for automatic detection and control of wind tunnel speed |
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| CN2836015Y (en) * | 2005-06-28 | 2006-11-08 | 北京凌天世纪自动化技术有限公司 | Automatic anemometer tester |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104501802A (en) * | 2015-01-09 | 2015-04-08 | 中国人民解放军63961部队 | Earth target capturing and identifying method used for high-speed aircraft |
| CN105424310A (en) * | 2015-11-05 | 2016-03-23 | 临沂金铭机械有限公司 | Grain layer air-inducing resistance test device |
| 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 |
| 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 |
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Application publication date: 20120711 |