CN104748936A - Missile wing expanding wind tunnel test device for box-type vertical launching - Google Patents
Missile wing expanding wind tunnel test device for box-type vertical launching Download PDFInfo
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- CN104748936A CN104748936A CN201510162187.XA CN201510162187A CN104748936A CN 104748936 A CN104748936 A CN 104748936A CN 201510162187 A CN201510162187 A CN 201510162187A CN 104748936 A CN104748936 A CN 104748936A
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Abstract
The invention provides a missile wing expanding wind tunnel test device for box-type vertical launching. The missile wing expanding wind tunnel test device comprises a drive control component, a winch, a steel cable, a guide component, a thrust bearing component, a buffer, a model adapter, a missile model and a simulation launching box. The drive control component and the winch are arranged on the outside of the top wall of a wind tunnel test period. One end of the steel cable fixedly winds the winch, and the other end of the steel cable is connected with the model adapter. The thrust bearing component is fixed on the inner wall of the top wall of the wind tunnel test period through an upper bearing cover. The buffer is arranged on a lower bearing cover. The simulation launching box is mounted on the lower wall of the wind tunnel test period. The bottom of the missile model is provided with the model adapter. The guide component comprises a linear guide rail and a slide block. Two ends of the linear guide rail are respectively fixed on the upper bearing cover and the simulation launching box. The slide block is fixed on the simulation adapter. The missile wing expanding wind tunnel test device is simple in structure, quick to respond, high in reliability and widely applied to the missile wing expanding wind tunnel test for box-type vertical launching.
Description
Technical field
The present invention relates to a kind of box Vertical-launched Missile missile wing and launch flow tunnel testing device, the missile wing being applied to box Vertical-launched Missile launches wind tunnel test.
Background technology
At present, many air defence missiles and ship-based missile all adopt box Vertical Launch, and this radiation pattern not only can realize 360 degree of comprehensive strikes, and can reduce taking up room of guided missile, increase to carry to play quantity, are convenient to transition transport and daily servicing simultaneously.The guided missile missile wing of many canister launch is all be folded in firing box, and when launching, guided missile departs from launching tube in a flash, folding wings rapid deployment.According to the needs of Project R&D, test unit to have carried out many tests launched about folding wings, and main observation folding wings launches the state of moment, measures the moment of its angular velocity launched and angular acceleration and expansion, to parameters such as the impulsive forces of rudderpost.Usual folding wings is launched test and is carried out under without the state of firing box, and the fixing laggard row blasting of guided missile is to simulate its emission state.
Launch test for ramp-launched Missile folded wing, usually not analog transmissions case, be just fixed in wind-tunnel by guided missile, by the speed of simulated missile outlet of drying, this test can not the outlet state of simulated missile really.The guided missile of Vertical Launch, need to simulate its beam wind environment, simple fixing guided missile can not meet testing requirements.Therefore need a kind of can the speed of accurate simulation guided missile outlet moment and acceleration, and the test unit of its Vertical Launch state and beam wind environment can be simulated.
Along with the development of lift-off technology, Project R&D department proposes the testing requirements such as speed, acceleration of simulated missile Vertical Launch state and outlet in beam wind environment, so that the process status observing folding wings launch more really and technical parameter thereof.Guided missile how is driven vertically to move in wind-tunnel and consume the gordian technique that its powerful kinetic energy is test unit.The power driving Missile Motion can use bottom boosting launch and pull two kinds of modes.Bottom boosting is launched and is only selected high-speed cylinder can the speed of simulated missile outlet and acceleration, and high-speed cylinder needs to build pipeline and connects source of the gas, and its response speed is comparatively slow, and costly, technical difficulty is large in operation and maintenance.Pull and can use the equipment such as windlass, but the similar devices on market is difficult to the requirement meeting speed and acceleration, therefore need designed, designed electromechanical equipment to provide power.Current servo control technology is very ripe, and servo motor rings speed and acceleration can both meet testing requirements, and electrical equipment fast response time, reliability are high, cost is low, operation and maintenance is more convenient.Therefore can consider to use the electromechanical equipment of servo motor driven as Power Component.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provides a kind ofly in beam wind environment, the Missile Body span of simulated missile Vertical Launch state and outlet speed and acceleration to open flow tunnel testing device.
Box Vertical-launched Missile missile wing of the present invention launches flow tunnel testing device and comprises drived control assembly, capstan winch, wire rope, guidance set, thrust bearing assembly, impact damper, model adapter, guided missile model and analog transmissions case, described drived control assembly and described capstan winch are all configured in the outside of test chamber roof, described drived control assembly is connected with the rotating shaft being welded in described capstan winch, can the rotation of capstan winch described in drived control, one end of described wire rope is fixed on described capstan winch, and is wrapped on described capstan winch, the roof of the described test chamber immediately below described capstan winch offers mounting hole, described thrust bearing assembly structure for be assembled with thrust bearing between upper ball cover and lower ball cover, and described thrust bearing assembly has mesopore, described thrust bearing assembly is fixed on the inwall of described test chamber roof by described upper ball cover in the mode of described mesopore and described mounting hole coaxial cable, described impact damper also has middle shaft through-hole, and it is arranged on described lower ball cover in the mode of described middle shaft through-hole and described mesopore coaxial cable, described analog transmissions case is installed on the lower wall of the described test chamber immediately below described impact damper, and for placing described guided missile model, described guided missile model has middle through hole, is provided with described model adapter in the bottom of described guided missile model, described guidance set comprises line slideway and slide block, the two ends of described line slideway are separately fixed on described upper ball cover and described analog transmissions case, and described line slideway is through the middle shaft through-hole of described impact damper and the middle through hole of described guided missile model, described slide block is fixed on described model adapter, the other end of described wire rope is through the mounting hole on described test chamber roof, and pass the middle through hole of shaft through-hole and described guided missile model in described impact damper, be connected with described institute model adapter, thus can under the control of described drived control assembly, described guided missile model is drawn high rapidly along described guide pole.
Preferred described drived control assembly comprises servo motor, reductor and electromagnetic clutch shaft coupling, the driving shaft of described servo motor is connected with described reductor shaft, the output shaft of described speed reduction unit is connected by shaft coupling one end with the rotating shaft being welded in described capstan winch, the other end of described rotating shaft is connected with described electromagnetic clutch, described rotating shaft is supported on base by the bearing assembly being symmetricly set on described capstan winch both sides, described servo motor, described reductor and described electromagnetic clutch are all arranged on described base by screw, described base through screws is fixed on the outside of described test chamber roof.
Preferred described impact damper comprises transfer panel, outer sleeve, inner sleeve, inner spring, outer spring and rubber blanket, described transfer panel is fixed on described lower ball cover, the top of described outer sleeve is fixed on described transfer panel, described inner sleeve is configured in described outer sleeve in the mode that can be free to slide, described outer spring is configured between described outer sleeve and described inner sleeve, described outer spring upper end abuts the convex edge, upper end of described inner sleeve, its lower end is connected to described outer sleeve bottom, described inner spring is configured in described inner sleeve, the upper end of described inner spring abuts with described transfer panel, its lower end is connected to described inner sleeve bottom, described rubber blanket is bonded on the bottom end face of described inner sleeve, for contacting with the described guided missile model in rising.
Preferred described analog transmissions case is the square chest or cylinder that coordinate described guided missile model to design, is arranged on the rotating disk that the lower wall of described test chamber configures, the lower wall of described analog transmissions case is provided with lower fixed seat by screw.
The upper end of preferred described guide pole is connected with described top bearing cover screw, and the lower end of described guide pole is connected with described lower fixed seat screw.
The present invention's beneficial effect is compared with prior art:
(1) the present invention can simulate the Vertical Launch state of guided missile in beam wind environment, and the speed of its outlet moment of energy accurate simulation and acceleration..
(2) the present invention is while making tested guided missile have powerful kinetic energy, and its power/brake assemblies and impact damper can be used to consume these kinetic energy, protection test equipment safety.
(2) servo motor in the present invention, reductor, electromagnetic clutch and guide rail are all matured products, good reliability.And the replacing of parts and safeguard all more convenient, save development cost and maintenance cost.
(3) the present invention adopts modular construction, can require to change the parts such as firing box, servo motor and reductor according to test mission, substantially reduce the production cycle, saved cost.
Accompanying drawing explanation
Fig. 1 is that box Vertical-launched Missile missile wing launches flow tunnel testing device structural representation;
Fig. 2 is power/brake assemblies structural representation;
Fig. 3 is bearing block structure schematic diagram;
Fig. 4 is buffer structure schematic diagram;
Fig. 5 is the full sectional view of inner sleeve;
Fig. 6 is the full sectional view of outer sleeve;
Fig. 7 is guide piece scheme of installation
Embodiment
As shown in Figure 1, the invention provides a kind of box Vertical-launched Missile missile wing and launch flow tunnel testing device, it comprises power/brake assemblies, guidance set, impact damper, model adapter 319 and analog transmissions case 320; Model adapter 319 is single component, is used for connecting guidance set and tested guided missile 2; Analog transmissions case 320 is square chest according to the design of tested guided missile 2 physical size or cylinder, and be arranged on the rotating disk of wind tunnel wall 1 by screw, rotating disk is considered as a part for wind tunnel wall 1.During dial rotation, dishpan simulation firing box 320 drives guidance set to rotate by the lower fixed seat 321 of fixed thereon.Slide block 318 in guidance set is connected with tested guided missile 2 by model adapter 319, and tested guided missile 2 can rotate with guidance set, to convert different wind surfaces.
As shown in Figure 2, described power/brake assemblies comprises servo motor 31, reductor 32, shaft coupling 33, rotating shaft 34, the bearing seat 35 of balanced configuration on capstan winch both sides, capstan winch 36, wire rope 322, electromagnetic clutch 37 and base 38.Wherein servo motor 31 output torque, for whole device provides power, reductor 32 reduces the rotating speed of servo motor 31, improves output torque simultaneously.Rotating shaft 34 and capstan winch 36 weld together, and its one end is connected with the output shaft of speed reduction unit 32 by shaft coupling 33.Be provided with bearing 351 in bearing seat 35 (with reference to Fig. 3), rotating shaft 34 is through the endoporus of bearing 351, and bearing seat 35 balanced configuration, on capstan winch 36 both sides, plays the effect of support.The other end of rotating shaft 34 is connected with electromagnetic clutch 37, and electromagnetic clutch 37 mainly plays braking action, and during energising, electromagnetic clutch 37 works, and plays braking action by friction force.One end of wire rope 322 is fixed on capstan winch 36, and is wrapped on capstan winch 36, and the other end is connected on model adapter 319, realizes moving up and down of tested guided missile 2 by pulling and discharging.Servo motor 31, reductor 32, bearing seat 35 and electromagnetic clutch 37 are all arranged on base 38 by screw, base 38 is fixed by screws in the outside of the roof of test chamber wall 1, the roof of test chamber wall 1 is provided with mounting hole, and the other end of wire rope 322 passes from mounting hole.
As shown in Figure 4, described impact damper comprises transfer panel 311, outer sleeve 312, inner sleeve 315, inner spring 313, outer spring 314 and rubber blanket 316.Wherein the cavity length of the length of inner sleeve 315 inner chamber, the natural extended length of outer spring 314 and outer sleeve 312 is all determined according to the design runlength of inner spring 313, inner spring 313 is freely placed in the inner chamber of inner sleeve 315 (with reference to Fig. 5), and inner spring 313 one end withstands on its inner chamber boss 3151; Outer spring 314 is enclosed within the cylindrical of inner sleeve 315, its one end withstands on the convex edge, upper end 3152 of inner sleeve 315, the endoporus 3121 of outer sleeve 312 (as shown in Figure 6) is enclosed within outer spring 314 through inner sleeve 315, its lower end boss 3122 contacts with the other end of outer spring 314, when outer spring 314 freely extends, outer sleeve 312 flange face 3123 is concordant with the free end of inner spring 313.Together with transfer panel 311 is bolted with outer sleeve 312, the free end of inner spring 313 and the bottom surface of transfer panel 311 contact.Rubber blanket 316 is bonded on the bottom end face 3153 of inner sleeve 315, and there is circular hole rubber blanket 316 inside, is used for through guide rail 317 and wire rope 322.After folding missile wing 21 launches, servo motor 31 stops, the rubber blanket 316 of tested guided missile 2 cushion at collision in free uphill process, inner spring 313 is compressed, the damping of inner spring 313 and rubber blanket 316 itself can consume a part of kinetic energy of tested guided missile 2, when inner spring 313 is completely by compression, the stop motion of tested guided missile 2.In inner spring 313 springback process, outer spring 314 is compressed in the convex edge, upper end 3152 of inner sleeve 315, this process can consume the elastic potential energy of a part of inner spring 313, after tested guided missile 2 departs from the rubber blanket 316 of impact damper completely, electromagnetic clutch 37 starts, and consumes the remaining kinetic energy of tested guided missile 2 by the friction of its interior arrangement and the damping of reductor 32 itself.
As shown in Figure 7, described guidance set comprises line slideway 317, slide block 318, top bearing cover 39, lower bearing end cap 310, thrust bearing 323 and lower fixed seat 321.Top bearing cover 39 and lower bearing end cap 310 coordinate with the two ends of thrust bearing 323 and are assembled into thrust bearing assembly, thrust bearing assembly has middle through hole, and be arranged on the inwall of the roof of test chamber wall 1 by top bearing cover 39, after installation, the middle through hole of thrust bearing assembly and mounting hole are on same axis.Slide block 318 can be free to slide along guide rail 317 length direction, but other direction degree of freedom are all restricted, line slideway 317 upper end is connected with screw with top bearing cover 39, line slideway 317 lower end is connected with screw with lower fixed seat 321, and lower fixed seat 321 uses screw to be fixed on analog transmissions case 320.Lower bearing end cap 310 uses screw to be connected with transfer panel 311, thus achieves guidance set and firing box 320 defines an entirety, and line slideway 317 can rotate with firing box 320.Guidance set effect is the direction of motion limiting tested guided missile 2, makes it can only move up and down along guide rail.In mounting hole, thrust bearing assembly, the middle through hole of the endoporus of through hole, the endoporus connecing dish 311, impact damper, tested guided missile 2 is all on same axis, guide rail 317 and wire rope 322 respectively from thrust bearing assembly in the endoporus of the endoporus of through hole, transfer panel 311, impact damper, tested guided missile 2 through hole pass.
The principle of work of box Vertical-launched Missile missile wing developing test device: before on-test, tested guided missile 2 and folding missile wing 21 thereof are placed in analog transmissions case 320, and the model adapter 319 in guided missile is connected with the free end of the wire rope 322 be wrapped on capstan winch 36.On-test, servo motor 31 drives capstan winch 36 to rotate by reductor 32, and now electromagnetic clutch 37 is in off-position.Along with the rotation of capstan winch 36, wire rope 322 is constantly wrapped on capstan winch 36, tested guided missile 2 rises fast under the dragging of wire rope 322, meets the requirements of speed and acceleration when the moment that tested guided missile 2 departs from analog transmissions case 320, and now folding missile wing 21 launches.Missile wing 21 is around the shaft foldable at the upper right corner (missile wing of the left side shown in Fig. 1 21) place, and rotating shaft place is provided with torsion-bar spring.In firing box, missile wing 21 upper limb after folding is attached on bomb body, lower edge is attached to (upper and lower edge refers to the upper lower edge of missile wing 21 shown in Fig. 1) on firing box 320 inwall, and the material that firing box 320 and missile wing 21 contact portion adopt friction factor smaller is to reduce the wearing and tearing to missile wing 21.The moment of the complete outlet of tested guided missile 2, four missile wings 21 are under the effect of torsion-bar spring restoring force, and rapid deployment around the shaft, missile wing 21 is locked at the fixed position under its flight attitude by the latch mechanism of missile wing 21 simultaneously.After folding missile wing 21 launches, tested guided missile 2 is in free ascent stage, does uniformly retarded motion, and servo motor 31 does uniformly retarded motion equally, and now wire rope 322 does not stress.Tested guided missile 2 cushion at collision moment, impact damper starts compression, and the kinetic energy of tested guided missile 2 gradates the elastic potential energy into impact damper, until tested guided missile upward movement stops starting resilience.In tested guided missile 2 springback process, its moment departing from rubber blanket 316 is no longer by the effect of impact damper screen resilience.In impact damper springback process, can consume a part of elastic potential energy by the effect of its inner two springs, final remaining elastic potential energy is converted to the kinetic energy of tested guided missile 2, and guided missile does accelerated motion downwards.Depart from impact damper moment at tested guided missile 2, electromagnetic clutch 37 is energized, and electromagnetic clutch 37 has started braking action, and the kinetic energy consuming tested guided missile 2 by the friction between its inner member makes it staticly in decline process get off, so far, and off-test.
The present invention can meet the requirement of Vertical-launched Missile under simulation beam wind environment, and the powerful kinetic energy that tested guided missile produces in test can be consumed, this test unit adopts modular construction, can be met the test of different model by replacing firing box and servo motor.
Above the preferred embodiment of the present invention is illustrated, but the present invention is not limited to above-described embodiment.To one skilled in the art, in the category described in claims, various modification or fixed case can be expected apparently, certainly also belong to technology category of the present invention.
Claims (5)
1. box Vertical-launched Missile missile wing launches a flow tunnel testing device, it is characterized in that: comprise drived control assembly, capstan winch, wire rope, guidance set, thrust bearing assembly, impact damper, model adapter, guided missile model and analog transmissions case;
Described drived control assembly and described capstan winch are all configured in the outside of test chamber roof, described drived control assembly is connected with the rotating shaft being welded in described capstan winch, can the rotation of capstan winch described in drived control, one end of described wire rope is fixed on described capstan winch, and is wrapped on described capstan winch; The roof of the described test chamber immediately below described capstan winch offers mounting hole, described thrust bearing assembly structure for be assembled with thrust bearing between upper ball cover and lower ball cover, and described thrust bearing assembly has mesopore, described thrust bearing assembly is fixed on the inwall of described test chamber roof by described upper ball cover in the mode of described mesopore and described mounting hole coaxial cable, described impact damper also has middle shaft through-hole, and it is arranged on described lower ball cover in the mode of described middle shaft through-hole and described mesopore coaxial cable;
Described analog transmissions case is installed on the lower wall of the described test chamber immediately below described impact damper, and for placing described guided missile model, described guided missile model has middle through hole, is provided with described model adapter in the bottom of described guided missile model;
Described guidance set comprises line slideway and slide block, the two ends of described line slideway are separately fixed on described upper ball cover and described analog transmissions case, and described line slideway is through the middle shaft through-hole of described impact damper and the middle through hole of described guided missile model, described slide block is fixed on described model adapter, the other end of described wire rope is through the mounting hole on described test chamber roof, and pass the middle through hole of shaft through-hole and described guided missile model in described impact damper, be connected with described institute model adapter, thus can under the control of described drived control assembly, described guided missile model is drawn high rapidly along described line slideway.
2. box Vertical-launched Missile missile wing according to claim 1 launches flow tunnel testing device, it is characterized in that: described drived control assembly comprises servo motor, reductor and electromagnetic clutch shaft coupling, the driving shaft of described servo motor is connected with described reductor shaft, the output shaft of described speed reduction unit is connected by shaft coupling one end with the rotating shaft being welded in described capstan winch, the other end of described rotating shaft is connected with described electromagnetic clutch, described rotating shaft is supported on base by the bearing assembly being symmetricly set on described capstan winch both sides, described servo motor, described reductor and described electromagnetic clutch are all arranged on described base by screw, described base through screws is fixed on the outside of described test chamber roof.
3. box Vertical-launched Missile missile wing according to claim 1 launches flow tunnel testing device, it is characterized in that: described impact damper comprises transfer panel, outer sleeve, inner sleeve, inner spring, outer spring and rubber blanket, described transfer panel is fixed on described lower ball cover, the top of described outer sleeve is fixed on described transfer panel, described inner sleeve is configured in described outer sleeve in the mode that can be free to slide, described outer spring is configured between described outer sleeve and described inner sleeve, described outer spring upper end abuts the convex edge, upper end of described inner sleeve, its lower end is connected to described outer sleeve bottom, described inner spring is configured in described inner sleeve, the upper end of described inner spring abuts with described transfer panel, its lower end is connected to described inner sleeve bottom, described rubber blanket is bonded on the bottom end face of described inner sleeve, for contacting with the described guided missile model in rising.
4. box Vertical-launched Missile missile wing according to claim 1 launches flow tunnel testing device, it is characterized in that: described analog transmissions case is the square chest or cylinder that coordinate described guided missile model to design, be arranged on by screw on the rotating disk that the lower wall of described test chamber configures, the lower wall of described analog transmissions case is provided with lower fixed seat.
5. box Vertical-launched Missile missile wing according to claim 4 launches flow tunnel testing device, and it is characterized in that: the upper end of described line slideway is connected with described top bearing cover screw, the lower end of described line slideway is connected with described lower fixed seat screw.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510162187.XA CN104748936B (en) | 2015-04-08 | 2015-04-08 | Box Vertical-launched Missile missile wing launches flow tunnel testing device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510162187.XA CN104748936B (en) | 2015-04-08 | 2015-04-08 | Box Vertical-launched Missile missile wing launches flow tunnel testing device |
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| CN104748936B CN104748936B (en) | 2017-07-07 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106017855A (en) * | 2016-08-01 | 2016-10-12 | 中国航天空气动力技术研究院 | Experiment device for low-speed wind tunnel tail vane unfolding tests |
| CN106247855A (en) * | 2016-09-13 | 2016-12-21 | 湖北航天技术研究院总体设计所 | A kind of liftable transmitting station of air deflector |
| CN106871748A (en) * | 2017-01-11 | 2017-06-20 | 北京理工大学 | For testing the turntable that missile wing launches under body multi-angle high rotational speeds |
| CN106871747A (en) * | 2017-01-11 | 2017-06-20 | 北京理工大学 | The device that missile wing launches is tested under a kind of body multi-angle high rotational speeds |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017855A (en) * | 2016-08-01 | 2016-10-12 | 中国航天空气动力技术研究院 | Experiment device for low-speed wind tunnel tail vane unfolding tests |
| CN106017855B (en) * | 2016-08-01 | 2018-08-07 | 中国航天空气动力技术研究院 | The experimental provision of low-speed wind tunnel tail vane expansion experiment |
| CN106247855A (en) * | 2016-09-13 | 2016-12-21 | 湖北航天技术研究院总体设计所 | A kind of liftable transmitting station of air deflector |
| CN106247855B (en) * | 2016-09-13 | 2018-06-19 | 湖北航天技术研究院总体设计所 | A kind of liftable transmitting station of air deflector |
| CN106871748A (en) * | 2017-01-11 | 2017-06-20 | 北京理工大学 | For testing the turntable that missile wing launches under body multi-angle high rotational speeds |
| CN106871747A (en) * | 2017-01-11 | 2017-06-20 | 北京理工大学 | The device that missile wing launches is tested under a kind of body multi-angle high rotational speeds |
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| CN104748936B (en) | 2017-07-07 |
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