CN104748936B - Box Vertical-launched Missile missile wing launches flow tunnel testing device - Google Patents

Box Vertical-launched Missile missile wing launches flow tunnel testing device Download PDF

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Publication number
CN104748936B
CN104748936B CN201510162187.XA CN201510162187A CN104748936B CN 104748936 B CN104748936 B CN 104748936B CN 201510162187 A CN201510162187 A CN 201510162187A CN 104748936 B CN104748936 B CN 104748936B
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missile
model
capstan winch
guided missile
fixed
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CN104748936A (en
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赵金海
刘丹
郑芳
苏浩
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China Academy of Aerospace Aerodynamics CAAA
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China Academy of Aerospace Aerodynamics CAAA
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Abstract

The present invention provides a kind of box Vertical-launched Missile missile wing and launches flow tunnel testing device, and it includes drive control component, capstan winch, steel wire rope, guidance set, thrust bearing assembly, buffer, model adapter, guided missile model and analog transmissions case;Drive control component is configured in the outside of test chamber roof with capstan winch, and one end of steel wire rope is fixed on capstan winch, and is wrapped on capstan winch;Thrust bearing assembly is fixed on the inwall of test chamber roof by upper ball cover, and buffer is arranged on lower ball cover;Analog transmissions case is installed on the lower wall of test chamber, and the bottom of guided missile model is provided with model adapter;Guidance set includes line slideway and sliding block, and the two ends of line slideway are separately fixed on upper ball cover and analog transmissions case, and sliding block is fixed on model adapter, and the other end of steel wire rope is connected with model adapter.Simple structure of the present invention, response is rapid, and reliability is high, can be widely applied to during box Vertical-launched Missile missile wing launches wind tunnel test.

Description

Box Vertical-launched Missile missile wing launches flow tunnel testing device
Technical field
Launch flow tunnel testing device the present invention relates to a kind of box Vertical-launched Missile missile wing, be applied to box Vertical Launch The missile wing of guided missile launches wind tunnel test.
Background technology
At present, many air defence missiles and ship-based missile all use box Vertical Launch, and this radiation pattern is not only able to reality Existing 360 degrees omnidirection strike, and can reduce taking up room for guided missile, increases to carry and plays quantity, at the same be easy to transition transport and Regular maintenance.The guided missile missile wing of many canister launch is folded in firing box, and in transmitting, guided missile departs from the one of launching tube Moment, folding wings rapid deployment.The need for Project R&D, test unit has been carried out what many was launched on folding wings Experiment, main observation folding wings launch the state of moment, measure its expansion angular speed and angular acceleration and the torque of expansion, The parameters such as the impulsive force to rudderpost.Usual folding wings launch experiment to be carried out in the state of non-emissive case, is carried out after fixed guided missile Blasting is simulating its emission state.
Launch to test for ramp-launched Missile folded wing, generally not analog transmissions case, guided missile is simply fixed on wind In hole, by the speed of simulated missile outlet of drying, this experiment can not real simulated missile outlet state.Vertical hair The guided missile penetrated is, it is necessary to simulate its beam wind environment, simple fixed guided missile can not meet test requirements document.Therefore a kind of energy is needed The speed and acceleration of enough accurate simulation guided missile outlet moments, and the experiment of its Vertical Launch state and beam wind environment can be simulated Device.
With the development of lift-off technology, Project R&D department proposes the simulated missile Vertical Launch state in beam wind environment And the test requirements document such as speed, the acceleration of outlet, so as to process status and its technology that more real observation folding wings are launched Parameter.How to drive guided missile to be movable in a vertical direction in wind-tunnel and consume the key that its powerful kinetic energy is experimental rig Technology.Two ways can be launched using bottom boosting and pulled on the power for driving Missile Motion.Bottom boosting ejection Have from high-speed cylinder can simulated missile outlet speed and acceleration, high-speed cylinder needs to build pipeline connection source of the gas, And its response speed is slower, and operation and maintenance is costly, and technical difficulty is big.Pulling can use the equipment such as hoist engine, but city Similar devices on field are difficult to meet the requirement of speed and acceleration, it is therefore desirable to which designed, designed electromechanical equipment provides power.Mesh Preceding servo control technique is very ripe, and servo motor rings speed and acceleration can meet test requirements document, and electrically set Standby fast response time, reliability high, low cost, operation and maintenance are more convenient.It can be considered to use servo motor driven Electromechanical equipment as Power Component.
The content of the invention
Technology solve problem of the invention is:Overcome the deficiencies in the prior art, there is provided one kind can in beam wind environment mould Flow tunnel testing device is opened in the Missile Body span for intending guided missile Vertical Launch state and outlet speed and acceleration.
Box Vertical-launched Missile missile wing of the invention launches flow tunnel testing device includes drive control component, capstan winch, steel Cord, guidance set, thrust bearing assembly, buffer, model adapter, guided missile model and analog transmissions case;It is described to drive control Component processed is configured in the outside of test chamber roof with the capstan winch, the drive control component be welded in the capstan winch Rotating shaft connection, be capable of the rotation of capstan winch described in drive control, one end of the steel wire rope is fixed on the capstan winch, and is wound On the capstan winch;Mounting hole, the thrust axis are offered on the roof of the test chamber immediately below the capstan winch During bearing assembly structure is that thrust bearing is assembled between upper ball cover and lower ball cover, and the thrust bearing assembly has Hole, the thrust bearing assembly is fixed on institute by way of the upper ball cover is with the mesopore and the mounting hole coaxial line State on the inwall of test chamber roof, the buffer also has middle shaft through-hole, and it is with the middle shaft through-hole and the mesopore The mode of coaxial line is arranged on the lower ball cover;The analog transmissions case is installed on the wind immediately below the buffer On the lower wall of hole test section, for placing the guided missile model, the guided missile model has middle through hole, in the guided missile model Bottom is provided with the model adapter;The guidance set includes line slideway and sliding block, the two ends point of the line slideway It is not fixed on the upper ball cover and the analog transmissions case, and the line slideway leads to through the axis of the buffer Hole and the middle through hole of the guided missile model, the sliding block are fixed on the model adapter, and the other end of the steel wire rope is worn The mounting hole crossed on the test chamber roof, and lead to through in shaft through-hole in the buffer and the guided missile model Hole, is connected such that it is able to fast along the guide post under the control of the drive control component with institute's model adapter Speed draws high the guided missile model.
It is preferred that the drive control component includes servo motor, reductor and electromagnetic clutch shaft coupling, the servo horse The drive shaft for reaching is connected with the reductor shaft, and the output shaft of the decelerator passes through shaft coupling and is welded in turning for the capstan winch One end connection of axle, the other end of the rotating shaft is connected with the electromagnetic clutch, and the rotating shaft is described by being symmetricly set on The bearing assembly of capstan winch both sides is supported on base, and the servo motor, the reductor and the electromagnetic clutch pass through Screw is arranged on the base, and the base is fixed by screws in the outside of the test chamber roof.
It is preferred that the buffer includes transfer panel, outer sleeve, inner sleeve, inner spring, outer spring and rubber blanket, the switching Disk is fixed on the lower ball cover, and the top of the outer sleeve is fixed on the transfer panel, and the inner sleeve is with can be free The mode of slip is configured in the outer sleeve, and the outer spring configuration is described between the outer sleeve and the inner sleeve Outer spring upper end abuts the upper end convex edge of the inner sleeve, and its lower end is connected to the outer sleeve bottom, and the inner spring is matched somebody with somebody It is placed in the inner sleeve, the upper end of the inner spring abuts with the transfer panel, its lower end is connected to the inner sleeve lower end Portion, the rubber blanket is bonded on the bottom end face of the inner sleeve, for being contacted with the guided missile model in rising.
It is preferred that the analog transmissions case is the square chest or cylinder that coordinate the guided missile model to design, it is arranged on by screw On the rotating disk configured on the lower wall of the test chamber, lower fixed seat is installed on the lower wall of the analog transmissions case.
It is preferred that the upper end of the guide post and the top bearing cover mode connects for screw, the lower end of the guide post with it is described Lower fixed seat mode connects for screw.
Compared with the prior art, the invention has the advantages that:
(1) present invention can simulate the Vertical Launch state of guided missile in beam wind environment, and can its outlet wink of accurate simulation Between speed and acceleration..
(2) present invention can use its power/brake assemblies and buffering while tested guided missile is had powerful kinetic energy Device consumes these kinetic energy, protection test equipment safety.
(2) servo motor in the present invention, reductor, electromagnetic clutch and guide rail are all matured product, good reliability.And And the replacing and maintenance of parts are all more convenient, save development cost and maintenance cost.
(3) present invention uses modular construction, can change firing box, servo motor and deceleration according to test mission requirement The parts such as machine, substantially reduce the production cycle, have saved cost.
Brief description of the drawings
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 guider scheme of installation
Specific embodiment
As shown in figure 1, launching flow tunnel testing device the invention provides a kind of box Vertical-launched Missile missile wing, it includes Power/brake assemblies, guidance set, buffer, model adapter 319 and analog transmissions case 320;Model adapter 319 is single One part, for connecting guidance set and tested guided missile 2;Analog transmissions case 320 is to be designed according to the actual size of tested guided missile 2 Square chest or cylinder, are arranged on the rotating disk of wind tunnel wall 1 by screw, and rotating disk is considered as a part for wind tunnel wall 1.Rotating disk is rotated When, the lower fixed seat 321 that dishpan simulation firing box 320 passes through to be fixed thereon drives guidance set to rotate.In guidance set Sliding block 318 connected by model adapter 319 and tested guided missile 2, tested guided missile 2 can be rotated with guidance set, with conversion Different wind surfaces.
As shown in Fig. 2 power/the brake assemblies include servo motor 31, reductor 32, shaft coupling 33, rotating shaft 34, right Claim configuration in the bearing block 35 on capstan winch both sides, capstan winch 36, steel wire rope 322, electromagnetic clutch 37 and base 38.Wherein servo motor 31 output torques, for whole device provides power, the rotating speed of the reduction servo motor 31 of reductor 32, while improving output torque. Rotating shaft 34 and capstan winch 36 weld together, and its one end is connected by shaft coupling 33 with the output shaft of decelerator 32.(the ginseng of bearing block 35 According to Fig. 3) in bearing 351 is installed, through the endoporus of bearing 351, the balanced configuration of bearing block 35 rises on the both sides of capstan winch 36 for rotating shaft 34 To the effect of support.The other end and electromagnetic clutch 37 of rotating shaft 34 are connected, and electromagnetic clutch 37 mainly plays braking action, are powered When electromagnetic clutch 37 work, braking action is played by frictional force.One end of steel wire rope 322 is fixed on capstan winch 36, and twines It is wound on capstan winch 36, the other end is connected on model adapter 319, the upper and lower of tested guided missile 2 is realized by pulling and discharging Motion.Servo motor 31, reductor 32, bearing block 35 and electromagnetic clutch 37 are arranged on base 38 by screw, base The outside of 38 roofs for being fixed by screws in test chamber wall 1, mounting hole is provided with the roof of test chamber wall 1, The other end of steel wire rope 322 is passed through from mounting hole.
As shown in figure 4, the buffer includes transfer panel 311, outer sleeve 312, inner sleeve 315, inner spring 313, outer bullet Spring 314 and rubber blanket 316.The wherein length of the inner chamber of inner sleeve 315, the natural extended length of outer spring 314 and outer sleeve 312 Cavity length determines that inner spring 313 is freely placed in inner sleeve 315 (reference picture 5) all in accordance with the design runlength of inner spring 313 In inner chamber, the one end of inner spring 313 is withstood on its inner chamber boss 3151;Outer spring 314 be enclosed within inner sleeve 315 it is cylindrical on, one End is withstood on the upper end convex edge 3152 of inner sleeve 315, and the endoporus 3121 of outer sleeve 312 (as shown in Figure 6) passes through 315 sets of inner sleeve On outer spring 314, another end in contact of its lower end boss 3122 and outer spring 314, when outer spring 314 freely extends, overcoat 312 flange faces 3123 of cylinder are concordant with the free end of inner spring 313.Transfer panel 311 and outer sleeve 312 are bolted one Rise, the free end of inner spring 313 and the bottom surface of transfer panel 311 are in contact.Rubber blanket 316 is bonded in the bottom end of inner sleeve 315 On face 3153, there is circular hole inside rubber blanket 316, for through guide rail 317 and steel wire rope 322.After the missile wing 21 of folding launches, watch Take motor 31 to stop, the rubber blanket 316 of the cushion at collision in free uphill process of tested guided missile 2, 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, and inner spring 313 is compressed completely When, the stop motion of tested guided missile 2.In the springback process of inner spring 313, the compression of upper end convex edge 3152 outer spring of inner sleeve 315 314, the process can consume the elastic potential energy of a part of inner spring 313, and tested guided missile 2 completely disengages from the rubber blanket 316 of buffer Afterwards, electromagnetic clutch 37 starts, and consuming tested guided missile 2 by the friction of its interior arrangement and reductor 32 damping of itself remains Remaining kinetic energy.
As shown in fig. 7, the guidance set includes line slideway 317, sliding block 318, top bearing cover 39, lower bearing end cap 310th, thrust bearing 323 and lower fixed seat 321.Top bearing cover 39 and lower bearing end cap 310 are matched somebody with somebody with the two ends of thrust bearing 323 Charge-coupled to dress up thrust bearing assembly, thrust bearing assembly has middle through hole, and is arranged on wind tunnel test by top bearing cover 39 On the inwall of the roof of section wall 1, after installation, the middle through hole and mounting hole of thrust bearing assembly are on same axis.It is sliding Block 318 can be along the length direction of guide rail 317 slidably, but other direction frees degree are restricted, on line slideway 317 End and the mode connects for screw of top bearing cover 39, the lower end of line slideway 317 and the mode connects for screw of lower fixed seat 321, lower fixed seat 321 It is fixed on analog transmissions case 320 using screw.Lower bearing end cap 310 is connected using screw with transfer panel 311, is thus achieved Guidance set forms an entirety with firing box 320, and line slideway 317 can be rotated with firing box 320.Guidance set is acted on It is the direction of motion for limiting tested guided missile 2, it is moved up and down along guide rail.Through hole in mounting hole, thrust bearing assembly, connect The endoporus of disk 311, the endoporus of buffer, tested guided missile 2 middle through hole on same axis, guide rail 317 and steel wire rope 322 through hole, the endoporus of transfer panel 311, the endoporus of buffer, the middle through hole of tested guided missile 2 are worn from thrust bearing assembly respectively Cross.
The operation principle of box Vertical-launched Missile missile wing developing test device:Before on-test, tested guided missile 2 and its folding Folded missile wing 21 is placed in analog transmissions case 320, the model adapter 319 in guided missile and the steel wire rope being wrapped on capstan winch 36 322 free end connection.On-test, servo motor 31 drives capstan winch 36 to rotate by reductor 32, now electromagnetic clutch 37 are in off-position.With the rotation of capstan winch 36, steel wire rope 322 is constantly wrapped on capstan winch 36, and tested guided missile 2 is in steel wire Rapid increase under the dragging of rope 322, speed and the acceleration of requirement are reached when the moment that tested guided missile 2 departs from analog transmissions case 320 Degree, the missile wing 21 for now folding launches.Missile wing 21 around the upper right corner (left side missile wing shown in Fig. 1 21) place shaft foldable, at rotating shaft It is provided with torsion-bar spring.In firing box, the upper limb of missile wing 21 after folding is attached on bomb body, and lower edge is attached to the inwall of firing box 320 Upper (upper and lower edge refers to the upper lower edge of missile wing 21 shown in Fig. 1), firing box 320 uses coefficient of friction with the contact portion of missile wing 21 Smaller material is reducing the abrasion to missile wing 21.The moment of the complete outlet of tested guided missile 2, four missile wings 21 are in torsion-bar spring In the presence of restoring force, rapid deployment around the shaft, while be locked at missile wing 21 under its flight attitude by the retaining mechanism of missile wing 21 Fixed position.After the missile wing 21 of folding launches, tested guided missile 2 is in free ascent stage, does uniformly retarded motion, servo motor 31 equally do uniformly retarded motion, and now steel wire rope 322 does not stress.The cushion at collision moment of tested guided missile 2, buffer starts pressure Contracting, the kinetic energy of tested guided missile 2 gradates the elastic potential energy for buffer, until tested guided missile ascending motion stops starting back Bullet.In the springback process of tested guided missile 2, its moment for departing from rubber blanket 316 is no longer acted on by buffer screen resilience.It is slow Rush in device springback process, a part of elastic potential energy can be consumed by its internal two effect of spring, final remaining elasticity Potential energy converting and energy is the kinetic energy of tested guided missile 2, and guided missile is accelerated downwards.Tested guided missile 2 depart from buffer moment, electromagnetism from Clutch 37 is powered, and electromagnetic clutch 37 has started braking action, and tested guided missile 2 is consumed by the friction between its inner member Kinetic energy make its it is static during decline get off, so far, off-test.
The present invention disclosure satisfy that the requirement of Vertical-launched Missile under simulation beam wind environment, and can consume tested guided missile in examination The powerful kinetic energy of middle generation is tested, the experimental rig uses modular construction, can be expired by changing firing box and servo motor The experiment of sufficient different model.
The preferred embodiment of the present invention is illustrated above, but the present invention is not limited to above-described embodiment.It is right For those skilled in the art, in the category described in claims, it should be apparent that it is conceivable that various modifications Or fixed case, technology category of the invention is fallen within certainly.

Claims (5)

1. a kind of box Vertical-launched Missile missile wing launches flow tunnel testing device, it is characterised in that:Including drive control component, twist Disk, steel wire rope, guidance set, thrust bearing assembly, buffer, model adapter, guided missile model and analog transmissions case;
The drive control component is configured in the outside of test chamber roof with the capstan winch, the drive control component with The rotating shaft connection of the capstan winch is welded in, is capable of the rotation of capstan winch described in drive control, one end of the steel wire rope is fixed on institute State on capstan winch, and be wrapped on the capstan winch;Peace is offered on the roof of the test chamber immediately below the capstan winch Dress hole, the thrust bearing assembly structure is that thrust bearing is assembled between upper ball cover and lower ball cover, and described is pushed away Power bearing assembly has mesopore, and the thrust bearing assembly is coaxial with the mounting hole with the mesopore by the upper ball cover The mode of line is fixed on the inwall of the test chamber roof, and the buffer has middle shaft through-hole, and it is with the axis Through hole is arranged on the lower ball cover with the mode of the mesopore coaxial line;
The analog transmissions case is installed on the lower wall of the test chamber immediately below the buffer, described for placing Guided missile model, the guided missile model has middle through hole, and the model adapter is provided with the bottom of the guided missile model;
The guidance set includes line slideway and sliding block, the two ends of the line slideway be separately fixed at the upper ball cover and On the analog transmissions case, and the line slideway through the buffer middle shaft through-hole and the guided missile model in lead to Hole, the sliding block is fixed on the model adapter, and the other end of the steel wire rope is passed through on the test chamber roof Mounting hole, and through shaft through-hole in the buffer and the middle through hole of the guided missile model, be connected with the model adapter, So as under the control of the drive control component, the guided missile model be drawn high rapidly along the line slideway.
2. box Vertical-launched Missile missile wing according to claim 1 launches flow tunnel testing device, it is characterised in that:It is described Drive control component include servo motor, reductor, electromagnetic clutch and shaft coupling, the drive shaft of the servo motor with it is described The axle connection of reductor, the output shaft of the reductor is connected by shaft coupling with the one end for the rotating shaft for being welded in the capstan winch, The other end of the rotating shaft is connected with the electromagnetic clutch, and the rotating shaft is by being symmetricly set on the bearing of the capstan winch both sides On base, the servo motor, the reductor and the electromagnetic clutch are arranged on described to modular support by screw On base, the base is fixed by screws in the outside of the test chamber roof.
3. box Vertical-launched Missile missile wing according to claim 1 launches flow tunnel testing device, it is characterised in that:It is described Buffer includes transfer panel, outer sleeve, inner sleeve, inner spring, outer spring and rubber blanket, and the transfer panel is fixed on the lower axle Hold and cover, the top of the outer sleeve is fixed on the transfer panel, the inner sleeve by can slidably in the way of configure In the outer sleeve, between the outer sleeve and the inner sleeve, the outer spring upper end abuts for the outer spring configuration The upper end convex edge of the inner sleeve, its lower end is connected to the outer sleeve bottom, and the inner spring is configured at the inner sleeve In, the upper end of the inner spring abuts with the transfer panel, and its lower end is connected to the inner sleeve bottom, and the rubber blanket glues It is connected on the bottom end face of the inner sleeve, for being contacted with the guided missile model in rising.
4. box Vertical-launched Missile missile wing according to claim 1 launches flow tunnel testing device, it is characterised in that:It is described Analog transmissions case is the square chest or cylinder that coordinate the guided missile model to design, and the test chamber is arranged on by screw On the rotating disk configured on lower wall, lower fixed seat is installed on the lower wall of the analog transmissions case.
5. box Vertical-launched Missile missile wing according to claim 4 launches flow tunnel testing device, it is characterised in that:It is described The upper end of line slideway and the top bearing cover mode connects for screw, the lower end of the line slideway and the lower fixed seat spiral shell Nail connection.
CN201510162187.XA 2015-04-08 2015-04-08 Box Vertical-launched Missile missile wing launches flow tunnel testing device Active CN104748936B (en)

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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
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
CN106871747B (en) * 2017-01-11 2018-08-17 北京理工大学 The device of test missile wing expansion under a kind of body multi-angle high rotational speeds
CN106871748B (en) * 2017-01-11 2018-09-07 北京理工大学 Turntable for testing missile wing expansion under body multi-angle high rotational speeds

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