CN206695973U - A kind of missile release device - Google Patents
A kind of missile release device Download PDFInfo
- Publication number
- CN206695973U CN206695973U CN201720486565.4U CN201720486565U CN206695973U CN 206695973 U CN206695973 U CN 206695973U CN 201720486565 U CN201720486565 U CN 201720486565U CN 206695973 U CN206695973 U CN 206695973U
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- China
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- swing rod
- missile
- driving lever
- broken plate
- release device
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Abstract
The utility model discloses a kind of missile release device, including body and missile, the missile is before releasing, the side of the missile is connected by rotating release member with body, its opposite side is connected by swing rod with the swing rod rotation controling mechanism set on body, the swing rod rotation controling mechanism is used for before missile release, limit the rotation of swing rod, and when missile needs to launch, for releasing the rotationally constrained of swing rod, the missile drives rotation release member to rotate and disengage the connection with body.The setting that the utility model passes through swing rod rotation controling mechanism, some aircraft can be made in wind-tunnel missile separation test, ensure that missile at the appointed time or specified location efficiently separates, makes such aircraft missile separation to carry out wind comfort with body.
Description
Technical field
The utility model belongs to missile in technical field of aerospace and separates wind tunnel test professional skill field, more particularly to one
Kind missile release device.
Background technology
In some aircraft, the jettisoning such as part-structure such as air intake duct radome fairing, this part knot are needed in flight course
Structure（Hereinafter referred to as missile）Be connected before releasing with body, in wind-tunnel missile separation test, how to solve missile with
Body is at the appointed time or specified location efficiently separates, and realizes that such aircraft missile separation can carry out wind tunnel simulation
It is crucial.
Utility model content
Goal of the invention of the present utility model is：For above-mentioned problem, there is provided one kind can be applied to some fly
Row device missile separates the missile release device of wind comfort.
What the technical solution of the utility model was realized in：A kind of missile release device, it is characterised in that：Including machine
Body and missile, before releasing, the side of the missile is connected the missile by rotating release member with body, and its is another
Side is connected by swing rod with the swing rod rotation controling mechanism set on body, and the swing rod rotation controling mechanism is used to launch
Before thing release, the rotation of swing rod is limited, and when missile needs to launch, for releasing the rotationally constrained of swing rod, the dispensing
Thing drives rotation release member to rotate and disengage the connection with body.
Missile release device described in the utility model, its described swing rod rotation controling mechanism includes driving lever, swing rod limits
Position pin and drive mechanism, the end of the driving lever and one end corresponding matching of swing rod, the drive mechanism are used to control driving lever
Rotate, so that driving lever provides the power rotated for swing rod, the swing rod spacer pin is arranged on body and for turning to swing rod
Dynamic trend is limited.
Missile release device described in the utility model, its drive mechanism are the linear drives being arranged in body
Device, the linear drive apparatus are connected by power accumulation of energy transmission mechanism with driving lever, and the power accumulation of energy transmission mechanism includes
The sliding block being arranged in body, the sliding block are slidably disposed on guide rail, and the guide rail is fixedly installed in body, described
Sliding block is connected with linear drive apparatus, and the linear drive apparatus is used for band movable slider and slided along guide rail, and slides one in sliding block
After Duan Hangcheng and the certain kinetic energy of deposit, contacted with driving lever, and drive driving lever to rotate.
Missile release device described in the utility model, its described driving lever is by driving lever driving lever, shift lever axis and symmetrical
The driving lever follower lever composition at shift lever axis both ends is arranged on, the driving lever driving lever is arranged in the middle part of shift lever axis, on the sliding block
It is provided with and driving lever driving lever corresponding matching chute, the driven boom end of driving lever and swing link end part corresponding matching.
Missile release device described in the utility model, one end of its swing rod is corresponding with the driven boom end of driving lever to match somebody with somebody
Close, its other end is hinged by pendulum shaft and missile, and described swing rod spacer pin one end is inserted on the pin-and-hole of body, another side pressure
It can infer swing rod spacer pin under the drive of driving lever follower lever and make towards the end face of rotation direction, the swing rod in swing rod
Swing rod obtains initial angular velocity.
Missile release device described in the utility model, it is threaded with and oscillating bar length direction on the swing rod
Vertically arranged swing rod pre-loading screw, the end of the swing rod pre-loading screw through swing rod and swing rod pre-loading screw are resisted against body
On.
Missile release device described in the utility model, its described rotation release member is broken plate, in the fracture
The single or double of plate is provided with weakening groove, and one end of the broken plate is connected with body, the other end of the broken plate and throwing
Thing connection is put, when needing to launch, the swing rod rotation controling mechanism releases to the rotationally constrained of swing rod the missile, described
Missile rotates around the weakening groove of broken plate, and the missile separates after broken plate fracture with body.
Missile release device described in the utility model, its described broken plate is weakening at groove before bending fracture, described
Two relative cell walls for weakening groove are contacted with each other, and after the cell wall contacts with each other, broken plate is broken by weakening groove.
Missile release device described in the utility model, its described weakening groove is V-shaped, and bending broken plate is until weaken groove
The angle that two relative cell walls are bent when contacting with each other is θ2, the included angle θ for weakening groove2No more than the reality of broken plate
Border is broken angle, θ1。
Missile release device described in the utility model, its described cell wall for weakening groove, which contacts with each other, makes weakening groove subsequent
The transfer of bending process move portion and translate a segment distance from broken plate weak point to notch direction is weakened, broken plate is around new rotation section
Continue to bend, broken plate weak point Main Load is become pulling force from moment of flexure, finally break broken plate weak point.
The utility model can be such that some aircraft are separated in wind-tunnel missile by the setting of swing rod rotation controling mechanism
In experiment, it is ensured that missile at the appointed time or specified location efficiently separates, separates such aircraft missile with body
Wind comfort can be carried out.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model.
Fig. 2 is partial enlarged drawing of the present utility model.
Fig. 3 is the structural representation of the utility model middle guide.
Fig. 4 is the structural representation of sliding block in the utility model.
Fig. 5 is the structural representation of driving lever in the utility model.
Fig. 6 is the structural representation of broken plate in the utility model.
Fig. 7 is the utility model action process schematic diagram.
Reference：1 is body, and 2 be missile, and 3 be swing rod, and 4 be driving lever, and 5 be swing rod spacer pin, and 6 be linear drives
Device, 7 be sliding block, and 8 be guide rail, and 9 be pendulum shaft, and 10 be swing rod pre-loading screw, and 11 be broken plate, and 12 is weaken groove, and 13 be lid
Plate, 41 be driving lever driving lever, and 42 be shift lever axis, and 43 be driving lever follower lever, and 61 be drive rod, and 71 be chute, and 111 be rotation section,
121 be cell wall.
Embodiment
Below in conjunction with the accompanying drawings, the utility model is described in detail.
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining
The utility model, it is not used to limit the utility model.
, it is necessary to explanation, term " middle part ", " top ", " lower section ", " interior ", " outer " in description of the present utility model
Orientation or position relationship Deng instruction are based on orientation shown in the drawings or position relationship, are for only for ease of and describe this practicality newly
Type and simplifying describes, rather than instruction or implies that signified device or part must have specific orientation, with specific orientation
Construction and operation, therefore it is not intended that to limitation of the present utility model.
As shown in figs. 1-7, a kind of missile release device, including body 1 and missile 2, the missile 2 are discharging
Before, the side of the missile 2 is connected by rotating release member with body 1, and its opposite side is by swing rod 3 with being set on body 1
The swing rod rotation controling mechanism connection put, the swing rod rotation controling mechanism are used for before the release of missile 2, limitation swing rod 3
Rotate, and when missile 2 needs to launch, for releasing the rotationally constrained of swing rod 3, the missile 2, which drives, rotates unblock structure
Part rotates and disengages the connection with body 1.
Wherein, the swing rod rotation controling mechanism includes driving lever 4, swing rod spacer pin 5 and drive mechanism, the driving lever 4
End and swing rod 3 one end corresponding matching, the drive mechanism is used to control driving lever 4 to rotate, carried so that driving lever 4 is swing rod 3
For the power of rotation, the swing rod spacer pin 5 is arranged on body 1 and is used for positioned at the top of swing rod 3, the swing rod spacer pin 5
The rotation of swing rod 3 is limited, the drive mechanism is the linear drive apparatus 6 being arranged in body 1, and the linear drive apparatus can
Select cylinder or linear electric motors, the direction of motion of drive rod 61 of the linear drive apparatus consistent with body y direction；In order to
Make missile separating dynamics process similar, it is necessary to the synchronous swing rod that releases is rotationally constrained and assign swing rod initial angular velocity, the angle
Speed is maximum to be connected up to 30rad/s, the linear drive apparatus 6 by power accumulation of energy transmission mechanism with driving lever 4, the power
Accumulation of energy transmission mechanism includes the sliding block 7 being arranged in body 1, and the sliding block 7 is slidably disposed on guide rail 8, the sliding block
Motion by guide rail limited can only along with the direction of motion of drive rod 61 similar in direction translational, the guide rail 8 is fixedly installed on machine
In body 1, the guide rail also acts as when bearing slipper push driving lever radial load and curved in addition to limitation sliding block can only move along guide rail
The effect of square, radial load and moment of flexure is prevented to be delivered on the drive rod of linear drive apparatus and cause drive rod clamping stagnation, the sliding block 7
It is connected with linear drive apparatus 6, the linear drive apparatus 6 is used for band movable slider 7 and slided along guide rail 8, and slides one in sliding block 7
After Duan Hangcheng and the certain kinetic energy of deposit, contacted with driving lever 4, and drive driving lever 4 to rotate, this section of stroke can be such that sliding block is connect with driving lever
The certain kinetic energy of deposit, these kinetic energy finally can partly pass to swing rod, be advantageous in linear drive apparatus power limited before touching
In the case of improve swing rod initial angular velocity.
In the present embodiment, the driving lever 4 by driving lever driving lever 41, shift lever axis 42 and is symmetricly set on 42 liang of shift lever axis
The driving lever follower lever 43 at end forms, and the driving lever driving lever 41 is arranged on the middle part of shift lever axis 42 lower section, is set on the sliding block 7
Have and the corresponding matching chute 71 of driving lever driving lever 41, driving lever driving lever direction and slide block movement direction near normal, the driving lever
The end of follower lever 43 and the end corresponding matching of swing rod 3, one end and the end corresponding matching of driving lever follower lever 43 of the swing rod 3, its
The other end is be hinged by pendulum shaft 9 and missile 2, and the driving lever driving lever changes the linear motion of sliding block under slipper push
Rotation for driving lever around shift lever axis, driving lever follower lever direction is approximate with swing rod point-blank, rotation of the driving lever around shift lever axis
Driving lever follower lever is driven, driving lever follower lever promotes swing rod；Described one end of swing rod spacer pin 5 is inserted on the pin-and-hole of body 1, the other end
The upper surface of swing rod 3 is pressed in, described swing rod spacer pin one end is pressed in swing rod surface rather than the original being connected by pin-and-hole with swing rod
Because being that this structure has bigger tolerance, and avoided in wind-tunnel narrow operating spaces for processing, rigging error
Carry out the difficult operation of hole position alignment, the slipper push driving lever driving lever, driving lever driving lever drives driving lever follower lever to remote
Body direction is rotated, and driving lever follower lever band driven fork is moved, and the swing rod 3 can be inferred under the drive of driving lever follower lever 43
Swing rod spacer pin 5 simultaneously makes swing rod 3 obtain initial angular velocity；The swing rod pretension being vertically arranged is threaded with the swing rod 3
Screw 10, the bottom of the swing rod pre-loading screw 10 through swing rod 3 and swing rod pre-loading screw 10 are resisted against on body 1, so as to
Drive missile to be adjacent to body by swing rod, rocked with eliminating missile caused by fit-up gap.
In wind-tunnel missile separation test, the requirement of similarity criterion is separated according to missile, in order to break as small as possible
Bad dummy vehicle aerodynamic configuration, it is desirable to which mechanism major part is located at mould impression.Wherein, larger-size linear drives dress
Put, guide rail, sliding block are fully located at body mould impression, only part driving lever, part swing rod pre-loading screw, part swing rod spacer pin
Expose body model, the body upper is provided with cover plate 13, and the destruction for model aerodynamic configuration is smaller.
As shown in fig. 6, the rotation release member is broken plate 11, it is provided with the single or double of the broken plate 11
Weaken groove 12, when weakening groove broken plate using opening one side, reduce direction bending to fluting, or groove fracture is weakened using double open
During plate, one side is bent thereto, and one end of the broken plate 11 is connected with the bottom of body 1, the other end of the broken plate 11 and
The bottom connection of missile 2, for the missile 2 when needing to launch, the swing rod rotation controling mechanism releases the rotation to swing rod 3
Turn limitation, the missile 2 rotates around the weakening groove 12 of broken plate 11, the missile 2 after the fracture of broken plate 11 with body 1
Separation, the broken plate 11 are weakening at groove 12 before bending fracture, and two relative cell walls 121 for weakening groove 12 mutually connect
Touch, after the cell wall 121 contacts with each other, broken plate 11 is broken by weakening groove 12.
In the present embodiment, the weakening groove 12 is V-shaped, when the shape contacts with each other two relative cell walls of weakening groove
Contact area is maximum, so as to reduce footprint pressure, weakens influence of the compressive deformation to fracture angle, bending broken plate 11 is until cut
The angle that weak groove 12 two relative cell wall 121 is bent when contacting with each other is θ2, the included angle θ for weakening groove 122It is not more than
The actual crack angle, θ of broken plate 111, the cell wall 121 for weakening groove 12 contacts with each other being folded over of making weakening groove 12 subsequent
Rotation section 111 translates a segment distance from the weak point of broken plate 11 to notch direction is weakened in journey, and broken plate 11 is around new rotation section
111 continue to bend, and the weak point Main Load of broken plate 11 is become pulling force from moment of flexure, finally break the weak point of broken plate 11,
Broken plate is broken.
Wherein, the fracture angle design method of the broken plate is specially：Remember that broken plate design fracture angle is θ, it is actual
Fracture angle is θ1, bending broken plate is until it is θ to weaken the angle bent when two relative cell walls of groove contact with each other2；Due to cutting
The influence of elongation percentage when influence and the Materials Fracture of compression are extruded when weak two relative cell walls of groove contact with each other so that θ1＞ θ2,
Wherein θ2It can be determined in machining, θ1Actual measurement is then needed, to make θ1Deviation between θ reaches the inclined of engineering license
In poor scope, following steps can be taken to determine θ2：
A. θ is selected2Initial value, θ2Initial value may be selected a value close to θ, in the case of rawness data can use
For θ, a value for being less than θ can be rule of thumb taken in the case where there are experience data；
B. according to θ2Design processing broken plate；
C. broken plate fracture angle, θ is measured1；
D. fracture angular deviation is judged（θ1-θ）Whether in the deviation range of license, if it is, current θ2I.e. as most
Whole result；If it is not, then by θ2Subtract（θ1-θ）As new θ2, repeat step b~step d.
Wherein, the broken plate is broken the difference of angle, θ according to design, and the toughness reguirements to fracture plate material is also different,
Whether checking fracture plate material meets the toughness reguirements under design fracture angle, according to the carrying demand in fracture process to shearing
Can be with the following method：
If weakness needs to remain higher shear resistance before broken plate fracture, θ can be processed with the material2Value
Not less than θ and weak point thickness identical broken plate, if bending angle reaches θ, broken plate does not occur human eye visible crack,
Then the toughness of material meets to require；If weakness need not remain higher shear resistance before broken plate fracture, can use
The material processes θ2Value is not less than θ and weak point thickness identical broken plate, if bending angle reaches θ, broken plate is not
Fracture completely, then toughness of material satisfaction requirement.
In missile launch process, missile weakens groove around broken plate under Aerodynamic force action and rotated, when missile turns
Broken plate is broken off after to certain angle, is connected and is fully disconnected between missile and body, missile can be under Aerodynamic force action
Depart from body.
Structure of the present utility model laterally and it is vertical needed for space is less than space needed for longitudinal direction, be adapted to be mounted within laterally with
The body inner chamber that vertical direction spatial is small, longitudinal space is big, the method for accumulation kinetic energy is accelerated to drop in advance before driving lever is promoted by sliding block
Low drive device power demand, can relax limitation of the drive device in terms of size, the energy (air pressure, voltage etc.), and swing rod is spacing
Pin limits swing rod motion by way of compression, simplifies the assembly work before experiment every time.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
All any modification, equivalent and improvement made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (10)
- A kind of 1. missile release device, it is characterised in that：Including body（1）And missile（2）, the missile（2）Releasing Before putting, the missile（2）Side by rotating release member and body（1）Connection, its opposite side pass through swing rod（3）With machine Body（1）The swing rod rotation controling mechanism connection of upper setting, the swing rod rotation controling mechanism are used in missile（2）Before release, Limit swing rod（3）Rotation, and in missile（2）When needing to launch, for releasing swing rod（3）Rotationally constrained, the dispensing Thing（2）Drive and rotate release member and rotate and disengage and body（1）Connection.
- 2. missile release device according to claim 1, it is characterised in that：The swing rod rotation controling mechanism includes dialling Bar（4）, swing rod spacer pin（5）And drive mechanism, the driving lever（4）End and swing rod（3）One end corresponding matching, it is described Drive mechanism is used to control driving lever（4）Rotate, so that driving lever（4）For swing rod（3）The power rotated, the swing rod spacer pin are provided （5）It is arranged on body（1）Above and for swing rod（3）Rotation trend limited.
- 3. missile release device according to claim 2, it is characterised in that：The drive mechanism is to be arranged on body （1）Interior linear drive apparatus（6）, the linear drive apparatus（6）Pass through power accumulation of energy transmission mechanism and driving lever（4）Connection, The power accumulation of energy transmission mechanism includes being arranged on body（1）Interior sliding block（7）, the sliding block（7）It is slidably disposed on and leads Rail（8）On, the guide rail（8）It is fixedly installed on body（1）It is interior, the sliding block（7）With linear drive apparatus（6）Connection, it is described Linear drive apparatus（6）For band movable slider（7）Along guide rail（8）Slide, and in sliding block（7）Slide a trip and deposit is certain After kinetic energy, with driving lever（4）Contact, and drive driving lever（4）Rotate.
- 4. missile release device according to claim 3, it is characterised in that：The driving lever（4）By driving lever driving lever （41）, shift lever axis（42）And it is symmetricly set on shift lever axis（42）The driving lever follower lever at both ends（43）Composition, the driving lever is actively Bar（41）It is arranged on shift lever axis（42）Middle part, in the sliding block（7）On be provided with and driving lever driving lever（41）Corresponding matching chute （71）, the driving lever follower lever（43）End and swing rod（3）End corresponding matching.
- 5. missile release device according to claim 4, it is characterised in that：The swing rod（3）One end and driving lever from Lever（43）End corresponding matching, its other end pass through pendulum shaft（9）With missile（2）It is be hinged, the swing rod spacer pin（5）One End is inserted in body（1）Pin-and-hole on, the other end is pressed in swing rod（3）Towards the end face of rotation direction, the swing rod（3）It can dial Bar follower lever（43）Drive under, infer swing rod spacer pin（5）And make swing rod（3）Obtain initial angular velocity.
- 6. missile release device according to claim 5, it is characterised in that：In the swing rod（3）On be threaded with With swing rod（3）The vertically arranged swing rod pre-loading screw of length direction（10）, the swing rod pre-loading screw（10）Through swing rod（3）And Swing rod pre-loading screw（10）End be resisted against body（1）On.
- 7. missile release device as claimed in any of claims 1 to 6, it is characterised in that：It is described to rotate unblock Component is broken plate（11）, in the broken plate（11）Single or double be provided with weakening groove（12）, the broken plate（11） One end and body（1）Connection, the broken plate（11）The other end and missile（2）Connection, the missile（2）Needing During dispensing, the swing rod rotation controling mechanism is released to swing rod（3）Rotationally constrained, the missile（2）Around broken plate（11） Weakening groove（12）Rotation, the missile（2）In broken plate（11）After fracture with body（1）Separation.
- 8. missile release device according to claim 7, it is characterised in that：The broken plate（11）Weakening groove（12） Before place's bending fracture, the weakening groove（12）Two relative cell walls（121）Contact with each other, the cell wall（121）Mutually connect After touch, broken plate（11）By weakening groove（12）Place's fracture.
- 9. missile release device according to claim 8, it is characterised in that：The weakening groove（12）V-shaped, bending is disconnected Split plate（11）Until weaken groove（12）Two relative cell walls（121）The angle bent when contacting with each other is θ2, the weakening groove （12）Included angle θ2No more than broken plate（11）Actual crack angle, θ1。
- 10. missile release device according to claim 9, it is characterised in that：The weakening groove（12）Cell wall（121） Contacting with each other makes weakening groove（12）Portion is moved in subsequent bending process transfer（111）From broken plate（11）Weak point to weaken notch Direction translates a segment distance, broken plate（11）Around new rotation section（111）Continue to bend, make broken plate（11）Weak point Main Load Become pulling force from moment of flexure, finally make broken plate（11）Weak point is broken.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720486565.4U CN206695973U (en) | 2017-05-04 | 2017-05-04 | A kind of missile release device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720486565.4U CN206695973U (en) | 2017-05-04 | 2017-05-04 | A kind of missile release device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206695973U true CN206695973U (en) | 2017-12-01 |
Family
ID=60448121
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720486565.4U Active CN206695973U (en) | 2017-05-04 | 2017-05-04 | A kind of missile release device |
Country Status (1)
| Country | Link |
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| CN (1) | CN206695973U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106950030A (en) * | 2017-05-04 | 2017-07-14 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of missile release device |
| CN108195550A (en) * | 2018-01-15 | 2018-06-22 | 中国航天空气动力技术研究院 | Model launches separation modified wind tunnel test mechanism |
-
2017
- 2017-05-04 CN CN201720486565.4U patent/CN206695973U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106950030A (en) * | 2017-05-04 | 2017-07-14 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of missile release device |
| CN108195550A (en) * | 2018-01-15 | 2018-06-22 | 中国航天空气动力技术研究院 | Model launches separation modified wind tunnel test mechanism |
| CN108195550B (en) * | 2018-01-15 | 2019-10-18 | 中国航天空气动力技术研究院 | Model launches separation modified wind tunnel test mechanism |
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