CN208671815U - Rudder wingfold device and micro missile - Google Patents
Rudder wingfold device and micro missile Download PDFInfo
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- CN208671815U CN208671815U CN201821179085.4U CN201821179085U CN208671815U CN 208671815 U CN208671815 U CN 208671815U CN 201821179085 U CN201821179085 U CN 201821179085U CN 208671815 U CN208671815 U CN 208671815U
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- rudder
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- rudder wing
- wing
- wingfold
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Abstract
The utility model relates to STT missile technical fields, more particularly, to a kind of rudder wingfold device and micro missile.The rudder wingfold device, including the rudder wing, steering gear flat, component and runner assembly are lifted, the runner assembly is installed on the steering gear flat, and the rudder wing is flexibly connected with the runner assembly；The component that lifts is installed between the rudder wing and the runner assembly；The aerofoil of the rudder wing can be affixed with the surface of the steering gear flat；The component that lifts is for lifting the rudder wing, so that the aerofoil of the rudder wing becomes upright state from the state of being affixed；The runner assembly is for rotating the rudder wing lifted.The micro missile, including the rudder wingfold device.The utility model is conducive to the occupied space for reducing guided missile by folding fin.
Description
Technical field
The utility model relates to STT missile technical fields, more particularly, to a kind of rudder wingfold device and micro missile.
Background technique
In recent years, unmanned air vehicle technique is quickly grown, and plays in executing microminiature target strike task more and more important
Role.Since the bullet-loading capacity of unmanned plane is limited, for the carrying for meeting unmanned plane, missile diameter and weight are proposed small-sized
Change, light-weighted requirement.As missile diameter is smaller and smaller, weight is more and more lighter, the primary portable guided missile quantity of unmanned plane
Increase immediately, but the fixed X layout empennage occupied space that traditional guided missile uses is larger, hinders unmanned plane bullet-loading capacity instead
Increase.
Utility model content
The purpose of this utility model is to provide a kind of rudder wingfold device and micro missiles, to solve to deposit in the prior art
It is larger in the fixed X layout empennage occupied space that traditional guided missile uses, the increased of unmanned plane bullet-loading capacity is hindered instead
Technical problem.
The utility model provides a kind of rudder wingfold device, including the rudder wing, steering gear flat, lifts component and runner assembly,
The runner assembly is installed on the steering gear flat, and the rudder wing is flexibly connected with the runner assembly；It is described to lift component peace
Loaded between the rudder wing and the runner assembly；The aerofoil of the rudder wing can be affixed with the surface of the steering gear flat；It is described
Component is lifted for lifting the rudder wing, so that the aerofoil of the rudder wing becomes upright state from the state of being affixed；The rotation
Component is for rotating the rudder wing lifted.
Further, the runner assembly includes drive shaft, hinged by pin shaft between the rudder wing and the drive shaft,
And the axis perpendicular of the axis of the pin shaft and the drive shaft；The drive shaft and the steering gear flat are rotatablely connected.
Further, the component that lifts includes the first torsional elastomer, and first torsional elastomer is installed on institute
It states between the rudder wing and the drive shaft.
Further, between one end of the drive shaft and the steering gear flat by bearing connect, the drive shaft it is another
One end is provided with free bearing, and the root of the rudder wing is connected with the free bearing by the pin shaft；Two sub- ears of the free bearing
Between there is rotary spacing portion, lift angle for limit the rudder wing.
Further, the runner assembly further includes the second torsional elastomer, for making the drive shaft around the axis of itself
Line rotation.
Further, the runner assembly further includes driving device, driving gear and driven gear, and the driving device is used
In driving the driving gear rotation, the driving gear is meshed with the driven gear；The driven gear is sheathed on institute
State in drive shaft, and be provided with latch assembly between the driven gear and the drive shaft, for make the driven gear with
It is able to maintain between the drive shaft opposing stationary；The driving device is fixed on the steering gear flat, the second torsion bullet
Property part is installed between the drive shaft and the driven gear.
Further, the latch assembly includes holddown spring and locating piece；The surface of the drive shaft offers positioning
Slot；Mounting hole is offered on the hole wall of the axle hole of the driven gear, the holddown spring and the locating piece are mounted on
In the mounting hole；The holddown spring be used for during the drive shaft turns, when the locating slot position with it is described
When the position of mounting hole is opposite, it is inserted into the locating piece in the locating slot.
Further, the first torsional elastomer is to place side by side double torsion spring, and the midfoot support for placing side by side double torsion spring is in institute
On the aerofoil for stating the rudder wing, the both ends for placing side by side double torsion spring respectively be embedded in the drive shaft.
Further, second torsional elastomer is torsionspring, and one end of the torsionspring is embedded in the driving
The other end of axis, the torsionspring is embedded in the driven gear.
Further, the quantity of the rudder wing is multiple, and multiple rudder wings are uniform along the outer peripheral surface of the steering gear flat
It lays.
The utility model additionally provides a kind of micro missile, including the rudder wingfold device.
Compared with prior art, the utility model has the following beneficial effects:
Rudder wingfold device provided by the utility model can be connected when in use with body, since the rudder wing is first to lift
Afterwards, it is then rotated further by, to realize the expansion of the rudder wing, therefore the rudder wing can be folded in rudder along the axial horizontal lying-type of the body of guided missile
Realize that guided missile is projected from launching tube by expansion module to reduce the occupied space of guided missile entirety in the outer surface of cabin
Afterwards, fin Automatic-expanding.
The micro missile that the utility model also provides, including the rudder wingfold device.It based on above-mentioned analysis it is found that should
The rudder wing of micro missile is conducive to the occupied space for reducing guided missile due to that can fold.
The additional aspect and advantage of the utility model will become obviously in following description section, or practical new by this
The practice of type is recognized.
Detailed description of the invention
It, below will be right in order to illustrate more clearly of specific embodiment of the present invention or technical solution in the prior art
Specific embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, it is described below
In attached drawing be that some embodiments of the utility model are not paying creativeness for those of ordinary skill in the art
Under the premise of labour, it is also possible to obtain other drawings based on these drawings.
Structural schematic diagram when Fig. 1 is the expansion for the rudder wingfold device that the utility model embodiment one provides；
The structural representation at another visual angle when Fig. 2 is the expansion for the rudder wingfold device that the utility model embodiment one provides
Figure；
Structural schematic diagram when Fig. 3 is the folding for the rudder wingfold device that the utility model embodiment one provides；
The structural representation at another visual angle when Fig. 4 is the folding for the rudder wingfold device that the utility model embodiment one provides
Figure；
Fig. 5 is the structural schematic diagram for the steering gear flat that the utility model embodiment one provides；
Fig. 6 is the structural schematic diagram at another visual angle for the steering gear flat that the utility model embodiment one provides；
Fig. 7 is the cross-sectional view for the steering gear flat that the utility model embodiment one provides；
Fig. 8 is the structural schematic diagram for the driven gear that the utility model embodiment one provides；
Fig. 9 is the cross-sectional view for the driven gear that the utility model embodiment one provides；
Figure 10 is the partial enlargement diagram in Fig. 2 at A.
Icon:
The 101- rudder wing；102- steering gear flat；103- head end；104- tail end；105- drive shaft；106- pin shaft；107- plane；
108- installation base；109- round plate；110- perforation；111- axis hole；112- rotary spacing portion；The sub- ear of 113-；114- cuts with scissors ear；
115- places side by side double torsion spring；116- driving device；117- driving gear；118- driven gear；119- positioning sleeve；120- bearing；
121- toothed region；122- smooth surface portion；123- torsionspring；124- holddown spring；125- positioning ball；126- spring jackscrew；
127- screw；128- mounting hole.
Specific embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with attached drawing, it is clear that described
Embodiment is the utility model a part of the embodiment, instead of all the embodiments.
The component of the utility model embodiment for usually describing and showing in attached drawing here can be with a variety of different
Configuration is to arrange and design.It therefore, is not below purport to the detailed description of the embodiments of the present invention provided in the accompanying drawings
In the range of limitation claimed invention, but it is merely representative of the selected embodiment of the utility model.
Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
It is in the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", " perpendicular
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings, and is only
For ease of description the utility model and simplify description, rather than the device or element of indication or suggestion meaning must have it is specific
Orientation, be constructed and operated in a specific orientation, therefore should not be understood as limiting the present invention.In addition, term " the
One ", " second ", " third " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
Embodiment one
Referring to shown in Fig. 1 to Figure 10, it includes the rudder wing that the utility model embodiment one, which provides a kind of rudder wingfold device,
101, steering gear flat 102, lift component and runner assembly, runner assembly is installed on steering gear flat 102, the rudder wing and runner assembly activity
Connection；Component is lifted to be installed between the rudder wing and runner assembly；The aerofoil of the rudder wing can be affixed with the surface of steering gear flat 102,
In the state that the aerofoil of the rudder wing and the surface of steering gear flat 102 are affixed, the aerofoil of the rudder wing is parallel with the axis of steering gear flat 102；Lift
Component is played for lifting the rudder wing, so that the aerofoil of the rudder wing becomes upright state from the state of being affixed, i.e. the rudder wing becomes from folded state
For upright state；Runner assembly for make the rudder wing lifted rotate, its rotation is made by runner assembly so that the aerofoil of the rudder wing from
With the axis perpendicular state of steering gear flat 102, become the aerofoil of the rudder wing state parallel with the axis of steering gear flat 102.
Shown in Figure 1, specifically, steering gear flat 102 has corresponding head end 103 and a tail end 104, the rudder wing is from head end
103 caudad 104 direction topple over and be affixed with the surface for realizing the aerofoil and steering gear flat 102 of the rudder wing.Steering gear flat 102 is tubular knot
Structure；The wing root of the rudder wing is hinged with runner assembly.It is the length direction of the rudder wing from the wing root of the rudder wing to the direction of the wingtip of the rudder wing,
When the aerofoil of the rudder wing is attached to the surface of steering gear flat 102, the length direction of the rudder wing is substantially parallel with the axis of tubular structure；?
When the rudder wing becomes upright state, the length direction of the rudder wing and the axis perpendicular of tubular structure.It should be noted that the embodiment
In, be affixed expression is that the aerofoil of the boat wing is located next to the surface of cabin cabin, to have gap between the two, can also be in contact.
The rudder wingfold device that the embodiment provides can be connected when in use with body, since the rudder wing is first to lift
Afterwards, it is then rotated further by, to realize the expansion of the rudder wing, therefore the rudder wing can be folded in rudder along the axial horizontal lying-type of the body of guided missile
Realize that guided missile is penetrated from launching tube by expansion module to reduce the occupied space of guided missile entirety in the outer surface of cabin 102
After out, fin Automatic-expanding.
In the optional scheme of the embodiment, the quantity of the rudder wing is multiple, and multiple rudder wings are equal along the outer peripheral surface of steering gear flat 102
Even laying.
Specifically, in the embodiment, by taking the quantity of the rudder wing is 4 as an example, to be specifically described.The two neighboring rudder wing
Between pair central angle be 90 °.The outer surface of steering gear flat 102 offers the plane 107 being affixed for the aerofoil of the rudder wing with it, this
Sample is after the rudder wing 1 folds, the unlikely maximum outside diameter beyond guided missile；The quantity of plane 107 is equal with the quantity of the rudder wing, and multiple flat
Face 107 and a pair of of the setting of multiple rudder wings one.The corresponding runner assembly of each rudder wing.
In the optional scheme of the embodiment, runner assembly includes drive shaft 105, passes through pin between the rudder wing and drive shaft 105
Axis 106 is hinged, and the axis perpendicular of the axis of pin shaft 106 and drive shaft 105；Drive shaft 105 and the rotation of steering gear flat 102 connect
It connects.During the rudder wing lifts, the rudder wing is rotated around the axis of pin shaft 106；After the rudder wing is at upright state, drive shaft 105 and rudder
The wing is rotated around the axis of drive shaft 105 together.
Referring to Fig. 3 and Fig. 7 specifically, steering gear flat 102 is internally provided with installation base 108, installation base 108 is fixed
In the center of the round plate 109 of boat engine room inside, which is located on the axis of steering gear flat 102.Steering gear flat 102
Perforation 110 is also provided on barrel, for passing through for drive shaft 105.The axis phase of the axis of drive shaft 105 and steering gear flat 102
Vertically.Installation base 108 is in round shape column.The circumferential direction of installation base 108 offers 4 axis holes 111.
It in the optional scheme of the embodiment, is connected, is driven by bearing 120 between one end and steering gear flat 102 of drive shaft 105
The other end of moving axis 105 is provided with free bearing, and the root of the rudder wing is connected with free bearing by pin shaft 106；The sub- ear 113 of two of free bearing
Between there is rotary spacing portion 112, lift angle for limit the rudder wing, that is to say, that two sub- ears 113 and rotary spacing portion
112 form a blind slot, and in this way after the rudder wing lifts, ear 114 is cut with scissors since the limitation in rotary spacing portion 112 is made in the root of the rudder wing
With to realize the limit to the angle of the rudder wing, in the embodiment, passing through so that the rudder wing can not continue around the rotation of pin shaft 106
Rotary spacing portion 112, so that the rudder wing is 0 °~90 ° around the rotational angle range of pin shaft 106.
Specifically, the free bearing of the other end of drive shaft 105 is hinged after stretching out in perforation 110 with the rudder wing.The rudder wing
Between two sub- ears 113 of the single hinge ear 114 insertion free bearing of root, and by pin shaft 106 realize the rudder wing and drive shaft 105 it
Between it is hinged.Bearing 120 is installed in axis hole, it is fixed by screw 127 between the outer ring of bearing 120 and the hole wall of axis hole.Bearing
120 inner ring is interference fitted or is connected by key with drive shaft 105, and such drive shaft 105 can rotate in axis hole.
In the optional scheme of the embodiment, lifting component includes the first torsional elastomer, and the first torsional elastomer is installed
Between the rudder wing and drive shaft 105, it can realize that the rudder wing automatically becomes upright state from folded state by the first torsional elastomer.
Specifically, the first torsional elastomer is to place side by side double torsion spring 115, place side by side the midfoot support of double torsion spring 115 in
On the aerofoil of the rudder wing, the both ends of double torsion spring 115 are placed side by side respectively with insertion drive shaft 105, place side by side the both ends point of double torsion spring 115
Not Qian Ru free bearing sub- ear 113 lateral surface on.
Referring to shown in Fig. 1 and Figure 10, in the optional scheme of the embodiment, runner assembly further includes driving device 116, active
Gear 117 and driven gear 118, driving device 116 is for driving driving gear 117 to rotate, driving gear 117 and driven gear
118 are meshed；Driven gear 118 is sheathed in drive shaft 105, and is provided with locking between driven gear 118 and drive shaft 105
Component, it is opposing stationary for making to be able to maintain between driven gear 118 and drive shaft 105；Driving device 116 is fixed on steering gear flat
On 102, the second torsional elastomer is installed between drive shaft 105 and driven gear 118.
Specifically, positioning sleeve 119 has been installed in drive shaft 105, for positioning driven gear 118 in drive shaft 105
On position.Positioning sleeve 119 is interference fitted or is connected by key with drive shaft 105.The circumferential direction of driven gear 118 has toothed region
121 and smooth surface portion 122, toothed region 121 has tooth.Driving device 116 includes motor and speed reducer, the output shaft of motor and deceleration
The input shaft of machine is fixedly connected, and driving gear 117 is fixedly installed on the output shaft of speed reducer.Motor and speed reducer is mounted on
The inside of steering gear flat 102.Motor can be servo motor.When driven gear 118 and drive shaft 105 are locked by latch assembly
When, motor outputs power to speed reducer, and speed reducer imparts power to driving gear 117 again, and driving gear 117 drives passively
Gear 118 rotates, and drive shaft 105 is rotated with driven gear 118, to realize that drive shaft 105 drives the rudder wing around drive shaft 105 again
Axis rotation, complete the rudder wing swing work functions.It should be noted that central angle corresponding to toothed region 121 can be
180°.In the state of motor no power, driving gear 117 not can rotate, and driven gear 118 will not rotate.
Shown in Figure 1, in the optional scheme of the embodiment, runner assembly further includes the second torsional elastomer, for making
Drive shaft 105 is rotated around the axis of itself.It can realize that the rudder wing lifted rotates automatically, by the second torsional elastomer in order to reality
The aerofoil of the existing rudder wing is parallel with the axis of steering gear flat 102.
Specifically, the second torsional elastomer is torsionspring 123, one end of torsionspring 123 is embedded in drive shaft 105,
The other end of torsionspring 123 is embedded in driven gear 118.It should be noted that runner assembly can save in the embodiment
Driving device 116, driving gear 117 and driven gear 118, to realize lifting and rotating around the axis of drive shaft 105 for the rudder wing,
At this point, one end of torsionspring 123 is embedded in drive shaft 105, the other end of torsionspring 123 is embedded in steering gear flat 102, i.e. torsion bullet
The other end of spring 123 is embedded in installation base 108.
In the optional scheme of the embodiment, latch assembly includes holddown spring 124 and locating piece；The surface of drive shaft 105
Offer locating slot；Mounting hole 128 is offered on the hole wall of the axle hole of driven gear 118, holddown spring 124 and locating piece are equal
It is installed in mounting hole；Holddown spring 124 is used in 105 rotation process of drive shaft, position and mounting hole when locating slot
When position is opposite, it is inserted into locating piece in locating slot.
Referring to shown in Fig. 8 and Fig. 9, specifically, mounting hole is located at the smooth surface portion 122 of driven gear 118；Locating piece is fixed
Position steel ball 125；Spring jackscrew 126 is also equipped in mounting hole, spring is between locating piece and spring jackscrew 126, spring top
Silk 126 is threadedly coupled with mounting hole, by the adjustable spring of spring jackscrew 126 to the elastic force of positioning ball 125.
The utility model embodiment additionally provides a kind of rudder wingfold method, which includes: on steering gear flat 102
Open up the binding face matched with the aerofoil of the rudder wing；Runner assembly is installed on steering gear flat 102, and by the rudder wing and steering gear flat 102
It is flexibly connected, then component is lifted in installation between the rudder wing and runner assembly, makes the aerofoil of the rudder wing from being affixed by lifting component
State becomes upright state, and rotates the rudder wing lifted by runner assembly.The rudder wingfold method uses the rudder wing
Folding device realizes the folding of the rudder wing.
In the utility model embodiment, the working principle of rudder wingfold device are as follows:
Rudder wingfold device is connected with the body of guided missile, the rudder wing is become into folded state from unfolded state: making the rudder wing
Axis after being rotated by 90 ° together with drive shaft 105, then by the rudder wing around pin shaft 106 rotates, and makes rudder wingfold, the aerofoil of the rudder wing is just
It can be affixed (shown in Figure 3) with the surface of steering gear flat 102, can be integrally put into guided missile in launching tube at this time, guided missile exists
When in launching tube, under the action of placing side by side the elastic force of double torsion spring 115, the wing of the rudder wing is slightly abutted against with the inner tube wall of launching tube.
After guided missile projects launching tube, for the barrel of launching tube to the constraint release of the rudder wing, being acted on using the elastic force for placing side by side double torsion spring makes rudder
The wing will be unfolded axial, even if the rudder wing is rotated around the axis of pin shaft, utilize the twisting force of torsionspring, drive shaft drives the rudder wing
In radial rotary, after being rotated by 90 °, in the locating slot of the positioning ball insertion drive shaft on driven gear, the rudder wing is all deployed into
Position.When making servo motor work, the rudder wing can be made the flight attitude of guided missile will to be adjusted in working condition is swung.
In conclusion rudder wingfold device provided by the embodiment of the utility model, the rudder wing can be put down along the axial direction of body
The formula of lying is folded in body outer surface, and consistent with diameter of the projectile body after folding, space hold is small, to the sealing protection of body without unfavorable shadow
Ring, after guided missile projects launching tube, the rudder wing can rapid Automatic-expanding under the action of the spring, motor control guided missile can be passed through after expansion
Flight attitude.The utility model has no adverse effect to the sealing protection of body, and the inside that can greatly improve steering gear flat 102 is empty
Between utilization rate, while the space of saving is used for warhead or engine, the explosion power or flying distance of guided missile can be improved.
Embodiment two
The utility model embodiment two provides a kind of micro missile, the rudder wingfold device provided including embodiment one.
Micro missile further includes body, and body is fixedly connected with the head end 103 of the steering gear flat 102 of rudder wingfold device.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should
Understand: it is still possible to modify the technical solutions described in the foregoing embodiments, or to some or all of
Technical characteristic is equivalently replaced；And these are modified or replaceed, it does not separate the essence of the corresponding technical solution, and this is practical new
The range of each embodiment technical solution of type.In the instructions provided here, numerous specific details are set forth.However, can
Understand, the embodiments of the present invention can be practiced without these specific details.In some instances, not in detail
Carefully show well-known methods, structures and techniques, so as not to obscure the understanding of this specification.In addition, those skilled in the art
It is understood that although certain features included by some embodiments described herein include other embodiments rather than other spies
Sign, but the combination of the feature of different embodiments means within the scope of the utility model and forms different implementation
Example.For example, in the following claims, the one of any of embodiment claimed can side in any combination
Formula come using.
Claims (10)
1. a kind of rudder wingfold device, which is characterized in that including the rudder wing, steering gear flat, lift component and runner assembly, the rotation
Component is installed on the steering gear flat, and the rudder wing is flexibly connected with the runner assembly；It is described lift component be installed on it is described
Between the rudder wing and the runner assembly；The aerofoil of the rudder wing can be affixed with the surface of the steering gear flat；It is described to lift component
For lifting the rudder wing, so that the aerofoil of the rudder wing becomes upright state from the state of being affixed；The runner assembly is used for
Rotate the rudder wing lifted.
2. rudder wingfold device according to claim 1, which is characterized in that the quantity of the rudder wing is multiple and multiple
The rudder wing is uniformly distributed along the outer peripheral surface of the steering gear flat；
The runner assembly includes drive shaft, hinged by pin shaft between the rudder wing and the drive shaft, and the pin shaft
The axis perpendicular of axis and the drive shaft；The drive shaft and the steering gear flat are rotatablely connected.
3. rudder wingfold device according to claim 2, which is characterized in that the component that lifts includes first elasticity of torsion
Part, and first torsional elastomer is installed between the rudder wing and the drive shaft.
4. rudder wingfold device according to claim 2, which is characterized in that one end of the drive shaft and the steering gear flat
Between connected by bearing, the other end of the drive shaft is provided with free bearing, and the root of the rudder wing and the free bearing pass through institute
Pin shaft is stated to be connected；There is rotary spacing portion between two sub- ears of the free bearing, lift angle for limit the rudder wing.
5. the rudder wingfold device according to any one of claim 2-4, which is characterized in that the runner assembly further includes
Second torsional elastomer, for rotating the drive shaft around the axis of itself.
6. rudder wingfold device according to claim 5, which is characterized in that the runner assembly further include driving device,
Driving gear and driven gear, the driving device is for driving the driving gear to rotate, the driving gear and the quilt
Moving gear is meshed；The driven gear is sheathed in the drive shaft, and is set between the driven gear and the drive shaft
It is equipped with latch assembly, it is opposing stationary for making to be able to maintain between the driven gear and the drive shaft；The driving device
It is fixed on the steering gear flat, second torsional elastomer is installed between the drive shaft and the driven gear.
7. rudder wingfold device according to claim 6, which is characterized in that the latch assembly includes holddown spring and determines
Position part；The surface of the drive shaft offers locating slot；Mounting hole, institute are offered on the hole wall of the axle hole of the driven gear
It states holddown spring and the locating piece is mounted in the mounting hole；The holddown spring is used in the drive shaft turns mistake
Cheng Zhong makes the locating piece be inserted into the positioning when the position of the locating slot is opposite with the position of the mounting hole
In slot.
8. rudder wingfold device according to claim 3, which is characterized in that the first torsional elastomer is to place side by side double torsion bullets
Spring, the midfoot support for placing side by side double torsion spring on the aerofoil of the rudder wing, the both ends for placing side by side double torsion spring respectively with
It is embedded in the drive shaft.
9. rudder wingfold device according to claim 6, which is characterized in that second torsional elastomer is torsion bullet
Spring, one end of the torsionspring are embedded in the drive shaft, and the other end of the torsionspring is embedded in the driven gear.
10. a kind of micro missile, which is characterized in that including rudder wingfold device as claimed in any one of claims 1-9 wherein.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821179085.4U CN208671815U (en) | 2018-07-24 | 2018-07-24 | Rudder wingfold device and micro missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821179085.4U CN208671815U (en) | 2018-07-24 | 2018-07-24 | Rudder wingfold device and micro missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208671815U true CN208671815U (en) | 2019-03-29 |
Family
ID=65829712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821179085.4U Active CN208671815U (en) | 2018-07-24 | 2018-07-24 | Rudder wingfold device and micro missile |
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| Country | Link |
|---|---|
| CN (1) | CN208671815U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109000521A (en) * | 2018-07-24 | 2018-12-14 | 湖北泰和电气有限公司 | Rudder wingfold device, micro missile and rudder wingfold method |
-
2018
- 2018-07-24 CN CN201821179085.4U patent/CN208671815U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109000521A (en) * | 2018-07-24 | 2018-12-14 | 湖北泰和电气有限公司 | Rudder wingfold device, micro missile and rudder wingfold method |
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