CN110260726A - A kind of grid rudder arrangement - Google Patents
A kind of grid rudder arrangement Download PDFInfo
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- CN110260726A CN110260726A CN201910452278.5A CN201910452278A CN110260726A CN 110260726 A CN110260726 A CN 110260726A CN 201910452278 A CN201910452278 A CN 201910452278A CN 110260726 A CN110260726 A CN 110260726A
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- rudder
- blade
- root
- frame
- groove
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/143—Lattice or grid fins
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a kind of grid rudder rudder-face devices, comprising: rudder face structure and locking-unlocking device；Wherein, rudder face structure is connected with locking-unlocking device；Rudder face structure includes the first rudder root, the second rudder root, rudder frame, several blades；Wherein, the first rudder root, the second rudder root are connected with rudder frame respectively, also, rudder frame is divided into first area, second area and third region by the first rudder root and the second rudder root；Several blades are set to first area, second area and third region.The present invention takes structure initial interpolation carrying, welds the scheme of auxiliary positioning, and pin removal pin shaft is inserted into flexural pivot hole scheme, has the advantages of reliable and stable load-carrying properties and deformation-compensated ability.
Description
Technical field
The invention belongs to the sub grade technical field of carrier rocket one more particularly to a kind of grid rudder arrangements.
Background technique
Currently, being widely used to guided missile, airship, delivery fire based on molding grid rudder rudder faces of modes such as welding, castings
The flight such as sub- grade of arrow one or gesture stability when returning, however founding method is integrally formed, high reliablity but production cost is higher.
In face of the competition of space launching market high quality, low cost, sheet metal welding scheme is at low cost, but it is steady to be limited to welding procedure
The reliable welding quality assessment of the factors such as qualitative and undetectability, welding scheme is welded by small exemplar dependent on same batch
Card, cannot directly evaluate, and there are certain risks in model application.
In addition, in the locking unlock scheme based on pin removal, in the case where considering the factors such as processing, assembly, loaded deformation, to protect
Demonstrate,prove pin removal pin shaft and be inserted into institute's locking structure hole, generally hole axle fit clearance is put it is sufficiently large, it is inclined to compensate assembly at this
Difference, thus pin removal pin shaft is only that line contacts with structure hole contact surface, is easy to cause in vibration environment, structure is because of hole shaft clearance
And cause unnecessary vibration, causing pin removal pin shaft to be caused by the extruding of structure hole part, friction, pin shaft is worn or structure is excessive
Dynamic response, eventually affect the normal work of infrastructure product and pin removal.
Currently, existing rudder face patent, to its monnolithic case section, there are right sound ropes, but to each plate of rudder face structure
Grafting scheme do not refer to.Pin removal pin shaft limit scheme there are no the improvement project for the defect.
Summary of the invention
Technical problem solved by the present invention is having overcome the deficiencies of the prior art and provide a kind of grid rudder arrangement, knot is taken
The initial interpolation carrying of structure, welds the scheme of auxiliary positioning, pin removal pin shaft is inserted into flexural pivot hole scheme, and having load-carrying properties stabilization can
The advantages of by with deformation-compensated ability.
The object of the invention is achieved by the following technical programs: a kind of grid rudder arrangement, comprising: rudder face structure and locking
Tripper；Wherein, the rudder face structure is connected with the locking-unlocking device；The rudder face structure include the first rudder root,
Second rudder root, rudder frame, several blades；Wherein, the first rudder root, the second rudder root are connected with the rudder frame respectively,
Also, the rudder frame is divided into first area, second area and third region by the first rudder root and the second rudder root；It is several
A blade is set to first area, second area and third region；Wherein, several blade staggers connect to form grid；Blade
At rudder frame link position, the interior sidewall surface of rudder frame offers several the first U-shaped half logical grooves, the blade being connected with rudder frame
It is inserted in the first U-shaped half logical groove；At blade and the first rudder root link position, it is second U-shaped half logical that the first rudder root is equipped with several
Groove, the blade being connected with the first rudder root are inserted in the second U-shaped half logical groove；At blade and the second rudder root link position, the
Two rudder roots are equipped with the logical groove of several thirds U-shaped half, and the blade being connected with the second rudder root is inserted in the logical groove of third U-shaped half；
At blade and blade stagger link position, what a blade offered 1/2 height in crossover location short transverse first U-shaped is lacked
Mouthful, another blade offers the second U-shaped notch of 1/2 height, the first U-shaped notch and second in crossover location short transverse
U-shaped notch interconnection.
In above-mentioned grid rudder arrangement, the rudder frame includes the first rudder frame in, the second rudder frame, third rudder frame side, the 4th rudder
Frame is in, five rudder frame and the 6th rudder frame side；Wherein, the first rudder frame in, the second rudder frame, third rudder frame in, four rudder frame,
5th rudder frame while and when six rudder frames be sequentially connected and connect；Wherein, one end of the second rudder root is connected to the first rudder frame Bian Yu
At the link position on two rudder frame sides, the other end of the second rudder root is inserted in the first U-shaped groove that the 4th rudder frame side opens up；Institute
The one end for stating the first rudder root is connected to the first rudder frame at link position while with six rudder frames, the other end of the first rudder root
It is inserted in the second U-shaped groove that the 4th rudder frame side opens up.
In above-mentioned grid rudder arrangement, further includes: the first pinboard and the second pinboard；Wherein, the first pinboard is set to
On blade；Second pinboard is set on blade and rudder frame.
In above-mentioned grid rudder arrangement, several blades are cross-linked to form grid in 90 °.
In above-mentioned grid rudder arrangement, the locking-unlocking device includes bracket, pin removal and regulating arm；Wherein, the tune
Joint arm is connected with the rudder frame；The pin removal is connected with the regulating arm；The bracket is connected with the pin removal.
In above-mentioned grid rudder arrangement, the regulating arm includes adjustable plate, lid and bulb；Wherein, one end of the adjustable plate
It is connected by hinged bolts with the rudder frame, the other end of the adjustable plate is provided with ball-and-socket；The bulb is set to institute
It states in ball-and-socket；It states bulb and is connected with the adjustable plate in the housing residence；In the pin shaft of the pin removal and the bulb
The through-hole in portion is clearance fit.
In above-mentioned grid rudder arrangement, the inner surface and the outer surface of the rudder face structure is concentric circle arc plane, the circle of inner surface
The diameter of cambered surface is greater than aircraft rocket body diameter 200mm or more.
In above-mentioned grid rudder arrangement, the blade being connected with rudder frame inserts in the first U-shaped half logical groove and welds；With the first rudder
The blade that root is connected inserts in the second U-shaped half logical groove and welds；It is logical that the blade being connected with the second rudder root inserts in third U-shaped half
Groove simultaneously welds；First U-shaped notch intersects and welds with the second U-shaped notch.
In above-mentioned grid rudder arrangement, first pinboard offers partial groove, is inserted in blade by partial groove,
Lifting surface load is carried by groove structure on two sides, carrying resistance area load is squeezed by bottom portion of groove contact surface.
In above-mentioned grid rudder arrangement, second pinboard offers partial groove, is inserted in blade by partial groove
And rudder frame, lifting surface load is carried by groove structure on two sides, carrying resistance area load is squeezed by bottom portion of groove contact surface.
Compared with prior art, the present invention has the following advantages:
1) rudder face structure of the invention itself carries, and for weld seam only as backup, reliability is higher.The grid rudder rudder face knot
The connection scheme of structure makes the blade, rudder root, the interstructural load of rudder frame pass through the structural bearing being inserted into mutually, welds only conduct
Auxiliary positioning and redundancy carry measure.The 100% structural material self performance that can be used that structure squeezes load-carrying properties participates in carrying,
And traditional scheme for being completely dependent on welding and realizing carrying, welding performance are generally less than the 80% of base material performance, consider that welding lacks
Fall into, weld seam such as can not detect at the factors, in addition, grid rudder structure is as easily led to moderate finite deformation using needing thin plate intensively to weld, into
One step reduces welding quality, and base material performance is used only in commissure when engineer application 50% carries out strength check, load-carrying efficiency
Far below the technical solution of the rudder face structure.
2) rudder face structure interpolation scheme carrying high reliablity of the invention, at low cost.The groove that each components are inserted into mutually
Position is guaranteed that each spare part interpolation molding uniquely determines the position of each spare part, the rudder face structure monnolithic case by machining
It can determine, positioned without tooling of additionally going into operation, reduce production cost and lead time；
3) after rudder face structure interpolation scheme of the invention is easier to ensure that welding quality, each spare part structure are inserted into mutually,
The fit clearance of thickness direction is easy to guarantee to smaller value, and mating surface has certain depth, to the length of components more rambunctious
It is low to spend tolerance.The welding deformation amount of preceding working procedure is less than the insertion depth, and does not interfere with the cooperation on thickness direction
Gap.The binding face length and the gap that can effectively ensure that welding pre-structure at welding groove port may be selected in welding position, it is easier to
Guarantee welding quality.The rudder face organization plan is avoided using in traditional rudder face components end face butt welding scheme, and preceding road welds
Connect process deformation after cause subsequent structural interface offset it is larger and influence welding quality even can not welding fabrication the case where.
4) assembly convenient degree and assembling quality can be improved in flexural pivot device of the invention: the flexural pivot device of the regulating arm can be mended
The rudder face structure is repaid because of the pin removal pin shaft caused by the reasons such as welding deformation or assembling deviation and adjusts arm aperture difference axis,
Convenient for assembly, and guarantee the local additional load that the pin removal pin shaft causes without forced assembly, influences pin removal work.Separately
Outside, because flexural pivot compensation solve the problems, such as peg-in-hole assembly, avoid traditional simple hole diameter enlargement (hole axle unilateral gap 1~
Scheme 2mm), it is ensured that shaft hole matching precision is high, gap is small (0.025~0.05mm of hole axle unilateral gap), improves connection
Rigidity avoids the oscillating load flowering structure vibration under wide arc gap and hits, and the pin shaft therefore caused damages, structure dynamics
Respond the risk factors such as excessive.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the grid rudder arrangement convex side schematic diagram of the embodiment of the present invention；
Fig. 2 grid rudder rudder face loading direction-resistance area load；
Fig. 3 grid rudder rudder face loading direction-lifting surface load；
Fig. 4 is the grid rudder rudder face structure concave side schematic diagram of the embodiment of the present invention；
Fig. 5 is part (rudder frame-blade) amplification decomposition figure at the A of described Fig. 4；
Fig. 6 is part (pinboard-rudder frame-blade) amplification decomposition figure at the B of described Fig. 4；
Fig. 7 is part (blade-blade) amplification decomposition figure at the C of described Fig. 4；
Blade the-the first rudder root partial enlargement exploded view of the described Fig. 4 of Fig. 8 (a)；
(the-the second rudder of blade root) partial enlargement exploded view at the D of the described Fig. 4 of Fig. 8 (b)；
Fig. 9 is cross-sectional view at the locking-unlocking device of the embodiment of the present invention.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.It should be noted that in the absence of conflict, embodiment in the present invention and
Feature in embodiment can be combined with each other.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the grid rudder arrangement convex side schematic diagram of the embodiment of the present invention.As shown in Figure 1, the grid rudder arrangement includes:
Rudder face structure 1 and locking-unlocking device 2.Wherein,
Rudder face structure 1 is connected with locking-unlocking device 2；
The rudder face structure 1 includes the first rudder root 1011, the second rudder root 1012, rudder frame 102, several blades；
The first rudder root 1011, the second rudder root 1012 are connected with the rudder frame 102 respectively, also, described
The rudder frame 102 is divided into first area, second area and third region by one rudder root 1011 and the second rudder root 1012；
Several blades are set to first area, second area and third region；Wherein, several blade staggers connect shape
At grid；At blade and 102 link position of rudder frame, the interior sidewall surface of rudder frame 102 offers several the first U-shaped half logical grooves
1021 (as shown in Figure 5), the blade being connected with rudder frame 102 are inserted in the first U-shaped half logical groove 1021；Blade and the first rudder root
At 1011 link positions, the first rudder root 1011 is equipped with several the second U-shaped half logical grooves 10111 (shown in such as Fig. 8 (a))), with the
The blade that one rudder root 1011 is connected is inserted in the second U-shaped half logical groove 10111；1012 link position of blade and the second rudder root
Place, the second rudder root 1012 are equipped with the logical groove 10121 (shown in such as Fig. 8 (b)) of several thirds U-shaped half), with 1012 phase of the second rudder root
The blade of connection is inserted in the logical groove 10121 of third U-shaped half；At blade and blade stagger link position, a blade is intersecting
The first U-shaped notch 300 of 1/2 height is offered on position height direction, another blade is opened in crossover location short transverse
The second U-shaped notch 400 equipped with 1/2 height, the first U-shaped notch 300 and the second U-shaped 400 interconnection of notch.
Specifically, several blades include several first blades 103, several second blades 104, several third leaves
Piece 105, several quaterfoils 106, several the 5th blades 107, several the 6th blades 108, the 7th blade the 1031, the 8th
Blade 1081；Wherein,
Several first blades 103, several second blades 104 and the 7th blade 1031 are all set in first area, the
The both ends of seven blades 1031 are connected with rudder frame 102, several first blades 103 and several second blades 104 intersect company
Connect to form grid, one end of each first blade 103 is connected with the first rudder root 1011, each first blade 103 it is another
One end is connected with the rudder frame 102, and one end of each second blade 104 is connected with the first rudder root 1011, Mei Ge
The other end of two blades 104 is connected with the rudder frame 102；Wherein, the interior sidewall surface of rudder frame 102 offers several the first U
The logical groove of type half, the first rudder root 1011 offer several the second U-shaped half logical grooves (and the boss at 5 that is equally spaced, boss
It is provided with U-shaped half logical groove at 3 or 4 in two side walls, only runs through in height in intrados side), the two of the 7th blade 1031
End is inserted in the corresponding first U-shaped half logical groove, and it is U-shaped that one end of each first blade 103 is inserted in corresponding second
Half logical groove, the other end of each first blade 103 are inserted in the corresponding first U-shaped half logical groove, each second blade 104
One end be inserted in the corresponding second U-shaped half logical groove, the other end of each second blade 104 is inserted in corresponding first
U-shaped half logical groove；
Several third blades 105 and several quaterfoils 106 are all set in second area, several third blades
105 form grid with several 106 interconnections of quaterfoil；
Several quaterfoils 106, several the 5th blades 107 and the 8th blade 1081 are all set in third region, the
The both ends of eight blades 1081 are connected with rudder frame 102, several quaterfoils 106 and several the 5th blades 107 intersect company
Connect to form grid, one end of each quaterfoil 106 is connected with the first rudder root 1011, each quaterfoil 106 it is another
One end is connected with the rudder frame 102, and one end of each 5th blade 107 is connected with the first rudder root 1011, Mei Ge
The other end of five blades 107 is connected with the rudder frame 102.
As shown in Figure 1, the rudder frame 102 include the first rudder frame in 1021, the second rudder frame 1022, third rudder frame side 1023,
4th rudder frame is in 1024, five rudder frame 1025 and the 6th rudder frame side 1026；Wherein, the first rudder frame is in 1021, the second rudder frame
1022, third rudder frame 1026 is sequentially connected and is connect while the 1024, the 5th rudder frame is in 1025 and six rudder frames in 1023, four rudder frame；
Wherein,
One end of the first rudder root 1011 be connected to the first rudder frame at 1021 and the second rudder frame 1022 link position
Place, the other end of the first rudder root 1011 are inserted in the 4th rudder frame side 1024 opens up first U-shaped groove 10241；
One end of the second rudder root 1012 be connected to the first rudder frame at 1021 and six rudder frames 1026 link position
Place, the other end of the second rudder root 1012 are inserted in the 4th rudder frame side 1024 opens up second U-shaped groove 10242.
As shown in Figure 1, the device further include: the first pinboard 1091 and the second pinboard 1092；Wherein, the first pinboard
1091 are set on blade；Second pinboard 1092 is set on blade and rudder frame 102.
First pinboard 1091 offers partial groove, is inserted in blade 105 and blade 106 by partial groove, passes through
Groove structure on two sides carries lifting surface load, squeezes carrying resistance area load by bottom portion of groove contact surface.
Second pinboard 1092 offers partial groove, is inserted in blade 105, blade 106 and first by partial groove
Rudder frame side 1021 carries lifting surface load by groove structure on two sides, squeezes carrying resistance area by bottom portion of groove contact surface and carries
Lotus.
Embodiment 1
The present invention provides a kind of grid rudder arrangements, as shown in Figure 1, including rudder face structure 1 and locking-unlocking device 2.
The rudder face structure 1 includes: the first rudder root 1011, the second rudder root 1012, rudder frame 102, the first blade 103, second
Blade 104, third blade 105, quaterfoil 106, the 5th blade 107, the 6th blade 108, pinboard 109.The rudder root
101, ± 45 ° of U-shaped half logical grooves, mutually insertion positioning are designed between rudder frame 102, blade 103~108,109 junction of pinboard
Afterwards, integral solder forms, as shown in Figure 1；The load of the rudder face structural bearing be lifting surface, resistance area load two large divisions,
As shown in Figure 2, Figure 3, Figure 4；
The rudder root 101 is section thickness grading structure, relatively thin close to locking device side, thicker close to splined hole side, and
Be equally spaced boss at 5, ± 45 ° of U-shaped half logical grooves is provided at 3 or 4 in boss two side walls, in height only in intrados
Side is run through, as shown in Figure 8.Rudder root improves pneumatic efficiency in resistance area side end face rounded corner, and resistance is washed away in reduction；
At 102 interior sidewall surface of rudder frame and blade cooperation, ± 45 ° of U-shaped half logical grooves are equidistantly provided with, are only existed in height
Inner arc surface side is run through, as shown in Figure 5.2 articulation holes are provided in the middle part of the 202 side rudder frame of pin removal, pass through 2 articulation holes
Bolt fastener is connect with the adjustable plate 20301 of the regulating arm 203；
First blade 103, the second blade 104, third blade 105, quaterfoil 106, the 5th blade the 107, the 6th
There is local crowning structure in 108 both ends of blade, the rudder root is inserted into partial blade one end, and the other end is inserted into rudder frame groove,
Partial blade both ends are inserted into 101 groove of rudder root.Lifting surface is carried by the mating surface in inserting paragraph short transverse to carry
Lotus carries resistance area load by the step surface on thickness direction, the dependence to weld seam carrying is greatly lowered, such as Fig. 5, Fig. 8
It is shown；
Between first blade 103 and the second blade 104, between third blade 105 and quaterfoil 106, the 5th leaf
It is in 90 ° of arrangements that intersect between piece 107 and the 6th blade 108, the U-shaped of 1/2 height is respectively opened in crossover location short transverse and is lacked
Mouthful, blade does not interrupt to keep continuous, lifting surface load is carried by the mating surface of inserting paragraph short transverse, by thickness side
Resistance area load is carried to notched bottoms mating surface, the dependence to weld seam carrying is greatly lowered, as shown in Figure 7；
It totally 4 pieces of the pinboard 109, is respectively provided with that there are partial grooves, is inserted into the blade 105,106 and rudder frame respectively
102, lifting surface load is carried by groove structure on two sides, carrying resistance area load is squeezed by bottom portion of groove contact surface, substantially
Degree reduces the dependence carried to weld seam, as shown in Figure 6.It is provided with 1 articulation through-hole on 4 pieces of pinboards 109, with outside
Driving mechanism is unfolded and passes through the connection carrying of articulation bolt fastener；
Local boss is arranged at pin removal end in the rudder root 101, is inserted into the rectangular opening that the rudder frame 102 is arranged, such as Fig. 3
It is shown, by the mating surface in boss and hole squeeze carrying lifting surface, resistance area load, be greatly lowered to weld seam carrying according to
Rely；
In the spline nose end of the rudder root 101, local boss is arranged in the rudder frame 102, is inserted into the rudder root 101 in root
In U-shaped half logical groove of rectangular boss, lifting surface load is carried by inserting paragraph short transverse mating surface, passes through thickness direction platform
Rank compressive plane carries resistance area load, and the dependence to weld seam carrying is greatly lowered, and carrying form is similar to Figure 6；
The groove location that each components of the rudder face structure 1 are inserted into mutually by machining guarantee, each spare part interpolation at
The position of each spare part is uniquely determined after type, the rudder face structure monnolithic case can determine, without increasing additional assembly
D type tooling is positioned, and production cost and lead time are reduced.
After the 1 interpolation scheme of rudder face structure is easier to ensure that welding quality, each spare part structure are inserted into mutually, thickness side
To fit clearance be easy to guarantee to smaller value, and mating surface has certain depth, to the length tolerance of components more rambunctious
It is required that low.The welding deformation amount of preceding working procedure is less than the insertion depth, and does not interfere with the fit clearance on thickness direction.Weldering
Connecing position may be selected the binding face length and the gap that can effectively ensure that welding pre-structure at welding groove port, it is easier to guarantee weldering
Connect quality.The rudder face organization plan, which avoids, to be used in traditional rudder face components end face butt welding scheme, preceding road welding sequence
Cause after deformation subsequent structural interface offset it is larger and influence welding quality even can not welding fabrication the case where.
Preferably, the blade tip is processed into round end, the rudder face, rudder root root of notch be processed into circular hole, avoid
Elongated hole root generates stress and concentrates.
Preferably, the blade of -45 ° of first blade 103, the second blade 105, third blade 107 etc. arrangements can combine
At 1 group of blade, the blade of 45 ° of second blade 104, quaterfoil 106, the 6th blade 108 etc. arrangements is combined into 1 group of company
Continuous blade, is not interrupted crossing at the rudder root 101, but by 4 groups of U-shaped grooves of 101 boss of rudder root in thickness direction
Upper connection, further increases load-carrying efficiency；
Preferably, the high temperature such as the preferable titanium alloy material of high-temperature behavior or GH4169 may be selected in 1 material of rudder face structure
Alloy；
Preferably, 1 surfaces externally and internally of rudder face structure is concentric circle arc plane, and it is straight that intrados diameter is greater than aircraft rocket body
Diameter 200mm or more guarantees that the installation space of the locking-unlocking device 2 is sufficient；
Preferably, the sprayable heat insulation material in 1 surface of rudder face structure；
The locking-unlocking device 2 includes: bracket 201, pin removal 202 and regulating arm 203, wherein the regulating arm 203
It is connected with the rudder frame 102；The pin removal 202 is connected with the regulating arm 203；The bracket 201 is pulled pin with described
Device 202 is connected.Regulating arm 203 includes adjustable plate 20301, lid 20302 and bulb 20303；Wherein, the adjustable plate 20301
One end be connected with the rudder frame 102 by hinged bolts, the other end of the adjustable plate 20301 is provided with ball-and-socket；Institute
Bulb 20303 is stated to be set in the ball-and-socket；The lid 20302 cover the bulb 20303 and with 20301 phase of adjustable plate
Connection；The through-hole at 20303 middle part of the pin shaft of the pin removal 202 and the bulb is clearance fit.The pin removal 202 is fire
The through-hole of work acting device, 20303 middle part of pin shaft and the bulb is clearance fit.Described 20301 one end of adjustable plate passes through 2
A hinged bolts are connect with rudder face structure, and ball-and-socket and 4 threaded holes are arranged in one end.Ball-and-socket and 4 spiral shells are arranged in the lid 20302
The bulb 20303 is pressed together on adjustable plate by keyhole by 4 fasteners, forms flexural pivot device, as shown in Figure 9.The flexural pivot
Device can compensate for the rudder face structure 1 because of 202 pin shaft of pin removal caused by the reasons such as welding deformation or assembling deviation and adjust
Joint arm hole is not coaxial, convenient for assembly, and guarantees the local additional load that 202 pin shaft of pin removal causes without forced assembly,
Influence pin removal work.In addition, avoiding traditional simple hole diameter enlargement because flexural pivot compensation solves the problems, such as peg-in-hole assembly
The scheme of (1~2mm of hole axle unilateral gap), it is ensured that shaft hole matching precision is high, gap it is small (hole axle unilateral gap 0.025~
0.05mm), coupling stiffness is improved, the oscillating load flowering structure vibration under wide arc gap is avoided and is hit, and is therefore caused
Pin shaft damage, the risk factors such as structure dynamic response is excessive.
Preferably, the high temperature such as the preferable titanium alloy material of high-temperature behavior or GH4169 may be selected in 1 material of rudder face structure
Alloy；
Preferably, the pin pulling out device can arrange the thermal protection before radome fairing is worked on the outside；
Preferably, the bolt hole that the bracket 201 is connect with aircraft rocket body is waist-shaped hole；
After grid rudder arrangement is assembled on aircraft rocket body, the bracket 201 of the locking-unlocking device 2 passes through spiral shell
Bolt fastener is connect with rocket body, by 1 closed-lock of rudder face structure in rocket body outer surface, keeps positive lock in inflight phase,
In aircraft return phase, the pin removal 202 works, and causes movement of pulling pin, pin shaft is pulled out out of the regulating arm 203 hole
It removes, the rudder face structure 1 unlocks, and locks after being expanded to certain angle under the action of external expansion driving mechanism, bears to return
Section air-flow washes away, and forms lifting surface load and resistance area load, and rudder face structure starts to complete its bearing function.
The rudder face structure of the present embodiment itself carrying, for weld seam only as backup, reliability is higher.The grid rudder rudder face knot
The connection scheme of structure makes the blade, rudder root, the interstructural load of rudder frame pass through the structural bearing being inserted into mutually, welds only conduct
Auxiliary positioning and redundancy carry measure.The 100% structural material self performance that can be used that structure squeezes load-carrying properties participates in carrying,
And traditional scheme for being completely dependent on welding and realizing carrying, welding performance are generally less than the 80% of base material performance, consider that welding lacks
Fall into, weld seam such as can not detect at the factors, in addition, grid rudder structure is as easily led to moderate finite deformation using needing thin plate intensively to weld, into
One step reduces welding quality, and base material performance is used only in commissure when engineer application 50% carries out strength check, load-carrying efficiency
Far below the technical solution of the rudder face structure.
The rudder face structure interpolation scheme carrying high reliablity, at low cost of the present embodiment.The groove that each components are inserted into mutually
Position is guaranteed that each spare part interpolation molding uniquely determines the position of each spare part, the rudder face structure monnolithic case by machining
It can determine, positioned without tooling of additionally going into operation, reduce production cost and lead time；
After the rudder face structure interpolation scheme of the present embodiment is easier to ensure that welding quality, each spare part structure are inserted into mutually,
The fit clearance of thickness direction is easy to guarantee to smaller value, and mating surface has certain depth, to the length of components more rambunctious
It is low to spend tolerance.The welding deformation amount of preceding working procedure is less than the insertion depth, and does not interfere with the cooperation on thickness direction
Gap.The binding face length and the gap that can effectively ensure that welding pre-structure at welding groove port may be selected in welding position, it is easier to
Guarantee welding quality.The rudder face organization plan is avoided using in traditional rudder face components end face butt welding scheme, and preceding road welds
Connect process deformation after cause subsequent structural interface offset it is larger and influence welding quality even can not welding fabrication the case where.
Assembly convenient degree and assembling quality can be improved in the flexural pivot device of the present embodiment: the flexural pivot device of the regulating arm can be mended
The rudder face structure is repaid because of the pin removal pin shaft caused by the reasons such as welding deformation or assembling deviation and adjusts arm aperture difference axis,
Convenient for assembly, and guarantee the local additional load that the pin removal pin shaft causes without forced assembly, influences pin removal work.Separately
Outside, because flexural pivot compensation solve the problems, such as peg-in-hole assembly, avoid traditional simple hole diameter enlargement (hole axle unilateral gap 1~
Scheme 2mm), it is ensured that shaft hole matching precision is high, gap is small (0.025~0.05mm of hole axle unilateral gap), improves connection
Rigidity avoids the oscillating load flowering structure vibration under wide arc gap and hits, and the pin shaft therefore caused damages, structure dynamics
Respond the risk factors such as excessive.
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.
Claims (10)
1. a kind of grid rudder arrangement, characterized by comprising: rudder face structure (1) and locking-unlocking device (2)；Wherein,
The rudder face structure (1) is connected with the locking-unlocking device (2)；
The rudder face structure (1) includes the first rudder root (1011), the second rudder root (1012), rudder frame (102), several blades；Its
In,
The first rudder root (1011), the second rudder root (1012) are connected with the rudder frame (102) respectively, also, described
The rudder frame (102) is divided into first area, second area and third by the first rudder root (1011) and the second rudder root (1012)
Region；
Several blades are set to first area, second area and third region；Wherein, several blade staggers connect to form net
Lattice；At blade and rudder frame (102) link position, the interior sidewall surface of rudder frame (102) offers several the first U-shaped half logical grooves
(1021), the blade being connected with rudder frame (102) is inserted in the first U-shaped half logical groove (1021)；Blade and the first rudder root
(1011) at link position, the first rudder root (1011) is equipped with several the second U-shaped half logical groove (10111), with the first rudder root
(1011) blade being connected is inserted in the second U-shaped half logical groove (10111)；Blade and second rudder root (1012) link position
Place, the second rudder root (1012) are equipped with U-shaped half logical groove (10121) of several thirds, the leaf being connected with the second rudder root (1012)
Piece is inserted in U-shaped half logical groove (10121) of third；At blade and blade stagger link position, a blade is in crossover location height
The first U-shaped notch (300) of 1/2 height is offered on degree direction, another blade offers in crossover location short transverse
The U-shaped notch of the second of 1/2 height (400), the first U-shaped notch (300) and the second U-shaped notch (400) interconnection.
2. grid rudder arrangement according to claim 1, it is characterised in that: the rudder frame (102) includes the first rudder frame side
(1021), the second rudder frame while at (1022), third rudder frame, (1023), the 4th rudder frame are in (1024), five rudder frames (1025) and
6th rudder frame side (1026)；Wherein, the first rudder frame (1022), third rudder frame side (1023), the 4th at (1021), the second rudder frame
Rudder frame (1025) and the 6th rudder frame side (1026) at (1024), five rudder frames are sequentially connected and connect；Wherein,
One end of the second rudder root (1012) is connected to the first rudder frame in the connection position of (1021) and (1022) when the second rudder frame
Place is set, the other end of the second rudder root (1012) is inserted in the first U-shaped groove that the 4th rudder frame side (1024) opens up
(10241)；
One end of the first rudder root (1011) is connected to the first rudder frame in the connection position of (1021) and (1026) when six rudder frames
Place is set, the other end of the first rudder root (1011) is inserted in the second U-shaped groove that the 4th rudder frame side (1024) opens up
(10242)。
3. grid rudder arrangement according to claim 1, it is characterised in that further include: the first pinboard (1091) and second turn
Fishplate bar (1092)；Wherein,
First pinboard (1091) is set on blade；
Second pinboard (1092) is set on blade and rudder frame (102).
4. grid rudder arrangement according to claim 1, it is characterised in that: several blades are cross-linked to form net in 90 °
Lattice.
5. grid rudder arrangement according to claim 1, it is characterised in that: the locking-unlocking device (2) includes bracket
(201), pin removal (202) and regulating arm (203)；Wherein,
The regulating arm (203) is connected with the rudder frame (102)；
The pin removal (202) is connected with the regulating arm (203)；
The bracket (201) is connected with the pin removal (202).
6. grid rudder arrangement according to claim 5, it is characterised in that: the regulating arm (203) includes adjustable plate
(20301), (20302) and bulb (20303) are covered；Wherein,
One end of the adjustable plate (20301) is connected by hinged bolts with the rudder frame (102), the adjustable plate
(20301) the other end is provided with ball-and-socket；
The bulb (20303) is set in the ball-and-socket；
The lid (20302) covers the bulb (20303) and is connected with the adjustable plate (20301)；
The pin shaft of the pin removal (202) and the through-hole in the middle part of the bulb (20303) are clearance fit.
7. grid rudder arrangement according to claim 5, it is characterised in that: the inner surface and appearance of the rudder face structure (1)
Face is concentric circle arc plane, and the diameter of the arc surface of inner surface is greater than aircraft rocket body diameter 200mm or more.
8. grid rudder arrangement according to claim 1, it is characterised in that: the blade being connected with rudder frame (102) inserts in
It simultaneously welds one U-shaped half logical groove (1021)；The blade being connected with the first rudder root (1011) inserts in the second U-shaped half logical groove
(10111) it and welds；The blade being connected with the second rudder root (1012) inserts in U-shaped half logical groove (10121) of third and welds；The
One U-shaped notch (300) is intersected and is welded with the second U-shaped notch (400).
9. grid rudder arrangement according to claim 3, it is characterised in that: first pinboard (1091) offers part
Groove is inserted in blade by partial groove, carries lifting surface load by groove structure on two sides, passes through bottom portion of groove contact surface
Squeeze carrying resistance area load.
10. grid rudder arrangement according to claim 3, it is characterised in that: second pinboard (1092) offers office
Portion's groove is inserted in blade and rudder frame (102) by partial groove, carries lifting surface load by groove structure on two sides, passes through
Bottom portion of groove contact surface squeezes carrying resistance area load.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910452278.5A CN110260726B (en) | 2019-05-28 | 2019-05-28 | Grid rudder device |
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| CN201910452278.5A CN110260726B (en) | 2019-05-28 | 2019-05-28 | Grid rudder device |
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| CN110260726B CN110260726B (en) | 2021-09-03 |
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| CN111086656A (en) * | 2019-12-09 | 2020-05-01 | 北京宇航***工程研究所 | Combined adjustable grid rudder unfolding and locking mechanism |
| CN111731467A (en) * | 2020-06-30 | 2020-10-02 | 北京星际荣耀空间科技有限公司 | Grid rudder and aircraft |
| CN114593643A (en) * | 2022-01-25 | 2022-06-07 | 北京宇航***工程研究所 | Double-hinge-rod type air rudder locking, unlocking and buffeting restraining mechanism |
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| CN114593643B (en) * | 2022-01-25 | 2024-02-09 | 北京宇航***工程研究所 | Double-hinge rod type air rudder locking and unlocking and buffeting restraining mechanism |
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|---|---|
| CN110260726B (en) | 2021-09-03 |
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