CN110260726B - Grid rudder device - Google Patents
Grid rudder device Download PDFInfo
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- CN110260726B CN110260726B CN201910452278.5A CN201910452278A CN110260726B CN 110260726 B CN110260726 B CN 110260726B CN 201910452278 A CN201910452278 A CN 201910452278A CN 110260726 B CN110260726 B CN 110260726B
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- rudder
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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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Abstract
The invention discloses a grid rudder control surface device, which comprises: a control surface structure and a locking and unlocking device; the control surface structure is connected with the locking and unlocking device; the rudder surface structure comprises a first rudder root, a second rudder root, a rudder frame and a plurality of blades; the first rudder root and the second rudder root are respectively connected with the rudder frame, and the first rudder root and the second rudder root divide the rudder frame into a first area, a second area and a third area; the plurality of blades are arranged in the first area, the second area and the third area. The invention adopts the scheme of initial splicing bearing of the structure, auxiliary positioning for welding and the scheme of inserting the pin shaft of the pin puller into the spherical hinge hole, and has the advantages of stable and reliable bearing performance and deformation compensation capability.
Description
Technical Field
The invention belongs to the technical field of a first sublevel of a carrier rocket, and particularly relates to a grid rudder device.
Background
At present, grid rudder surfaces formed based on welding, casting and the like are widely applied to attitude control during flying or returning of missiles, airships, carrier rockets and the like in a one-sub level mode, but the casting scheme is integrally formed, so that the reliability is high, and the production cost is high. In the face of competition of high quality and low cost in the space launch market, the metal plate tailor-welding scheme is low in cost but limited by factors such as welding process stability and non-detectability, the welding quality reliability evaluation of the tailor-welding scheme depends on the side evidence of small welded samples in the same batch, cannot be directly evaluated, and has certain risk in model application.
In addition, in the locking and unlocking scheme based on the pin puller, under the consideration of factors such as processing, assembly, loaded deformation and the like, in order to ensure that the pin puller pin shaft is inserted into the locked structural hole, the hole shaft fit clearance is generally enlarged enough to compensate the assembly deviation at the position, so that the pin puller pin shaft is only in line contact with the structural hole contact surface, which easily causes unnecessary vibration of the structure due to the hole shaft clearance in a vibration environment, causes the pin puller pin shaft to be locally extruded and rubbed by the structural hole to cause pin shaft abrasion, or causes an overlarge dynamic response of the structure, and finally affects the normal work of the structural product and the pin puller.
At present, the existing rudder surface patents all have the acoustic cable for the whole profile section, but the plugging scheme of each plate of the rudder surface structure is not mentioned. The pin shaft limiting scheme of the pin puller has no improvement scheme aiming at the defect.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the grid rudder device is provided, the scheme of initial splicing, bearing and auxiliary positioning of welding is adopted, and the scheme of inserting the pin puller pin shaft into the spherical hinge hole has the advantages of stable and reliable bearing performance and deformation compensation capacity.
The purpose of the invention is realized by the following technical scheme: a grid rudder apparatus comprising: a control surface structure and a locking and unlocking device; the control surface structure is connected with the locking and unlocking device; the rudder surface structure comprises a first rudder root, a second rudder root, a rudder frame and a plurality of blades; the first rudder root and the second rudder root are respectively connected with the rudder frame, and the first rudder root and the second rudder root divide the rudder frame into a first area, a second area and a third area; the blades are arranged in the first area, the second area and the third area; wherein, a plurality of blades are connected in a staggered manner to form a grid; at the connecting position of the blade and the rudder frame, a plurality of first U-shaped semi-through grooves are formed in the inner side wall surface of the rudder frame, and the blade connected with the rudder frame is inserted into the first U-shaped semi-through grooves; the blade is connected with the first rudder root, the first rudder root is provided with a plurality of second U-shaped semi-through grooves, and the blade connected with the first rudder root is inserted into the second U-shaped semi-through grooves; the blades connected with the second rudder root are inserted into the third U-shaped semi-through grooves; the blades and the blades are in staggered connection, a first U-shaped notch with the height of 1/2 is formed in one blade in the height direction of the crossing position, a second U-shaped notch with the height of 1/2 is formed in the other blade in the height direction of the crossing position, and the first U-shaped notch is in crossed connection with the second U-shaped notch.
In the grid rudder device, the rudder frame comprises a first rudder frame side, a second rudder frame side, a third rudder frame side, a fourth rudder frame side, a fifth rudder frame side and a sixth rudder frame side; the first rudder frame edge, the second rudder frame edge, the third rudder frame edge, the fourth rudder frame edge, the fifth rudder frame edge and the sixth rudder frame edge are connected in sequence; one end of the second rudder root is connected to the connecting position of the first rudder frame edge and the second rudder frame edge, and the other end of the second rudder root is inserted into a first U-shaped groove formed in the fourth rudder frame edge; one end of the first rudder root is connected to the connecting position of the first rudder frame edge and the sixth rudder frame edge, and the other end of the first rudder root is inserted into a second U-shaped groove formed in the fourth rudder frame edge.
The grid rudder apparatus further includes: a first adapter plate and a second adapter plate; the first adapter plate is arranged on the blade; the second adapter plate is arranged on the blade and the rudder frame.
In the grid rudder device, a plurality of blades are connected in a 90-degree staggered manner to form a grid.
In the grid rudder device, the locking and unlocking device comprises a bracket, a pin puller and an adjusting arm; the adjusting arm is connected with the rudder frame; the pin puller is connected with the adjusting arm; the bracket is connected with the pin puller.
In the grid rudder device, the adjusting arm comprises an adjusting plate, a cover and a ball head; one end of the adjusting plate is connected with the rudder frame through a hinged hole bolt, and the other end of the adjusting plate is provided with a ball socket; the ball head is arranged in the ball socket; the cover covers the ball head and is connected with the adjusting plate; and a pin shaft of the pin puller is in clearance fit with the through hole in the middle of the ball head.
In the grid rudder device, the inner surface and the outer surface of the control surface structure are concentric arc surfaces, and the diameter of the arc surface of the inner surface is more than 200mm larger than the diameter of the aircraft arrow body.
In the grid rudder device, the blades connected with the rudder frame are inserted into the first U-shaped semi-through groove and welded; the blade connected with the first rudder root is inserted into the second U-shaped semi-through groove and welded; the blade connected with the second rudder root is inserted into the third U-shaped semi-through groove and welded; the first U-shaped notch and the second U-shaped notch are crossed and welded.
In the grid rudder device, the first adapter plate is provided with a local groove, the first adapter plate is inserted into the blades through the local groove, the two side structures of the groove bear lifting surface load, and the bottom contact surface of the groove extrudes to bear resistance surface load.
In the grid rudder device, the second adapter plate is provided with a local groove, the second adapter plate is inserted into the blade and the rudder frame through the local groove, the lifting surface load is borne through structures on two sides of the groove, and the resistance surface load is borne through the extrusion of the contact surface at the bottom of the groove.
Compared with the prior art, the invention has the following beneficial effects:
1) the control surface structure of the invention bears the weight of itself, and the welding seam is only used as backup, thus the reliability is higher. The splicing scheme of the grid rudder control surface structure enables loads among the blades, the rudder root and the rudder frame structure to be borne through mutually inserted structures, and welding is only used as auxiliary positioning and redundant bearing measures. The bearing performance of the structure extrusion can be realized by adopting 100% of the self performance of the structural material to participate in bearing, the traditional scheme of completely depending on welding to realize bearing is adopted, the welding performance is generally less than 80% of the performance of the master material, factors such as welding defects, incapability of detecting welding seams and the like are considered, in addition, if the grid rudder structure is subjected to sheet intensive welding, large deformation is easily caused, the welding quality is further reduced, only 50% of the performance of the master material is used for strength checking at the welding seams during engineering application, and the bearing efficiency is far lower than the technical scheme of the rudder surface structure.
2) The control surface structure splicing scheme has high bearing reliability and low cost. The mutually inserted groove positions of all parts are ensured by machining, the positions of all parts are uniquely determined by splicing, inserting and molding the parts, the overall appearance of the control surface structure can be determined, extra production tools are not needed for positioning, and the production cost and the development period are reduced;
3) the splicing scheme of the control surface structure of the invention is easier to ensure the welding quality, after the component structures are mutually inserted, the fit clearance in the thickness direction is easy to ensure to a smaller value, and the fit surface has a certain depth, thus having low requirement on the length tolerance of the hard-to-control components. The welding deformation amount of the previous process is less than the insertion depth, and the fit clearance in the thickness direction is not influenced. The welding position can select the welding groove, so that the length and the gap of the binding surface of the structure before welding can be effectively ensured, and the welding quality can be ensured more easily. The control surface structure scheme avoids the condition that the welding quality is influenced or even the welding forming cannot be carried out due to the fact that the deviation of the butt joint surface of the subsequent structure is large after the welding procedure of the previous channel is deformed in the traditional control surface part end surface butt welding scheme.
4) The spherical hinge device can improve the assembly convenience and the assembly quality: the spherical hinge device of the adjusting arm can compensate the condition that the pin shaft of the pin puller and the hole of the adjusting arm are not coaxial due to welding deformation or assembly deviation of the control surface structure, so that assembly is facilitated, and the pin puller is ensured not to have local additional load caused by forced assembly to influence the work of the pin puller. In addition, because the problem of shaft hole assembly has been solved in the ball pivot compensation, avoided the scheme of traditional simple increase aperture (hole axle unilateral clearance 1 ~ 2mm), can guarantee that the shaft hole cooperation precision is high, the clearance is little (hole axle unilateral clearance 0.025 ~ 0.05mm), improved connection rigidity, avoided structural vibration and striking under the vibration load under the big clearance to and the consequently risk factor such as round pin axle damage, the too big of structure dynamic response that cause.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic view of the convex side of a grid rudder unit according to an embodiment of the present invention;
FIG. 2 grid rudder surface load direction-resistive surface load;
FIG. 3 grid rudder surface load direction-lifting surface load;
FIG. 4 is a schematic view of a concave side of a grid rudder surface structure according to an embodiment of the present invention;
FIG. 5 is an enlarged exploded view of the part A (rudder frame-blade) in FIG. 4;
FIG. 6 is an enlarged exploded view of the part B (the adapter plate, the rudder frame and the blade) in FIG. 4;
FIG. 7 is an enlarged exploded view of the portion C (blade-blade) of FIG. 4;
FIG. 8(a) is a partially enlarged exploded view of the blade-first rudder root of FIG. 4;
fig. 8(b) is a partial enlarged exploded view of fig. 4 at D (blade-second rudder root);
fig. 9 is a sectional view of the locking and unlocking device according to the embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic view of the convex side of a grid rudder unit according to an embodiment of the present invention. As shown in fig. 1, the grid rudder apparatus includes: a control surface structure 1 and a locking and unlocking device 2. Wherein the content of the first and second substances,
the control surface structure 1 is connected with the locking and unlocking device 2;
the control surface structure 1 comprises a first rudder root 1011, a second rudder root 1012, a rudder frame 102 and a plurality of blades;
the first rudder root 1011 and the second rudder root 1012 are respectively connected to the rudder frame 102, and the first rudder root 1011 and the second rudder root 1012 divide the rudder frame 102 into a first region, a second region, and a third region;
the blades are arranged in the first area, the second area and the third area; wherein, a plurality of blades are connected in a staggered manner to form a grid; at the connection position of the blade and the rudder frame 102, a plurality of first U-shaped half-through grooves 10211 (shown in fig. 5) are formed on the inner side wall surface of the rudder frame 102, and the blade connected with the rudder frame 102 is inserted into the first U-shaped half-through grooves 10211; at the connecting position of the blades and the first rudder root 1011, the first rudder root 1011 is provided with a plurality of second U-shaped semi-through grooves 10111 (as shown in fig. 8 (a)), and the blades connected with the first rudder root 1011 are inserted into the second U-shaped semi-through grooves 10111; at the connecting position of the blades and the second rudder root 1012, the second rudder root 1012 is provided with a plurality of third U-shaped half-through grooves 10121 (as shown in fig. 8 (b)), and the blades connected with the second rudder root 1012 are inserted into the third U-shaped half-through grooves 10121; at the crossed connection position of the blades, a first U-shaped notch 300 with the height of 1/2 is formed in the height direction of the crossed position of one blade, a second U-shaped notch 400 with the height of 1/2 is formed in the height direction of the crossed position of the other blade, and the first U-shaped notch 300 is in crossed connection with the second U-shaped notch 400.
Specifically, the plurality of blades include a plurality of first blades 103, a plurality of second blades 104, a plurality of third blades 105, a plurality of fourth blades 106, a plurality of fifth blades 107, a plurality of sixth blades 108, a seventh blade 1031, and an eighth blade 1081; wherein the content of the first and second substances,
the plurality of first blades 103, the plurality of second blades 104 and the seventh blade 1031 are all arranged in a first area, two ends of the seventh blade 1031 are all connected with the rudder frame 102, the plurality of first blades 103 and the plurality of second blades 104 are connected in a cross manner to form a grid, one end of each first blade 103 is connected with the first rudder root 1011, the other end of each first blade 103 is connected with the rudder frame 102, one end of each second blade 104 is connected with the first rudder root 1011, and the other end of each second blade 104 is connected with the rudder frame 102; the rudder base 1011 is provided with a plurality of second U-shaped half-through grooves (5 bosses are equidistantly distributed, and 3 or 4U-shaped half-through grooves are formed in the two side wall surfaces of each boss and only penetrate through the inner arc surface in height), the two ends of the seventh blade 1031 are inserted into the corresponding first U-shaped half-through grooves, one end of each first blade 103 is inserted into the corresponding second U-shaped half-through groove, the other end of each first blade 103 is inserted into the corresponding first U-shaped half-through groove, one end of each second blade 104 is inserted into the corresponding second U-shaped half-through groove, and the other end of each second blade 104 is inserted into the corresponding first U-shaped half-through groove;
the plurality of third blades 105 and the plurality of fourth blades 106 are arranged in the second area, and the plurality of third blades 105 and the plurality of fourth blades 106 are connected in a cross mode to form a grid;
the plurality of fourth blades 106, the plurality of fifth blades 107 and the eighth blade 1081 are all disposed in the third area, both ends of the eighth blade 1081 are all connected with the rudder frame 102, the plurality of fourth blades 106 and the plurality of fifth blades 107 are connected in a cross manner to form a grid, one end of each fourth blade 106 is connected with the first rudder root 1011, the other end of each fourth blade 106 is connected with the rudder frame 102, one end of each fifth blade 107 is connected with the first rudder root 1011, and the other end of each fifth blade 107 is connected with the rudder frame 102.
As shown in fig. 1, the rudder frame 102 includes a first rudder frame edge 1021, a second rudder frame edge 1022, a third rudder frame edge 1023, a fourth rudder frame edge 1024, a fifth rudder frame edge 1025, and a sixth rudder frame edge 1026; the first rudder frame edge 1021, the second rudder frame edge 1022, the third rudder frame edge 1023, the fourth rudder frame edge 1024, the fifth rudder frame edge 1025 and the sixth rudder frame edge 1026 are sequentially connected; wherein the content of the first and second substances,
one end of the first rudder root 1011 is connected to the connecting position of the first rudder frame edge 1021 and the second rudder frame edge 1022, and the other end of the first rudder root 1011 is inserted into a first U-shaped groove 10241 formed in the fourth rudder frame edge 1024;
one end of the second rudder root 1012 is connected to the connection position of the first rudder frame edge 1021 and the sixth rudder frame edge 1026, and the other end of the second rudder root 1012 is inserted into the second U-shaped groove 10242 formed in the fourth rudder frame edge 1024.
As shown in fig. 1, the apparatus further comprises: a first adaptor plate 1091 and a second adaptor plate 1092; wherein the first adaptor plate 1091 is disposed on the blade; a second adapter plate 1092 is provided on the blade and rudder frame 102.
The first adapter plate 1091 is provided with a local groove, and is inserted into the blade 105 and the blade 106 through the local groove, and bears the lifting surface load through the structure on both sides of the groove, and bears the resisting surface load through the contact surface extrusion at the bottom of the groove.
The second adapter plate 1092 is provided with a local groove, and is inserted in the blade 105, the blade 106 and the first rudder frame edge 1021 through the local groove, and bears the lifting surface load through the structures on the two sides of the groove, and bears the resistance surface load through the bottom contact surface extrusion of the groove.
Example 1
The invention provides a grid rudder device which comprises a control surface structure 1 and a locking and unlocking device 2 as shown in figure 1.
The control surface structure 1 includes: the rudder comprises a first rudder root 1011, a second rudder root 1012, a rudder frame 102, a first blade 103, a second blade 104, a third blade 105, a fourth blade 106, a fifth blade 107, a sixth blade 108 and an adapter plate 109. +/-45-degree U-shaped half-through grooves are formed in the joints of the rudder root 101, the rudder frame 102, the blades 103-108 and the adapter plate 109, and are integrally welded and formed after being mutually inserted and positioned, as shown in figure 1; the load carried by the control surface structure is two major parts of the load of a lifting surface and a resistance surface, as shown in fig. 2, 3 and 4;
the rudder root 101 is a structure with gradually-changed section thickness, is thinner close to the locking device side and thicker close to the spline hole side, is provided with 5 bosses at equal intervals, is provided with 3 or 4 +/-45-degree U-shaped semi-through grooves on the side wall surfaces of the two sides of the boss, and penetrates through the inner arc surface side only in height, as shown in fig. 8. The rudder root is rounded at the side end face of the resistance surface, so that the pneumatic efficiency is improved, and the scouring resistance is reduced;
the matching position of the inner side wall surface of the rudder frame 102 and the blade is provided with +/-45-degree U-shaped semi-through grooves at equal intervals, and the grooves only penetrate through the inner arc surface side in height, as shown in fig. 5. 2 hinge holes are formed in the middle of the rudder frame close to the pin puller 202, and are connected with the adjusting plate 20301 of the adjusting arm 203 through 2 hinge hole bolt fasteners;
local protruding structures are arranged at two ends of each of the first blade 103, the second blade 104, the third blade 105, the fourth blade 106, the fifth blade 107 and the sixth blade 108, one end of each of the partial blades is inserted into the rudder root, the other end of each of the partial blades is inserted into a groove of the rudder frame, and two ends of each of the partial blades are inserted into grooves of the rudder root 101. The lifting surface load is borne through the matching surface in the height direction of the insertion section, the resistance surface load is borne through the step surface in the thickness direction, and the dependence on the welding seam load is greatly reduced, as shown in fig. 5 and 8;
the first blade 103 and the second blade 104, the third blade 105 and the fourth blade 106, and the fifth blade 107 and the sixth blade 108 are arranged in a 90-degree mutual crossing manner, U-shaped notches with the height of 1/2 are respectively formed in the height direction of the crossing positions, the blades are not broken to keep continuity, the matching surface in the height direction of the insertion section bears lifting surface load, the matching surface at the bottom of the notch in the thickness direction bears resisting surface load, and the dependence on seam bearing is greatly reduced, as shown in FIG. 7;
the adapter plates 109 are provided with local grooves, the local grooves are respectively inserted into the blades 105 and 106 and the rudder frame 102, the lifting surface load is borne through structures on two sides of each groove, the resistance surface load is borne through the extrusion of the contact surface at the bottom of each groove, and the dependence on the bearing of a welding seam is greatly reduced, as shown in fig. 6. 1 hinged through hole is formed in each of the 4 adapter plates 109, and the adapter plates are connected with an external unfolding driving mechanism through hinged bolt fasteners for bearing;
the rudder root 101 is provided with a local boss at the end of the pin puller and is inserted into a rectangular hole formed in the rudder frame 102, and as shown in fig. 3, the load of a lifting surface and a resisting surface is extruded and borne through the matching surfaces of the boss and the hole, so that the dependence on the bearing of a welding seam is greatly reduced;
at the spline hole end of the rudder root 101, the rudder frame 102 is provided with a local boss, the local boss is inserted into the U-shaped semi-through groove of the rectangular boss at the root of the rudder root 101, the matched surface in the height direction of the insertion section bears the load of a lifting surface, the extruded surface of the step in the thickness direction bears the load of a resistance surface, the dependence on the bearing of a welding seam is greatly reduced, and the bearing form is similar to that shown in fig. 6;
the mutually inserted groove positions of all parts of the control surface structure 1 are guaranteed by machining, the positions of all parts are uniquely determined after all parts are spliced and inserted, the overall appearance of the control surface structure can be determined without adding extra assembly dimension tooling for positioning, and the production cost and the development period are reduced.
The splicing scheme of the control surface structure 1 is easier to guarantee the welding quality, after all component structures are mutually inserted, the fit clearance in the thickness direction is easy to guarantee to a smaller value, the fit surface has a certain depth, and the requirement on the length tolerance of the hard-to-control components is low. The welding deformation amount of the previous process is less than the insertion depth, and the fit clearance in the thickness direction is not influenced. The welding position can select the welding groove, so that the length and the gap of the binding surface of the structure before welding can be effectively ensured, and the welding quality can be ensured more easily. The control surface structure scheme avoids the condition that the welding quality is influenced or even the welding forming cannot be carried out due to the fact that the deviation of the butt joint surface of the subsequent structure is large after the welding procedure of the previous channel is deformed in the traditional control surface part end surface butt welding scheme.
Preferably, the blade tip is processed into the button head, the recess root of rudder face, rudder root is processed into the round hole, avoids the elongated hole root to produce stress concentration.
Preferably, the blades arranged at-45 degrees such as the first blade 103, the second blade 105, the third blade 107 and the like can be combined into 1 group of blades, and the blades arranged at 45 degrees such as the second blade 104, the fourth blade 106, the sixth blade 108 and the like can be combined into 1 group of continuous blades, and are not interrupted at the position crossing the rudder root 101, but 4 groups of U-shaped grooves of the boss of the rudder root 101 are communicated in the thickness direction, so that the bearing efficiency is further improved;
preferably, the material of the control surface structure 1 can be a titanium alloy material with better high-temperature performance or a high-temperature alloy such as GH 4169;
preferably, the inner surface and the outer surface of the control surface structure 1 are concentric arc surfaces, and the diameter of the inner arc surface is more than 200mm larger than that of an aircraft arrow body, so that sufficient installation space of the locking and unlocking device 2 is ensured;
preferably, the surface of the control surface structure 1 can be sprayed with a heat-proof material;
the locking and unlocking device 2 includes: the rudder frame comprises a bracket 201, a pin puller 202 and an adjusting arm 203, wherein the adjusting arm 203 is connected with the rudder frame 102; the pin puller 202 is connected with the adjusting arm 203; the bracket 201 is connected with the pin puller 202. The adjusting arm 203 comprises an adjusting plate 20301, a cover 20302 and a ball head 20303; one end of the adjusting plate 20301 is connected to the rudder frame 102 through a hinged hole bolt, and the other end of the adjusting plate 20301 is provided with a ball socket; the ball head 20303 is arranged in the ball socket; the cover 20302 covers the ball head 20303 and is connected to the adjustment plate 20301; the pin shaft of the pin puller 202 is in clearance fit with the through hole in the middle of the ball head 20303. The pin puller 202 is an initiating explosive device, and a pin shaft of the pin puller is in clearance fit with a through hole in the middle of the ball head 20303. One end of the adjusting plate 20301 is structurally connected with the control surface through 2 hinged hole bolts, and one end is provided with a ball socket and 4 threaded holes. The cover 20302 is provided with a ball socket and 4 bolt holes, and the ball head 20303 is pressed on the adjusting plate by 4 fasteners to form a ball hinge device, as shown in fig. 9. The spherical hinge device can compensate the condition that the pin shaft of the pin puller 202 is not coaxial with the adjusting arm hole due to welding deformation or assembly deviation and the like of the control surface structure 1, is convenient to assemble, and ensures that the pin shaft of the pin puller 202 is not subjected to local additional load caused by forced assembly to influence the work of the pin puller. In addition, because the problem of shaft hole assembly has been solved in the ball pivot compensation, avoided the scheme of traditional simple increase aperture (hole axle unilateral clearance 1 ~ 2mm), can guarantee that the shaft hole cooperation precision is high, the clearance is little (hole axle unilateral clearance 0.025 ~ 0.05mm), improved connection rigidity, avoided structural vibration and striking under the vibration load under the big clearance to and the consequently risk factor such as round pin axle damage, the too big of structure dynamic response that cause.
Preferably, the material of the control surface structure 1 can be a titanium alloy material with better high-temperature performance or a high-temperature alloy such as GH 4169;
preferably, the pin pulling device can be arranged on the outer side of the fairing for thermal protection before operation;
preferably, the bolt hole for connecting the bracket 201 with the aircraft arrow body is a kidney-shaped hole;
after grid rudder device assembles on the aircraft arrow body, locking unlocking device 2 support 201 passes through bolt fastener and arrow body coupling, will the closed locking of rudder face structure 1 is at arrow body surface, keeps reliable locking at the flight section, returns the section at the aircraft, the action of pulling out pin ware 202 causes the action of pulling out the round pin, follows the round pin axle adjust the downthehole pull out of arm 203, 1 unblocks of rudder face structure, expands under outside expansion actuating mechanism's the effect and locks after certain angle, bears the washing away of returning the section air current, forms lifting surface load and resistance surface load, and its bearing function is accomplished promptly to the rudder face structure.
The control surface structure of the embodiment bears the load, and the welding seam is only used as a backup, so that the reliability is higher. The splicing scheme of the grid rudder control surface structure enables loads among the blades, the rudder root and the rudder frame structure to be borne through mutually inserted structures, and welding is only used as auxiliary positioning and redundant bearing measures. The bearing performance of the structure extrusion can be realized by adopting 100% of the self performance of the structural material to participate in bearing, the traditional scheme of completely depending on welding to realize bearing is adopted, the welding performance is generally less than 80% of the performance of the master material, factors such as welding defects, incapability of detecting welding seams and the like are considered, in addition, if the grid rudder structure is subjected to sheet intensive welding, large deformation is easily caused, the welding quality is further reduced, only 50% of the performance of the master material is used for strength checking at the welding seams during engineering application, and the bearing efficiency is far lower than the technical scheme of the rudder surface structure.
The control surface structure splicing scheme of the embodiment has high bearing reliability and low cost. The mutually inserted groove positions of all parts are ensured by machining, the positions of all parts are uniquely determined by splicing, inserting and molding the parts, the overall appearance of the control surface structure can be determined, extra production tools are not needed for positioning, and the production cost and the development period are reduced;
the control surface structure of this embodiment is pieced together and is inserted the scheme and guarantee welding quality more easily, and each spare part structure inserts the back each other, and thickness direction's fit clearance is easily guaranteed to less value, and the fitting surface has certain degree of depth, and the length tolerance to the difficult controlled spare part requires lowly. The welding deformation amount of the previous process is less than the insertion depth, and the fit clearance in the thickness direction is not influenced. The welding position can select the welding groove, so that the length and the gap of the binding surface of the structure before welding can be effectively ensured, and the welding quality can be ensured more easily. The control surface structure scheme avoids the condition that the welding quality is influenced or even the welding forming cannot be carried out due to the fact that the deviation of the butt joint surface of the subsequent structure is large after the welding procedure of the previous channel is deformed in the traditional control surface part end surface butt welding scheme.
The ball pivot device of this embodiment can improve convenient degree of assembly and assembly quality: the spherical hinge device of the adjusting arm can compensate the condition that the pin shaft of the pin puller and the hole of the adjusting arm are not coaxial due to welding deformation or assembly deviation of the control surface structure, so that assembly is facilitated, and the pin puller is ensured not to have local additional load caused by forced assembly to influence the work of the pin puller. In addition, because the problem of shaft hole assembly has been solved in the ball pivot compensation, avoided the scheme of traditional simple increase aperture (hole axle unilateral clearance 1 ~ 2mm), can guarantee that the shaft hole cooperation precision is high, the clearance is little (hole axle unilateral clearance 0.025 ~ 0.05mm), improved connection rigidity, avoided structural vibration and striking under the vibration load under the big clearance to and the consequently risk factor such as round pin axle damage, the too big of structure dynamic response that cause.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (10)
1. A grid rudder apparatus characterized by comprising: a control surface structure (1) and a locking and unlocking device (2); wherein the content of the first and second substances,
the control surface structure (1) is connected with the locking and unlocking device (2);
the control surface structure (1) comprises a first control root (1011), a second control root (1012), a control frame (102) and a plurality of blades; wherein the content of the first and second substances,
the first rudder root (1011) and the second rudder root (1012) are respectively connected with the rudder frame (102), and the first rudder root (1011) and the second rudder root (1012) divide the rudder frame (102) into a first area, a second area and a third area;
the blades are arranged in the first area, the second area and the third area; wherein, a plurality of blades are connected in a staggered manner to form a grid; at the connecting position of the blade and the rudder frame (102), a plurality of first U-shaped semi-through grooves (10211) are formed in the inner side wall surface of the rudder frame (102), and the blade connected with the rudder frame (102) is inserted into the first U-shaped semi-through grooves (10211); at the connecting position of the blades and the first rudder root (1011), the first rudder root (1011) is provided with a plurality of second U-shaped semi-through grooves (10111), and the blades connected with the first rudder root (1011) are inserted into the second U-shaped semi-through grooves (10111); at the connecting position of the blades and the second rudder root (1012), the second rudder root (1012) is provided with a plurality of third U-shaped semi-through grooves (10121), and the blades connected with the second rudder root (1012) are inserted into the third U-shaped semi-through grooves (10121); at the crossed connection positions of the blades, a first U-shaped notch (300) with the height of 1/2 is formed in one blade in the height direction of the crossed position, a second U-shaped notch (400) with the height of 1/2 is formed in the other blade in the height direction of the crossed position, and the first U-shaped notch (300) is in crossed connection with the second U-shaped notch (400).
2. The grid rudder apparatus according to claim 1, wherein: the rudder frame (102) comprises a first rudder frame edge (1021), a second rudder frame edge (1022), a third rudder frame edge (1023), a fourth rudder frame edge (1024), a fifth rudder frame edge (1025) and a sixth rudder frame edge (1026); the first rudder frame edge (1021), the second rudder frame edge (1022), the third rudder frame edge (1023), the fourth rudder frame edge (1024), the fifth rudder frame edge (1025) and the sixth rudder frame edge (1026) are sequentially connected; wherein the content of the first and second substances,
one end of the second rudder root (1012) is connected to the connecting position of the first rudder frame edge (1021) and the second rudder frame edge (1022), and the other end of the second rudder root (1012) is inserted into a first U-shaped groove (10241) formed in the fourth rudder frame edge (1024);
one end of the first rudder root (1011) is connected to the connecting position of the first rudder frame edge (1021) and the sixth rudder frame edge (1026), and the other end of the first rudder root (1011) is inserted into a second U-shaped groove (10242) formed in the fourth rudder frame edge (1024).
3. The grid rudder apparatus according to claim 1, further comprising: a first adaptor plate (1091) and a second adaptor plate (1092); wherein the content of the first and second substances,
a first adapter plate (1091) is disposed on the blade;
the second adapter plate (1092) is arranged on the blade and the rudder frame (102).
4. The grid rudder apparatus according to claim 1, wherein: a plurality of blades are connected in a 90-degree staggered manner to form a grid.
5. The grid rudder apparatus according to claim 1, wherein: the locking and unlocking device (2) comprises a bracket (201), a pin puller (202) and an adjusting arm (203); wherein the content of the first and second substances,
the adjusting arm (203) is connected with the rudder frame (102);
the pin puller (202) is connected with the adjusting arm (203);
the bracket (201) is connected with the pin puller (202).
6. The grid rudder apparatus according to claim 5, wherein: the adjusting arm (203) comprises an adjusting plate (20301), a cover (20302) and a ball head (20303); wherein the content of the first and second substances,
one end of the adjusting plate (20301) is connected with the rudder frame (102) through a hinged hole bolt, and the other end of the adjusting plate (20301) is provided with a ball socket;
the ball head (20303) is disposed within the socket;
the cover (20302) covers the ball head (20303) and is connected with the adjusting plate (20301);
and a pin shaft of the pin puller (202) is in clearance fit with a through hole in the middle of the ball head (20303).
7. The grid rudder apparatus according to claim 5, wherein: the inner surface and the outer surface of the control surface structure (1) are concentric arc surfaces, and the diameter of the arc surface of the inner surface is more than 200mm larger than the diameter of an aircraft arrow body.
8. The grid rudder apparatus according to claim 1, wherein: blades connected with the rudder frame (102) are inserted into the first U-shaped half-through groove (10211) and welded; the blade connected with the first rudder root (1011) is inserted into the second U-shaped semi-through groove (10111) and welded; the blade connected with the second rudder root (1012) is inserted into the third U-shaped semi-through groove (10121) and welded; the first U-shaped notch (300) and the second U-shaped notch (400) are crossed and welded.
9. The grid rudder apparatus according to claim 3, wherein: the first adapter plate (1091) is provided with a local groove, the blades are inserted into the local groove, the lifting surface load is borne through structures on two sides of the groove, and the resistance surface load is borne through the extrusion of a contact surface at the bottom of the groove.
10. The grid rudder apparatus according to claim 3, wherein: the second adapter plate (1092) is provided with a local groove, the second adapter plate is inserted into the blade and the rudder frame (102) through the local groove, the lifting surface load is borne through structures on two sides of the groove, and the resistance surface load is borne through the bottom contact surface extrusion of the groove.
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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 true CN110260726B (en) | 2021-09-03 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111086656B (en) * | 2019-12-09 | 2021-07-13 | 北京宇航系统工程研究所 | 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 |
| CN114593643B (en) * | 2022-01-25 | 2024-02-09 | 北京宇航系统工程研究所 | Double-hinge rod type air rudder locking and unlocking and buffeting restraining mechanism |
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| US7800032B1 (en) * | 2006-11-30 | 2010-09-21 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
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| CN1187794A (en) * | 1995-05-11 | 1998-07-15 | 危姆派尔国家机械建筑设计局 | Rocket with lattice control surfaces and lattice control surface for rocket |
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