CN115164653B - Rudder piece zero-position combined type debugging device and debugging method - Google Patents
Rudder piece zero-position combined type debugging device and debugging method Download PDFInfo
- Publication number
- CN115164653B CN115164653B CN202210771602.1A CN202210771602A CN115164653B CN 115164653 B CN115164653 B CN 115164653B CN 202210771602 A CN202210771602 A CN 202210771602A CN 115164653 B CN115164653 B CN 115164653B
- Authority
- CN
- China
- Prior art keywords
- rudder
- brackets
- concave arc
- bracket
- debugging
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 22
- 230000000149 penetrating effect Effects 0.000 claims description 9
- 238000012545 processing Methods 0.000 abstract description 14
- 230000009286 beneficial effect Effects 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 6
- 238000010923 batch production Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 11
- 230000001360 synchronised effect Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
- F42B33/001—Devices or processes for assembling ammunition, cartridges or cartridge elements from parts
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Connection Of Plates (AREA)
Abstract
The invention discloses a rudder piece zero-position combined type debugging device and a debugging method, wherein the debugging device comprises four brackets and four screws, wherein the brackets are uniformly distributed along the circumferential direction; the inner surface of the bracket is an inward concave arc surface, and the radius of the inward concave arc surface is equal to the radius of the outer circular surface of the cabin body; the two side surfaces of the bracket are inclined surfaces extending along the radial direction of the inward-concave arc surface, and the outer end part of one side surface is provided with a convex block; a screw is fixedly connected between any two adjacent brackets along the circumferential direction, the four brackets are opposite to each other, a cylindrical cavity is formed between the four brackets, and a rudder piece accommodating space is formed between the four brackets; the distance L1 between adjacent sides of two adjacent brackets is greater than the thickness L4 of the rudder sheet. The debugging device can realize debugging of the zero position of the rudder piece after the assembly of the cabin body, reduces the design and processing precision of the related structure of the rudder shaft system, greatly reduces the processing difficulty and the processing cost, and is beneficial to batch production.
Description
Technical Field
The invention relates to the technical field of rudder piece zero position debugging, in particular to a rudder piece zero position combined debugging device and a rudder piece zero position combined debugging method.
Background
The missile with the conventional pneumatic layout generally adopts movable rudder plates to implement maneuvering control, a plurality of rudder plates are installed on a missile cabin body through rudder shafts, a plurality of steering engines are also installed on the cabin body, each steering engine output shaft is connected with a corresponding rudder shaft for transmission, the steering engines are subjected to space limitation or pneumatic influence, and some missile rudder shafts are higher than the external circular surface of the cabin body after being installed, and some missile rudder shafts are lower than the external circular surface of the cabin body after being installed. The zero position of the rudder piece relative to the cabin body directly influences the missile control effect and precision, and the zero position precision of the rudder piece needs to be controlled in the cabin section assembly process.
The conventional method is to improve the size and form tolerance of the installation structures such as the cabin body and the rudder shaft, the cabin body and the steering engine, the rudder shaft and the rudder piece, and the like, improve the corresponding interface precision, determine the zero position of the output shaft of the steering engine after debugging before delivering the steering engine, directly install the steering engine and the rudder shaft on the cabin body during assembly of the cabin section, and directly install the rudder piece on the rudder shaft. In order to improve zero position precision of rudder pieces or reduce machining precision of related structural members, rudder shafts are removed from the shafting structural design, and the rudder pieces are directly connected with a steering engine output shaft; the rudder piece and the rudder shaft are directly designed into an integrated structure in the aspect of the structural design of the shafting, and then are connected with the steering engine output shaft.
However, in the prior art, the processing difficulty and the processing cost are increased by a method for improving the precision of the related structure of the rudder shaft system, which is not beneficial to mass production of products, and the installation error of the related structure in the assembly of the cabin section cannot be avoided.
Disclosure of Invention
In view of the above, the invention provides a rudder piece zero position combined type debugging device and a debugging method, the debugging device can realize debugging of rudder piece zero positions after assembly of a cabin body, can reduce the installation errors of related structures during assembly of cabin sections, reduces the design and processing precision of related structures of rudder shaft systems, greatly reduces the processing difficulty and processing cost, is beneficial to mass production, and improves the zero position precision of rudder pieces.
The invention adopts the following specific technical scheme:
the invention provides a rudder piece zero-position combined type debugging device, which comprises four brackets and four screws, wherein the brackets are uniformly distributed along the circumferential direction;
the inner surface of the bracket is a concave arc surface, and the radius of the concave arc surface is equal to the radius of the outer circular surface of the cabin body; the bracket is provided with two side surfaces along the circumferential direction of the inward-concave arc surface, the two side surfaces are inclined surfaces extending along the radial direction of the inward-concave arc surface, and the outer end part of one side surface is provided with a bump;
the screw is fixedly connected between any two adjacent brackets along the circumferential direction, the four brackets are opposite to each other, a cylindrical cavity is formed between the four brackets, and a rudder piece accommodating space is formed between the four brackets; the distance L1 between adjacent sides of two adjacent brackets is greater than the thickness L4 of the rudder sheet.
Further, two end faces of the bracket are parallel planes and are perpendicular to the central axis of the concave arc surface;
the convex blocks enable one side surface of the bracket to be composed of a first side surface, a second side surface and a third side surface which are sequentially connected from inside to outside, and the other side surface is a fourth side surface; the first side face, the second side face, the third side face and the fourth side face are all parallel to the central axis of the concave arc face, the first side face and the fourth side face extend along the radial direction of the concave arc face, the third side face is parallel to the first side face, and the second side face is parallel to the fourth side face and perpendicular to the first side face;
the outer surface of the bracket is composed of a first outer surface, a second outer surface, a third outer surface, a fourth outer surface and a fifth outer surface which are sequentially connected; the first outer surface, the second outer surface, the third outer surface, the fourth outer surface and the fifth outer surface are all parallel to the central axis of the concave arc surface, the first outer surface vertically intersects the fourth side surface, the first outer surface is parallel to the fourth outer surface, the second outer surface is parallel to the fifth outer surface, the second outer surface is vertical to the first outer surface, an included angle between the third outer surface and the second outer surface is 135 degrees, and the fifth outer surface vertically intersects the third side surface;
the bracket is provided with a threaded hole penetrating through the fourth side surface and the second outer surface and a through hole penetrating through the fourth outer surface and the third side surface;
one end of the screw penetrates through the through hole of one bracket and then is in threaded connection with the threaded hole of the other bracket, and the screw is used for fixedly connecting the two adjacent brackets together.
Furthermore, the distance between the two end surfaces of the bracket is L3, and the length of a rudder piece arranged on the cabin body is L6, wherein L3 is smaller than L6;
the central angle corresponding to the inward-concave arc surface is 90 degrees;
the rudder piece is arranged at the rear zero position of the cabin body, and the precision allowable error of the zero position angle is theta, wherein L1/2=L4/2+L3. Arctan theta;
the distance between the second side surface and the central axis of the inward-concave arc surface is L2;
the distance between the slightly chord of the rudder blade and the central axis of the cabin body is L5, and L2 is more than L5.
Still further, the screw head of the screw is provided with knurling to facilitate manual tightening.
In addition, the invention also provides a debugging method adopting the debugging device, and the debugging method comprises the following steps:
fixing a cabin provided with rudder pieces, keeping the central axis of the outer circular surface of the cabin horizontal, and rotating the four rudder pieces to the vicinity of a zero position;
placing four brackets in the open spaces of two adjacent rudder pieces, uniformly distributing two end surfaces of the four brackets on two sides of a rudder shaft, installing screws on the four brackets and slowly screwing the screws to gradually screw the four screws into the open spaces, so that the concave arc surfaces of the brackets are close to the outer circular surface of the cabin;
step three, when the concave arc surfaces of the four brackets are abutted against the outer circular surface of the cabin body, zero debugging of the four rudder pieces is completed;
when the concave arc surfaces of the four brackets are not abutted against the outer circular surface of the cabin body, the first side surface or the fourth side surface of the brackets are in line contact with the rudder piece, the rudder piece in line contact with the first side surface or the fourth side surface of the brackets is rotated, so that the contact line of the rudder piece and the first side surface or the fourth side surface is close to the rudder shaft on the rudder piece, if the contact line is far away from the rudder shaft, the rudder piece is reversely rotated, and the corresponding screw is slowly screwed in until the concave arc surfaces of the four brackets are abutted against the outer circular surface of the cabin body, zero debugging of the four rudder pieces is completed, and zero error is +/-theta.
Further, when turning the rudder blade in the third step, the gaps between each rudder blade and the first side surface and the fourth side surface are equal in the thickness direction of the rudder blade, and at this time, the zero positions of the four rudder blades are at 0 °.
The beneficial effects are that:
(1) The rudder piece zero-position combined type debugging device comprises four brackets which are uniformly distributed along the circumferential direction, and screws which are used for fixedly connecting the four brackets in pairs; the inner surfaces of the brackets are concave arc surfaces with the radius equal to that of the outer circular surface of the cabin body, and a cylindrical cavity for accommodating the cabin body is formed among the four brackets; the two side surfaces of the support are inclined surfaces extending along the radial direction of the inward-concave arc surface, the outer end part of one side surface is provided with a convex block, a rudder piece accommodating space is formed between two adjacent supports through the convex block, and the distance L1 between the side surfaces of the two adjacent supports is larger than the thickness L4 of the rudder piece. When the debugging device is used for debugging the zero position of the rudder sheet, the four brackets are arranged in the open space of the adjacent rudder sheet at the peripheral side of the cabin body, so that the cabin body is accommodated in the cylindrical cavity in the middle of the four brackets, the rudder sheet is correspondingly inserted into the rudder sheet accommodating space between the adjacent brackets, the concave arc surfaces of the brackets are tightly attached to the outer circular surface of the cabin body to realize the positioning of the brackets, the zero position of the rudder sheet is debugged through the matching of the opposite side surfaces of the two adjacent brackets and the rudder sheet, the zero position synchronous debugging of the four rudder sheets can be realized through one-time installation and positioning of the four brackets, the structure is simple, the debugging is convenient, and the zero position of the rudder sheet can be quickly and effectively debugged; meanwhile, the distance L1 between the adjacent side surfaces of the two adjacent brackets is larger than the thickness L4 of the rudder piece, a gap is reserved between the rudder piece and the two side surfaces of the adjacent brackets, the zero error range to be met after the rudder piece is installed on the cabin is fully considered, the zero precision of the rudder piece is ensured, the debugging difficulty of the zero position of the rudder piece is reduced, and the debugging efficiency is improved; therefore, the debugging device can realize debugging of the zero position of the rudder piece after the assembly of the cabin body, can reduce the installation error of the related structure during the assembly of the cabin section, reduces the design and processing precision of the related structure of the rudder shaft system, greatly reduces the processing difficulty and the processing cost, is beneficial to batch production, and improves the zero position precision of the rudder piece.
(2) The bracket is provided with a threaded hole penetrating through the fourth side surface and the second outer surface and a through hole penetrating through the fourth outer surface and the third side surface; one end of the screw penetrates through the through hole of one bracket and then is in threaded connection with the threaded hole of the other bracket, so that the two adjacent brackets are fixedly connected together; through screw hole and the through-hole of setting on the support, can utilize the screw to realize the fixed connection of two adjacent supports, be convenient for dismouting between the support through the screw connection for connection structure between the support is simple, convenient.
(3) Because the screw head of screw is provided with the knurl of being convenient for hand and twist, when connecting adjacent support through the screw, can increase frictional force through the knurl, make things convenient for operating personnel manual in with screw in support, need not to use the zero position debugging of instrument can realize the rudder piece.
(4) According to the debugging method, in the cabin body assembly process, the zero position synchronous debugging of the four rudder pieces can be realized through one-time installation and positioning of the four brackets with the same structure by utilizing the open spaces of the four adjacent rudder pieces, and the zero position debugging of the single rudder piece, the two rudder pieces and the three rudder pieces can be realized through the combined installation and positioning of the different number of brackets.
(5) In the debugging process by adopting the debugging method, when the rudder piece operation is executed in the third step, gaps between each rudder piece and the first side face and gaps between each rudder piece and the fourth side face are equal in the thickness direction of the rudder piece, so that the four rudder pieces can be ensured to be exactly in zero positions, and the zero position precision of the four rudder pieces can be further improved through the operation.
Drawings
FIG. 1 is a schematic structural view of a rudder piece zero-position combined type debugging device;
FIG. 2 is a side view of the rudder blade zero-position combination type debugging device of FIG. 1;
FIG. 3 is a schematic view of the first bracket in FIG. 1;
FIG. 4 is a schematic cross-sectional view of the first bracket of FIG. 3;
FIG. 5 is a schematic view of the rudder blade debugging device of FIG. 1;
FIG. 6 is a side view of FIG. 5;
FIG. 7 is a schematic view of the structure when debugging two rudder plates;
fig. 8 is a schematic diagram of the structure when a single rudder blade is debugged.
Wherein 1-first bracket, 2-second bracket, 3-third bracket, 4-fourth bracket, 5-first screw, 6-second screw, 7-third screw, 8-fourth screw, 9-cabin, 10-rudder shaft, 11-first rudder piece, 12-second rudder piece, 13-third rudder piece, 14-fourth rudder piece, 15-inner surface, 16-bump, 17-cylindrical cavity, 18-containing space, 19-first side, 20-second side, 21-third side, 22-fourth side, 23-first outer surface, 24-second outer surface, 25-third outer surface, 26-fourth outer surface, 27-fifth outer surface, 28-threaded hole, 29-through hole
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
Example 1
The embodiment of the invention provides a rudder piece zero-position combined type debugging device, which comprises four brackets and four screws, wherein the brackets are uniformly distributed along the circumferential direction, as shown in the structures of fig. 1 and 2; in the present embodiment, the four brackets have the same structure, namely, a first bracket 1, a second bracket 2, a third bracket 3 and a fourth bracket 4 which are distributed in the counterclockwise direction in fig. 1, and each bracket is called a head end in the front and a tail end in the rear in the counterclockwise direction; the four screws have the same structure and are positioned at four corners of the debugging device, namely a first screw 5, a second screw 6, a third screw 7 and a fourth screw 8 which are distributed in the anticlockwise direction in fig. 1; the first screw 5 connects the head end of the first bracket 1 and the tail end of the second bracket 2 together; the second screw 6 connects the head end of the second bracket 2 and the tail end of the third bracket 3 together; the third screw 7 connects the head end of the third bracket 3 and the tail end of the fourth bracket 4 together; the head end of the fourth bracket 4 and the tail end of the first bracket 1 are connected together by the fourth screw 8, so that the four brackets are sequentially connected end to end through the four screws to form a closed annular structure; as shown in the structure of fig. 5, the rudder pieces are illustrated by taking a first rudder piece 11, a second rudder piece 12, a third rudder piece 13 and a fourth rudder piece 14 which are circumferentially distributed around the cabin 9 as an example, and when in debugging, the first rudder piece 11 is inserted into a gap between the first bracket 1 and the second bracket 2, the second rudder piece 12 is inserted into a gap between the second bracket 2 and the third bracket 3, the third rudder piece 13 is inserted into a gap between the third bracket 3 and the fourth bracket 4, and the fourth rudder piece 14 is inserted into a gap between the fourth bracket 4 and the first bracket 1;
as shown in the structures of fig. 3 and 4, the inner surface 15 of the bracket is a concave arc surface, and the radius R of the concave arc surface is equal to the radius of the outer circular surface of the cabin body 9; the bracket is provided with two side surfaces along the circumferential direction of the inward-concave arc surface, the two side surfaces are inclined surfaces extending along the radial direction of the inward-concave arc surface, one side surface is provided with a lug 16 at the outer end part of the side surface, and the lug 16 is of a cuboid structure;
a screw is fixedly connected between any two adjacent brackets along the circumferential direction, the four brackets are opposite to each other, a cylindrical cavity 17 is formed between the four brackets, and a rudder piece accommodating space 18 is formed between the four brackets; the distance L1 between adjacent sides of two adjacent brackets is greater than the thickness L4 of the rudder sheet.
The rudder piece zero-position combined type debugging device comprises four brackets which are uniformly distributed along the circumferential direction, and screws which are used for fixedly connecting the four brackets in pairs; the inner surface 15 of the bracket is a concave arc surface with the same radius as the outer circular surface of the cabin 9, and a cylindrical cavity 17 for accommodating the cabin 9 is formed among the four brackets; the two side surfaces of the brackets are inclined surfaces extending along the radial direction of the inward-concave arc surface, one side surface is provided with a lug 16 at the outer end part, a rudder piece accommodating space 18 is formed between two adjacent brackets through the lug 16, and the distance L1 between the side surfaces of the two adjacent brackets is larger than the thickness L4 of the rudder piece. When the debugging device is adopted to debug the zero position of the rudder piece, four brackets are arranged in the open space of the adjacent rudder piece at the peripheral side of the cabin body 9, so that the cabin body 9 is accommodated in the cylindrical cavity 17 in the middle of the four brackets, the rudder piece is correspondingly inserted into the rudder piece accommodating space 18 between the adjacent brackets respectively, the concave arc surface of the brackets and the outer circular surface of the cabin body 9 are tightly attached to realize the bracket positioning, the debugging of the zero position of the rudder piece is realized through the matching of the opposite side surfaces of the two adjacent brackets and the rudder piece, the zero position synchronous debugging of the four rudder pieces can be realized through one-time installation positioning of the four brackets, the structure is simple, the debugging is convenient, and the zero position of the rudder piece can be quickly and effectively debugged; meanwhile, the distance L1 between the adjacent side surfaces of the two adjacent brackets is larger than the thickness L4 of the rudder piece, a gap is reserved between the rudder piece and the two side surfaces of the adjacent brackets, the zero error range to be met after the rudder piece is installed on the cabin 9 is fully considered, the zero precision of the rudder piece is ensured, the debugging difficulty of the zero position of the rudder piece is reduced, and the debugging efficiency is improved; therefore, the debugging device can realize debugging of the zero position of the rudder piece after the assembly of the cabin body 9, can reduce the installation error of the related structure during the assembly of the cabin section, reduces the design and processing precision of the related structure of the rudder shaft 10, greatly reduces the processing difficulty and the processing cost, is beneficial to batch production, and improves the zero position precision of the rudder piece.
In a specific embodiment, as shown in the structures in fig. 2 and 6, two end faces of the bracket are parallel planes and are perpendicular to the central axis of the concave arc surface;
as shown in fig. 3, the bump 16 makes one side of the bracket consist of a first side 19, a second side 20 and a third side 21, which are sequentially connected from inside to outside, and the other side is a fourth side 22; wherein the first side 19, the second side 20, the third side 21, and the fourth side 22 are all parallel to the central axis of the concave arc surface; the first side surface 19 and the fourth side surface 22 extend along the radial direction of the concave arc surface, the third side surface 21 is parallel to the first side surface 19, the second side surface 20 is parallel to the fourth side surface 22, and the second side surface 20 is perpendicular to the first side surface 19;
the outer surface of the bracket is composed of a first outer surface 23, a second outer surface 24, a third outer surface 25, a fourth outer surface 26 and a fifth outer surface 27 which are sequentially connected; the first outer surface 23, the second outer surface 24, the third outer surface 25, the fourth outer surface 26 and the fifth outer surface 27 are all parallel to the central axis of the concave arc surface, the first outer surface 23 perpendicularly intersects the fourth side surface 22, the first outer surface 23 is parallel to the fourth outer surface 26, the second outer surface 24 is parallel to the fifth outer surface 27, the second outer surface 24 is perpendicular to the first outer surface 23, an included angle between the third outer surface 25 and the second outer surface 24 is 135 degrees, and the fifth outer surface 27 perpendicularly intersects the third side surface 21;
as shown in the structure of fig. 4, the bracket is provided with a screw hole 28 penetrating the fourth side surface 22 and the second outer surface 24, and a through hole 29 penetrating the fourth outer surface 26 and the third side surface 21, the through hole 29 penetrating the bump 16; one end of the screw passes through the through hole 29 of one bracket and then is in threaded connection with the threaded hole 28 of the other bracket, so as to fixedly connect the two adjacent brackets together. As shown in the structure of fig. 5, when the first bracket 1 and the second bracket 2 are connected through the first screw 5, the threaded end of the first screw 5 passes through the through hole 29 of the first bracket 1 and then is in threaded fit with the threaded hole 28 of the second bracket 2, so that the head end of the first bracket 1 and the tail end of the second bracket 2 are fixedly connected together.
Since the bracket is provided with a threaded hole 28 through the fourth side 22 and the second outer surface 24, and a through hole 29 through the fourth outer surface 26 and the third side 21; one end of the screw passes through the through hole 29 of one bracket and then is in threaded connection with the threaded hole 28 of the other bracket, so as to fixedly connect the two adjacent brackets together; through screw hole 28 and through-hole 29 that set up on the support, can utilize the screw to realize the fixed connection of two adjacent supports, be convenient for dismouting between the support through the screw connection for connection structure between the support is simple, convenient.
As shown in the structures of fig. 1, 2, 5 and 6, the distance between the two end faces of the bracket is L3, and the length of a rudder piece arranged on the cabin body 9 is L6, wherein L3 is less than L6; the central angle corresponding to the concave arc surface is 90 degrees; the rudder piece is arranged on the cabin body 9, and the zero angle precision allowable error is theta, wherein L1/2=L4/2+L3. Arctan theta; the distance between the second side surface 20 and the central axis of the concave arc surface is L2; the distance between the slightly chord of the rudder piece and the central axis of the cabin 9 is L5, and L2 is more than L5. The screw head of the screw is provided with knurling which is convenient for hand screwing.
Because the screw head of screw is provided with the knurl of being convenient for hand and twist, when connecting adjacent support through the screw, can increase frictional force through the knurl, make things convenient for operating personnel manual in with screw in support, need not to use the zero position debugging of instrument can realize the rudder piece.
Example two
The embodiment of the invention provides a debugging method adopting the debugging device, which comprises the following steps:
fixing a cabin 9 with rudder pieces, keeping the central axis of the outer circular surface of the cabin 9 horizontal, and rotating the four rudder pieces to the vicinity of a zero position;
placing four brackets in the open spaces of two adjacent rudder pieces, uniformly distributing two end surfaces of the four brackets on two sides of the rudder shaft 10, installing screws on the four brackets and slowly screwing the screws to gradually screw the four screws, so that the concave arc surfaces of the brackets are close to the outer circular surface of the cabin body 9;
step three, when the concave arc surfaces of the four brackets are close to the outer circular surface of the cabin body 9, zero debugging of the four rudder pieces is completed;
when the concave arc surfaces of the four brackets are not close to the outer circular surface of the cabin 9, the first side surface 19 or the fourth side surface 22 of the brackets are in contact with the rudder piece and are in line contact, the rudder piece in contact with the first side surface 19 or the fourth side surface 22 of the brackets is rotated, so that the contact line of the rudder piece and the first side surface 19 or the fourth side surface 22 is close to the rudder shaft 10 on the rudder piece, if the contact line is far away from the rudder shaft 10, the rudder piece is reversely rotated, and the corresponding screw is slowly screwed in until the concave arc surfaces of the four brackets are close to the outer circular surface of the cabin 9, zero debugging of the four rudder pieces is completed, and zero error is +/-theta.
In the assembly process of the cabin body 9, the debugging method utilizes the open space of two adjacent rudder pieces at four places, can realize zero position synchronous debugging of four rudder pieces through one-time installation and positioning of four brackets with the same structure, can realize zero position debugging of single rudder piece, two rudder pieces and three rudder pieces through combined installation and positioning of different number of brackets, and is simple and practical, and the debugging method can be used for debugging zero positions of different number of rudder pieces quickly and effectively. As shown in the structure of fig. 7, the first rudder piece 11 and the second rudder piece 12 are zero-adjusted by using the first bracket 1, the second bracket 2 and the third bracket 3 combined. As shown in the structure of fig. 8, the first rudder blade 11 is zero-position debugged by adopting the combined first bracket 1 and second bracket 2.
On the basis of the above debugging method, when turning the rudder pieces in the third step to carry out zero debugging, the gaps between each rudder piece and the first side surface 19 and the fourth side surface 22 can be equal along the thickness direction of the rudder piece, and at this time, the zero positions of the four rudder pieces are 0 degrees.
In the debugging process by adopting the debugging method, when the rudder piece operation is executed in the third step, the gaps between each rudder piece and the first side surface 19 and the fourth side surface 22 are equal along the thickness direction of the rudder piece, so that the four rudder pieces can be ensured to be exactly at zero positions, and the zero position precision of the four rudder pieces can be further improved by the operation.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The rudder piece zero-position combined type debugging device is characterized by comprising four brackets and four screws, wherein the brackets are uniformly distributed along the circumferential direction;
the inner surface of the bracket is a concave arc surface, and the radius of the concave arc surface is equal to the radius of the outer circular surface of the cabin body; the bracket is provided with two side surfaces along the circumferential direction of the inward-concave arc surface, the two side surfaces are inclined surfaces extending along the radial direction of the inward-concave arc surface, and the outer end part of one side surface is provided with a bump;
the screw is fixedly connected between any two adjacent brackets along the circumferential direction, the four brackets are opposite to each other, a cylindrical cavity is formed between the four brackets, and a rudder piece accommodating space is formed between the four brackets; the distance L1 between the adjacent side surfaces of two adjacent brackets is greater than the thickness L4 of the rudder sheet;
the two end faces of the bracket are parallel planes and are perpendicular to the central axis of the concave arc surface;
the convex blocks enable one side surface of the bracket to be composed of a first side surface, a second side surface and a third side surface which are sequentially connected from inside to outside, and the other side surface is a fourth side surface; the first side face, the second side face, the third side face and the fourth side face are all parallel to the central axis of the concave arc face, the first side face and the fourth side face extend along the radial direction of the concave arc face, the third side face is parallel to the first side face, and the second side face is parallel to the fourth side face and perpendicular to the first side face;
the outer surface of the bracket is composed of a first outer surface, a second outer surface, a third outer surface, a fourth outer surface and a fifth outer surface which are sequentially connected; the first outer surface, the second outer surface, the third outer surface, the fourth outer surface and the fifth outer surface are all parallel to the central axis of the concave arc surface, the first outer surface vertically intersects the fourth side surface, the first outer surface is parallel to the fourth outer surface, the second outer surface is parallel to the fifth outer surface, the second outer surface is vertical to the first outer surface, an included angle between the third outer surface and the second outer surface is 135 degrees, and the fifth outer surface vertically intersects the third side surface;
the bracket is provided with a threaded hole penetrating through the fourth side surface and the second outer surface and a through hole penetrating through the fourth outer surface and the third side surface;
one end of the screw penetrates through the through hole of one bracket and then is in threaded connection with the threaded hole of the other bracket, and the screw is used for fixedly connecting the two adjacent brackets together;
the distance between the two end faces of the bracket is L3, and the length of a rudder piece arranged on the cabin body is L6;
the central angle corresponding to the inward-concave arc surface is 90 degrees;
the rudder piece is arranged at the rear zero position of the cabin body, and the precision allowable error of the zero position angle is theta, wherein L1/2=L4/2+L3. Arctan theta;
the distance between the second side surface and the central axis of the inward-concave arc surface is L2;
the distance between the slightly chord of the rudder blade and the central axis of the cabin body is L5, and L2 is more than L5.
2. The debugging device of claim 1, wherein L3 < L6.
3. Debugging device according to any one of claims 1-2, wherein the screw head of the screw is provided with knurling facilitating manual screwing.
4. A debugging method using the debugging device according to any one of claims 1-3, comprising the steps of:
fixing a cabin provided with rudder pieces, keeping the central axis of the outer circular surface of the cabin horizontal, and rotating the four rudder pieces to the vicinity of a zero position;
placing four brackets in the open spaces of two adjacent rudder pieces, uniformly distributing two end surfaces of the four brackets on two sides of a rudder shaft, installing screws on the four brackets and slowly screwing the screws to gradually screw the four screws into the open spaces, so that the concave arc surfaces of the brackets are close to the outer circular surface of the cabin;
step three, when the concave arc surfaces of the four brackets are abutted against the outer circular surface of the cabin body, zero debugging of the four rudder pieces is completed;
when the concave arc surfaces of the four brackets are not abutted against the outer circular surface of the cabin body, the first side surface or the fourth side surface of the brackets are in line contact with the rudder piece, the rudder piece in line contact with the first side surface or the fourth side surface of the brackets is rotated, so that the contact line of the rudder piece and the first side surface or the fourth side surface is close to the rudder shaft on the rudder piece, if the contact line is far away from the rudder shaft, the rudder piece is reversely rotated, and the corresponding screw is slowly screwed in until the concave arc surfaces of the four brackets are abutted against the outer circular surface of the cabin body, zero debugging of the four rudder pieces is completed, and zero error is +/-theta.
5. The debugging method of claim 4, wherein when turning the rudder pieces in the third step, gaps between each rudder piece and the first side surface and the fourth side surface are made equal in the thickness direction of the rudder piece, and four rudder piece zero positions are at 0 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210771602.1A CN115164653B (en) | 2022-06-30 | 2022-06-30 | Rudder piece zero-position combined type debugging device and debugging method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210771602.1A CN115164653B (en) | 2022-06-30 | 2022-06-30 | Rudder piece zero-position combined type debugging device and debugging method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115164653A CN115164653A (en) | 2022-10-11 |
| CN115164653B true CN115164653B (en) | 2023-12-05 |
Family
ID=83489475
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210771602.1A Active CN115164653B (en) | 2022-06-30 | 2022-06-30 | Rudder piece zero-position combined type debugging device and debugging method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115164653B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001174198A (en) * | 1999-12-21 | 2001-06-29 | Mitsubishi Electric Corp | Guided missile |
| CN109059682A (en) * | 2018-08-31 | 2018-12-21 | 西安航天动力技术研究所 | A kind of steering engine mechanical zero fast alignment device |
| CN109163626A (en) * | 2018-09-21 | 2019-01-08 | 湖南金翎箭信息技术有限公司 | A kind of zero adjuster and method of the Missile Actuator rudder wing |
| CN109737825A (en) * | 2019-01-28 | 2019-05-10 | 西安深瞳智控技术有限公司 | Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method |
| RU2722329C1 (en) * | 2019-07-25 | 2020-05-29 | Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени Академика П.Д. Грушина" | Missile |
| CN113154958A (en) * | 2021-04-09 | 2021-07-23 | 北京机械设备研究所 | Mechanical zero calibration device and method for harmonic reducer steering engine |
| EP3882564A1 (en) * | 2020-03-14 | 2021-09-22 | Diehl Defence GmbH & Co. KG | Guided missile and method for ejecting a guided missile from a support platform |
| CN113513952A (en) * | 2021-03-30 | 2021-10-19 | 北京机械设备研究所 | Electric steering engine, zero position calibration method and device for electric steering engine and storage medium |
-
2022
- 2022-06-30 CN CN202210771602.1A patent/CN115164653B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001174198A (en) * | 1999-12-21 | 2001-06-29 | Mitsubishi Electric Corp | Guided missile |
| CN109059682A (en) * | 2018-08-31 | 2018-12-21 | 西安航天动力技术研究所 | A kind of steering engine mechanical zero fast alignment device |
| CN109163626A (en) * | 2018-09-21 | 2019-01-08 | 湖南金翎箭信息技术有限公司 | A kind of zero adjuster and method of the Missile Actuator rudder wing |
| CN109737825A (en) * | 2019-01-28 | 2019-05-10 | 西安深瞳智控技术有限公司 | Guided missile rudder face mechanical zero and electrical null position while calibration tool and application method |
| RU2722329C1 (en) * | 2019-07-25 | 2020-05-29 | Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени Академика П.Д. Грушина" | Missile |
| EP3882564A1 (en) * | 2020-03-14 | 2021-09-22 | Diehl Defence GmbH & Co. KG | Guided missile and method for ejecting a guided missile from a support platform |
| CN113513952A (en) * | 2021-03-30 | 2021-10-19 | 北京机械设备研究所 | Electric steering engine, zero position calibration method and device for electric steering engine and storage medium |
| CN113154958A (en) * | 2021-04-09 | 2021-07-23 | 北京机械设备研究所 | Mechanical zero calibration device and method for harmonic reducer steering engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115164653A (en) | 2022-10-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106813537B (en) | A kind of helm gear of four axis combination precision actuation | |
| EP3725458B1 (en) | Bolt tightening mechanism and battery pack mounting bracket | |
| CN204495559U (en) | A kind of resilient bearing torsional rigidity proving installation | |
| CN111189634B (en) | Large RV reducer transmission error testing device and testing method | |
| CN115164653B (en) | Rudder piece zero-position combined type debugging device and debugging method | |
| JP2021084186A (en) | Tool change device | |
| CN109500528B (en) | Welding device for triangular frame of steel structure spherical reticulated shell | |
| CN115200426B (en) | Rudder sheet zero position self-adaptive debugging device and debugging method | |
| CN204028430U (en) | A kind of angle adjustment joint platform | |
| CN211178214U (en) | Motor centering device for rack | |
| CN109466802A (en) | A kind of aerospace craft flight control system and its Electromechanical Actuators | |
| CN104002083A (en) | Multi-vehicle-type welding fixture frame connecting mechanism | |
| CN212172576U (en) | Auxiliary tool for mounting aircraft landing gear | |
| CN115235298B (en) | Rudder sheet zero debugging tool and debugging method | |
| CN111006803B (en) | Torsion bar spring angular deviation fixing and retaining device for torsion test and test method | |
| CN208614637U (en) | Circular shaft clamping tooling | |
| CN206668919U (en) | Power transmission shaft and test carriage | |
| JPS58193931A (en) | Flexible shaft coupling | |
| JP4234656B2 (en) | Waveguide connection structure | |
| CN108562313A (en) | Connection sheet and structure of installing encoders | |
| CN214216126U (en) | Rudder device of aircraft and aircraft | |
| CN217453881U (en) | Zero alignment tool for angular displacement sensor | |
| CN219131277U (en) | Main machine box machining component internal stay clamp | |
| CN115636088A (en) | Novel projectile body cabin section connecting mechanism | |
| CN203512022U (en) | Fixing device for control plane of aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |