CN111306994B - Reusable composite material missile bracket - Google Patents
Reusable composite material missile bracket Download PDFInfo
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- CN111306994B CN111306994B CN202010255060.3A CN202010255060A CN111306994B CN 111306994 B CN111306994 B CN 111306994B CN 202010255060 A CN202010255060 A CN 202010255060A CN 111306994 B CN111306994 B CN 111306994B
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- missile
- bracket
- annular
- groove
- axial
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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
Abstract
The invention discloses a reusable composite material missile bracket, and belongs to the technical field of launching weapon supporting devices. The reusable composite material missile bracket comprises an annular bracket, a supporting beam and a rotor fixing device; the annular groove of the annular bracket is used for connecting the missile body, and the annular bracket is connected with one end surface of the supporting beam; the rotor fixing device is connected with the other end face of the support beam corresponding to one end face, and the rotor fixing device is used for fixing the rotor. The problem that the missile bracket adopts a split connection structure and cannot bear high overload is solved, and the missile bracket adopts a cylindrical barrel structure and is easy to interfere with a missile; and all are disposable, cause the use cost height, the unable quick response's of unable problem. The invention adopts an assembly connection structure, improves the stability of the whole installation structure, can bear high overload force, avoids interference on the missile, can be repeatedly used for many times, reduces the use cost of the missile bracket and meets the requirement of quick response.
Description
Technical Field
The invention relates to the technical field of launching weapon supporting devices, in particular to a reusable composite material missile bracket.
Background
The missile bracket is an auxiliary support part which guides the missile body to move in the barrel on the missile. Missile brackets are typically made of steel, aluminum alloys, magnesium alloys, plastics, and the like. When the missile is used, after the missile is ejected out of the cylinder, the missile bracket flies out along with the missile body by utilizing airflow resistance and centrifugal force; because the missile bracket is of the "passive" mass of the missile, the mass of the missile bracket is as light as possible; meanwhile, the missile bracket still bears high overload force, if the self mass is overlarge, the missile bracket can also cause overload damage, and when the missile flies away from the barrel, the missile bracket is required to quickly fly out together with the missile body, so that the interference of the missile bracket to the missile is minimized.
The prior missile bracket mainly has two structures: the missile bracket is characterized in that a plurality of arc-shaped plates are clamped on a missile body, the missile body is supported along the radial direction of the missile body, the structure is simple, and the missile bracket is made of composite materials, so that the aim of light weight is fulfilled. However, the missile brackets are of the split connection structure, and the missile brackets are generally light in weight and cannot bear high axial load.
The second missile bracket is a cylindrical barrel structure and is directly sleeved on a missile body to enable the missile body to be supported along the axial direction of the missile body, and the missile bracket is made of metal materials and can bear high overload force. However, the metal material causes the structural arrangement of the missile bracket to be thick and heavy, the overall weight is heavy, and the interference to the missile is large when the missile bracket is used.
In addition, when the existing missile bracket is used, the existing missile bracket needs to fly away together with the missile body, so that the existing missile bracket is a disposable consumable product and cannot be reused. Therefore, the structural design also causes the problem that the missile bracket is high in use cost and cannot meet the requirement of quick response.
Disclosure of Invention
The invention aims to provide a reusable composite material missile bracket, aiming at solving the problems that the missile bracket adopts a split connection structure in the prior art, has lighter weight and can not bear high axial load; the missile bracket adopts a cylindrical barrel structure, and the weight is heavier, so that the missile is easily interfered; and above-mentioned two kinds of structures are disposable, cause the use cost height of guided missile bracket, can't satisfy the technical problem of quick response demand.
The invention provides a reusable composite material missile bracket which comprises an annular bracket, a support beam and a rotor fixing device, wherein the annular bracket is arranged on the support beam;
the annular groove of the annular bracket is used for connecting the missile body, and the annular bracket is connected with one end surface of the supporting beam;
the rotor fixing device is connected with the other end face of the support beam corresponding to one end face, and the rotor fixing device is used for fixing the rotor.
Furthermore, the end surface of the annular bracket connected with the missile body is provided with a radial avoidance groove consistent with the radial direction of the missile body;
the radial avoiding groove is used for protecting a fixing mechanism of the missile body in the radial direction of the outer peripheral surface.
Furthermore, the peripheral surface of the annular bracket is provided with an axial avoidance groove which is parallel to the axial direction of the missile body;
the axial avoidance groove is used for protecting the fixing mechanism of the missile body in the axial direction.
Further, the inner circumferential surface of the annular bracket is connected with an axial guide block, and an axial guide groove is formed between the axial guide block and the inner circumferential surface of the annular bracket;
the axial guide groove is used for guiding the missile body to move along the axial direction of the annular groove.
Furthermore, one end of the axial guide block is connected with a first turnover plate, and the first turnover plate is connected with one end of the inner circumferential surface of the annular bracket;
the other end of the axial guide block is connected with a second turnover plate, and the second turnover plate is connected with the other end of the inner circumferential surface of the annular bracket.
Furthermore, the outer peripheral surface of the annular bracket is connected with an adaptive block;
the adapting block is used for supporting the fixing mechanism of the missile body in the axial direction.
Furthermore, the rotor fixing device comprises a fixing plate, a side rib plate and a stop block;
the fixed plate is connected with the other end face corresponding to one end face of the supporting beam, the side rib plate is connected to the fixed plate, and a limit groove for accommodating the rotor is formed between the side rib plate and the fixed plate;
the stop block is connected to the side rib plate and arranged in the limit groove.
Furthermore, the stop block is provided with a weight reduction groove.
Furthermore, the number of the weight reducing grooves is multiple, and a partition plate is arranged between every two adjacent weight reducing grooves.
Furthermore, the section of the weight-reducing groove is any one of a triangle, a square and an irregular shape.
Compared with the prior art, the reusable composite material missile bracket has the following advantages:
the annular groove of the annular bracket is used for connecting the missile body so as to limit the connection position of the missile body; the annular bracket is connected to one end face of the support beam, and the rotor fixing device is connected to the other end face of the support beam corresponding to one end face of the support beam, so that the annular bracket and the rotor fixing device are respectively arranged on the two end faces of the support beam; the rotor fixing device is used for fixing the rotor and limiting the installation position of the rotor; the annular bracket, the support beam and the rotor fixing device are in an assembly connection structure, so that the mounting position precision of the whole missile bracket is ensured; when the missile is used, under the pushing action of the rotor, the missile bracket bears high overload force along with the missile body, then the missile bracket accelerates to move along the axis of the annular bracket in a shooting way, and the missile bracket is separated from the missile body by utilizing the braking of the rotor, so that the interference on the missile is avoided; the missile bracket disclosed by the invention cannot fly out along with the missile body, can be recycled repeatedly, reduces the use cost of the missile bracket, and can meet the requirement of quick response.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic view of the upper position of a reusable composite missile bracket according to an embodiment of the invention;
FIG. 2 is an enlarged view of portion A of FIG. 1;
FIG. 3 is a schematic structural diagram of an outer side surface of an axial guide block according to an embodiment of the present invention;
FIG. 4 is a schematic structural view of an inner side surface of an axial guide block according to an embodiment of the present invention;
FIG. 5 is a schematic view of the configuration of the lower position of the reusable composite missile bracket provided by an embodiment of the invention;
FIG. 6 is a schematic view of the upper position of the ring holder according to the embodiment of the present invention;
FIG. 7 is a schematic view of the lower position of the ring holder according to the embodiment of the present invention;
FIG. 8 is a structural diagram of a support beam according to an embodiment of the present invention;
fig. 9 is a schematic structural diagram of an upper position of a mover fixing device according to an embodiment of the present invention;
fig. 10 is a schematic structural diagram of a lower position of a mover fixing device according to an embodiment of the present invention;
fig. 11 is a left side view of a mover fixing device provided in an embodiment of the present invention;
fig. 12 is a front view of a mover fixing device according to an embodiment of the present invention.
Description of reference numerals:
100-an annular receptacle; 200-a support beam;
300-mover fixing means; 400-a mover;
101-a ring groove; 102-radial avoidance slots;
103-axial avoidance slots; 104-axial guide block;
105-axial guide grooves; 106-a first flap;
107-a second flap; 108-an adaptation block;
301-a fixed plate; 302-a flank plate;
303-a stop block; 304-a limiting groove;
305-weight reduction slots; 306-partition plate.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 10, the reusable composite missile bracket provided by the present invention comprises an annular bracket 100, a support beam 200 and a mover fixing device 300;
the annular groove 101 of the annular bracket 100 is used for connecting missile bodies, and the annular bracket 100 is connected with one end face of the support beam 200;
the mover fixing device 300 is connected to the other end surface of the support beam 200 corresponding to one end surface, and the mover fixing device 300 is used to fix the mover 400.
In one embodiment of the present invention, as shown in fig. 1, 2, 5 and 8, the ring holder 100 is a cylindrical barrel structure; an annular groove 101 is formed in the middle of the annular bracket 100, and the annular groove 101 is an annular through groove; the missile body is installed in the annular groove 101, and the installation position of the missile body is locked.
In this embodiment, the support beam 200 is a hollow structure, and is a cross beam, and the cross beam is connected and fixed by hollow square pipes.
In other embodiments, the support beam 200 may be configured in other structures according to the actual use requirement, for example: the supporting beam is formed by connecting a plurality of crisscross beams, or the supporting beam is formed by connecting a plurality of built-in annular beams which are sequentially sleeved outside.
In this embodiment, the annular bracket 100 has an upper flange at the upper end and a lower flange at the lower end for connecting with other devices; the lower flanging of the annular bracket 100 is connected to the upper end face of the supporting beam 200 through bolts, the rotor fixing device 300 is connected to the lower end face of the supporting beam 200 through bolts, and the annular bracket 100, the supporting beam 200 and the rotor fixing device 300 are of a split and independently formed structure, and then are assembled through a fastening bolt mechanical connection mode, so that the forming difficulty of the whole missile bracket is simplified, the size assembling precision is guaranteed, the overall weight is reduced to a certain degree, and high overload force can be borne.
The mover fixing device 300 fixes the mover 400 and locks the mounting position of the mover 400.
In the using process, when the missile body is launched, under the pushing of the rotor 400 in the rotor fixing device 300, the whole missile bracket bears high overload force along with the missile body, at the moment, the load is more than 4 tons, the acceleration is more than 8g, and then the missile bracket is accelerated to move along the shooting direction, namely the axial movement of the annular bracket 100; when the missile body reaches a certain stroke, the rotor 400 starts to brake, and the high-acceleration stop of the whole missile bracket is realized through the interaction between the stop block 303 of the rotor fixing device 300 and the rotor 400, wherein the acceleration is more than 40g, so that the interference on the missile is avoided; and after the projectile body breaks away from, the whole missile bracket can not fly out along with the projectile body, and can be used repeatedly, so that the requirement of future quick response and repeated use is met, and the use cost of the missile bracket is reduced.
Further, the end face of the annular bracket 100 connected with the missile body is provided with a radial avoidance groove 102 consistent with the radial direction of the missile body;
the radial avoidance groove 102 is used for protecting the fixing mechanism of the missile body in the radial direction.
In an embodiment of the present invention, as shown in fig. 6, a missile body is installed in an annular groove 101 along the upper end surface of an annular bracket 100, a radial avoidance groove 102 is formed on the upper end surface of the annular bracket 100, the radial avoidance groove 102 is a downward-recessed arc-shaped groove formed on the upper end surface of the annular bracket 100, and the diameter direction of the arc-shaped groove is consistent with the diameter direction of the missile body, so that after the installation of the missile body is completed, because the fixing mechanisms are radially formed on the outer peripheral surface of the missile body, the fixing mechanisms can be protected by using the recessed arc-shaped groove, and the outer peripheral surface of the missile body is prevented from being worn.
In a specific embodiment, two opposite radial avoiding grooves 102 are formed on the upper end surface of the annular bracket 100, and the fixing mechanisms at two opposite positions on the outer circumferential surface of the missile body are respectively protected by the two radial avoiding grooves 102, so that the radial abrasion of the fixing mechanisms on the outer circumferential surface of the missile body is avoided.
In other embodiments, the number of the radial evasion grooves 102 may also be set to other numbers according to the number of the fixing mechanisms on the outer circumferential surface of the missile body, and the specific positions of the radial evasion grooves 102 may also be set correspondingly according to the positions of the fixing mechanisms on the outer circumferential surface of the missile body.
Further, the outer circumferential surface of the annular bracket 100 is provided with an axial avoidance groove 103 parallel to the axial direction of the projectile body;
the axial avoidance groove 103 is used for protecting a fixing mechanism of the missile body in the axial direction of the peripheral surface.
In an embodiment of the present invention, as shown in fig. 6 and 7, an axial evasion groove 103 is formed along the outer circumferential surface of the annular bracket 100, the axial evasion groove 103 is an inwardly recessed arc-shaped groove formed on the outer circumferential surface of the annular bracket 100, and the axial direction of the arc-shaped groove is parallel to the axial direction of the missile body, so after the installation of the missile body is completed, since the fixing mechanisms are axially formed on the outer circumferential surface of the missile body, the recessed arc-shaped groove can be used to protect the fixing mechanisms and avoid abrasion on the outer circumferential surface of the missile body.
In a specific embodiment, the outer circumferential surface of the arc-shaped bracket 100 forms two axial avoiding grooves 103 which are oppositely arranged, and the fixing mechanisms at two positions opposite to the outer circumferential surface of the missile body are respectively protected by the two axial avoiding grooves 103, so that the fixing mechanisms on the outer circumferential surface of the missile body are prevented from being worn along the axial direction of the missile body.
In other embodiments, the number of the axial evasion grooves 103 may also be set to other numbers according to the number of the fixing mechanisms on the outer circumferential surface of the missile body, and the specific positions of the axial evasion grooves 103 may also be set correspondingly according to the positions of the fixing mechanisms on the outer circumferential surface of the missile body.
Further, an axial guide block 104 is connected to the inner circumferential surface of the annular bracket 100, and an axial guide groove 105 is formed between the axial guide block 104 and the inner circumferential surface of the annular bracket 100;
the axial guide slots 105 are used to guide the axial movement of the projectile along the annular slot 101.
In one embodiment of the present invention, as shown in fig. 1 and 2, an axial guide block 104 is bolted to an inner circumferential surface of the ring bracket 100 to form a guide block; as shown in fig. 3 and 4, the axial guide block 104 has a U-shaped cross section, and an axial guide groove 105 is defined between the axial guide block 104 and the inner circumferential surface of the annular bracket 100; the axial guide groove 105 has a square through groove structure so as to guide the projectile body and increase the guiding area of the projectile body.
Further, one end of the axial guide block 104 is connected with a first flap 106, and the first flap 106 is connected with one end of the inner circumferential surface of the annular bracket 100;
the other end of the axial guide 104 is connected to a second flap 107, and the second flap 107 is connected to the other end of the inner circumferential surface of the annular holder 100.
In one embodiment of the present invention, as shown in fig. 1, 2, 3, and 4, a first flap 106 is formed at the upper end of the axial guide block 104, and the first flap 106 is fixedly connected to the upper flap of the inner circumferential surface of the annular bracket 100 by a bolt, so that the connection area between the upper end of the axial guide block 104 and the upper end of the inner circumferential surface of the annular bracket 100 is increased; a second turnover plate 107 is formed under the axial guide block 104, and the second turnover plate 107 is fixedly connected with a downward turnover edge of the inner circumferential surface of the annular bracket 100 by bolts, so that the connection area between the lower end of the axial guide block 104 and the lower end of the inner circumferential surface of the annular bracket 100 is increased.
Further, an adapter block 108 is connected to the outer circumferential surface of the annular bracket 100;
the adapter block 108 is used for supporting the fixing mechanism of the missile body in the axial direction of the outer peripheral surface.
In one embodiment of the present invention, as shown in fig. 6 and 7, an adapter block 108 is connected to the outer circumferential surface of the annular bracket 100 by bolts, the adapter block 108 is in the shape of a bar, and the length of the adapter block 108 is parallel to the axial direction of the annular bracket 100.
In this embodiment, the number of the adapter blocks 108 is plural, the plurality of adapter blocks 108 are respectively bolted to positions on two sides of the outer peripheral surface of the annular bracket 100, which are close to the radial avoidance groove 102, positions on two sides of the axial avoidance groove 103, and positions on two sides of the axial guide block 104, and the positions on two sides of the radial avoidance groove 102, positions on two sides of the axial avoidance groove 103, and positions on two sides of the axial guide block 104 are respectively reinforced by the plurality of adapter blocks 108.
The adapter block 108 is bolted to the ring bracket 100 for easy replacement.
Further, the mover fixing device 300 includes a fixing plate 301, a side rib plate 302, and a stopper 303;
a fixing plate 301 is connected to the other end surface corresponding to one end surface of the support beam 200, a side rib plate 302 is connected to the fixing plate 301, and a limit groove 304 for accommodating the mover 400 is formed between the side rib plate 302 and the fixing plate 301;
the stopper 303 is attached to the side rib 302 and is disposed in the stopper groove 304.
In an embodiment of the present invention, as shown in fig. 9, 10, 11 and 12, the fixing plate 301 is a rectangular plate, and the front end and the rear end of the rectangular plate are arc-shaped structures so as to be adapted to the arc-shaped surface of the lower end surface of the supporting beam 200; the fixing plate 301 is connected to the lower end face of the support beam 200 by bolts, and the mounting position of the fixing plate 301 is locked; the side rib plate 302 is arranged at the bottom of the fixing plate 301 in a penetrating mode through bolts and connected to the lower end face of the supporting beam 200, and the cross section of the side rib plate 302 is of a triangular structure so as to support and fix the lower end face of the fixing plate 301; in the present embodiment, the number of the side ribs 302 is two, and an inverted U-shaped limiting groove 304 is formed between the two side ribs 302 and the fixing plate 301, so that the mover 400 can be received in the limiting groove 304; the number of the stop blocks 303 is two, the inner side surface of each side rib plate 302 is connected with one stop block 303 through bolts, the cross section of each stop block 303 is of a triangular structure, the mover 400 is limited in the limiting groove 304 through the stop blocks 303, and due to the fact that the stop blocks 303 are wearing parts, the stop blocks 303 are connected through bolts, and disassembly, assembly and replacement are facilitated.
Further, the stopper 303 is provided with a weight-reduction groove 305.
Further, the number of the lightening grooves 305 is plural, and a partition 306 is provided between adjacent lightening grooves 305.
In one embodiment of the present invention, as shown in fig. 10, a weight-reducing groove 305 is provided in the lower end surface of the stopper 303, the weight-reducing groove 305 being a groove recessed inward along the lower end surface of the stopper 303, and the weight-reducing groove 305 is provided to reduce the weight of the entire stopper 303.
In one embodiment of the present invention, a weight-reducing slot 305 is disposed on the lower end surface of the stopper 303, and the slotting direction of the weight-reducing slot 305 is parallel to the moving direction of the mover 400; a plurality of screw holes are provided in the lightening groove 305 to facilitate fixing of the side wall of the stopper 303 to the side rib 302 by bolts.
In another embodiment of the present invention, a plurality of weight-reducing grooves 305 are provided on the lower end surface of the stopper 303, and the slotting direction of the weight-reducing grooves 305 is arranged in parallel with the moving direction of the mover 400; the plurality of lightening slots 305 are uniformly distributed, adjacent lightening slots 305 are not communicated, and the lightening slots are arranged at intervals through the partition plate 306, so that each lightening slot 305 is internally provided with a threaded hole, and the side wall of the stop block 303 is conveniently fixed on the lateral rib plate 302 through a bolt.
In another embodiment of the present invention, a lightening groove 305 is formed in the front end surface of the left side of the stopper 303 of fig. 10, and the lightening groove 305 is a through groove formed along the front and rear end surfaces of the stopper 303 such that the slotting direction of the lightening groove 305 is perpendicular to the moving direction of the mover 400; a plurality of screw holes are provided in the lightening groove 305 to facilitate fixing of the side wall of the stopper 303 to the side rib 302 by screws.
Further, the weight-reduction groove 305 has a cross section of any one of a triangle, a square, and an irregular shape.
In one embodiment of the present invention, the lightening slots 305 are triangular in cross-section to accommodate the triangular configuration of the stops 303 to ensure lightening of the weight within the stops 303.
In other embodiments of the present invention, the section of the weight-reducing groove 305 may be square, irregular, etc., as long as the purpose of reducing the weight inside the stopper 303 can be achieved.
In the above embodiment of the invention, the annular bracket 100, the support beam 200, the fixed plate 301 and the side rib plate 302 are all made of carbon fiber composite materials, the stop block 303 is made of aluminum alloy or titanium alloy, the whole missile bracket adopts the above connection structure, the main body is made of composite materials, and the local part is made of metal materials, so that the missile bracket can bear high overload force without causing interference to the missile, can be used for multiple times, and saves the cost.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. A reusable composite material missile bracket, characterized by comprising an annular bracket (100), a support beam (200) and a rotor fixture (300);
the annular groove (101) of the annular bracket (100) is used for connecting missile bodies, and the annular bracket (100) is connected with one end face of the support beam (200);
the rotor fixing device (300) is connected with the other end face of the support beam (200) corresponding to one end face, and the rotor fixing device (300) is used for fixing the rotor (400);
an axial guide block (104) is connected to the inner circumferential surface of the annular bracket (100), and an axial guide groove (105) is formed between the axial guide block (104) and the inner circumferential surface of the annular bracket (100);
the axial guide groove (105) is used for guiding the missile projectile to move axially along the annular groove (101);
the mover fixing device (300) comprises a fixing plate (301), a side rib plate (302) and a stop block (303);
the fixing plate (301) is connected to the other end face corresponding to one end face of the supporting beam (200), the side rib plate (302) is connected to the fixing plate (301), and a limiting groove (304) for accommodating the rotor (400) is formed between the side rib plate (302) and the fixing plate (301);
the stop block (303) is connected to the side rib plate (302) and is arranged in the limit groove (304).
2. -reusable composite missile bracket according to claim 1 wherein the end face of the annular bracket (100) that connects to the missile hull is provided with a radial escape slot (102) coinciding with the radial direction of the missile hull;
the radial avoidance groove (102) is used for protecting a fixing mechanism of the missile body in the radial direction of the outer peripheral surface.
3. A reusable composite missile bracket according to claim 1 wherein the outer circumferential surface of the annular bracket (100) is provided with axial evasion slots (103) parallel to the axial direction of the missile body;
the axial avoidance groove (103) is used for protecting a fixing mechanism of the missile body in the axial direction of the outer peripheral surface.
4. The reusable composite missile bracket of claim 1 wherein the axial guide block (104) has a first flap (106) attached to one end of the axial guide block, the first flap (106) being attached to one end of the inner circumferential surface of the annular bracket (100);
the other end of the axial guide block (104) is connected with a second turnover plate (107), and the second turnover plate (107) is connected with the other end of the inner peripheral surface of the annular bracket (100).
5. The reusable composite material missile bracket of claim 1 wherein an adapter block (108) is attached to the outer circumferential surface of the annular bracket (100);
the adaptation block (108) is used for supporting a fixing mechanism of the missile body in the axial direction of the peripheral surface.
6. The reusable composite missile bracket of claim 1 wherein the stop block (303) is provided with weight reduction slots (305).
7. The reusable composite missile bracket of claim 6 wherein the number of weight-reducing slots (305) is a plurality and a spacer plate (306) is disposed between adjacent weight-reducing slots (305).
8. The reusable composite missile bracket of claim 7 wherein the weight-reduction slots (305) are any one of triangular, square and irregular in cross-section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010255060.3A CN111306994B (en) | 2020-05-07 | 2020-05-07 | Reusable composite material missile bracket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010255060.3A CN111306994B (en) | 2020-05-07 | 2020-05-07 | Reusable composite material missile bracket |
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| CN111306994A CN111306994A (en) | 2020-06-19 |
| CN111306994B true CN111306994B (en) | 2021-06-01 |
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| CN202010255060.3A Active CN111306994B (en) | 2020-05-07 | 2020-05-07 | Reusable composite material missile bracket |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115307495B (en) * | 2022-08-09 | 2023-10-03 | 厦门普诚科技有限公司 | Bullet storage device |
| CN116428077A (en) * | 2023-03-16 | 2023-07-14 | 大连理工大学 | Main frame structure of carrier rocket engine with I-shaped section load beam |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH363908A (en) * | 1956-04-05 | 1962-08-15 | Boelkow Entwicklungen Kg | Rocket propelled missile |
| CN105387764A (en) * | 2015-11-25 | 2016-03-09 | 中国空空导弹研究院 | Guided missile supporting table and drum missile butt joint tool employing guided missile supporting table |
| CN205279856U (en) * | 2015-11-25 | 2016-06-01 | 中国空空导弹研究院 | Prevent rolling guided missile brace table of guided missile and butt joint frock |
| CN206691376U (en) * | 2016-09-20 | 2017-12-01 | 中国人民解放军海军航空工程学院 | A kind of quick carry servicing unit of guided missile |
-
2020
- 2020-05-07 CN CN202010255060.3A patent/CN111306994B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH363908A (en) * | 1956-04-05 | 1962-08-15 | Boelkow Entwicklungen Kg | Rocket propelled missile |
| CN105387764A (en) * | 2015-11-25 | 2016-03-09 | 中国空空导弹研究院 | Guided missile supporting table and drum missile butt joint tool employing guided missile supporting table |
| CN205279856U (en) * | 2015-11-25 | 2016-06-01 | 中国空空导弹研究院 | Prevent rolling guided missile brace table of guided missile and butt joint frock |
| CN206691376U (en) * | 2016-09-20 | 2017-12-01 | 中国人民解放军海军航空工程学院 | A kind of quick carry servicing unit of guided missile |
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|---|---|
| CN111306994A (en) | 2020-06-19 |
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