CN109018275B - Vortex excitation oscillation self-adaptive suppression device of underwater vehicle - Google Patents
Vortex excitation oscillation self-adaptive suppression device of underwater vehicle Download PDFInfo
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- CN109018275B CN109018275B CN201810942821.5A CN201810942821A CN109018275B CN 109018275 B CN109018275 B CN 109018275B CN 201810942821 A CN201810942821 A CN 201810942821A CN 109018275 B CN109018275 B CN 109018275B
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- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
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Abstract
The invention discloses a vortex excitation oscillation self-adaptive suppression device for an underwater vehicle. The device comprises six parts, namely a fixed vertical wing, a rotatable vertical wing, a fixed horizontal wing, a rotatable horizontal wing, a cylindrical mandrel and a rubber gasket; wherein the rotatable vertical wing is connected with the fixed vertical wing through the cylindrical mandrel; the rotatable horizontal wing is connected with the fixed horizontal wing through the cylindrical mandrel; the fixed vertical wing and the fixed horizontal wing are connected and fastened through a bolt; the rotatable vertical wing and the rotatable horizontal wing can rotate around the cylindrical mandrel so as to adapt to different incoming flow directions in the ocean; the angle between the rotatable streamline wing and the incoming flow direction is adjusted in a self-adaptive mode, so that the formation and development of vortices are restrained, and the whole underwater vehicle can be quickly restored to a balanced state. The invention can reduce deflection and shake of the underwater vehicle under the action of vortex-induced oscillation, and has high application value in marine environment.
Description
Technical Field
The invention belongs to the technical field of ocean engineering, and particularly relates to a vortex excitation oscillation self-adaptive suppression device for an underwater vehicle.
Background
With the continuous acceleration of exploration of oceans by human beings, people increasingly realize that oceans are bound to become a basic environment for human beings to live, and oceans have abundant resources such as organisms and mineral products to become an important fulcrum of economic development and are an important outlet for solving population expansion, resource shortage and environmental deterioration; the ocean is an important factor influencing global climate and carbon cycle due to huge water area and water storage capacity, and is an important object for researching human living environment; oceans have been regarded as an important defense barrier due to their permeability and natural geographic pattern, and are highly valued by countries throughout the world.
At present, the development of blue ocean land and the expansion of living and developing space have been raised as national strategies of various countries in the world along the sea. Ocean detection engineering and equipment are the basis for ocean development, control and comprehensive management, the national ocean competitiveness is intensively reflected, and the ocean engineering equipment technical level marks the national comprehensive national strength and the scientific and technological level to a certain extent. In the field of marine engineering equipment, seabed sonar systems are increasingly used in modern anti-diving, marine hydrology and resource surveying. However, both the active sonar system and the passive sonar system are affected by vortex-induced oscillation during the working process, so that the underwater vehicle deflects, overturns and swings to different degrees. In the test process, the phenomenon of trembling of the monitoring system caused by vortex excitation oscillation is found, so that the cable is broken due to fatigue damage, the cable core is broken, the signal wire is in electric leakage and short circuit, the cable is broken, and the major safety accident that the ocean monitoring equipment is lost is caused, so that the method has important significance for effectively preventing the vortex-induced vibration on the design and research of the underwater vehicle.
At present, the influence of vortex-induced oscillation is reduced by using streamline airfoil design or active control, and the effect of solving the vortex-induced oscillation in a self-adaptive manner cannot be effectively achieved by using the streamline airfoil design under the condition of complex incoming flow environments such as ocean and the like generally existing; the active control is difficult to install and maintain and high in cost, and meanwhile, the active control method is high in control difficulty and complexity in the actual operation process.
Disclosure of Invention
The invention aims to provide an adaptive suppression device for vortex excitation oscillation of an underwater vehicle, which has a simple structure and reliable performance and can cope with incoming flows in any direction.
The technical scheme for realizing the purpose of the invention is as follows: a vortex excitation oscillation self-adaptive suppression device for an underwater vehicle comprises a right side fixed vertical wing, a left side fixed vertical wing, a right side rotatable vertical wing, a left side rotatable vertical wing, an upper fixed horizontal wing, a middle fixed horizontal wing, a lower fixed horizontal wing, a rotatable horizontal wing and three cylindrical mandrels;
the right rotatable vertical wing and the left rotatable vertical wing are respectively connected with the right fixed vertical wing and the left fixed vertical wing through a cylindrical mandrel; the rotatable horizontal wing is connected with the upper fixed horizontal wing through the cylindrical mandrel; the right fixed vertical wing and the left fixed vertical wing are respectively connected and fastened with the upper fixed horizontal wing, the middle fixed horizontal wing and the lower fixed horizontal wing through bolts;
the upper fixed type horizontal wing and the rotatable type horizontal wing are positioned through the cylindrical mandrel, and meanwhile, the rotatable type horizontal wing realizes rotation angle limitation through the arc-shaped groove and the cylindrical boss; the right fixed vertical wing and the left fixed vertical wing are respectively positioned with the right rotatable vertical wing and the left rotatable vertical wing through the cylindrical mandrel, and the right rotatable vertical wing and the left rotatable vertical wing realize rotation angle limitation through the arc-shaped groove and the cylindrical boss.
Furthermore, the translational freedom degrees of the rotatable horizontal wing, the right rotatable vertical wing and the left rotatable vertical wing are limited by the rotatable horizontal wing, the right rotatable vertical wing, the left rotatable vertical wing and the left rotatable vertical wing through two side baffles and a cylindrical mandrel;
the rotatable horizontal wing, the right rotatable vertical wing and the left rotatable vertical wing can rotate freely around the cylindrical mandrel, and the rotation amplitude of the rotatable horizontal wing, the right rotatable vertical wing and the left rotatable vertical wing is limited by the upper cylindrical boss of the rotatable horizontal wing, the right rotatable vertical wing and the left rotatable vertical wing and the upper circular arc-shaped grooves of the upper fixed horizontal wing, the middle fixed horizontal wing, the lower fixed horizontal wing, the right fixed vertical wing and the left fixed vertical wing.
Furthermore, the depth and the width of the arc-shaped groove are respectively 1-1.2 cm larger than the height and the diameter of the cylindrical boss, the rotatable horizontal wing, the right rotatable vertical wing and the left rotatable vertical wing are only in contact with the two ends of the groove in the rotating process, contact collision cannot occur at other positions, and the rotating amplitude limited by the arc-shaped groove is within the range of +/-20 degrees.
Furthermore, cylindrical grooves are formed in two ends of the right rotatable vertical wing, the cylindrical grooves are matched with the cylindrical special rubber gasket for use, and the cylindrical special rubber gasket is fixedly connected with the bottom surface of the cylindrical grooves by adopting an adhesive method; a first circular through hole is formed in the center of the end face of the cylindrical groove and used for being matched with the first cylindrical mandrel, and two ends of the first cylindrical mandrel are fixed through a first nut and a first flat washer, so that the right rotatable vertical wing can rotate around the first cylindrical mandrel;
the cylindrical groove end face is further provided with a first cylindrical boss, the first cylindrical boss is located on the outer side of the first circular through hole and is matched with the first circular arc-shaped groove in the right fixed vertical wing for use, the rotating angle of the right rotatable vertical wing is +/-20 degrees, the first cylindrical boss is only in limit contact with two limit end positions of the first circular arc-shaped groove, and the first cylindrical boss is not in contact with the bottom face and the side face of the first circular arc-shaped groove in the moving process.
Furthermore, first baffle plates are arranged at two ends of the right fixed vertical wing and are in direct contact with the cylindrical special rubber gasket, and the first baffle plates limit the translational freedom degree of the right rotatable vertical wing along the first cylindrical mandrel;
the circular end face of the first baffle plate is provided with a first rectangular groove, a first circular arc-shaped groove and a second circular through hole, the right fixed vertical wing and the right rotatable vertical wing are installed in a matched mode, and the first cylindrical boss enters the first circular arc-shaped groove through the first rectangular groove; the fixed vertical wing's of right side airfoil is last to set up horizontal boss, and horizontal boss provides the horizontal plane and is used for the nut installation.
Furthermore, both ends of the rotatable horizontal wing are provided with round-corner rectangular grooves, the round-corner rectangular grooves are matched with the round-corner rectangular special rubber gasket for use, and the round-corner rectangular special rubber gasket is fixedly connected with the bottom surface of the round-corner rectangular grooves by adopting an adhesive method; a third circular through hole is formed in the center of the end face of the rotatable horizontal wing and is used for being matched with the second cylindrical mandrel, and two ends of the second cylindrical mandrel are fixed through a second nut and a second flat gasket, so that the rotatable horizontal wing can rotate around the second cylindrical mandrel; the rotatable horizontal wing end face is further provided with a second cylindrical boss, the second cylindrical boss is located on the outer side of the third circular through hole and is matched with a second circular arc-shaped groove in the upper fixed horizontal wing for use, so that the rotation angle of the rotatable horizontal wing is +/-20 degrees, the second cylindrical boss is only in limit contact with two limit end positions of the second circular arc-shaped groove, and the second cylindrical boss is not in contact with the bottom face and the side face of the second circular arc-shaped groove in the movement process.
Furthermore, second baffles are arranged at two ends of the upper fixed type horizontal wing and are in contact with the cylindrical special rubber gasket, and the second baffles limit the translational freedom degree of the rotatable type horizontal wing along the second cylindrical mandrel; the circular end face of the second baffle is provided with a second rectangular groove, a second circular arc-shaped groove and a third circular through hole, the upper fixed horizontal wing and the rotatable horizontal wing are installed in a matched mode, and the second cylindrical boss enters the second circular arc-shaped groove through the second rectangular groove; two first threaded holes are respectively formed in two sides of the wing side of the upper fixed type horizontal wing, and the upper fixed type horizontal wing is fixedly connected with the right fixed type vertical wing and the left fixed type vertical wing through a cylindrical threaded shaft, a third nut and a third flat gasket together with a through hole in the horizontal boss.
Further, the center fixed horizontal wing is welded at a position away from the topside 1/4 of the underwater vehicle; step-shaped oblique sections are arranged on two sides of the middle fixed type horizontal wing, so that interference generated when the right rotatable vertical wing rotates is avoided; two second threaded holes are respectively formed in two side faces of the middle fixed type horizontal wing, and the middle fixed type horizontal wing is fixedly connected with the right fixed type vertical wing and the left fixed type vertical wing through the cylindrical threaded shaft, the third nut and the third flat gasket together with the through holes in the horizontal bosses.
Further, the lower fixed horizontal wing is welded at a position away from the underwater vehicle floor 1/4; two third threaded holes are respectively formed in the two side faces of the lower fixed type horizontal wing, and the lower fixed type horizontal wing, the right fixed type vertical wing and the left fixed type vertical wing are tightly connected through a cylindrical threaded shaft, a third nut and a flat third gasket together with a through hole in the horizontal boss.
Furthermore, the structural overall dimension of the rounded rectangular special rubber gasket is the same as that of the rounded rectangular groove on the rotatable horizontal wing, the rounded rectangular special rubber gasket is provided with a first through hole, and the dimension of the first through hole is the same as that of a third circular through hole on the rotatable horizontal wing; the fillet rectangular special rubber gasket is provided with a first arc-shaped groove, and the shape and the size of the first arc-shaped groove are the same as those of a second arc-shaped groove on the fixed horizontal wing;
the structural overall dimension of the cylindrical special rubber gasket is the same as that of the cylindrical groove on the rotatable vertical wing, the cylindrical special rubber gasket is provided with a second through hole, and the dimension of the second through hole is the same as that of the first circular through hole on the rotatable vertical wing; the cylindrical special rubber gasket is provided with a second arc-shaped groove, and the shape and the size of the second arc-shaped groove are the same as those of the first arc-shaped groove on the right fixed vertical wing;
the parameters of the fillet rectangular special rubber gasket and the cylindrical special rubber gasket are that the thickness is 1.5cm, and the specific gravity is rho 1.04 × 103kg/m3The elastic modulus is 1.5-1.8 MPa, and the resilience of the force is more than 60%.
Compared with the prior art, the invention has the following remarkable advantages: (1) vortex-induced vibration caused by incoming flow in different directions can be effectively inhibited through the rotation of the rotating wings around the mandrel, and the vortex-induced vibration suppression device is suitable for being applied to environments with frequently changing incoming flow directions such as oceans; (2) the special rubber gasket has certain deformation and vibration reduction capacity, can reduce the influence on the fixed wing and the underwater vehicle when the rotatable wing rotates, and adopts the separable rubber gasket, so that the fixed wing and the rotatable wing can be quickly replaced and maintained easily in the later period, and the friction coefficient between the fixed wing and the rotatable wing can be adjusted according to the actual condition; (3) the upper cylindrical boss of the rotatable wing and the upper arc groove of the fixed wing are matched for use, so that the deflection amplitude limitation of the rotatable wing can be realized, and the excessive deflection of the rotatable wing is avoided, so that the vibration condition of the underwater vehicle is aggravated; (4) rectangular grooves are formed in the circular end faces of the baffles on the two sides of the fixed wing, so that the rotary wing can be conveniently detached and installed.
Drawings
Fig. 1 is a schematic structural diagram of the adaptive suppression device for vortex-induced oscillation of the underwater vehicle.
FIG. 2 is a schematic view of a rotatable vertical wing structure according to the present invention.
Fig. 3 is a schematic view of a fixed vertical wing structure according to the present invention.
Fig. 4 is a schematic view of a rotatable horizontal wing structure according to the present invention.
Fig. 5 is a schematic view of the structure of the upper fixed horizontal wing in the present invention.
Fig. 6 is a schematic view of the middle fixed horizontal wing and its fixed position in the present invention.
Fig. 7 is a schematic view of the lower fixed horizontal wing and its fixed position in the present invention.
Fig. 8 is a structural schematic diagram of the special rubber gasket with the arc rectangle in the invention.
Fig. 9 is a schematic structural view of a circular special rubber gasket in the invention.
FIG. 10 is a schematic view of a partial wing installation of the present invention.
Detailed Description
Specific embodiments of the present invention are further described below with reference to the accompanying drawings.
The invention relates to a vortex excitation oscillation self-adaptive suppression device of an underwater vehicle, which consists of an upper fixed horizontal wing, a middle fixed horizontal wing and a lower fixed horizontal wing, a rotatable horizontal wing, a left fixed vertical wing, a right fixed vertical wing, a left rotatable vertical wing, a right rotatable vertical wing, three cylindrical mandrels and six special rubber gaskets. Wherein four special rubber gaskets are cylindrical, two special rubber gaskets are fillet rectangle, have seted up a convex through-hole, a circular through-hole on the rubber gasket, and ultra-thin stainless steel thin slice is inlayed to rubber gasket top surface, and rubber gasket bottom surface links firmly with rotatable wing through gluing. The diameter of the cylindrical mandrel is slightly smaller than that of the through hole in the rotatable wing, threads are arranged at two ends of the cylindrical mandrel, the cylindrical mandrel is fixedly connected with the rotatable wing and the fixed wing through the through holes in the rotatable wing and the fixed wing through threaded nuts, and the rotatable wing can rotate around the cylindrical mandrel.
The two ends of the upper rotatable horizontal wing are respectively provided with a rounded rectangular groove, and the appearance of the rounded rectangular groove is the same as that of a rubber gasket used in cooperation. The upper rotatable horizontal wing is formed by NACA wing section simulation optimization design, cylindrical bosses at two ends of the upper rotatable horizontal wing are matched with arc-shaped grooves in the upper fixed horizontal wing for use, the effect of limiting the rotation amplitude of the rotating wing is achieved, and the cylindrical bosses and the arc-shaped grooves are only in contact when the two ends are limited. Go up fixed horizontal wing both sides and have outstanding baffle, it has convex recess and cylinder through-hole to open on the baffle, direct contact between both sides baffle and the rubber gasket that has ultra-thin stainless steel thin slice, and a rectangular channel has been seted up to baffle circular arc terminal surface, the installation, the dismantlement of the horizontal wing of upward rotation type of being convenient for. The two side surfaces of the middle fixed horizontal wing adopt stepped cut surfaces to avoid interference with the left and right rotary vertical wings. The middle fixed horizontal wing is fixedly connected with the fixed vertical wing at two sides through threaded nuts, and the middle fixed horizontal wing is directly and fixedly connected with an underwater vehicle in a welding mode. The lower fixed type horizontal wing and the left and right fixed type vertical wings are fixedly connected through threaded nuts, and the lower fixed type horizontal wing is fixedly connected with the underwater vehicle through welding.
There is the baffle fixed perpendicular wing both sides, it has cylinder hole and convex recess to open on the baffle, baffle circular arc terminal surface is opened there is the rectangular channel, the installation of the perpendicular wing of the rotatable formula of being convenient for, dismantle, what fixed perpendicular wing adopted is that imitative NACA wing section optimal design forms, fixed perpendicular wing is equipped with five horizontal bosss, wherein three horizontal boss effect is for making things convenient for nut horizontal contact, two other horizontal bosss are for guaranteeing and upper and lower fixed horizontal wing contact level, pass through threaded nut fastening connection between fixed horizontal wing and the fixed perpendicular wing. The cylindrical bosses at the two ends of the rotatable vertical wing are matched with the arc-shaped grooves in the fixed vertical wing for use, so that the effect of limiting the rotation range of the rotary wing is achieved, and the cylindrical bosses and the arc-shaped grooves are only contacted when the two ends are limited.
The invention further discloses the self-adaptive suppression device for vortex-induced oscillation of the underwater vehicle, which is disclosed by the invention, in detail in the following with reference to the attached drawings.
As shown in fig. 1, the vortex excitation oscillation self-adaptive suppression device for the underwater vehicle comprises a right fixed vertical wing 2, a left fixed vertical wing 11, a right rotatable vertical wing 15, a left rotatable vertical wing 13, an upper fixed horizontal wing 6, a middle fixed horizontal wing 12, a lower fixed horizontal wing 14, a rotatable horizontal wing 10 and three cylindrical mandrels;
the right rotatable vertical wing 15 and the left rotatable vertical wing 13 are respectively connected with the right fixed vertical wing 2 and the left fixed vertical wing 11 through cylindrical mandrels; the rotatable horizontal wing 10 is connected with the upper fixed horizontal wing 6 through a cylindrical mandrel; the right fixed vertical wing 2 and the left fixed vertical wing 11 are respectively fastened with the upper fixed horizontal wing 6, the middle fixed horizontal wing 12 and the lower fixed horizontal wing 14 through bolts;
the upper fixed type horizontal wing 6 and the rotatable type horizontal wing 10 are positioned through a cylindrical mandrel, and meanwhile, the rotatable type horizontal wing 10 realizes rotation angle limitation through an arc-shaped groove and a cylindrical boss; the right fixed vertical wing 2 and the left fixed vertical wing 11 are respectively positioned with the right rotatable vertical wing 15 and the left rotatable vertical wing 13 through a cylindrical mandrel, and the right rotatable vertical wing 15 and the left rotatable vertical wing 13 realize rotation angle limitation through an arc-shaped groove and a cylindrical boss.
Furthermore, the translational degrees of freedom of the rotatable horizontal wing 10, the right rotatable vertical wing 15 and the left rotatable vertical wing 13 are limited by the rotatable horizontal wing 10, the right rotatable vertical wing 15, the left rotatable vertical wing 13 and the cylindrical mandrel;
the rotatable horizontal wing 10, the right rotatable vertical wing 15 and the left rotatable vertical wing 13 can rotate freely around the cylindrical mandrel, and the rotation amplitude of the rotatable horizontal wing 10, the right rotatable vertical wing 15 and the left rotatable vertical wing 13 is limited by the circular arc-shaped grooves on the upper cylindrical boss, the upper fixed horizontal wing 6, the middle fixed horizontal wing 12, the lower fixed horizontal wing 14, the right fixed vertical wing 2 and the left fixed vertical wing 11.
Further, the depth and the width of the circular arc-shaped groove are respectively 1-1.2 cm larger than the height and the diameter of the cylindrical boss, the rotatable horizontal wing 10, the right rotatable vertical wing 15 and the left rotatable vertical wing 13 are only in contact with the two ends of the groove in the rotating process, contact collision cannot occur at other positions, and the rotating amplitude limited by the circular arc-shaped groove is within the range of +/-20 degrees.
As shown in fig. 2, cylindrical grooves 19 are formed at two ends of the right rotatable vertical wing 15, the cylindrical grooves 19 are used in cooperation with cylindrical special rubber gaskets 40, and the cylindrical special rubber gaskets 40 are fixedly connected with the bottom surfaces of the cylindrical grooves 19 by adopting an adhesive method; a first circular through hole 20 is formed in the center of the end face of the cylindrical groove 19 and used for being matched with the first cylindrical mandrel 3, and two ends of the first cylindrical mandrel 3 are fixed through a first nut 4 and a first flat washer 5, so that the right rotatable vertical wing 15 can rotate around the first cylindrical mandrel 3; the end face of the cylindrical groove 19 is further provided with a first cylindrical boss 21, the first cylindrical boss 21 is located on the outer side of the first circular through hole 20 and is matched with the first circular arc-shaped groove 24 on the right fixed vertical wing 2 for use, so that the rotation angle of the right rotatable vertical wing 15 is +/-20 degrees, the first cylindrical boss 21 is only in limited contact with two limit end positions of the first circular arc-shaped groove 24, and the first cylindrical boss 21 is not in contact with the bottom face and the side face of the first circular arc-shaped groove 24 in the movement process.
As shown in fig. 3, the first baffle plates 22 are arranged at two ends of the right fixed vertical wing 2, the first baffle plates 22 are in direct contact with the cylindrical special rubber gasket 40, and the first baffle plates 22 limit the translational degree of freedom of the right rotatable vertical wing 15 along the first cylindrical mandrel 3; the circular end face of the first baffle plate 22 is provided with a first rectangular groove 26, a first circular arc-shaped groove 24 and a second circular through hole 23, the right fixed vertical wing 2 and the right rotatable vertical wing 15 are installed in a matched mode, and the first cylindrical boss 21 enters the first circular arc-shaped groove 24 through the first rectangular groove 26; the airfoil of the right fixed vertical wing 2 is provided with a horizontal boss 25, and the horizontal boss 25 provides a horizontal plane for nut installation.
As shown in fig. 4, rounded rectangular grooves 29 are formed at two ends of the rotatable horizontal wing 10, the rounded rectangular grooves 29 are used in cooperation with rounded rectangular special rubber gaskets 37, and the rounded rectangular special rubber gaskets 37 are fixedly connected with the bottom surfaces of the rounded rectangular grooves 29 by an adhesive method; a third circular through hole 28 is formed in the center of the end face of the rotatable horizontal wing 10 and is used for being matched with the second cylindrical mandrel 7, and two ends of the second cylindrical mandrel 7 are fixed through a second nut 8 and a second flat washer 9, so that the rotatable horizontal wing 10 can rotate around the second cylindrical mandrel 7; the end face of the rotatable horizontal wing 10 is further provided with a second cylindrical boss 27, the second cylindrical boss 27 is located outside the third circular through hole 28 and is matched with the second circular arc-shaped groove 31 on the upper fixed horizontal wing 6 for use, so that the rotation angle of the rotatable horizontal wing 10 is +/-20 degrees, the second cylindrical boss 27 is only in limited contact with the two limit end positions of the second circular arc-shaped groove 31, and the second cylindrical boss 27 is not in contact with the bottom face and the side face of the second circular arc-shaped groove 31 in the movement process.
As shown in fig. 5, the two ends of the upper fixed horizontal wing 6 are provided with second baffles 33, the second baffles 33 are in contact with the cylindrical special rubber gasket 40, and the second baffles 33 limit the translational degree of freedom of the rotatable horizontal wing 10 along the second cylindrical mandrel 7; the circular end face of the second baffle 33 is provided with a second rectangular groove 32, a second circular arc-shaped groove 31 and a third circular through hole 30, the upper fixed type horizontal wing 6 is matched and installed with the rotatable type horizontal wing 10, and the second cylindrical boss 27 enters the second circular arc-shaped groove 31 through the second rectangular groove 32; two first threaded holes 34 are respectively formed in two sides of the wing side of the upper fixed type horizontal wing 6, and the first threaded holes 34 and the through holes in the horizontal bosses 25 are used for tightly connecting the upper fixed type horizontal wing 6 with the right fixed type vertical wing 2 and the left fixed type vertical wing 11 through the cylindrical threaded shaft 16, the third nut 17 and the third flat washer 18.
As shown in fig. 6, the fixed horizontal wing 12 is welded at a position about 1/4 from the topside of the underwater vehicle 1; the step-shaped inclined cross sections are arranged on the two sides of the middle fixed type horizontal wing 12, so that interference generated when the right rotatable vertical wing 15 rotates is avoided; two second threaded holes 35 are respectively formed in two side faces of the middle fixed type horizontal wing 12, and the second threaded holes 35 are tightly connected with the through holes in the horizontal boss 25 through the cylindrical threaded shaft 16, the third nut 17 and the third flat washer 18 to enable the middle fixed type horizontal wing 12 to be tightly connected with the right fixed type vertical wing 2 and the left fixed type vertical wing 11 respectively.
As shown in fig. 7, the lower fixed horizontal wing 14 is welded at a position approximately 1/4 a from the underside of the underwater vehicle 1; two third threaded holes 36 are respectively formed in two side faces of the lower fixed type horizontal wing 14, and the third threaded holes 36 are tightly connected with the through holes in the horizontal boss 25 through the cylindrical threaded shaft 16, the third nut 17 and the flat third washer 18 to tightly connect the lower fixed type horizontal wing 14 with the right fixed type vertical wing 2 and the left fixed type vertical wing 11.
As shown in fig. 8, the structural overall dimension of the rounded rectangular special rubber gasket 37 is the same as that of the rounded rectangular groove 29 on the rotatable horizontal wing 10, and the rounded rectangular special rubber gasket 37 is provided with a first through hole 38, and the dimension of the first through hole 38 is the same as that of the third circular through hole 28 on the rotatable horizontal wing 10; the fillet rectangle special rubber gasket 37 is provided with a first circular arc groove 39, and the shape and the size of the first circular arc groove 39 are the same as those of the second circular arc groove 31 on the fixed horizontal wing 6;
as shown in fig. 9, the structural external dimension of the cylindrical special rubber gasket 40 is the same as the cylindrical groove 19 on the rotatable vertical wing 15, and the cylindrical special rubber gasket 40 is provided with a second through hole 41, and the dimension of the second through hole 41 is the same as the dimension of the first circular through hole 20 on the rotatable vertical wing 15; the cylindrical special rubber gasket 40 is provided with a second circular arc groove 42, and the shape and the size of the second circular arc groove 42 are the same as those of the first circular arc groove 24 on the right fixed vertical wing 2.
The parameters of the rounded rectangular special rubber gasket 37 and the cylindrical special rubber gasket 40 are that the thickness is 1.5cm, and the specific gravity is rho 1.04 × 103kg/m3The elastic modulus is 1.5-1.8 MPa, and the resilience of the force is more than 60%.
As shown in fig. 10, the upper fixed horizontal wing 6 is connected to the rotatable horizontal wing 10 through a second cylindrical mandrel 7, a second nut 8, a second flat washer 9, and a rounded rectangular special rubber gasket 37, so that the rotatable horizontal wing 10 can rotate around the upper fixed horizontal wing 6; the upper fixed horizontal wing 6 is fixedly connected with the right fixed vertical wing 2 and the left fixed vertical wing 11 through a cylindrical threaded shaft, a nut and a flat gasket; the right fixed vertical wing 2 is connected with the right rotatable vertical wing 15 through a first cylindrical mandrel 3, a first nut 4, a first flat washer 5 and a cylindrical special rubber gasket 40, so that the right rotatable vertical wing 15 can rotate around the right fixed vertical wing 2; the left fixed vertical wing 11 and the left rotatable vertical wing 13 are connected through a cylindrical mandrel, a nut and a circular rubber gasket, so that the left rotatable vertical wing 13 can rotate around the left fixed vertical wing 11.
The right fixed vertical wing 2, the left fixed vertical wing 11, the right rotatable vertical wing 15, the left rotatable vertical wing 13, the upper fixed horizontal wing 6, the middle fixed horizontal wing 12, the lower fixed horizontal wing 14 and the rotatable horizontal wing 10 are all designed by streamline wing profiles and adopt NACA standard wing profiles.
The contact surfaces of the rotatable horizontal wing 10, the right rotatable vertical wing 15 and the left rotatable vertical wing 13 are fixedly connected by gluing, the rubber gaskets, the upper fixed horizontal wing 6, the middle fixed horizontal wing 12, the lower fixed horizontal wing 14, the right fixed vertical wing 2 and the left fixed vertical wing 11 are covered with a layer of ultrathin stainless steel sheet, and the contact surfaces of the ultrathin stainless steel sheet, the upper fixed horizontal wing 6, the middle fixed horizontal wing 12, the lower fixed horizontal wing 14, the right fixed vertical wing 2 and the left fixed vertical wing 11 are covered with a layer of ultrathin stainless steel sheet, The coefficient of friction of the left stationary vertical wing 11 is 0.24.
The vortex-induced vibration induced by incoming flows in different directions can be effectively inhibited through the rotation of the rotating wings around the mandrel, and the vortex-induced vibration suppression device is suitable for being applied to environments with frequently changing incoming flow directions such as oceans.
Claims (10)
1. The vortex excitation oscillation self-adaptive suppression device for the underwater vehicle is characterized by comprising a right fixed vertical wing (2), a left fixed vertical wing (11), a right rotatable vertical wing (15), a left rotatable vertical wing (13), an upper fixed horizontal wing (6), a middle fixed horizontal wing (12), a lower fixed horizontal wing (14), a rotatable horizontal wing (10) and three cylindrical mandrels;
the right rotatable vertical wing (15) and the left rotatable vertical wing (13) are respectively connected with the right fixed vertical wing (2) and the left fixed vertical wing (11) through cylindrical mandrels; the rotatable horizontal wing (10) is connected with the upper fixed horizontal wing (6) through a cylindrical mandrel; the right fixed vertical wing (2) and the left fixed vertical wing (11) are respectively connected and fastened with the upper fixed horizontal wing (6), the middle fixed horizontal wing (12) and the lower fixed horizontal wing (14) through bolts;
the upper fixed type horizontal wing (6) and the rotatable type horizontal wing (10) are positioned through a cylindrical mandrel, and meanwhile, the rotatable type horizontal wing (10) realizes rotation angle limitation through an arc-shaped groove and a cylindrical boss; the right fixed vertical wing (2) and the left fixed vertical wing (11) are respectively positioned with the right rotatable vertical wing (15) and the left rotatable vertical wing (13) through a cylindrical mandrel, and the right rotatable vertical wing (15) and the left rotatable vertical wing (13) realize rotation angle limitation through an arc-shaped groove and a cylindrical boss.
2. The adaptive suppression device for vortex-induced oscillation of an underwater vehicle as claimed in claim 1, wherein the rotatable horizontal wing (10) is connected with the upper fixed horizontal wing (6), the right rotatable vertical wing (15) is connected with the right fixed vertical wing (2), the left rotatable vertical wing (13) is connected with the left fixed vertical wing (11) in a positioning manner by a cylindrical mandrel, and the translational degrees of freedom of the rotatable horizontal wing (10), the right rotatable vertical wing (15) and the left rotatable vertical wing (13) are limited by the rotatable horizontal wing (10), the right rotatable vertical wing (15), baffles at two sides of the left rotatable vertical wing (13) and the cylindrical mandrel;
the rotatable horizontal wing (10), the right rotatable vertical wing (15) and the left rotatable vertical wing (13) can rotate freely around the cylindrical mandrel, and the rotation amplitude of the rotatable horizontal wing (10), the right rotatable vertical wing (15) and the left rotatable vertical wing (13) is limited by the cylindrical boss on the rotatable horizontal wing (10), the right rotatable vertical wing (15) and the left rotatable vertical wing (13) and the circular arc-shaped groove on the upper fixed horizontal wing (6), the right fixed vertical wing (2) and the left fixed vertical wing (11).
3. The adaptive suppression device for vortex-induced oscillation of the underwater vehicle as claimed in claim 1 or 2, wherein the depth and the width of the circular arc groove are respectively 1-1.2 cm greater than the height and the diameter of the cylindrical boss, the rotatable horizontal wing (10), the right rotatable vertical wing (15) and the left rotatable vertical wing (13) are only in contact with the two ends of the groove in the rotating process, contact collision cannot occur at other positions, and the rotation amplitude limited by the circular arc groove is within the range of +/-20 degrees.
4. The adaptive suppression device for vortex-induced oscillation of an underwater vehicle as claimed in claim 3, wherein cylindrical grooves (19) are formed at two ends of the right rotatable vertical wing (15), the cylindrical grooves (19) are matched with cylindrical special rubber gaskets (40) for use, and the cylindrical special rubber gaskets (40) are fixedly connected with the bottom surfaces of the cylindrical grooves (19) by adopting an adhesive method; a first circular through hole (20) is formed in the center of the end face of the cylindrical groove (19) and used for being matched with the first cylindrical mandrel (3), and two ends of the first cylindrical mandrel (3) are fixed through a first nut (4) and a first flat gasket (5), so that the right rotatable vertical wing (15) can rotate around the first cylindrical mandrel (3);
the end face of the cylindrical groove (19) is also provided with a first cylindrical boss (21), the first cylindrical boss (21) is positioned on the outer side of the first circular through hole (20) and is matched with a first circular arc groove (24) on the right fixed vertical wing (2) for use, so that the rotating angle of the right rotatable vertical wing (15) is +/-20 degrees, the first cylindrical boss (21) is only in limit contact with two limit ends of the first circular arc groove (24), and the first cylindrical boss (21) is not in contact with the bottom surface and the side surface of the first circular arc groove (24) in the movement process;
the parameters of the cylindrical special rubber gasket (40) are that the thickness is 1.5cm, and the specific gravity is rho 1.04 × 103kg/m3The elastic modulus is 1.5-1.8 MPa, and the resilience of the force is more than 60%.
5. The adaptive suppression device for vortex-induced oscillation of an underwater vehicle as claimed in claim 4, wherein the two ends of the right fixed vertical wing (2) are provided with first baffles (22), the first baffles (22) are in direct contact with a cylindrical special rubber gasket (40), and the first baffles (22) limit the translational freedom of the right rotatable vertical wing (15) along the first cylindrical mandrel (3);
a first rectangular groove (26), a first circular arc-shaped groove (24) and a second circular through hole (23) are formed in the circular end face of the first baffle plate (22), the right fixed vertical wing (2) and the right rotatable vertical wing (15) are installed in a matched mode, and the first cylindrical boss (21) enters the first circular arc-shaped groove (24) through the first rectangular groove (26); and a horizontal boss (25) is arranged on the airfoil surface of the right fixed vertical wing (2), and the horizontal boss (25) provides a horizontal plane for nut installation.
6. The adaptive suppression device for vortex-induced oscillation of the underwater vehicle as claimed in claim 5, wherein rounded rectangular grooves (29) are formed at two ends of the rotatable horizontal wing (10), the rounded rectangular grooves (29) are matched with rounded rectangular special rubber gaskets (37) for use, and the rounded rectangular special rubber gaskets (37) are fixedly connected with the bottom surfaces of the rounded rectangular grooves (29) by adopting an adhesive method; a third circular through hole (28) is formed in the center of the end face of the rotatable horizontal wing (10) and is used for being matched with the second cylindrical mandrel (7), and two ends of the second cylindrical mandrel (7) are fixed through a second nut (8) and a second flat gasket (9), so that the rotatable horizontal wing (10) can rotate around the second cylindrical mandrel (7); the end face of the rotatable horizontal wing (10) is also provided with a second cylindrical boss (27), the second cylindrical boss (27) is positioned outside the third circular through hole (28) and is matched with a second circular arc groove (31) on the upper fixed horizontal wing (6) for use, so that the rotating angle of the rotatable horizontal wing (10) is +/-20 degrees, the second cylindrical boss (27) is only in limit contact with two limit ends of the second circular arc groove (31), and the second cylindrical boss (27) is not in contact with the bottom surface and the side surface of the second circular arc groove (31) in the movement process;
the parameters of the special rubber gasket (37) with the round corners and the rectangles are that the thickness is 1.5cm, and the specific gravity is rho 1.04 × 103kg/m3The elastic modulus is 1.5-1.8 MPa, and the resilience of the force is more than 60%.
7. The adaptive suppression device for vortex-induced oscillation of an underwater vehicle as claimed in claim 6, wherein the two ends of the upper fixed horizontal wing (6) are provided with second baffles (33), the second baffles (33) are in contact with a special rubber gasket (37) in a rectangular shape with round corners, and the second baffles (33) limit the translational freedom of the rotatable horizontal wing (10) along the second cylindrical mandrel (7); a second rectangular groove (32), a second arc-shaped groove (31) and a third circular through hole (30) are formed in the circular end face of the second baffle (33), the upper fixed type horizontal wing (6) and the rotatable type horizontal wing (10) are installed in a matched mode, and the second cylindrical boss (27) enters the second arc-shaped groove (31) through the second rectangular groove (32); two first threaded holes (34) are respectively formed in two sides of the wing side of the upper fixed type horizontal wing (6), the first threaded holes (34) and through holes in the horizontal boss (25) are connected with the upper fixed type horizontal wing (6) in a fastening mode through a cylindrical threaded shaft (16), a third nut (17) and a third flat gasket (18) respectively, and the upper fixed type horizontal wing (6) is connected with the right fixed type vertical wing (2) and the left fixed type vertical wing (11) in a fastening mode.
8. The adaptive suppression device of vortex-induced oscillations of underwater vehicles according to claim 5, characterized in that said central fixed horizontal wing (12) is welded at a distance 1/4 from the top surface of the underwater vehicle (1); step-shaped oblique sections are arranged on two sides of the middle fixed type horizontal wing (12) to avoid interference when the right rotatable type vertical wing (15) rotates; two second threaded holes (35) are respectively formed in two side faces of the middle fixed type horizontal wing (12), the second threaded holes (35) and through holes in the horizontal bosses (25) are connected with the middle fixed type horizontal wing (12) in a fastening mode through cylindrical threaded shafts (16), third nuts (17) and third flat washers (18) respectively, and the middle fixed type horizontal wing (12) is connected with the right fixed type vertical wing (2) and the left fixed type vertical wing (11) in a fastening mode.
9. The adaptive suppression device of vortex-induced oscillations of underwater vehicles according to claim 5, characterized in that said lower fixed horizontal wing (14) is welded at a distance 1/4 from the bottom surface of the underwater vehicle (1); two third threaded holes (36) are respectively formed in two side faces of the lower fixed type horizontal wing (14), the third threaded holes (36) and through holes in the horizontal boss (25) are connected with the lower fixed type horizontal wing (14) and the right fixed type vertical wing (2) and the left fixed type vertical wing (11) in a fastening mode through cylindrical threaded shafts (16), third nuts (17) and flat third gaskets (18).
10. The adaptive suppression device for vortex-induced oscillation of an underwater vehicle as claimed in claim 6, wherein the rounded rectangular special rubber gasket (37) has the same structural external dimension as the rounded rectangular groove (29) on the rotatable horizontal wing (10), and the rounded rectangular special rubber gasket (37) is provided with a first through hole (38), and the first through hole (38) has the same dimension as the third circular through hole (28) on the rotatable horizontal wing (10); the fillet rectangle special rubber gasket (37) is provided with a first arc-shaped groove (39), and the shape and the size of the first arc-shaped groove (39) are the same as those of a second arc-shaped groove (31) on the fixed horizontal wing (6);
the structural overall dimension of the cylindrical special rubber gasket (40) is the same as that of the cylindrical groove (19) on the rotatable vertical wing (15), the cylindrical special rubber gasket (40) is provided with a second through hole (41), and the dimension of the second through hole (41) is the same as that of the first circular through hole (20) on the rotatable vertical wing (15); the cylindrical special rubber gasket (40) is provided with a second arc-shaped groove (42), and the shape and the size of the second arc-shaped groove (42) are the same as those of the first arc-shaped groove (24) on the right fixed vertical wing (2).
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