CN112429169A - Method for constructing low-flow-resistance contour curved surface of non-revolving body underwater vehicle - Google Patents
Method for constructing low-flow-resistance contour curved surface of non-revolving body underwater vehicle Download PDFInfo
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- CN112429169A CN112429169A CN202011419615.XA CN202011419615A CN112429169A CN 112429169 A CN112429169 A CN 112429169A CN 202011419615 A CN202011419615 A CN 202011419615A CN 112429169 A CN112429169 A CN 112429169A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B71/00—Designing vessels; Predicting their performance
- B63B71/10—Designing vessels; Predicting their performance using computer simulation, e.g. finite element method [FEM] or computational fluid dynamics [CFD]
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
- B63B1/40—Other means for varying the inherent hydrodynamic characteristics of hulls by diminishing wave resistance
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
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- 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
- Y02T70/00—Maritime or waterways transport
- Y02T70/10—Measures concerning design or construction of watercraft hulls
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- 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
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Abstract
The invention relates to a method for constructing the shape of an underwater vehicle, which is suitable for the design of a low flow resistance shape curved surface of a non-revolving body underwater vehicle. In order to solve the problems of large fluid resistance and large difficulty in designing the low flow resistance shape of the conventional open-frame type non-revolving body underwater vehicle at high navigational speed, the patent provides a construction method for improving and applying a mature revolving body linear design method to the non-revolving body shape design. The patent adopts a mature revolving body linear Myring linear construction method with small resistance and combines a construction method of a B spline surface to create a construction method applied to non-revolving body curved surface design. The design method has the advantages that the shape of the underwater vehicle is designed, the flow resistance is greatly reduced, the engineering design problem of the non-revolving body underwater vehicle at high flow speed is solved, certain universality is realized, and the reference value is used for the shape curved surface design of other non-revolving body underwater vehicles with resistance reduction requirements.
Description
Technical Field
The invention relates to a method for constructing a low flow resistance contour curved surface of a non-revolving body underwater vehicle.
Background
The underwater vehicle technology is taken as an important means for human beings to explore and research the ocean, and is rapidly developed under the background of a great era of strong ocean countries. In the technology of underwater vehicles, the shape and the structural layout of fluid are the key points for the performance of the vehicle.
The structural shape design of underwater vehicles can be roughly divided into two types: the remote control type aircraft is good in low-speed navigation maneuverability, and the cruise type aircraft is high-speed and medium-speed navigation. The former is mainly used for controlling performance due to low navigational speed, and generally adopts an open-frame structure layout, so that various devices, sensors and the like are conveniently arranged. The latter is mainly in a layout of a revolving body structure and is in a streamline shape when the range and the speed are heavily ridden. For inland rivers and acute bay zones with high flow velocity, more underwater vehicle application requirements such as salvage and rescue exist, the flow resistance of a conventional control type low-speed sailing device in the water area is too large, the control performance is greatly reduced, and generally, a specified task is difficult to complete. The project aims to develop an underwater remote control aircraft capable of stably sailing at high flow speed, and the underwater remote control aircraft has low flow resistance and operation performance, so that the open-frame type low-speed sailing vehicle needs to be subjected to adaptive improvement design, and a non-revolving body fluid shape construction method is sought.
At present, the research on the structure of the underwater low flow resistance contour curved surface is less, the research is mostly dependent on hydrodynamic simulation and experimental research, and a reported mature theoretical method is not disclosed yet, so that a universal non-rotary fluid contour design and construction method is required to be found.
Disclosure of Invention
The technical problem solved by the invention is as follows: in order to solve the problems of large fluid resistance and large difficulty in designing the low flow resistance shape of the conventional open-frame type non-revolving body underwater vehicle at high navigational speed, the patent provides a construction method for improving and applying a mature revolving body linear design method to the non-revolving body shape design, and solves the problem of the low flow resistance shape design of the underwater vehicle suitable for high flow rate.
Compared with the current situations that the design difficulty of the non-revolving body shape curved surface of the underwater vehicle is large, theoretical support is lacked and the like, the design method of the torpedo-like type underwater vehicle shape streamline structure of the revolving body is mature, and a semielliptic curve, a parabolic curve, an nystrom curve equation, a Glan Well curve equation, a Myring equation and the like are common. If the mature method of the linear design of the revolving body is applied to the aspect of the structure of the outline curve of the non-revolving body, a large amount of theoretical design work can be saved. Therefore, the patent aims to adopt a mature revolving body linear Myring linear construction method with small resistance and combine the construction method of a B spline surface to create a construction method applied to non-revolving body curved surface design. According to the actual engineering background in the project, the configuration method is used for designing the shape curved surface of the underwater vehicle, and CFD hydrodynamic simulation verification is carried out on the design result so as to judge the feasibility of the theoretical method.
The technical scheme of the invention is as follows: a method for constructing a low flow resistance shape curved surface of a non-revolving body underwater vehicle comprises the following steps:
step 1: constructing a wire form, comprising the sub-steps of:
step 1.1: the aircraft is axially segmented into a bow section A, a middle section B and a tail end C; wherein, the bow section A and the middle section B are distinguished by a bow part-middle part construction line 4, the middle section B and the tail end C are distinguished by a middle part-tail part construction line 6, and planes formed by the bow part-middle part construction line 4 and the middle part-tail part construction line 6 are parallel to each other; the middle section B is a parallel section; the bow section A and the tail end C are further divided through a plurality of construction lines respectively, and the starting point and the end point of the division line are both on the boundary line; the horizontal construction line 5 is a vertical symmetrical construction line of the aircraft;
step 1.2: determining the basic parameters of the Myring linear type of a bow section A, a middle section B and a tail end C:
the bow linear equation is:
the tail end linear equation is:
in the formula, a is the length of the bow; b is the length of the middle parallel segment; c is the tail end length; d is the width (height) of the middle body of the aircraft; theta is the departure angle (theta is more than 0 degree and less than 90 degrees), Rad; n is a sharpness factor (0 to + ∞) and is dimensionless; the bigger n and theta are, the more plump the fore-aft line type is;
step 2: the method for generating the B-spline surface is adopted, each partial surface is constructed through CATIA-V5 software, and the method comprises the following substeps:
substep 2.1: respectively generating curved surfaces of the sub-parts of the bow section A divided by a plurality of structural lines, and sewing the four regional structural curved surfaces after the curved surfaces are generated, so as to obtain a complete structural curved surface of the bow section A;
substep 2.2: constructing a structural curved surface middle section B;
substep 2.3: respectively generating curved surfaces of the sub-parts of the tail end C divided by the plurality of construction lines, and then stitching the four regional construction curved surfaces to obtain a complete construction curved surface of the tail end C;
and step 3: and sewing the bow section A, the middle section B and the tail end C to obtain the complete shape of the curved surface of the underwater vehicle.
The further technical scheme of the invention is as follows: the bow section A comprises a bow right side construction line 1, a bow central symmetry construction line 2, a bow left side construction line 3, a bow-middle construction line 4 and a horizontal symmetry construction line 5 of the aircraft; the bow part central symmetry construction line 2 is determined according to the left-right symmetry plane of the bow part of the aircraft; the horizontal symmetrical construction line 5 of the aircraft is determined according to the upper and lower symmetrical planes of the aircraft, and the bow section A comprises a bow right side construction line 1 and a bow left side construction line 3 which are symmetrically positioned at two sides of a bow central symmetrical construction line 2; the three lines of the bow right structural line 1, the bow centrosymmetric structural line 2 and the bow left structural line 3 are encircled along the axial direction of the aircraft.
The further technical scheme of the invention is as follows: the construction method of the middle section B is normal stretching.
The further technical scheme of the invention is as follows: the constructed line type tail end C comprises a horizontal symmetrical constructed line 5 of the aircraft, a middle-tail constructed line 6, a tail left second constructed line 7, a tail left first constructed line 8, a tail right first constructed line 9 and a tail right second constructed line 10; the tail left two construction lines 7, the tail left one construction line 8, the tail right one construction line 9 and the tail right two construction lines 10 are constructed along the axial direction of the aircraft, and the linear tail end C area is evenly divided.
Effects of the invention
The invention has the technical effects that: the design method for jointly constructing the non-revolving body fluid appearance curved surface combines the revolving body linear theory and the curved surface construction method, and can solve the defects of high difficulty in constructing the non-revolving body curved surface, long design period and the like in engineering. The shape of the underwater vehicle designed according to the created non-revolving body fluid curved surface design method has greatly reduced flow resistance, solves the engineering design problem of the non-revolving body underwater vehicle under high flow speed, has certain universality, and has reference value for the shape curved surface design of other non-revolving body underwater vehicles with resistance reduction requirements.
Drawings
FIG. 1: non-revolving body underwater vehicle structure line type schematic diagram
FIG. 2: non-revolving body underwater vehicle structure curved surface schematic diagram
Description of reference numerals: 1-a bow right construction line; 2-bow central symmetry construction line; 3-a bow left side construction line; 4-bow-mid construction line; 5-constructing a line horizontally and symmetrically by the aircraft; 6-mid-tail construction line; 7-tail left two construction lines; 8-tail left construction line; 9-a tail right construction line; 10-two construction lines on the right of the tail; a-a bow section; b-middle section; c-tail end.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Referring to fig. 1-2, the present invention comprises the following steps:
the method comprises the following steps: structural wire type
The non-rotary body aircraft is shown in a structural line type in the attached figure 1. Determining the basic length, width and height dimensions according to the overall design index requirements of the aircraft, and segmenting the aircraft into a bow section (A), a middle section (B) and a tail end (C); and determining the basic Myring linear parameters of the bow section (A), the middle section (B) and the tail end (C) of the aircraft according to the distributed sizes of the sections and by combining proper sharpness factors and departure angles.
The mering linear bow section linear equation is as follows:
the tail end linear equation is:
in the formula, a is the length of the bow; b is the length of the middle parallel segment; c is the tail end length; d is the width (height) of the middle body of the aircraft; θ is the departure angle, Rad; n is a sharpness factor and is dimensionless.
The tectonic line type bow section (A) consists of a bow part right side tectonic line (1), a bow part central symmetry tectonic line (2), a bow part left side tectonic line (3), a bow part-middle tectonic line (4) and a navigation device horizontal symmetry tectonic line (5). The bow part central symmetry construction line (2) is determined according to the left-right symmetry plane of the bow part of the aircraft; the horizontal symmetrical construction line (5) of the aircraft is determined according to the upper and lower symmetrical planes of the aircraft, and a linear equation can be determined by combining the size of the bow and a proper sharpness factor. In order to make the linear transition of the bow part (A) smooth, a bow part left side construction line (3) and a bow part right side construction line (1) are added to the bow part (A), the size of the bow part left side construction line and the size of the bow part right side construction line can be calculated from the intersection point position of the bow part left side construction line and the horizontal symmetrical construction line (5) of the aircraft, the sharpness factor of the bow part left side construction line and the sharpness factor of the bow part right side construction line are consistent with each other, and therefore the two added. A bow-middle construction line (4) separates the bow (A) from the middle (B), which is determined according to the parallel middle (B) of the aircraft, and the construction is simpler. So far, all the construction line equations of the bow section (A) are known, and the construction curve of the bow section (A) can be drawn. The values of the corresponding construction line parameters are shown in table 1.
TABLE 1 bow segment (A) construction curve parameter dereferencing
The structural linear middle section (B) consists of a bow-middle structural line (4), a horizontal symmetrical structural line (5) of the aircraft and a middle-tail structural line (6). Wherein the bow-mid construction line (4) and the aircraft horizontal symmetry construction line (5) are shared with the bow (A), the construction equation of which is a known quantity. A mid-tail construction line (6) separates the mid portion (B) from the tail portion (C). The mid-aircraft section (B) is a parallel section, so the mid-tail construction line (6) equation is known. So far, all the construction linear equations of the middle section (B) are known, and a middle section (B) construction curve can be drawn.
The structure line type tail end (C) is composed of a horizontal symmetrical structure line (5) of the aircraft, a middle-tail structure line (6), a tail left second structure line (7), a tail left first structure line (8), a tail right first structure line (9) and a tail right second structure line (10). Compared with the bow (A) construction line, the tail (C) construction line does not have a centrosymmetric construction line, and is replaced by four vertical construction lines. The tail left construction line (8) and the tail right construction line (9) are distributed in a bilateral symmetry mode, and the tail left construction line (7) and the tail right construction line (10) are also distributed in a bilateral symmetry mode. The dimensions of the four construction lines can be calculated according to the intersection point position of the horizontal symmetrical construction lines (5) of the aircraft, and the construction equations of the four construction lines can be determined by selecting proper departure angles. So far, all the construction linear equations of the tail section (C) are known, and a construction curve of the tail section (C) can be drawn. The values of the corresponding construction line parameters are shown in table 2.
TABLE 2 values of tail section (C) construction curve parameters
Step two: structural curved surface
The curved surface of the non-revolving body aircraft is shown in the attached figure 2. According to the aircraft structure line type, the corresponding section of structure curved surface can be drawn by combining a curved surface generation method. The spline surface generation method can be seen in the CATIA-V5 design software spline surface generation theory.
The bow section (A) of the structural curved surface is divided into four regions by a structural line in the vertical direction, the structural curved surface of each region is sequentially finished by adopting a B-spline surface generation technology and taking a horizontal symmetrical structural line (5) of the aircraft as a guide line, wherein the boundary condition is tangency. And sewing the four area structural curved surfaces to obtain the bow complete structural curved surface.
The middle section (B) of the structural curved surface is a parallel stretching curved surface, and the structural principle is simple.
The tail section (C) of the structural curved surface is divided into five regions by a vertical structural line, the generation of the structural curved surface of each region is sequentially finished by adopting a B-spline surface generation technology and taking a horizontal symmetrical structural line (5) of an aircraft as a guide line, the boundary condition is tangent, and the drawing of the tail structural curved surface is finally finished. And sewing the three sections of structural curved surfaces into a whole to obtain the complete shape of the external curved surface of the underwater vehicle.
And (3) leading the generated aircraft shape curved surface generating entity into CFD simulation analysis software, completing links such as grid division, boundary condition setting and the like, and performing simulation analysis and verification on the designed aircraft curved surface flow resistance. Through simulation analysis, the flow resistance of the aircraft is reduced by 90% compared with an open-frame aircraft capable of accommodating the same equipment and the same sensor under the condition of eight water flow velocities, and the feasibility and the beneficial engineering effect of the created non-revolving body aircraft shape curved surface construction method are verified.
Claims (4)
1. A method for constructing a low flow resistance shape curved surface of a non-revolving body underwater vehicle is characterized by comprising the following steps:
step 1: constructing a wire form, comprising the sub-steps of:
step 1.1: the aircraft is axially segmented into a bow section (A), a middle section (B) and a tail end (C); wherein, the bow section (A) and the middle section (B) are distinguished by a bow part-middle part construction line (4), the middle section (B) and the tail end (C) are distinguished by a middle part-tail part construction line (6) as a boundary, and planes formed by the bow part-middle part construction line (4) and the middle part-tail part construction line (6) are parallel to each other; the middle section (B) is a parallel section; the bow section (A) and the tail end (C) are further divided through a plurality of construction lines respectively, and the starting point and the end point of the division line are both on the boundary line; the horizontal construction line (5) is a vertical symmetrical construction line of the aircraft;
step 1.2: determining the basic parameters of the Myring linear type of a bow section (A), a middle section (B) and a tail end (C):
the bow linear equation is:
the tail end linear equation is:
in the formula, a is the length of the bow; b is the length of the middle parallel segment; c is the tail end length; d is the width (height) of the middle body of the aircraft; theta is the departure angle (theta is more than 0 degree and less than 90 degrees), Rad; n is a sharpness factor (0 to + ∞) and is dimensionless; the bigger n and theta are, the more plump the fore-aft line type is;
step 2: the method for generating the B-spline surface is adopted, each partial surface is constructed through CATIA-V5 software, and the method comprises the following substeps:
substep 2.1: respectively generating curved surfaces of sub parts of the bow section (A) divided by a plurality of structural lines, and then sewing the four regional structural curved surfaces to obtain a complete structural curved surface of the bow section (A);
substep 2.2: constructing a structural curved surface middle section (B);
substep 2.3: respectively generating curved surfaces of the sub-parts of the tail end (C) divided by the plurality of structural lines, and then stitching the four regional structural curved surfaces to obtain a complete structural curved surface of the tail end (C);
and step 3: and sewing the bow section (A), the middle section (B) and the tail end (C) to obtain the complete shape of the curved surface of the underwater vehicle.
2. The method for constructing the low flow resistance curved surface of the non-revolving body underwater vehicle as claimed in claim 1, wherein the bow section (A) comprises a bow right side construction line (1), a bow central symmetry construction line (2), a bow left side construction line (3), a bow-middle construction line (4) and a vehicle horizontal symmetry construction line (5); the bow part central symmetry construction line (2) is determined according to the left-right symmetry plane of the bow part of the aircraft; the horizontal symmetrical construction line (5) of the aircraft is determined according to the up-down symmetrical plane of the aircraft, and the bow section (A) comprises a bow right side construction line (1) and a bow left side construction line (3) which are symmetrically positioned at two sides of a bow central symmetrical construction line (2); the three lines of the bow part right side construction line (1), the bow part central symmetry construction line (2) and the bow part left side construction line (3) are encircled along the axial direction of the aircraft.
3. The method for constructing the curved surface with the low flow resistance of the non-revolving body underwater vehicle as claimed in claim 1, wherein the method for constructing the middle section (B) is normal stretching.
4. The method for constructing the curved surface with the low flow resistance of the non-revolving body underwater vehicle as claimed in claim 1, wherein the tail end (C) of the constructed line type comprises a horizontal symmetrical constructed line (5) of the vehicle, a middle-tail constructed line (6), a left-second tail constructed line (7), a left-first tail constructed line (8), a right-first tail constructed line (9) and a right-second tail constructed line (10); the tail left two construction lines (7), the tail left one construction line (8), the tail right one construction line (9) and the tail right two construction lines (10) are constructed along the axial direction of the aircraft, and the linear tail end (C) area is evenly divided.
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Cited By (1)
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| CN114132428A (en) * | 2021-11-29 | 2022-03-04 | 江苏科技大学 | Composite drag reduction method for underwater vehicle |
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| CN114132428B (en) * | 2021-11-29 | 2022-09-23 | 江苏科技大学 | Composite drag reduction method for underwater vehicle |
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