CN112429169B - Low-flow-resistance profile curved surface construction method for non-rotary body underwater vehicle - Google Patents
Low-flow-resistance profile curved surface construction method for non-rotary body underwater vehicle Download PDFInfo
- Publication number
- CN112429169B CN112429169B CN202011419615.XA CN202011419615A CN112429169B CN 112429169 B CN112429169 B CN 112429169B CN 202011419615 A CN202011419615 A CN 202011419615A CN 112429169 B CN112429169 B CN 112429169B
- Authority
- CN
- China
- Prior art keywords
- bow
- line
- construction
- tail
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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]
-
- 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
-
- 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
-
- 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
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Underground Structures, Protecting, Testing And Restoring Foundations (AREA)
- Processing Or Creating Images (AREA)
Abstract
The invention relates to an appearance construction method of an underwater vehicle, which is suitable for the design of a low-flow-resistance appearance curved surface of a non-revolving body underwater vehicle. In order to solve the problems of large fluid resistance and large low flow resistance appearance design difficulty of the existing open frame type non-revolving body underwater vehicle under high navigational speed, the patent provides a construction method for improving and applying a mature revolving body linear design method to non-revolving body appearance design. The patent adopts a mature revolution body linear Myring linear construction method with small resistance and combines with a B spline surface construction method to create a construction method applied to non-revolution body curved surface design. The designed appearance of the non-rotary body underwater vehicle has greatly reduced flow resistance, solves the engineering design problem of the non-rotary body underwater vehicle under high flow velocity, has certain universality and has reference value for the appearance curved surface design of other non-rotary body underwater vehicles with the resistance reduction requirement.
Description
Technical Field
The invention relates to a method for constructing a low-flow-resistance profile curved surface of a non-revolving body underwater vehicle.
Background
The technology of underwater vehicles is used as an important means for exploring and researching the ocean by human beings, and is rapidly developed under the background of the great age of the ocean. In underwater vehicle technology, fluid appearance and structural layout are key to vehicle performance.
The structural profile design of underwater vehicles can be broadly divided into two types: one is a remote control type aircraft with good low-speed navigation operability, and the other is a cruise type aircraft for medium-high-speed navigation. The former has low navigational speed and high control performance, and is generally laid out in an open frame structure, so that various devices and sensors are conveniently arranged. The latter focuses on range and speed, mostly adopts the layout of a revolving body structure, and is streamline. For inland and acute bay ground zones with higher flow velocity, more underwater vehicles such as salvage and rescue are required to be applied, the flow resistance of the conventional control type low-speed vehicle in the water area is overlarge, the control performance is greatly reduced, and the designated task is generally difficult to complete. The project is to develop an underwater remote control aircraft capable of stably sailing at a high flow rate, and low flow resistance and control performance are considered, so that an open frame type low-speed aircraft is required to be subjected to adaptive improvement design, and a non-revolving body fluid appearance construction method is sought.
At present, less researches are conducted on underwater low-flow-resistance profile curved surface structures, the researches depend on hydrodynamic simulation and test, no reported mature theoretical method is disclosed, and therefore a general non-rotary fluid profile design construction method is required to be sought.
Disclosure of Invention
The invention solves the technical problems that: in order to solve the problems of large fluid resistance and large low flow resistance appearance design difficulty of the existing open frame type non-rotary body underwater vehicle under high navigational speed, the patent provides a construction method for improving and applying a mature rotary body linear design method to non-rotary body appearance design, and solves the problem of low flow resistance appearance design of the underwater vehicle adapting to high flow rate.
Compared with the current situations that the design difficulty of the non-revolving body appearance curved surface of the underwater vehicle is high, theoretical support is lacked and the like, the design method of the appearance streamline structure of the revolving body of the torpedo-like underwater vehicle is mature, and the semi-elliptic curve, the parabolic curve, the nystrom curve equation, the gram curve equation, the Myring equation and the like are common. If the maturing method of the linear design of the revolution body is applied to the aspect of curve construction of the non-revolution body appearance, a great deal of theoretical design work can be saved. Therefore, the patent aims to adopt a mature revolution body linear Myring linear construction method with small resistance and combine with a B spline surface construction method to create a construction method applied to non-revolution body surface design. And designing an appearance curved surface of the underwater vehicle by using the construction method according to the actual engineering background in the project, and carrying out CFD hydrodynamic simulation verification on the design result 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 profile curved surface of a non-rotary underwater vehicle comprises the following steps:
step 1: a build line comprising the sub-steps of:
step 1.1: axially segmenting the aircraft into a bow section A, a middle section B and a tail end C; the bow section A and the middle section B are distinguished by a bow-middle construction line 4, the middle section B and the tail end C are distinguished by a middle-tail construction line 6, and planes formed by the bow-middle construction line 4 and the middle-tail 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 dividing line fall on the dividing line; the horizontal construction line 5 is an aircraft up-down symmetrical construction line;
step 1.2: determining Myring linear basic parameters of the bow section A, the middle section B and the tail end C:
the bow section line equation is:
the tail end linear equation is:
wherein a is the length of the bow; b is the length of the middle parallel section; c is the tail end length; d is the aircraft intermediate width (height); θ is the angle of departure (0 ° < θ < 90 °), rad; n is a sharpness factor (0- + infinity), dimensionless; the greater n and theta are, the more full the stern line is;
step 2: adopting a B spline surface generating method, constructing each part of curved surface by CATIA-V5 software, and comprises the following substeps:
substep 2.1: generating curved surfaces of sub-parts of the bow section A divided by a plurality of construction lines respectively, and sewing four regional construction curved surfaces after generating to obtain a complete construction curved surface of the bow section (A);
substep 2.2: constructing a curved surface middle section B;
substep 2.3: generating curved surfaces of the sub-parts of the tail end C divided by a plurality of construction lines respectively, and sewing the four regional construction curved surfaces after generating, so as to obtain a complete construction curved surface of the tail end C;
step 3: and sewing the bow section A, the middle section B and the tail end C to obtain the complete shape of the appearance curved surface of the underwater vehicle.
The invention further adopts the technical scheme that: the bow section A comprises a bow right side construction line 1, a bow center symmetry construction line 2, a bow left side construction line 3, a bow-middle construction line 4 and an aircraft horizontal symmetry construction line 5; the bow center symmetry construction line 2 is determined according to the left-right symmetry plane of the bow 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 center symmetrical construction line 2; the bow right side construction line 1, the bow center symmetry construction line 2 and the bow left side construction line 3 are encircling along the axial direction of the aircraft.
The invention further adopts the technical scheme that: the construction method of the middle section B is normal stretching.
The invention further adopts the technical scheme that: the structural line type tail end C comprises an aircraft horizontal symmetrical structural line 5, a middle-tail structural line 6, a tail left two structural line 7, a tail left one structural line 8, a tail right one structural line 9 and a tail right two structural line 10; wherein 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 profile curved surface combines the revolving body linear theory and the curved surface construction method, and can solve the defects of high difficulty in construction of the non-revolving body curved surface, long design period and the like in engineering. The appearance of the underwater vehicle designed according to the created non-revolving body fluid curved surface design method greatly reduces the flow resistance, solves the engineering design difficulty of the non-revolving body underwater vehicle under the high flow velocity, has certain universality and has reference value for the appearance curved surface design of other non-revolving body underwater vehicles with the resistance reduction requirement.
Drawings
Fig. 1: structure line type schematic diagram of non-revolving body underwater vehicle
Fig. 2: curved surface schematic diagram of non-revolving body underwater vehicle structure
Reference numerals illustrate: 1-a bow right side construction line; 2-a bow central symmetry construction line; 3-a left side construction line of the bow; 4-bow-middle construction line; 5-horizontal symmetrical construction lines of the aircraft; 6-mid-tail build line; 7-a tail left two-construction line; 8-a tail left construction line; 9-a right tail construction line; 10-a tail right two-construction line; a-bow section; b-middle section; c-tail end.
Detailed Description
In the description of the present invention, it should 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", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1-2, the present invention includes the steps of:
step one: structural wire type
The construction line of the non-gyratory vehicle is shown in 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 according to the allocated size of each section, the Myring linear basic parameters of the bow section (A), the middle section (B) and the tail end (C) of the aircraft can be determined by combining the proper sharpness factors and departure angles.
The Myring linear bow linear equation is:
the tail end linear equation is:
wherein a is the length of the bow; b is the length of the middle parallel section; c is the tail end length; d is the aircraft intermediate width (height); θ is the angle of departure, rad; n is a sharpness factor, dimensionless.
The structure line type bow section (A) consists of a bow right side structure line (1), a bow center symmetry structure line (2), a bow left side structure line (3), a bow-middle structure line (4) and an aircraft horizontal symmetry structure line (5). The bow central symmetry construction line (2) is determined according to the left-right symmetry plane of the bow 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 linear equation can be determined by combining the size of the bow and an appropriate sharpness factor. In order to smooth the linear transition of the bow part (A), a bow left side construction line (3) and a bow right side construction line (1) are added to the bow part (A), the size of the bow is calculated from the position of an intersection point of the bow left side construction line and the bow right side construction line with a horizontal symmetrical construction line (5) of the aircraft, and the sharpness factor of the bow is consistent with the center symmetrical construction line (2) of the bow part, so that two construction line equations are added to determine the bow part. A bow-middle construction line (4) separates the bow (A) from the middle (B), which is defined by the parallel middle ends (B) of the aircraft, and is of relatively simple construction. 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 corresponding values of the construction line parameters are shown in Table 1.
Table 1 values of the parameters of the construction curve of the bow section (A)
The structural line type middle section (B) consists of a bow-middle structural line (4), an aircraft horizontal symmetrical structural line (5) and a middle-tail structural line (6). Wherein the bow-middle construction line (4) and the horizontal symmetrical construction line (5) of the aircraft are shared with the bow (A), and the construction equation is a known quantity. A mid-tail build line (6) separates the mid portion (B) from the tail portion (C). The midsection (B) of the aircraft is a parallel section, so the mid-tail build line (6) equation is known. So far, all the construction linear equations of the middle section (B) are known, and the construction curve of the middle section (B) can be drawn.
The structural line type tail end (C) consists of a horizontal symmetrical structural line (5) of the aircraft, a middle-tail structural line (6), a tail left two structural line (7), a tail left one structural line (8), a tail right one structural line (9) and a tail right two structural line (10). Compared with the bow part (A) structural line, the tail part (C) structural line does not have a central symmetry structural line, and four vertical structural lines are used instead. Wherein the left tail construction line (8) and the right tail construction line (9) are distributed in a bilateral symmetry manner, and the left tail construction line (7) and the right tail construction line (10) are also distributed in a bilateral symmetry manner. The size 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 a proper departure angle is selected, so that a construction equation of the four construction lines can be determined. To this end, the tail section (C) construction curve can be plotted, knowing all the construction linear equations of the tail section (C). The corresponding construction line parameter values are shown in Table 2.
Table 2 parameter values of the construction curve of the end section (C)
Step two: structural curved surface
The curved surface of the non-revolving body aircraft is shown in figure 2. According to the aircraft structure line type, the corresponding section structure curved surface can be drawn by combining the curved surface generating method. The spline surface generation method can refer to a CATIA-V5 design software spline surface generation theory.
The constructing curved surface bow section (A) is divided into four areas by a vertical constructing line, a B spline surface generating technology is adopted, and the constructing curved surface of each area is sequentially completed by taking a horizontal symmetrical constructing line (5) of the aircraft as a guide line, wherein boundary conditions are tangent. And sewing the four regional structural curved surfaces to obtain a 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 structural curved surface tail section (C) is divided into five areas by a vertical structural line, a B spline surface generation technology is adopted, the structural curved surfaces of all areas are sequentially generated by taking a horizontal symmetrical structural line (5) of the aircraft as a guide line, boundary conditions are tangential, and finally the drawing of the structural curved surfaces of the tail is completed. And sewing the three-section structural curved surface into a whole to obtain the complete shape of the appearance curved surface of the underwater vehicle.
And importing the generated entity for generating the appearance curved surface of the aircraft into CFD simulation analysis software to finish links such as grid division, boundary condition setting and the like, so that simulation analysis and verification can be performed on the flow resistance of the designed aircraft curved surface. 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 sensors under the condition of eight water-saving flow rates, and the feasibility and beneficial engineering effect of the contour curved surface construction method of the non-revolving body aircraft are verified.
Claims (4)
1. The method for constructing the low-flow-resistance profile curved surface of the non-rotary underwater vehicle is characterized by comprising the following steps of: step 1: a build line comprising the sub-steps of:
step 1.1: axially segmenting the aircraft into a bow section (A), a middle section (B) and a tail end (C); the bow section (A) and the middle section (B) are distinguished by a bow-middle construction line (4), the middle section (B) and the tail end (C) are distinguished by a middle-tail construction line (6) as a boundary, and planes formed by the bow-middle construction line (4) and the middle-tail 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 dividing line fall on the dividing line; the horizontal symmetrical construction line (5) is an aircraft vertical symmetrical construction line;
step 1.2: determining Myring linear basic parameters of a bow section (A), a middle section (B) and a tail end (C):
the bow section line equation is:
the tail end linear equation is:
wherein a is the length of the bow; b is the length of the middle parallel section; c is the tail end length; d is the width or height of the vehicle intermediate; θ is the angle of departure (0 ° < θ < 90 °), rad; n is a sharpness factor (0- + infinity), dimensionless; the greater n and theta are, the more full the stern line is;
step 2: adopting a B spline surface generating method, constructing each part of curved surface by CATIA-V5 software, and comprises the following substeps:
substep 2.1: generating curved surfaces of the sub-parts of the bow section (A) divided by a plurality of construction lines respectively, and sewing the four regional construction curved surfaces after generating, so as to obtain a complete construction curved surface of the bow section (A);
substep 2.2: constructing a curved surface middle section (B);
substep 2.3: generating curved surfaces of the sub-parts of the tail end (C) divided by a plurality of construction lines respectively, and sewing the four regional construction curved surfaces after generating, so as to obtain a complete construction curved surface of the tail end (C);
step 3: and sewing the bow section (A), the middle section (B) and the tail end (C) to obtain the complete shape of the appearance curved surface of the underwater vehicle.
2. The method for constructing a low flow resistance profile curved surface of a non-rotary body underwater vehicle according to claim 1, wherein the bow section (a) comprises a bow right side construction line (1), a bow center 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 central symmetry construction line (2) is determined according to the left-right symmetry plane of the bow of the aircraft; the horizontal symmetrical construction line (5) of the aircraft is determined according to the upper and lower symmetry 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 center symmetrical construction line (2); the bow right side construction line (1), the bow center symmetry construction line (2) and the bow left side construction line (3) are encircling along the axial direction of the aircraft.
3. A method of constructing a curved surface of a low flow resistance profile for an underwater vehicle other than a solid of revolution as claimed in claim 1, wherein said method of constructing said intermediate section (B) is a normal stretch.
4. A method of constructing a low flow resistance profile curve for an underwater vehicle other than a gyrorotor as defined in claim 1 wherein the build line type tail end (C) comprises a vehicle horizontal symmetry build line (5), a mid-tail build line (6), a tail left two build line (7), a tail left one build line (8), a tail right one build line (9) and a tail right two build line (10); wherein the method comprises the steps of
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, so that the linear tail end (C) area is evenly divided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419615.XA CN112429169B (en) | 2020-12-06 | 2020-12-06 | Low-flow-resistance profile curved surface construction method for non-rotary body underwater vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419615.XA CN112429169B (en) | 2020-12-06 | 2020-12-06 | Low-flow-resistance profile curved surface construction method for non-rotary body underwater vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112429169A CN112429169A (en) | 2021-03-02 |
| CN112429169B true CN112429169B (en) | 2023-08-04 |
Family
ID=74691689
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011419615.XA Active CN112429169B (en) | 2020-12-06 | 2020-12-06 | Low-flow-resistance profile curved surface construction method for non-rotary body underwater vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112429169B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114132428B (en) * | 2021-11-29 | 2022-09-23 | 江苏科技大学 | Composite drag reduction method for underwater vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB673905A (en) * | 1949-08-30 | 1952-06-11 | Timothy Herbert Scott | Improvements in or relating to navigable vessels |
| US5402743A (en) * | 1988-06-06 | 1995-04-04 | Holderman; Jim D. | Deep chine hull design |
| JP2018161947A (en) * | 2017-03-24 | 2018-10-18 | 国立研究開発法人 海上・港湾・航空技術研究所 | Inwardly inclined upper bow shape, vessel provided with inwardly inclined upper bow shape, and design method for inwardly inclined upper bow shape |
| WO2018199853A1 (en) * | 2017-04-27 | 2018-11-01 | İstanbul Tekni̇k Üni̇versi̇tesi̇ | Design method for generation and parametric modification of yacht hull surfaces |
| CN109460058A (en) * | 2018-11-22 | 2019-03-12 | 中国船舶重工集团公司第七0五研究所 | A kind of tail portion propulsion traversing control method of low speed submarine navigation device underwater mating |
| CN110065606A (en) * | 2019-05-16 | 2019-07-30 | 大连理工大学 | A kind of streamlined quadrotor submarine navigation device that vector promotes |
-
2020
- 2020-12-06 CN CN202011419615.XA patent/CN112429169B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB673905A (en) * | 1949-08-30 | 1952-06-11 | Timothy Herbert Scott | Improvements in or relating to navigable vessels |
| US5402743A (en) * | 1988-06-06 | 1995-04-04 | Holderman; Jim D. | Deep chine hull design |
| JP2018161947A (en) * | 2017-03-24 | 2018-10-18 | 国立研究開発法人 海上・港湾・航空技術研究所 | Inwardly inclined upper bow shape, vessel provided with inwardly inclined upper bow shape, and design method for inwardly inclined upper bow shape |
| WO2018199853A1 (en) * | 2017-04-27 | 2018-11-01 | İstanbul Tekni̇k Üni̇versi̇tesi̇ | Design method for generation and parametric modification of yacht hull surfaces |
| CN109460058A (en) * | 2018-11-22 | 2019-03-12 | 中国船舶重工集团公司第七0五研究所 | A kind of tail portion propulsion traversing control method of low speed submarine navigation device underwater mating |
| CN110065606A (en) * | 2019-05-16 | 2019-07-30 | 大连理工大学 | A kind of streamlined quadrotor submarine navigation device that vector promotes |
Non-Patent Citations (1)
| Title |
|---|
| 超空化航行器稳定性分析及最优控制设计;范辉;张宇文;;信息与控制(第04期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112429169A (en) | 2021-03-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101774419B (en) | Three-body skimming boat with oblique stepped structure | |
| CN112429169B (en) | Low-flow-resistance profile curved surface construction method for non-rotary body underwater vehicle | |
| CN102092457B (en) | Ship | |
| US20120065942A1 (en) | Method of an all-speed propeler | |
| CN102971210A (en) | Rocking-reduction device for floating body | |
| CN108469263A (en) | A kind of method and system carrying out form point optimization based on curvature | |
| CN110316340B (en) | High-stability underwater vehicle hydrodynamic layout for low-speed movement | |
| CN113071628B (en) | Lofting method for stern section molded line containing shaft packing plate | |
| JP2013043633A (en) | Method for forming of ship stern structure with asymmetrical torsion flow control fin attached thereon | |
| Truong et al. | The EFD and CFD study of rudder-bulb-fin system in ship and propeller wake field of KVLCC2 tanker in calm water | |
| CN106114755A (en) | A kind of ship surface inner shell indulges bone arrangement method | |
| CN201941943U (en) | Hidden bow structure | |
| CN103569310B (en) | Full formed ship | |
| KR20180023270A (en) | Structure for Improving the Ship Stern Flow | |
| CN110588880B (en) | Unfolding method of bilge keel base plate | |
| US3675605A (en) | Ship or boat hull construction | |
| JP2649786B2 (en) | Propeller and method for determining its optimum shape | |
| CN103661790A (en) | Straight-wall sliding channel type sharp-bilge planing boat model | |
| Nursal et al. | Investigation on resistance effects through towing test and CFD analysis on catamaran boat hull form | |
| CN106828773B (en) | A kind of FPSO shiplines design method | |
| Castaldi | Experimental study on stepped spray deflectors for planning hull | |
| CN105511404B (en) | A kind of hyperbolicity stringer expansion processing method with complex characteristic | |
| Pérez-Arribas et al. | Parametric generation of planing hulls with NURBS surfaces | |
| WO2017170359A1 (en) | Ship rudder and ship | |
| CN116561916B (en) | CATIA V6-based metal enclosure wall parameterized modeling method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |