CN108956081B - Test device for ship surface rotor wing starting process - Google Patents
Test device for ship surface rotor wing starting process Download PDFInfo
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- CN108956081B CN108956081B CN201810614120.9A CN201810614120A CN108956081B CN 108956081 B CN108956081 B CN 108956081B CN 201810614120 A CN201810614120 A CN 201810614120A CN 108956081 B CN108956081 B CN 108956081B
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000012360 testing method Methods 0.000 title claims abstract description 17
- 238000006073 displacement reaction Methods 0.000 claims abstract description 12
- 230000001133 acceleration Effects 0.000 claims abstract description 9
- 230000005540 biological transmission Effects 0.000 claims description 2
- 238000012018 process simulation test Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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Abstract
The embodiment of the invention discloses a test device for a ship surface rotor wing starting process, relates to the technical field of aerodynamics, and can be used for researching the influence of complex working conditions on the blade flapping angle and the blade tip flapping displacement in the ship surface rotor wing starting process. The invention comprises the following steps: the ship surface rotor starting process simulation test device mainly comprises a ship model and a rotor system model, wherein the rotor system comprises a seesaw type rotor and an articulated type rotor. The basic structure of the test system device comprises a ship model 1, wherein the ship model comprises a hangar 2, a deck 3, blades 4, a stopper 5, a hub 6, a blade clamping device 7, a rotating shaft 8, a central hinge 9, an anti-skid nut 10, a bolt 11, an angle sensor 12, a motor 13, a motor bolt 14, a bearing 15, a detachable ship superstructure 16, a hangar door 17 and an acceleration sensor 19. The invention is suitable for researching the start/stop of the rotor craft under the sea surface working condition.
Description
Technical Field
The invention relates to the technical field of aerodynamics, in particular to a test device for a ship surface rotor wing starting process.
Background
Different from the working condition on the land, the rotor craft can encounter more complex pneumatic problems when flying and landing on the sea. Under the general condition, the aerodynamic lift of rotor and paddle centrifugal force all increase along with the rotational speed increase of rotor, adopt traditional design scheme can design a lot of unmanned aerial vehicle, helicopter etc. rotor crafts that are adapted to land and use. However, rotorcraft are much more complex if they are operated at sea, such as: the sea surface meteorological condition is complex, the wind direction is changeable, and the air is often accompanied with the generation of motion forms such as separation, backflow, vortex and the like when flowing through the superstructure of the ship. In addition, the opening and closing of the ship hangar door also has great influence on the flow field of the ship deck.
And the rotor craft is starting with stall stage, and the rotor rotational speed is lower, and centrifugal force is less, and the paddle is slender soft, and is sensitive to outside air current change, very easily produces excessively when rotatory and waves. Due to excessive flapping, the rotor blades may physically collide with the helicopter fuselage. These factors all contribute to the complexity of the aerodynamic phenomena of the rotorcraft in the offshore environment, making it difficult to accurately predict the aerodynamic characteristics of the rotor using theoretical analysis methods.
Especially in the civilian field, because of lack of suitable experimental apparatus, the civilian unmanned aerial vehicle product that has been put into the market at present for many years is difficult directly to be applied to marine environment, and marine industry equipment is the field of each country's key concern, and military technology among them changes civilian comparatively long, and this all restricts the development of civilian rotor craft under marine operating mode environment.
Disclosure of Invention
The embodiment of the invention provides a test device for a ship surface rotor wing starting process, which is used for researching the influence of complex working conditions on blade flapping angles and blade tip flapping displacement in the ship surface rotor wing starting process.
In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:
the ship surface rotor starting process simulation test device mainly comprises a ship model and a rotor system model, wherein the rotor system comprises a seesaw type rotor and an articulated type rotor. The basic structure of the test system device comprises a ship model (1) (comprising a hangar (2) and a deck (3)), a blade (4), a stop block (5), a hub (6), a blade clamping device (7), a rotating shaft (8), a center hinge (9), an anti-skidding nut (10), a bolt (11), an angle sensor (12), a motor (13), a motor bolt (14), a bearing (15), a detachable ship superstructure (16), a hangar door (17) and an acceleration sensor (19).
This embodiment is used for waving the displacement to warship face rotor starting process paddle and waving the angle and the tip of a oar and waving the displacement and effectively measure, adopts angle sensor to measure the paddle and wave the angle, and acceleration sensor measures the tip of a oar and waves the displacement. The test device is specifically used for testing in a wind tunnel, and can simulate blade flapping phenomena of ship surface rotors in different starting time duration and in the starting process of seesaw type rotors and hinged rotors under the sea conditions of different wind speeds and wind directions, so that the blade flapping problems of different rotor types under different sea conditions can be researched.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic diagram of a seesaw rotor simulation test apparatus provided in an embodiment of the present invention;
FIG. 2 is a schematic view of an articulated rotor simulation test apparatus according to an embodiment of the present invention;
FIG. 3 is a schematic view of a teeter-totter rotor stop arrangement provided in accordance with an embodiment of the present invention;
figure 4 is a schematic view of an articulated rotor stop arrangement according to an embodiment of the present invention;
FIG. 5 is a schematic view of a motor installation provided by an embodiment of the present invention;
fig. 6 is a schematic view of an upper-level building of a ship model and an opening and closing of a hangar door provided in an embodiment of the present invention;
FIG. 7 is a schematic view of a rotor in various starting positions according to an embodiment of the present invention;
wherein: the device comprises a ship model-1, a hangar-2, a deck-3, blades-4, a stopper-5, a hub-6, a blade clamping device-7, a rotating shaft-8, a central hinge-9, an anti-slip nut-10, a bolt-11, an angle sensor-12, a motor-13, a motor bolt-14, a bearing-15, a ship superstructure-16, a hangar door-17, a groove-18 and an acceleration sensor-19.
Detailed Description
In order to make the technical solutions of the present invention better understood, the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention. As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or coupled. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The embodiment of the invention provides a test device for a ship surface rotor wing starting process, as shown in figure 1,
the device comprises naval vessel model (1) and rotor system, and rotor system installs on deck (3).
The ship model (1) comprises a hangar (2) and a deck (3).
The rotor system includes: the propeller comprises a propeller blade (4), a limiting block (5), a propeller hub (6), a propeller blade clamping device (7), a rotating shaft (8), a center hinge (9), an anti-slip nut (10), a bolt (11), an angle sensor (12), a motor (13), a motor bolt (14), a bearing (15) and an acceleration sensor (19).
The angle sensor (12) is fixed below the blade clamping device (7), and the acceleration sensor (19) is embedded in the blade tip.
The paddle (4) is connected with the paddle clamping device (7) through bolts, the paddle clamping device (7) is connected with the paddle hub (6), and the paddle hub (6) drives the paddle (4) to rotate up and down in the vertical direction around the central hinge (9).
And anti-slip nuts (10) are additionally arranged at two ends of the central hinge (9) and fixed on the rotating shaft (8), and the anti-slip nuts (10) are used for preventing the propeller hub (6) from being separated from the central hinge (9).
This embodiment is used for waving the angle to the warship face rotor starting process paddle and effectively measures, adopts angle sensor to measure the paddle and waves the angle, and acceleration sensor measures the tip of a blade and waves the displacement. The test device is specifically used for testing in a wind tunnel, and can simulate blade flapping phenomena of ship surface rotors in different starting time duration and in the starting process of seesaw type rotors and hinged rotors under the sea conditions of different wind speeds and wind directions, so that the blade flapping problems of different rotor types under different sea conditions can be researched.
Specifically, as shown in fig. 1, the rotor system employs a seesaw rotor system. According to the schematic diagram of the seesaw rotor wing limiting device shown in fig. 3, a limiting block (5) is arranged above a hub (6) and fixed on a rotating shaft (8) through a bolt (11), and the limiting block (5) is used for preventing the rotor wing tip from generating overlarge flapping displacement.
Specifically, as shown in fig. 2, the rotor system employs an articulated rotor system. As shown in the schematic diagram of the articulated rotor limiting device shown in fig. 4, a hub (6) of the articulated rotor is a three-joint and is connected with 3 blades (4) through blade clamping devices (7). A groove (18) is arranged in the hub (6), and the groove (18) is used for replacing a stop block (5) to prevent the rotor tip from generating overlarge flapping displacement.
Further, as shown in fig. 5, the rotating shaft (8) is connected with a motor (13) through a transmission device, and the motor (13) is fixed on the back of the deck (3) through a motor bolt (14).
A bearing (15) is additionally arranged between the deck (3) and the rotating shaft (8) and used for ensuring the coaxiality of the motor and the rotating shaft.
Wherein, the deck (3) is provided with at least 1 opening for installing the bearing (15). For example: as shown in fig. 7, the openings made in the deck (3) are distributed uniformly on the deck (3) in an aligned manner, so as to study the aerodynamic conditions of the rotor in different starting positions.
Further, the ship model (1) further comprises: the detachable ship comprises an upper building (16) and a hangar door (17) of the ship. The superstructure (16) of the ship model can be loaded and unloaded as required, and the hangar door (17) can be opened and closed, as shown in fig. 6. Therefore, the influence of the opening and closing of the ship superstructure and the hangar door on the ship surface flow field can be simulated, and the influence of the flow field on the blade flapping angle in the starting process of the ship surface rotor wing is explored.
In the practical application of the embodiment, the ship surface rotor wing starting process simulation test device is placed in a wind tunnel to simulate the starting process of a real ship-based helicopter on a ship. After the airfield of the incoming flow flows through the hangar of the ship, the airflow is separated and reflowed, the airflow acts on the rotor blade which is just started, the rotor rotating speed is low, the centrifugal force is small, the blade is slender and soft, the external airflow is sensitive to change, excessive waving is extremely easy to generate during rotation, and the rotor blade can physically collide with the helicopter fuselage due to excessive waving. In the wind tunnel test, the starting position of the rotor wing is changed, and the displacement of the blade tip and the flapping angle of the blade are measured so as to explore the optimal starting position of the ship surface.
The measurement process comprises the following steps: the test devices of two different rotor models are respectively carried out in wind tunnels with wind speeds of 3m/s, 4m/s and 5m/s (equivalent to the actual wind speeds of 15m/s, 20m/s and 25m/s) and wind directions of 0 degrees, 10 degrees, 20 degrees and 30 degrees. The start times of the two different rotor models were 2s, 3.2s, 4.2s, 5.2s (corresponding to actual start times 10s, 15s, 20s, 25s), respectively. Simultaneously, the starting position A1-C3 of the rotor is changed, as shown in figure 7. The blade tip flapping displacement and the blade flapping angle of different rotor models in the presence or absence of superstructure, opening and closing of a hangar door, different wind speeds, different wind directions and different starting positions in different starting time are measured respectively. Therefore, the flapping of the blades of the ship surface rotor in the starting process and the collision process of the blades and the aircraft body are effectively simulated.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the apparatus embodiment, since it is substantially similar to the method embodiment, it is relatively simple to describe, and reference may be made to some descriptions of the method embodiment for relevant points. The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (1)
1. A test device for a ship surface rotor wing starting process is characterized by comprising a ship model (1) and a rotor wing system, wherein the rotor wing system is installed on a deck (3);
the ship model (1) comprises a hangar (2) and a deck (3);
the rotor system includes: the device comprises a blade (4), a stop block (5), a hub (6), a blade clamping device (7), a rotating shaft (8), a central hinge (9), an anti-skidding nut (10), a bolt (11), an angle sensor (12), a motor (13), a motor bolt (14), a bearing (15) and an acceleration sensor (19);
the angle sensor (12) is fixed below the blade clamping device (7), and the acceleration sensor (19) is embedded in the blade tip;
the paddle (4) is connected with the paddle clamping device (7) through bolts, the paddle clamping device (7) is connected with the paddle hub (6), and the paddle hub (6) drives the paddle (4) to rotate up and down around the central hinge (9) in the vertical direction;
anti-slip nuts (10) are additionally arranged at two ends of the central hinge (9) and fixed on the rotating shaft (8), and the anti-slip nuts (10) are used for preventing the propeller hub (6) from being separated from the central hinge (9);
if the rotor system adopts a seesaw rotor system, then:
the limiting block (5) is arranged above the hub (6) and is fixed on the rotating shaft (8) through a bolt (11), and the limiting block (5) is used for preventing the rotor tip of the rotor from generating overlarge flapping displacement;
if the rotor system employs an articulated rotor system, then: the hub (6) of the hinged rotor wing is a three-joint and is respectively connected with 3 blades (4) through a blade clamping device (7);
a groove (18) is arranged in the hub (6), and the groove (18) is used for replacing a stop block (5) to prevent the rotor tip from generating overlarge flapping displacement;
the rotating shaft (8) is connected with a motor (13) through a transmission device, and the motor (13) is fixed on the back of the deck (3) through a motor bolt (14);
a bearing (15) is additionally arranged between the deck (3) and the rotating shaft (8) and used for ensuring the coaxiality of the motor and the rotating shaft;
the deck (3) is provided with at least 1 opening for installing a bearing (15);
the open holes arranged on the deck (3) are uniformly distributed on the deck (3) in an array form; the ship model (1) further comprises: a detachable ship superstructure (16) and an openable hangar door (17).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810614120.9A CN108956081B (en) | 2018-06-14 | 2018-06-14 | Test device for ship surface rotor wing starting process |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810614120.9A CN108956081B (en) | 2018-06-14 | 2018-06-14 | Test device for ship surface rotor wing starting process |
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| CN108956081A CN108956081A (en) | 2018-12-07 |
| CN108956081B true CN108956081B (en) | 2020-12-25 |
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| CN113942639B (en) * | 2021-10-09 | 2023-05-05 | 中国直升机设计研究所 | Centrifugal blade swing limiting system of helicopter |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8308433B2 (en) * | 2010-09-30 | 2012-11-13 | General Electric Company | System and method for controlling wind turbine blades |
| CN105716837A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Airborne rotor motion measurement method based on PSD optical imaging |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4582013A (en) * | 1980-12-23 | 1986-04-15 | The Holland Corporation | Self-adjusting wind power machine |
| JP2010044032A (en) * | 2008-08-08 | 2010-02-25 | Noriaki Yamaguchi | Wind tunnel for reinforcing torque as wind turbine |
| EP2226766A3 (en) * | 2009-03-02 | 2014-06-11 | Sikorsky Aircraft Corporation | Rotor system health monitoring using shaft load measurements and virtual monitoring of loads |
| CN102963533B (en) * | 2012-12-14 | 2015-06-10 | 中国航空工业集团公司上海航空测控技术研究所 | Helicopter health and usage monitoring system (HUMS) and method thereof |
| CN103954426B (en) * | 2014-03-31 | 2016-08-17 | 南京航空航天大学 | A kind of rotor dynamic testing equipment |
| CN206155788U (en) * | 2016-10-25 | 2017-05-10 | 深圳创壹通航科技有限公司 | Rotor device and autogyro of autogyro |
| CN106599419B (en) * | 2016-12-02 | 2019-07-12 | 中国船舶工业系统工程研究院 | Naval vessel stern flow field numerical simulation and the control methods of wind tunnel test aggregation of data |
| CN107140202B (en) * | 2017-05-12 | 2023-06-20 | 郑可为 | Centrifugal swing hinge rotor head |
| CN107310721A (en) * | 2017-07-17 | 2017-11-03 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
| CN207141389U (en) * | 2017-08-15 | 2018-03-27 | 深圳市道通智能航空技术有限公司 | Fold propeller, Power Component and unmanned vehicle |
| CN107672793B (en) * | 2017-08-25 | 2021-02-26 | 珠海磐磊智能科技有限公司 | Rotor wing device, aircraft and flight control method of aircraft |
-
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- 2018-06-14 CN CN201810614120.9A patent/CN108956081B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8308433B2 (en) * | 2010-09-30 | 2012-11-13 | General Electric Company | System and method for controlling wind turbine blades |
| CN105716837A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Airborne rotor motion measurement method based on PSD optical imaging |
Non-Patent Citations (1)
| Title |
|---|
| An investigation into the phenomenon of helicopter blade sailing;Newman,Simon James;《University of Southampton》;19951231;全文 * |
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