CN109855837B - Model semi-constrained launching device for aircraft water inlet and outlet test and test method - Google Patents
Model semi-constrained launching device for aircraft water inlet and outlet test and test method Download PDFInfo
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- CN109855837B CN109855837B CN201811480791.7A CN201811480791A CN109855837B CN 109855837 B CN109855837 B CN 109855837B CN 201811480791 A CN201811480791 A CN 201811480791A CN 109855837 B CN109855837 B CN 109855837B
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Abstract
The invention relates to a model semi-constrained launching device for an aircraft water-in and water-out test and a test method, and belongs to the technical field of aviation test devices. A C-shaped guide rail support frame is arranged in a water tank of the device; a guide rail matched with the support frame is arranged in the C-shaped guide rail support frame, and the C-shaped guide rail support frame slides along the extending direction of the water tank; the guide rail is provided with a slidable launching mechanism; a test model is arranged on the launching mechanism; the launching mechanism is connected with the water tank through a tension spring. The test method can simulate different water inlet, water outlet and water skimming tests by adopting different angles, and the test method, the model semi-constrained launching device and the simulation method of the model semi-constrained launching device for the water inlet and outlet tests of the aircraft can launch the test model to a set speed by adjusting the tension of the tension spring on the launching mechanism, so that the requirement of test research on the speed index of the aircraft is met.
Description
Technical Field
The invention relates to a model semi-constrained launching device for an aircraft water-in and water-out test and a test method, and belongs to the technical field of aviation test devices.
Background
The water entering and exiting of the aircraft is a transient complex dynamic process, relates to the phenomena of slamming, wetting invasion, cavitation movement and the like, and complex problems of impact load evaluation, load reduction design, water entering and exiting attitude stability control and the like, and has important research value.
At present, various countries in the world generally adopt test equipment such as high-speed free projectile/constrained projectile water tanks, large-scale water tanks, high-speed water tanks and the like to carry out the research of the water entering and leaving of the aircraft. Under the condition of free projectile, the model can reach high speed and can reflect the water entering state exactly, but due to lack of constraint, the posture of the model can be unstable, and therefore the risk is high. Under the condition of a constrained projectile, the model can be launched to a higher speed along the constraint device, so that the model has better safety, but due to the constraint effect, the water inlet and outlet state cannot be reflected exactly, and the development of a water inlet and outlet test is not facilitated.
Disclosure of Invention
The invention aims to solve the technical problem of the background art and provides a model semi-constrained launching device for a water outlet and inlet test of an aircraft, which adopts a semi-constrained method to control the motion posture of a model and ensure the safety, so that parameters such as the speed, the water outlet and inlet angle and the like of the model meet the test requirements; meanwhile, the influence of the restraint device on the water outlet and inlet of the model is reduced or eliminated, so that the test can accurately reflect the water outlet and inlet state of the model.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention relates to a model semi-constrained launching device for an aircraft water inlet and outlet test, which comprises a water tank for the test, wherein a C-shaped guide rail supporting frame is arranged in the water tank; a guide rail matched with the support frame is arranged in the C-shaped guide rail support frame, and the C-shaped guide rail support frame slides along the extending direction of the water tank; the guide rail is provided with a slidable launching mechanism; arranging a test model on the transmitter; the launching mechanism is connected with the water tank through a tension spring.
The invention relates to a model semi-constrained launching device for an aircraft water inlet and outlet test, wherein the middle part of a C-shaped guide rail supporting frame is arranged on a water tank through a base; the base is arranged on the top of the horizontal plane of the water tank; the base slides on the top of the horizontal surface of the sink.
The model semi-constrained launching device for the aircraft water inlet and outlet test is characterized in that a water tank is immersed below the middle part of a C-shaped guide rail supporting frame; the middle part of the C-shaped guide rail supporting frame is higher than the water tank.
The invention relates to a model semi-constrained launching device for an aircraft water inlet and outlet test, wherein a supporting plate is arranged in a water tank and is vertical to a horizontal plane; two side walls in the water tank are respectively provided with a supporting plate, and the supporting plates are arranged in parallel; the tension springs on the launching mechanism are respectively fixed with the supporting plate.
The model semi-constrained launching device for the water inlet and outlet test of the aircraft is characterized in that a buffer layer is laid on the bottom surface of a water tank.
The model semi-constrained launching device for the aircraft water inlet and outlet test is characterized in that the guide rail is arranged on the inner cambered surface of the C-shaped guide rail supporting frame.
The invention relates to a model semi-constrained launching device for a water test of an aircraft, which is characterized in that two guide rails are arranged in parallel.
The invention discloses a test method of a model semi-constrained launcher for a test of the water entering and exiting of an aircraft,
1) injecting water into the water tank during the test, wherein the liquid level reaches the position close to the upper opening of the water tank, and the lower half part of the C-shaped guide rail supporting device is immersed in the water;
2) electrifying the simulation device, attracting the test model on the launching mechanism, and keeping the tension spring in a tight state; the launching mechanism is positioned on the upper part of the water surface of the guide rail by adjusting the position of the launching mechanism on the guide rail, and a simulation test model underwater motion test is carried out; placing the launching mechanism below the water surface of the guide rail, and performing a simulation test model water outlet motion test; adjusting the position of the launching mechanism to the joint of the guide rail and the water surface, and performing a simulation test model water surface skimming flight test;
3) the launching mechanism is powered off, and the test model is actuated by the tension of the tension spring;
4) when the test model passes through the position near the supporting plate, the tension spring releases tension, the test model is in an unconstrained state, the motion state and the flow characteristic of the test model are observed and recorded by using test equipment, and the water inlet and outlet characteristic of the test model, or the water surface sweeping flight characteristic of the test model, or the hydrodynamic characteristic of the test model moving underwater is analyzed.
The invention relates to a test method of a model semi-constrained launching device for an aircraft water inlet and outlet test.
The test method of the model semi-constrained launcher for the aircraft water inlet and outlet test can be used for developing the water inlet and outlet test of the aircraft test model and also can be used for developing a water surface skimming flight test or an underwater horizontal launching test.
By adopting the technical means, the invention has the following technical effects:
according to the test method of the model semi-constrained launching device for the aircraft water inlet and outlet test, the model semi-constrained launching device and the simulation method, the test model can be launched to the set speed by adjusting the tension of the tension spring on the launching mechanism, so that the requirement of test research on the speed index of the aircraft is met.
The test method of the model semi-constrained launching device for the aircraft water inlet and outlet test is characterized in that the model semi-constrained launching device is connected with the tension spring in the launching process, the motion posture of the test model is always in a controllable state, and accidents such as accidental collision with a water tank, injury to people and the like are avoided.
The invention relates to a test method of a model semi-constrained launching device for an aircraft water inlet and outlet test.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
In order to make the purpose and technical solution of the embodiments of the present invention clearer, the technical solution of the embodiments of the present invention will be clearly and completely described below with reference to the drawings of the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the invention without any inventive step, are within the scope of protection of the invention.
As shown in fig. 1: the model semi-constrained launching device for the water inlet and outlet test of the aircraft comprises a water tank 1 for the test, wherein a C-shaped guide rail support frame 2 is arranged in the water tank 1; two guide rails 10 are arranged on the inner side of the C-shaped guide rail supporting device 2; the C-shaped guide rail support frame 2 slides along the extending direction of the water tank 1; the guide rail 10 is provided with a slidable launching mechanism 4; a test model 5 is arranged on the launching mechanism 4; the launching mechanism 4 is connected with the water tank 1 through a tension spring 6.
The C-shaped rail support 2 is mounted on the base 3. The base 3 can move horizontally along the water tank 1 to adjust the position of the C-shaped guide rail supporting device 2.
The launching mechanism 4 can move along with the guide rail 10, and simultaneously drives the test model 5 to synchronously move along the guide rail 10, so that the launching direction of the test model 5 is changed.
The launching mechanism 4 fixes the test model 5 by an electromagnet suction mode. When the electromagnet is electrified, the test model 5 is fixed on the launching mechanism 4 under the action of attraction force of the electromagnet. When the electromagnet is powered off, the test model 5 is not influenced by the attraction force of the electromagnet any more and is launched out under the tension of the tension spring 6. The test model 5 reciprocates under the tension of the tension spring 6 until the test model is attenuated to a static state by the resistance of water.
One end of the tension spring 6 is connected to the test model 5, and the other end is connected to the support plate 7. The support plate 7 is movable in the vertical direction to adjust the vertical position of the fixing point of the tension spring 6.
The relative position between the base 3 and the supporting plate 7 is adjusted, so that the loosening or tightening state of the tension spring 6 can be changed.
The buffer layer 8 is laid on the bottom surface 9 of the water tank to protect the safety of the test model 5 and the water tank 1.
The test method of the invention is as follows:
during the test, water is injected into the water tank 1, the liquid level reaches the position close to the upper opening of the water tank 1, and the lower half part of the C-shaped guide rail supporting device 2 is immersed into the water.
The test model 5 is arranged on the tension spring 6, the other end of the tension spring 6 is arranged on the support plate 7, and the vertical position of the support plate 7 is adjusted, so that the fixed point of the tension spring 6 on the support plate 7 is positioned near the liquid level.
The base 3 is moved to the position of the supporting plate 7, the test model 5 and the tension spring 6 are installed on the launching mechanism 4, at the moment, the tension spring 6 is in a loose state due to the fact that the base 3 is close to the supporting plate 7, the electromagnet on the launching mechanism 4 is in a power-on state, and the test model 5 is fixed through attraction.
The base 3 is moved towards the direction far away from the supporting plate 7, so that the tension spring 6 is in a tight state and reaches a certain tension value.
The position of the launching mechanism 4 on the guide rail 10 is adjusted, and the launching direction of the test model 5 is changed. If the water outlet or water inlet test is carried out, the test model 5 is moved to a specific position under the water surface or on the water surface along the guide rail 10, so that the launching points to the water surface and has a certain water outlet or water inlet launching angle. If the water surface skimming flight test is carried out, the test model 5 is moved to the position above the water surface along the guide rail 10, and meanwhile, the vertical position of the supporting plate 7 is adjusted, so that the fixed point of the tension spring 6 on the supporting plate 7 is positioned above the water surface, and the launching is directed to the horizontal direction. If the underwater horizontal launching test is carried out, the test model 5 is moved to the position below the water surface along the guide rail 10, and meanwhile, the vertical position of the supporting plate 7 is adjusted, so that the fixed point of the tension spring 6 on the supporting plate 7 is positioned below the water surface, and the launching points to the horizontal direction.
The emission signal is released, the electromagnet on the emission mechanism 4 is powered off, the test model 5 loses the suction effect of the electromagnet and moves along the preset water outlet or water inlet angle under the tension effect of the tension spring 6. Along with the movement of the test model 5 towards the direction of the supporting plate 7, the tension of the tension spring 6 is gradually reduced from the maximum value to zero, meanwhile, the test model 5 is accelerated to move under the action of the tension spring 6, and the maximum speed is reached when the tension of the tension spring 6 is reduced to zero. This speed is the target speed that the test model 5 is required to achieve in the test. If the water outlet test or the water inlet test is carried out, the test model 5 reaches the highest speed near the water surface, at the moment, the tension of the tension spring 6 is reduced to zero, and the test model 5 is in an unconstrained state near the water surface. If the water surface skimming flight test or the underwater horizontal launching test is carried out, the test model 5 reaches the maximum speed when reaching the position of the supporting plate 7 and is in an unconstrained state.
When the test model 5 is in an unconstrained state, the motion state and the flow characteristic of the test model 5 are observed and recorded by using test equipment, and the water inlet and outlet characteristics of the test model 5, or the water surface skimming flight characteristic of the test model 5, or the hydrodynamic characteristic of the underwater motion of the test model 5 are analyzed.
With the continuous movement of the test model 5, the distance between the test model 5 and the supporting plate 7 is gradually increased, and the tension of the tension spring 6 is increased from zero. The test model 5 returns to the stressed state and decelerates to move under the action of the increasingly large constraint force of the tension spring 6 until the test model 5 decelerates to zero speed, so that the test model 5 is ensured to have a moving limit after being launched and not to collide with the side wall of the water tank 1 and the bottom surface 9 of the water tank.
The test model 5 will continue to reciprocate several times under the tension of the tension spring 6 until it is damped to a stationary state by the resistance of water.
The test method of the model semi-constrained launching device for the aircraft water inlet and outlet test is characterized in that the model semi-constrained launching device is connected with the tension spring in the launching process, the motion posture of the test model is always in a controllable state, and accidents such as accidental collision with a water tank, injury to people and the like are avoided.
The invention relates to a test method of a model semi-constrained launching device for an aircraft water inlet and outlet test.
The above description is only for the preferred 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 (6)
1. Model semi-constrained launcher for aircraft water-in and out tests, comprising a tank (1) for testing, characterized in that: a C-shaped guide rail support frame (2) is arranged in the water tank (1); a guide rail (10) matched with the support frame is arranged in the C-shaped guide rail support frame (2), and the C-shaped guide rail support frame (2) slides along the extending direction of the water tank (1); the guide rail (10) is provided with a slidable launching mechanism (4); a test model (5) is arranged on the launching mechanism (4); the launching mechanism (4) is connected with the water tank (1) through a tension spring (6);
the middle part of the C-shaped guide rail support frame (2) is arranged on the water tank (1) through the base (3); the base (3) is arranged on the top of the horizontal plane of the water tank (1); the base (3) slides on the top of the horizontal plane of the water tank (1);
the lower part of the middle part of the C-shaped guide rail support frame (2) is immersed into the water tank (1); the middle part of the C-shaped guide rail support frame (2) is higher than the water tank (1).
2. The model semi-constrained launcher for aircraft water in and out trials according to claim 1, characterized in that: a supporting plate (7) is arranged in the water tank (1) and is vertical to the horizontal plane; two side walls in the water tank (1) are respectively provided with a supporting plate (7), and the supporting plates (7) are arranged in parallel; the tension springs (6) on the launching mechanism (4) are respectively fixed with the supporting plate (7).
3. The model semi-constrained launcher for aircraft water in and out trials according to claim 1, characterized in that: a buffer layer (8) is laid on the bottom surface (9) of the water tank (1).
4. The model semi-constrained launcher for aircraft water in and out trials according to claim 1, characterized in that: the guide rail (10) is arranged on the inner arc surface of the C-shaped guide rail support frame (2).
5. The model semi-constrained launcher for aircraft water in and out trials according to claim 4, characterized in that: the two guide rails (10) are arranged in parallel.
6. Method for testing a model semi-constrained launcher for aircraft water-in and out tests according to any of the preceding claims 1 to 5, characterized in that: the test procedure is as follows
1) During the test, water is injected into the water tank (1), the liquid level reaches the position close to the upper opening of the water tank (1), and the lower half part of the C-shaped guide rail supporting device (2) is immersed in the water;
2) electrifying the simulation device, attracting the test model (5) on the launching mechanism (4), and keeping the tension spring (6) in a tight state; the launching mechanism (4) is positioned at the upper part of the water surface of the guide rail (10) by adjusting the position of the launching mechanism (4) on the guide rail (10), and a simulation test model (5) underwater movement test is carried out; the launching mechanism (4) is positioned below the water surface of the guide rail (10), and a simulation test model (5) water outlet motion test is carried out; adjusting the position of the launching mechanism to the joint of the guide rail and the water surface, and carrying out a water surface skimming flight test of the simulation test model (5);
3) the launching mechanism (4) is powered off, and the test model (5) is actuated by the tension of the tension spring (6);
4) when the test model (5) passes through the position near the supporting plate (7), the tension is released completely by the tension spring (6), the test model (5) is in an unconstrained state, the motion state and the flow characteristic of the test model (5) are observed and recorded by using test equipment, and the water inlet and outlet characteristics of the test model (5), or the water surface sweeping flight characteristic of the test model (5), or the hydrodynamic characteristic of the underwater motion of the test model (5) are analyzed.
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| CN111220352B (en) * | 2020-01-19 | 2020-12-11 | 中国科学院力学研究所 | Variable-angle hydrofoil constraint water inlet experimental device |
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| CN114275189B (en) * | 2021-12-29 | 2023-06-20 | 绵阳小巨人动力设备有限公司 | Fixing and recovering device for underwater emission simulation of navigation device |
| CN114379820B (en) * | 2022-03-24 | 2022-05-20 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Variable-angle variable-speed model water outlet and inlet device |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201464155U (en) * | 2009-07-16 | 2010-05-12 | 浙江理工大学 | Fastening protector of underwater supersonic-speed gas-jet experimental water tank |
| CN102095569A (en) * | 2010-11-09 | 2011-06-15 | 浙江理工大学 | Device for testing underwater high-speed object generated along with supercavity |
| CN202255830U (en) * | 2011-10-20 | 2012-05-30 | 浙江理工大学 | Plane supercavitation generation device |
| CN202614502U (en) * | 2012-05-18 | 2012-12-19 | 浙江理工大学 | Experimental device for interaction between horizontal supercavity and free surface |
| CN103792063A (en) * | 2014-01-09 | 2014-05-14 | 浙江理工大学 | Supercavitation experiment generating device capable of launching submarine launched navigation body in variable angle mode |
| CN105334019A (en) * | 2015-11-11 | 2016-02-17 | 哈尔滨工程大学 | Multi-angle object water entry and wave-making motion experimental device |
| KR20160146179A (en) * | 2015-06-12 | 2016-12-21 | 삼성중공업 주식회사 | Ship for wave resistance |
| CN106323590A (en) * | 2016-08-22 | 2017-01-11 | 浙江大学 | Experiment device for stable multi-angle entering-into-water of object |
| CN106932171A (en) * | 2017-04-29 | 2017-07-07 | 吉林大学 | A kind of across medium ROV enters water and water outlet test system |
| CN108312795A (en) * | 2018-02-05 | 2018-07-24 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Aerial-underwater paleocinetic amphibious aircraft and sailing method can be achieved in one kind |
| KR101884426B1 (en) * | 2018-03-19 | 2018-08-30 | 주식회사 요트북 | Divedome structure for water leisure, water leisure application for using the same and server linkageing application |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103091068A (en) * | 2011-11-02 | 2013-05-08 | 王聪 | Testing method for vertical launch of underwater moving body |
| CN102650566B (en) * | 2012-05-18 | 2014-04-16 | 浙江理工大学 | Experimental device of interaction of horizontal supercavity and free surface |
| CN103257030B (en) * | 2013-05-15 | 2015-06-17 | 浙江理工大学 | Constraint type experiment supercavity generating device |
-
2018
- 2018-12-05 CN CN201811480791.7A patent/CN109855837B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201464155U (en) * | 2009-07-16 | 2010-05-12 | 浙江理工大学 | Fastening protector of underwater supersonic-speed gas-jet experimental water tank |
| CN102095569A (en) * | 2010-11-09 | 2011-06-15 | 浙江理工大学 | Device for testing underwater high-speed object generated along with supercavity |
| CN202255830U (en) * | 2011-10-20 | 2012-05-30 | 浙江理工大学 | Plane supercavitation generation device |
| CN202614502U (en) * | 2012-05-18 | 2012-12-19 | 浙江理工大学 | Experimental device for interaction between horizontal supercavity and free surface |
| CN103792063A (en) * | 2014-01-09 | 2014-05-14 | 浙江理工大学 | Supercavitation experiment generating device capable of launching submarine launched navigation body in variable angle mode |
| KR20160146179A (en) * | 2015-06-12 | 2016-12-21 | 삼성중공업 주식회사 | Ship for wave resistance |
| CN105334019A (en) * | 2015-11-11 | 2016-02-17 | 哈尔滨工程大学 | Multi-angle object water entry and wave-making motion experimental device |
| CN106323590A (en) * | 2016-08-22 | 2017-01-11 | 浙江大学 | Experiment device for stable multi-angle entering-into-water of object |
| CN106932171A (en) * | 2017-04-29 | 2017-07-07 | 吉林大学 | A kind of across medium ROV enters water and water outlet test system |
| CN108312795A (en) * | 2018-02-05 | 2018-07-24 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Aerial-underwater paleocinetic amphibious aircraft and sailing method can be achieved in one kind |
| KR101884426B1 (en) * | 2018-03-19 | 2018-08-30 | 주식회사 요트북 | Divedome structure for water leisure, water leisure application for using the same and server linkageing application |
Non-Patent Citations (2)
| Title |
|---|
| Hybrid windowed thruster for laser thermal propulsion;HE ZHEN;《JOURNAL OF SPACECRAFT AND ROCKETS》;20131031;全文 * |
| 高速航行体水下发射水动力学研究进展;王一伟;《力学进展》;20180531;全文 * |
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