CN113008515B - Multi-angle water-entering simulation auxiliary device for winged cone model - Google Patents
Multi-angle water-entering simulation auxiliary device for winged cone model Download PDFInfo
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- CN113008515B CN113008515B CN202110213038.7A CN202110213038A CN113008515B CN 113008515 B CN113008515 B CN 113008515B CN 202110213038 A CN202110213038 A CN 202110213038A CN 113008515 B CN113008515 B CN 113008515B
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Abstract
The utility model provides a take wing cone model multi-angle to go into water simulation auxiliary device, including taking wing cone model, slider and connecting plate, embedded groove one and embedded groove two are seted up to the tip of taking wing cone model, embedded groove three is seted up to the lateral wall of embedded groove two, the cooperation has the sealing washer in the embedded groove three, adsorb magnet one in the embedded groove one, be equipped with the convex part on one side panel of connecting plate, the connecting plate pastes the tip that leans on takes wing cone model, and the convex part card is in embedded groove two, attached magnet two on the opposite side face of connecting plate, magnet two and magnet one are inhaled mutually, the connecting plate is fixed on the slider, slider and track cooperate, be equipped with the dog on the slider, this application takes wing cone model to be separated after accelerating to appointed speed, and only need overcome the frictional force that magnet two provided and sealing washer provide during the separation, influence such as model dead weight and moment of torsion can be overcome during quiescent condition, can avoid dragging the speed decay that causes during dynamic separation, can accomplish the accurate control of speed size and direction during the dynamic separation.
Description
Technical Field
The invention relates to the technical field of water inlet tests of winged cone models, in particular to a multi-angle water inlet simulation auxiliary device of a winged cone model.
Background
For the problem of multi-angle water entry of the winged cone complex-structure model, the acceleration can not be carried out in a conventional gun launching mode, the acceleration mode of a rocket pry track is generally adopted, and then the static constraint can not be carried out in a bullet belt or adapter matching mode. For the problem of the inclined water, when the model is in a static state, in addition to the self gravity, the torque caused by the self weight exists, so that the model is difficult to keep parallel to the launching track in the initial state, and the speed direction of the subsequent model when the model is separated from the tail end of the track is influenced. In a static state, if a threaded connection type matching mode is adopted to overcome the dead weight and the torque of the model, the pulling force is too large during dynamic separation, so that the connection structure is damaged, and the posture is uncontrollable and the speed attenuation is large during separation.
Disclosure of Invention
The applicant aims at the defects in the prior art and provides the multi-angle water-entering simulation auxiliary device for the winged cone model, so that the influences of the dead weight, the torque and the like of the model can be overcome in a static state, the speed attenuation caused by dragging can be avoided in dynamic separation, and the accurate control of the speed and the direction in the dynamic separation can be realized.
The technical scheme adopted by the invention is as follows: the utility model provides a take wing cone model multi-angle to go into water simulation auxiliary device, including taking wing cone model, slider and connecting plate, embedded groove one and embedded groove two are seted up to the tip of taking wing cone model, embedded groove three is seted up to the lateral wall of embedded groove two, the cooperation has the sealing washer among the embedded groove three, adsorb magnet one among the embedded groove one, be equipped with the convex part on one side panel of connecting plate, the connecting plate pastes the tip that leans on and takes wing cone model, and the convex part card is in embedded groove two, attached magnet two on the opposite side panel of connecting plate, magnet two and magnet one attract mutually, the connecting plate is fixed on the slider, slider and track cooperate, be equipped with the dog on the slider.
As a further improvement of the above technical solution:
the second embedded groove is annular, the convex part is annular, the third embedded groove extends along the inner side groove wall of the second embedded groove in the circumferential direction, and the second embedded groove surrounds the periphery of the first embedded groove.
The sliding block comprises two parallel side plates and an intermediate plate vertically connected between the two side plates, wherein the inner corners of one end of each of the two side plates are provided with an angular notch, one inner wall of the angular notch is a first plane, the other inner wall of the angular notch is a second plane, the first plane and the end face of one end of the side plate are arranged in parallel at intervals, the first plane is provided with a plurality of first threaded holes, the second plane is provided with a strip seam, one end of the strip seam extends to the end face of one end of the side plate, the periphery of the connecting plate is provided with a plurality of second threaded holes, the first threaded holes correspond to the second threaded holes, mounting screws are mounted on the first threaded holes to realize connection of the connecting plate and the sliding block, a wing plate circumferentially arranged at one end of the winged cone model penetrates through the strip seam, and sliding chutes matched with rails are respectively formed in the outer side faces of the two side plates.
The stop block is mounted on one of the side plates.
The connecting plate is an aluminum plate.
The applicant provides a multi-angle water-entering simulation method for the winged cone model aiming at the defects in the prior art, the influences of the self weight, the torque and the like of the model can be overcome in a static state, the speed attenuation caused by dragging can be avoided in dynamic separation, and the accurate control on the speed and the direction in the dynamic separation can be realized.
The technical scheme adopted by the invention is as follows: a multi-angle water entry simulation method for a winged cone model comprises the following steps:
acquiring the mass and the mass center of the winged cone model and the sizes of the first embedded groove, the second embedded groove and the third embedded groove, and determining the included angle between the winged cone model and the horizontal plane in a static state according to the water inlet angle required by the test;
determining how much force is needed to overcome the dead weight and the torque of the winged cone model according to the mass and the mass center of the winged cone model and the included angle between the winged cone model and the horizontal plane in a static state, thereby determining the number of the first magnets, the arrangement mode of the first magnets in the first embedded grooves and the specification of the sealing ring;
the winged cone model is connected with the connecting plate in an adsorption mode, the connecting plate and the sliding block are fixedly connected through the screws, and the sliding block is connected with a rail of the rocket pry launching device through the sliding groove and can slide on the rail;
after the winged cone model, the sliding block and the connecting plate are driven by the solid rocket engine to accelerate to the appointed water inlet speed, the stop block arranged on the sliding block collides with a preset brake cylinder, the sliding block and the connecting plate decelerate, the winged cone model continues to move under the action of inertia, when the dragging force is larger than the sum of the suction force of the first magnet and the friction force of the sealing ring, the winged cone model is separated from the connecting plate, and the winged cone model smoothly enters water according to the preset water inlet speed and the water inlet angle.
The invention has the following beneficial effects: this application area wing cone model need separate after being accelerated to appointed speed, and only need overcome the suction that magnet two provided and the frictional force that the sealing washer provided during the separation, can not destroy the main structure of taking wing cone model and the pulling power except that gravity when separating, two suctions of magnet, sealing washer frictional force all is along the track direction, and then the velocity direction when having guaranteed the separation is along the track, the accurate control of velocity direction has been accomplished, influence such as model dead weight and moment of torsion can be overcome when quiescent condition.
Drawings
FIG. 1 is a cross-sectional view of a winged cone model of the present invention.
Fig. 2 is an enlarged view of a portion a of fig. 1.
Fig. 3 is a view showing the arrangement of the seal ring and the magnet in fig. 2.
Fig. 4 is a sectional view of the connection plate.
Fig. 5 is a front view of the connection plate.
Fig. 6 is a structural view of the slider.
Fig. 7 is a view showing an installation structure of the winged cone model.
Fig. 8-10 are schematic views of an arrangement of different numbers of magnets.
Wherein: 10. a winged cone model; 11. the first embedded groove; 12. a second embedded groove; 13. a third embedded groove; 14. a wing plate; 20. a slider; 21. a side plate; 211. a chute; 22. a middle plate; 23. a first plane; 231. a first threaded hole; 24. a second plane; 241. strip sewing; 30. a connecting plate; 31. a convex portion; 32. a second threaded hole; 40. a seal ring; 50. and a stop block.
Detailed Description
The following describes embodiments of the present invention with reference to the drawings.
As shown in fig. 1-10, the multi-angle water entry simulation auxiliary device for the winged cone model of the present embodiment includes a winged cone model 10, a slider 20 and a connecting plate 30, the end of the winged cone model 10 is provided with a first embedded groove 11 and a second embedded groove 12, the side wall of the second embedded groove 12 is provided with a third embedded groove 13, the third embedded groove 13 is matched with a sealing ring 40, the first embedded groove 11 adsorbs a first magnet, a side plate of the connecting plate 30 is provided with a convex portion 31, the connecting plate 30 is attached to the end of the winged cone model 10, the convex portion 31 is clamped in the second embedded groove 12, the other side plate of the connecting plate 30 is attached with a second magnet, the second magnet and the first magnet attract each other, the connecting plate 30 is fixed on the slider 20, the slider 20 is matched with a rail, and the slider 20 is provided with a stopper 50.
The second embedded groove 12 is annular, the convex portion 31 is annular, the third embedded groove 13 extends along the inner groove wall circumference of the second embedded groove 12, and the second embedded groove 12 surrounds the periphery of the first embedded groove 11.
The sliding block 20 comprises two parallel side plates 21 and a middle plate 22 vertically connected between the two side plates 21, wherein an inner corner of one end of each of the two side plates 21 is provided with an angular notch, one inner wall of the angular notch is a first plane 23, the other inner wall of the angular notch is a second plane 24, the first plane 23 and the end surface of one end of the side plate 21 are arranged in parallel at intervals, the first plane 23 is provided with a plurality of threaded holes 231, the second plane 24 is provided with a strip seam 241, one end of the strip seam 241 extends to the end surface of one end of the side plate 21, the periphery of the connecting plate 30 is provided with a plurality of threaded holes two 32, the first threaded holes 231 and the threaded holes two 32 correspond to each other and are provided with mounting screws to realize the connection between the connecting plate 30 and the sliding block 20, a wing plate 14 arranged at one end of the winged cone model 10 in the circumferential direction penetrates through the strip seam 241, and sliding grooves 211 matched with rails are respectively formed in the outer side surfaces of the two side plates 21.
The stop 50 is mounted on one of the side plates 21.
The connecting plate 30 is an aluminum plate.
The multi-angle water inlet simulation method for the winged cone model comprises the following steps:
acquiring the mass and the mass center of the winged cone model 10 and the sizes of the first embedded groove 11, the second embedded groove 12 and the third embedded groove 13, and determining the included angle between the winged cone model 10 and the horizontal plane in a static state according to the water inlet angle required by the test;
determining how much force is needed to overcome the dead weight and the torque of the winged cone model 10 according to the mass and the mass center of the winged cone model 10 and the included angle between the winged cone model 10 and the horizontal plane in a static state, thereby determining the number of the first magnets, the arrangement mode of the first magnets in the first embedded grooves 11 and the specification of the sealing ring 40;
the winged cone model 10 is connected with the connecting plate 30 in an adsorption mode, the connecting plate 30 is fixedly connected with the sliding block 20 through screws, and the sliding block 20 is connected with a track of a rocket pry launching device through a sliding groove 211, so that the sliding block 20 can slide on the track;
after the winged cone model 10, the sliding block 20 and the connecting plate 30 are driven by a solid rocket engine to accelerate to the appointed water entry speed, the stop block 50 arranged on the sliding block 20 collides with a preset brake cylinder, the sliding block 20 and the connecting plate 30 decelerate, the winged cone model 10 continues to move under the action of inertia, when the dragging force is larger than the sum of the suction force between the first magnet and the second magnet and the friction force of the sealing ring 40, the winged cone model 10 is separated from the connecting plate 30, and the winged cone model 10 smoothly enters water according to the preset water entry speed and the water entry angle.
The application overcomes the force and the torque (generalized force F3) caused by the dead weight of the wing-contained cone model 10 in the static state and the water inlet angle in the inclined water inlet problem together by the attraction F1 provided by the magnet II and the friction force F2 provided by the sealing ring 40, a safety coefficient n is given, the requirement of static self-locking can be met only by setting F1+ F2 to be more than or equal to (1 + n) F3, thereby realizing accurate control and greatly reducing the adverse effect of the dragging force on speed attenuation during separation. The winged cone model 10 can basically ensure that the speed is separated according to the speed when the stop block 50 on the sliding block 20 collides with a preset brake cylinder, and the accurate control of the speed is realized.
This application takes wing cone model 10 to need separate after being accelerated to appointed speed, and only need overcome the suction that magnet two provided and the frictional force that sealing washer 40 provided during the separation, can not destroy the major structure of taking wing cone model 10 and draw power, two suction of magnet, the equal along the track direction of 40 frictional forces of sealing washer of dragging except that gravity when separating, and then speed direction when having guaranteed the separation is along the track, has accomplished speed direction's accurate control.
This application design is simple easily to be realized, through the accurate control to power and moment of torsion during static state to possible accurate control to speed size and direction during dynamic separation.
In the present application, the number and the arrangement rule of the first magnets can be obtained according to experiments, and the number and the arrangement rule of the second magnets are consistent with those of the first magnets, specifically, reference may be made to fig. 8, 9, and 10, and it should be noted that the arrangement of the first magnets and the second magnets is not limited to the several manners of fig. 8 to 10, and is specifically arranged according to actual calculation.
The above description is intended to be illustrative and not restrictive, and the scope of the invention is defined by the appended claims, which may be modified in any manner within the scope of the invention.
Claims (5)
1. The utility model provides a winged cone model multi-angle simulation auxiliary device that entries which characterized in that: the wing-mounted cone model comprises a wing-mounted cone model (10), a sliding block (20) and a connecting plate (30), wherein a first embedded groove (11) and a second embedded groove (12) are formed in the end part of the wing-mounted cone model (10), a third embedded groove (13) is formed in the side wall of the second embedded groove (12), a sealing ring (40) is matched in the third embedded groove (13), a first magnet is adsorbed in the first embedded groove (11), a convex part (31) is arranged on one side plate surface of the connecting plate (30), the connecting plate (30) is attached to the end part of the wing-mounted cone model (10), the convex part (31) is clamped in the second embedded groove (12), a second magnet is attached to the other side plate surface of the connecting plate (30), the second magnet and the first magnet attract each other, the connecting plate (30) is fixed on the sliding block (20), the sliding block (20) is matched with a track, and a stop block (50) is arranged on the sliding block (20),
the simulation method of the multi-angle water-entering simulation auxiliary device for the winged cone model comprises the following steps of:
acquiring the mass and the mass center of the winged cone model (10) and the sizes of the first embedded groove (11), the second embedded groove (12) and the third embedded groove (13), and determining the included angle between the winged cone model (10) and the horizontal plane in a static state according to the water inlet angle required by the test;
determining how much force is needed to overcome the dead weight and the torque of the winged cone model (10) according to the mass and the mass center of the winged cone model (10) and the included angle between the winged cone model (10) and the horizontal plane in a static state, thereby determining the number of the first magnets, the arrangement mode of the first magnets in the embedded groove I (11) and the specification of the sealing ring (40);
the winged cone model (10) is connected with the connecting plate (30) in an adsorption mode, the connecting plate (30) is fixedly connected with the sliding block (20) through screws, and the sliding block (20) is connected with a track of the rocket pry launching device through a sliding groove (211) so that the sliding block (20) can slide on the track;
after the winged cone model (10), the sliding block (20) and the connecting plate (30) are driven by a solid rocket engine to accelerate to the appointed water entry speed, the stop block (50) arranged on the sliding block (20) collides with a preset brake cylinder, the sliding block (20) and the connecting plate (30) decelerate, the winged cone model (10) continues to move under the action of inertia, and when the dragging force is larger than the sum of the suction force of the magnet I and the friction force of the sealing ring (40), the winged cone model (10) is separated from the connecting plate (30), and the winged cone model (10) smoothly enters water according to the preset water entry speed and the water entry angle.
2. The winged cone model multi-angle water-entry simulation auxiliary device of claim 1, wherein: the second embedded groove (12) is annular, the convex part (31) is annular, the third embedded groove (13) extends along the circumferential direction of the inner side groove wall of the second embedded groove (12), and the second embedded groove (12) surrounds the periphery of the first embedded groove (11).
3. The winged cone model multi-angle water-entry simulation auxiliary device of claim 2, wherein: the sliding block (20) comprises two parallel side plates (21) and a middle plate (22) vertically connected between the two side plates (21), wherein an inner corner of one end of each of the two side plates (21) is provided with an angular notch, one inner wall of each angular notch is a first plane (23), the other inner wall of each angular notch is a second plane (24), the first plane (23) and the end face of one end of the side plate (21) are arranged in parallel at intervals, the first plane (23) is provided with a plurality of first threaded holes (231), the second plane (24) is provided with a strip seam (241), one end of the strip seam (241) extends to the end face of one end of the side plate (21), the periphery of the connecting plate (30) is provided with a plurality of second threaded holes (32), the first threaded holes (231) correspond to the second threaded holes (32) and are provided with screws to achieve connection of the connecting plate (30) and the sliding block (20), a wing plate (14) circumferentially arranged at one end of the winged cone model (10) penetrates through the strip seam (241), and sliding grooves (211) matched with rails are respectively formed in the outer side faces of the two side plates (21).
4. The winged cone model multi-angle water-entry simulation auxiliary device of claim 3, wherein: the stop block (50) is mounted on one of the side plates (21).
5. The winged cone model multi-angle water-entry simulation auxiliary device of claim 1, wherein: the connecting plate (30) is an aluminum plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110213038.7A CN113008515B (en) | 2021-02-26 | 2021-02-26 | Multi-angle water-entering simulation auxiliary device for winged cone model |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110213038.7A CN113008515B (en) | 2021-02-26 | 2021-02-26 | Multi-angle water-entering simulation auxiliary device for winged cone model |
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| Publication Number | Publication Date |
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| CN113008515A CN113008515A (en) | 2021-06-22 |
| CN113008515B true CN113008515B (en) | 2023-04-18 |
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Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2000016386A (en) * | 1998-07-06 | 2000-01-18 | Mitsubishi Heavy Ind Ltd | Underwater navigating body |
| AU2011215552B2 (en) * | 2010-02-11 | 2015-07-23 | Kimberly A. Carraha | Rocket launch system and supporting apparatus |
| CN106323590B (en) * | 2016-08-22 | 2019-04-02 | 浙江大学 | Object stablizes multi-angle and enters water experimental provision |
| CN106840599B (en) * | 2017-01-23 | 2019-04-16 | 大连理工大学 | A kind of sail body with the velocity of following enters water experimental provision |
| CN106932171B (en) * | 2017-04-29 | 2023-04-14 | 吉林大学 | Cross-medium aircraft water inlet and outlet test system |
| CN108593255B (en) * | 2018-05-28 | 2019-10-22 | 西北工业大学 | A kind of ventilated supercavitation sail body rotation test device for water tunnel experiment |
| CN109855837B (en) * | 2018-12-05 | 2020-07-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Model semi-constrained launching device for aircraft water inlet and outlet test and test method |
| CN109781384B (en) * | 2019-02-28 | 2020-06-02 | 大连理工大学 | Multi-navigation-body parallel water-entry experimental device |
| CN110220840B (en) * | 2019-06-12 | 2021-07-27 | 西安近代化学研究所 | Explosive acceleration device and method |
| CN110816783B (en) * | 2019-10-25 | 2021-05-14 | 哈尔滨工业大学（威海） | Launching device for water-entering experiment of navigation body and method for realizing continuous release of launching device |
| CN212313897U (en) * | 2020-03-30 | 2021-01-08 | 成都云鼎智控科技有限公司 | A flyer fixed knot constructs for flyer emitter |
| CN111854545B (en) * | 2020-06-04 | 2022-09-30 | 中国人民解放军国防科技大学 | Boosting gliding small-sized test rocket system |
| CN111721499A (en) * | 2020-07-01 | 2020-09-29 | 黄淮学院 | Experimental device for oblique water inlet and outlet of structure |
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