CN114001601A - Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof - Google Patents
Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof Download PDFInfo
- Publication number
- CN114001601A CN114001601A CN202111199235.4A CN202111199235A CN114001601A CN 114001601 A CN114001601 A CN 114001601A CN 202111199235 A CN202111199235 A CN 202111199235A CN 114001601 A CN114001601 A CN 114001601A
- Authority
- CN
- China
- Prior art keywords
- gas
- tail
- posture
- fairing
- control system
- 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.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
- F42B19/12—Propulsion specially adapted for torpedoes
- F42B19/26—Propulsion specially adapted for torpedoes by jet propulsion
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention provides a ventilation load reduction and posture adjustment device for high-speed medium-crossing water inlet and an adjustment method thereof. The invention utilizes compressed air in a high-pressure air tank to test ventilation, generates supercavity at the moment of entering water, utilizes supercavity technology to realize load reduction, simultaneously realizes adjustment in different directions through ventilation holes in different directions at the tail end of a navigation body rectifying cap, and simultaneously the tail end is provided with a pressure sensor, so that when tail shooting happens, prediction is obtained, the high-pressure air tank ventilates air holes in the tail end, and the influence of the tail shooting is reduced.
Description
Technical Field
The invention relates to a ventilation load reduction and posture adjustment device for high-speed cross-medium water entry and an adjustment method thereof, belonging to the technical field of high-speed water entry of moving objects.
Background
The water entry process is briefly described as follows: the object is subjected to a process of aqueous medium in an air medium. With the increasingly vigorous development of naval equipment, the high-speed medium-crossing navigation body is gradually diversified, and the water entry speed is gradually improved. When the navigation body enters water at a high speed, the navigation body can inevitably bear huge impact load, not only can damage devices inside the navigation body, but also can greatly influence the structural strength of the navigation body and the navigation stability of the navigation body. Since the advent of the "snowstorm" supercavity torpedo, cavitation technology in underwater drag reduction has been emphasized by various countries. The cavitation drag reduction technology changes the wetting condition of the moving object and water to the outside to be a cavitation wrapping moving object, changes the density of surrounding fluid medium, and reduces the resistance in the navigation process to a great extent. However, in the field of precise striking, a navigation body flying at high speed in the air can bear huge impact resistance when the navigation body starts to contact with the water surface, so that the stability of the water entering trajectory of the navigation body is influenced, even the navigation body is broken, and the fuel-carrying navigation body explodes, and therefore, the problem of load reduction of the high-speed navigation body entering water becomes a hot problem of domestic and foreign research.
The load reduction of the high-speed entering of the navigation body is one of the research core directions in the entering field. The traditional load reduction mode is realized by increasing a load reduction drag reduction head cap or buffering an elastic material and the like, but after high-speed water entering is subjected to huge impact load, the built head cap is easy to damage, and the elastic material can also deform under the impact load and threatens the ballistic stability. After the vacuole is closed, in order to continuously ensure the high-speed navigation of the navigation body, a manual ventilation method is mostly adopted, the navigation body is ventilated at the head part, but the navigation posture of the navigation body under water cannot be adjusted, and secondly, the vacuole shape presents asymmetry in the process of entering water in an inclined mode. The lower side of the navigation body is in contact with water, so that the lower side vacuole is not directly communicated with the atmosphere, the upper side vacuole of the bomb body is directly communicated with the air, the air flow rate of the upper side vacuole is always higher than that of the lower side vacuole in the vacuole opening process, the navigation body deflects, the tail of the navigation body and the wall surface of the vacuole continuously collide and rebound, overlarge dynamic stress response can cause the bomb body to lose efficacy, and the whole navigation body still vibrates while rotating around the head. Along with the generation of tail jet flow and tail shooting phenomena, certain requirements are also placed on the strength of the tail structure of the navigation body, and the tail shooting also influences the stability of the whole trajectory of the navigation body and negatively influences accurate hitting.
Disclosure of Invention
The invention provides a ventilation load-reducing and posture-adjusting device for high-speed cross-medium water inlet and an adjusting method thereof, aiming at solving the technical problems in the prior art mentioned in the background technology.
The invention provides a ventilation load reduction and posture adjustment device for high-speed medium-crossing water inlet, which comprises a rectifier valve, a vent hole group, a tail end air hole of a rectifier cap, a porous airflow blocker, a rotatable funnel-shaped pipe, a high-pressure air tank, a tail gas pipeline, a tail gas regulating valve, a tail air hole, a computer control system, a fairing, a navigation body shell and a pressure sensor, wherein the rotatable funnel-shaped pipe is arranged in the tail end air hole of the rectifier cap;
the fairing is arranged at the head of the navigation body shell, a fairing valve is arranged at the central position of the fairing, a vent hole group is also arranged at the head of the fairing, and a tail end air hole of a fairing cap is arranged at the tail end of the fairing; the tail end air hole of the rectifying cap is connected with a porous airflow blocker through an attitude adjusting gas pipeline, a gas regulating valve is arranged on the attitude adjusting gas pipeline, a vent hole group on the rectifying valve is connected with the porous airflow blocker through a gas pipeline, the porous airflow blocker is connected with a rotatable funnel-shaped pipe and then connected with a high-pressure gas tank, and a tail air hole at the same radial position as a head vent hole group is arranged at the tail end of the aircraft shell;
install high-pressure gas pitcher in the navigation body casing, the afterbody gas pocket is connected to high-pressure gas pitcher through afterbody gas piping, be provided with afterbody gas control valve on the afterbody gas piping, arrange pressure sensor at the afterbody gas pocket back, pressure sensor feeds back pressure information to computer control, opening and close of high-pressure gas pitcher and the rotation of rotatable funnel venturi tube, the opening and close of afterbody gas control valve and gas control valve all receive computer control system's control.
Preferably, the navigation body shell is of a revolving body structure, and the openings on the navigation body shell are uniformly distributed and are all 4 arrays along the circumferential direction.
Preferably, a battery power supply is further installed in the navigation body shell.
Preferably, the porous airflow blocker is provided with 5 holes, namely a central hole and 4 surrounding radiation holes, wherein the 4 surrounding radiation holes are positioned on the periphery of the central hole and are uniformly distributed along the circumferential direction.
Preferably, the central hole is connected with a gas pipeline to ventilate the vent hole group, the 4 surrounding radiation holes are connected with an attitude adjusting gas pipeline to ventilate the air holes at the tail end of the rectifying cap, and the contact area of the rotatable funnel-shaped pipe and the porous airflow blocker determines which pipeline is ventilated.
A method for adjusting a ventilation load-reducing and posture adjusting device for high-speed cross-medium water inflow specifically comprises the following steps:
(1) in the initial stage of entering water, posture adjustment is not needed, the rotatable funnel-shaped pipe is positioned in the center, the high-pressure gas tank only ventilates the ventilating hole group through a gas pipeline to form supercavity wrapping the navigation body, and the supercavity technology is utilized to achieve the purpose of reducing resistance of the supercavity;
(2) when the posture needs to be adjusted subsequently, the rotatable funnel-shaped pipe is controlled to rotate by a computer according to needs and is matched with the porous airflow blocker to adjust the ventilation volume of the air hole, so that the posture is adjusted;
(3) when cavitation shrinkage is about to occur under the condition of tail flapping, the pressure sensor at the tail part can feed information back to the computer control system, the computer control system controls the tail end gas pipeline to be opened, the tail end air hole is ventilated, the posture is adjusted, and the interference of the tail flapping is avoided.
The ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and the adjustment method thereof have the beneficial effects that:
the invention utilizes compressed air in a high-pressure air tank to test ventilation, generates supercavity at the moment of entering water, utilizes supercavity technology to realize load reduction, simultaneously realizes adjustment in different directions through ventilation holes in different directions at the tail end of a navigation body rectifying cap, and simultaneously the tail end is provided with a pressure sensor, so that when tail shooting happens, prediction is obtained, the high-pressure air tank ventilates air holes in the tail end, and the influence of the tail shooting is reduced.
Drawings
FIG. 1 is a schematic exterior view of a high-speed cross-media water-entering aeration load-reducing and posture-adjusting device according to the present invention;
FIG. 2 is a schematic cross-sectional view of the high-speed cross-medium water-entering aeration load-reducing and posture-adjusting device according to the present invention;
FIG. 3 is a schematic view showing a covering surface of a rotatable funnel-shaped tube, wherein (a) is a view showing a contact between the rotatable funnel-shaped tube and a porous airflow blocker when the water is introduced and the load is reduced, (b) is a view showing a contact between the rotatable funnel-shaped tube and the porous airflow blocker when the posture of any one of four directions of the air holes is adjusted by ventilating the air holes at the tail end of one of the two rectifying caps while the water is introduced and the load is reduced, and (c) is a view showing a contact between the rotatable funnel-shaped tube and the porous airflow blocker when the posture of different directions is adjusted by ventilating the air holes at the tail ends of the two rectifying caps by a difference in ventilation amount;
the device comprises a rectifier valve 1, a vent hole group 2, a rectifier cap tail end air hole 3, a gas regulating valve 4, an attitude regulating gas pipeline 5, a gas pipeline 6, a porous airflow blocker 7, a rotatable funnel-shaped pipe 8, a high-pressure gas tank 9, a tail gas pipeline 10, a tail gas regulating valve 11, a tail vent hole 12, a computer control system 13, a battery power supply 14, a rectifier cover 15, a navigation body shell 16, a corrugated pipeline 17, a gas pipeline 18 and a pressure sensor 19.
Detailed Description
The first embodiment is as follows: the present embodiment is explained with reference to fig. 1 to 3. The ventilation load reduction and posture adjustment device for high-speed medium-crossing water inlet comprises a rectifier valve 1, a ventilation hole group 2, a rectifier cap tail end air hole 3, a gas regulating valve 4, a posture regulating gas pipeline 5, a gas pipeline 6, a porous airflow blocker 7, a rotatable funnel-shaped pipe 8, a high-pressure gas tank 9, a tail gas pipeline 10, a tail gas regulating valve 11, a tail air hole 12, a computer control system 13, a fairing 15, a navigation body shell 16 and a pressure sensor 19; the fairing 15 is arranged at the head of the aircraft shell 16, a fairing valve 1 is arranged at the central position of the fairing 15, a vent hole group 2 is also arranged at the head of the fairing 15, and a fairing cap tail end air hole 3 is arranged at the tail end of the fairing 15; the tail gas hole 3 of the rectifying cap is connected with a porous gas flow blocker 7 through a posture adjusting gas pipeline 5, a gas adjusting valve 4 is arranged on the posture adjusting gas pipeline 5, a gas vent group 2 on the rectifying valve 1 is connected with the porous gas flow blocker 7 through a gas pipeline 6, the porous gas flow blocker 7 is connected with a rotatable funnel-shaped pipe 8 and then connected with a high-pressure gas tank 9, and a tail gas hole 12 at the same radial position as the head gas vent group 2 is arranged at the tail end of the aircraft shell 16;
install high-pressure gas pitcher 9 in the navigation body casing 16, afterbody gas pocket 12 is connected to high-pressure gas pitcher 9 through afterbody gas pipeline 10, be provided with afterbody gas control valve 11 on the afterbody gas pipeline 10, arrange pressure sensor 19 at afterbody gas pocket 12 back, pressure sensor 19 feeds back pressure information to computer control 13, opening and close of high-pressure gas pitcher 9 and the rotation of rotatable funnel venturi tube 8, the opening and close of afterbody gas control valve 11 and gas control valve 4 all receive computer control system 13. The high pressure gas tank 9 serves as a source of all aeration and is directly controlled by the computer control system 13.
The entire hull of the vehicle 16 is of a solid of revolution and therefore is also evenly distributed throughout the opening, i.e. a 4-array-per-revolution is achieved. The fairing 15 is arranged at the head, a fairing valve 1 is arranged at the center of the fairing, and a vent hole group 2 is arranged at the periphery 4 of the head of the aircraft body to uniformly spray high-pressure gas.
The tail end air hole 3 of the fairing cap is a small hole at the tail end of the fairing 15, and air is conveyed to the fairing along the direction from head to tail of the navigation body shell 1 through the attitude adjusting gas pipeline 5 for ventilation, and the attitude adjusting gas pipeline is mainly used for adjusting the attitude of the navigation body shell 16.
The gas regulating valve 4 is arranged on the gas pipeline 5 and controls the on-off of gas at the gas hole 3 at the tail end of the rectifying cap.
The porous airflow blocker 7, specifically referring to the enlargement of fig. 2 and fig. 3(a), the porous airflow blocker 7 is provided with 5 holes, which are a central hole and 4 peripheral radiation holes, respectively, wherein the 4 peripheral radiation holes are located at the periphery of the central hole and are uniformly distributed along the circumferential direction. The central hole is connected with a gas pipeline 6 to ventilate the vent hole group 2, 4 surrounding radiation holes are connected with an attitude adjusting gas pipeline 5 to ventilate the air hole 3 at the tail end of the rectifying cap, and the contact area of the rotatable funnel-shaped pipe 8 and the porous airflow blocker 7 determines which pipeline is ventilated. In other words, the blocking is to ventilate only one direction of the air hole. The rotatable funnel-shaped tube 8 controls the supply of gas to the different gas lines.
When the navigation body enters water for a certain distance, cavitation closing can occur, the cavitation can be reduced or even closed at the tail end of the navigation body, at the moment, the pressure sensor 19 detects the pressure change of the surrounding flow field, signals are transmitted to the computer control system 13, the computer control system 13 controls the tail valve 11 to ventilate the tail vent hole 12, the effect of delaying cavitation closing is achieved, and tail shooting is prevented.
The fairing 15 is connected with the whole navigation type body shell 16 through threads at the head end of the fairing, and the fairing 15 is provided with the fairing valve 1 and the air hole groups 2 which are uniformly arranged in the circumferential direction. The regulating gas hole 3 is connected with a porous gas flow blocker 7 through a gas pipeline 5 of a gas regulating valve 4, meanwhile, the vent hole 2 on the rectifier valve 1 is also connected with the porous gas flow blocker 7 through a gas pipeline 6, and the porous gas flow blocker 7 is connected with a rotatable funnel-shaped pipe 8 and is connected with a high-pressure gas tank 9.
A similar tail gas port 12 is also connected to the high pressure gas line 9 via a gas line 10 with a tail gas regulating valve 11, behind the tail gas port 12 a pressure sensor 19 is arranged.
A computer control system 13 and a battery voltage 14 are arranged in front of and behind the high pressure gas tank 9.
The adjusting method of the ventilation load reduction and posture adjustment device for high-speed cross-medium water inflow specifically comprises the following steps:
(1) in the initial stage of entering water, the posture is not required to be adjusted, the rotatable funnel-shaped pipe 8 is positioned in the center, the high-pressure gas tank 9 only ventilates the ventilating hole group 2 through the gas pipeline 6 to form supercavity wrapping the navigation body, and the supercavity technology is utilized to achieve the purpose of reducing the resistance of the supercavity.
(2) When the posture needs to be adjusted subsequently, the rotatable funnel-shaped pipe 8 rotates through the computer control system 13 according to needs, the ventilation volume of the air hole is adjusted, and the posture is adjusted. The specific adjustment process is that the computer control system 13 is initially set to adjust the posture at a certain moment after entering water, and the corresponding trachea is ventilated at the moment and deflected to which direction. The computer control system 13 controls the corrugated pipeline 17, and the corrugated pipeline 17 drives the whole funnel-shaped pipe 8 to rotate so as to ventilate different air pipes. The computer control system 13 is triggered by the impact load at the moment of entering water, and the time of entering water is triggered by the computer 13 to start calculation.
(3) When cavitation shrinkage is about to occur, the tail pressure sensor 19 of the tail part feeds information back to the computer control system 13, the tail gas regulating valve 11 is opened, the tail vent hole 12 is ventilated, the posture is adjusted, and the interference of tail beating is avoided.
As shown in fig. 2, the rotatable funnel-shaped tube 8 in the left side is connected to a gas line 18 via a corrugated line 17 which is free to rotate and is controlled by the computer control system 13 and leads to the high-pressure gas tank 9. The pleated tubing 17 is controlled by the computer control system 13 to allow different positions of ventilation, see in particular fig. 3. The gas line 18 is a straight line and the pipe 17 is a corrugated line (the shape of the folds of the suction pipe) and allows directional adjustment of the funnel-shaped pipe 8.
Fig. 3 shows a contact diagram of the rotatable funnel-shaped tube 8 and the porous airflow blocker 7, which is divided into three parts, (1) a contact diagram of the rotatable funnel-shaped tube 8 and the porous airflow blocker 7 for ventilation and load reduction at the time of water entry, (2) attitude adjustment in any one of four air vent directions can be performed by ventilating one of the air vent holes 3 at the tail end of the rectifying cap while ventilating and load reduction, and (3) attitude adjustment in different directions can be realized by ventilating two air vent holes 3 at the tail end of the rectifying cap while ventilating and load reduction, and by means of the difference of ventilation volume. Fig. 3(c) shows that the funnel-shaped tube 8 performs ventilation adjustment along the direction of the ventilation holes in addition to the ventilation load reduction, but when the covering surface of the funnel-shaped tube 8 on the porous airflow blocker 7 relates to 2 pipelines, the covering surface is not along the direction of the ventilation holes any more, the ventilation areas of two different air tubes are different, the ventilation flow rate is also different, and the adjustment direction is also different.
Claims (8)
1. A ventilation load reduction and posture adjustment device for high-speed medium-crossing water inlet is characterized by comprising a rectifier valve (1), a vent hole group (2), a rectifier cap tail end air hole (3), a porous airflow blocker (7), a rotatable funnel-shaped pipe (8), a high-pressure air tank (9), a tail gas pipeline (10), a tail gas regulating valve (11), a tail vent hole (12), a computer control system (13), a fairing (15), a navigation body shell (16) and a pressure sensor (19);
the fairing (15) is arranged at the head of the aircraft shell (16), a fairing valve (1) is arranged at the central position of the fairing (15), a vent hole group (2) is also arranged at the head of the fairing (15), and a fairing cap tail end air hole (3) is arranged at the tail end of the fairing (15); the tail end air hole (3) of the rectifying cap is connected with a porous airflow blocker (7) through an attitude adjusting gas pipeline (5), a gas adjusting valve (4) is arranged on the attitude adjusting gas pipeline (5), a vent hole group (2) on the rectifying valve (1) is connected with the porous airflow blocker (7) through a gas pipeline (6), the porous airflow blocker (7) is connected with a rotatable funnel-shaped pipe (8) and then connected with a high-pressure gas tank (9), and a tail vent hole (12) at the same radial position as the head vent hole group (2) is arranged at the tail end of the aircraft shell (16);
install high-pressure gas jar (9) in navigation body casing (16), afterbody air vent (12) are connected to high-pressure gas jar (9) through afterbody gas piping (10), be provided with afterbody gas control valve (11) on afterbody gas piping (10), arrange pressure sensor (19) at afterbody air vent (12) back, pressure sensor (19) feed back pressure information to computer control system (13), the opening and close of high-pressure gas jar (9) and the rotation of rotatable funnel venturi tube (8), afterbody gas control valve (11) and gas control valve 4 open and close all receive computer control system's (13) control.
2. The aeration load shedding and posture adjustment device for high-speed cross-medium water inflow according to claim 1, wherein the navigation body shell (16) is in a revolving body structure, and the openings on the navigation body shell are uniformly distributed and are all arranged in 4 arrays along the circumferential direction.
3. The high speed cross-media water entry aeration load shedding and attitude adjustment device of claim 1, wherein a battery power supply (14) is also mounted within the hull housing (16).
4. The aeration load reduction and posture adjustment device for high-speed cross-medium water inlet according to claim 1, characterized in that the porous airflow blocker (7) is provided with 5 holes, namely a central hole and 4 surrounding radiation holes, wherein the 4 surrounding radiation holes are located on the periphery of the central hole and are uniformly distributed along the circumferential direction.
5. The aeration load reduction and posture adjustment device for high-speed cross-media water inlet according to claim 4, characterized in that the central hole is connected with a gas pipeline (6) to aerate the aeration hole group (2), 4 surrounding radiation holes are connected with a posture adjustment gas pipeline (5) to aerate the tail end air hole (3) of the rectification cap, and the contact area of the rotatable funnel-shaped pipe (8) and the porous airflow blocker (7) determines which pipeline is aerated.
6. The aeration load reduction and posture adjustment device for high-speed cross-medium water inlet according to claim 1, characterized in that a corrugated pipeline (17) and a gas pipeline (18) are installed at the connection position of the rotatable funnel-shaped pipe (8) and the high-pressure gas tank (9), and the rotatable funnel-shaped pipe (8), the corrugated pipeline (17), the gas pipeline (18) and the high-pressure gas tank (9) are connected in sequence.
7. An adjusting method of the ventilation, load reduction and posture adjusting device for high-speed cross-medium water inflow according to any one of claims 1 to 6, which is characterized by comprising the following steps:
(1) in the initial stage of water entering, the posture is not required to be adjusted, the rotatable funnel-shaped pipe (8) is positioned in the center, the high-pressure gas tank (9) only ventilates the ventilating hole group (2) through the gas pipeline (6) to form supercavitation wrapping the navigation body shell (16), and the supercavitation technology is utilized to achieve the purpose of reducing resistance of the supercavitation;
(2) when the posture needs to be adjusted subsequently, the funnel-shaped pipe (8) can be rotated to be matched with the porous airflow blocker (7) through the computer control system (13) to adjust the ventilation volume of each air hole according to needs, so that the posture is adjusted;
(3) when cavitation shrinkage is about to occur under the condition of tail beat, the pressure sensor (19) at the tail part feeds information back to the computer control system (13), the computer control system (13) controls the tail part gas regulating valve (11) to be opened, the tail part vent hole (12) is ventilated, the posture is adjusted, and the interference of the tail beat is avoided.
8. The adjusting method of the ventilation load-reducing and posture adjusting device for high-speed cross-medium water inflow according to claim 7, characterized in that the computer control system (13) is triggered by the instantaneous impact load of water inflow, and the water inflow time is triggered by the computer control system (13) to start calculating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111199235.4A CN114001601B (en) | 2021-10-14 | 2021-10-14 | Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111199235.4A CN114001601B (en) | 2021-10-14 | 2021-10-14 | Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114001601A true CN114001601A (en) | 2022-02-01 |
| CN114001601B CN114001601B (en) | 2022-07-08 |
Family
ID=79922883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111199235.4A Active CN114001601B (en) | 2021-10-14 | 2021-10-14 | Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114001601B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114701599A (en) * | 2022-04-19 | 2022-07-05 | 吉林大学 | Buffer device for high-speed water entry of navigation body |
| CN114839988A (en) * | 2022-04-28 | 2022-08-02 | 哈尔滨工业大学 | Protective tail cover separation time sequence control method during high-speed water entry of navigation body |
| CN115285347A (en) * | 2022-07-01 | 2022-11-04 | 哈尔滨工程大学 | Bionic load reduction structure configuration for high-speed inclined water entry and water entry method |
| CN117416507A (en) * | 2023-12-18 | 2024-01-19 | 中国空气动力研究与发展中心空天技术研究所 | Water-entering load-reducing device and bionic cross-medium aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5955698A (en) * | 1998-01-28 | 1999-09-21 | The United States Of America As Represented By The Secretary Of The Navy | Air-launched supercavitating water-entry projectile |
| US20140061364A1 (en) * | 2012-07-17 | 2014-03-06 | Raytheon Company | Integrated propulsion and attitude control system from a common pressure vessel for an interceptor |
| CN109341443A (en) * | 2018-09-01 | 2019-02-15 | 哈尔滨工程大学 | A kind of reversed jet bubbling crystallzation assists high speed to enter water to lower shock loading mechanism |
| CN111829402A (en) * | 2020-06-10 | 2020-10-27 | 中山大学 | Method for assisting high-speed water entry by forward water spraying, air spraying and air ventilating cavitation |
| CN111846160A (en) * | 2020-06-10 | 2020-10-30 | 中山大学 | Water spraying, air jetting and ventilating forward cavitation-assisted high-speed water inlet mechanism |
| CN112413043A (en) * | 2020-11-19 | 2021-02-26 | 大连理工大学 | Air bag type composite load reduction device for sailing body entering water |
| CN112781448A (en) * | 2020-12-29 | 2021-05-11 | 哈尔滨工程大学 | Anti-submarine missile based on water inlet buffer device and control method |
-
2021
- 2021-10-14 CN CN202111199235.4A patent/CN114001601B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5955698A (en) * | 1998-01-28 | 1999-09-21 | The United States Of America As Represented By The Secretary Of The Navy | Air-launched supercavitating water-entry projectile |
| US20140061364A1 (en) * | 2012-07-17 | 2014-03-06 | Raytheon Company | Integrated propulsion and attitude control system from a common pressure vessel for an interceptor |
| CN109341443A (en) * | 2018-09-01 | 2019-02-15 | 哈尔滨工程大学 | A kind of reversed jet bubbling crystallzation assists high speed to enter water to lower shock loading mechanism |
| CN111829402A (en) * | 2020-06-10 | 2020-10-27 | 中山大学 | Method for assisting high-speed water entry by forward water spraying, air spraying and air ventilating cavitation |
| CN111846160A (en) * | 2020-06-10 | 2020-10-30 | 中山大学 | Water spraying, air jetting and ventilating forward cavitation-assisted high-speed water inlet mechanism |
| CN112413043A (en) * | 2020-11-19 | 2021-02-26 | 大连理工大学 | Air bag type composite load reduction device for sailing body entering water |
| CN112781448A (en) * | 2020-12-29 | 2021-05-11 | 哈尔滨工程大学 | Anti-submarine missile based on water inlet buffer device and control method |
Non-Patent Citations (1)
| Title |
|---|
| 魏英杰等: "超空泡射弹尾拍问题研究进展", 《舰船科学技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114701599A (en) * | 2022-04-19 | 2022-07-05 | 吉林大学 | Buffer device for high-speed water entry of navigation body |
| CN114701599B (en) * | 2022-04-19 | 2023-02-28 | 吉林大学 | Buffer device for high-speed water entry of navigation body |
| CN114839988A (en) * | 2022-04-28 | 2022-08-02 | 哈尔滨工业大学 | Protective tail cover separation time sequence control method during high-speed water entry of navigation body |
| CN115285347A (en) * | 2022-07-01 | 2022-11-04 | 哈尔滨工程大学 | Bionic load reduction structure configuration for high-speed inclined water entry and water entry method |
| CN117416507A (en) * | 2023-12-18 | 2024-01-19 | 中国空气动力研究与发展中心空天技术研究所 | Water-entering load-reducing device and bionic cross-medium aircraft |
| CN117416507B (en) * | 2023-12-18 | 2024-02-20 | 中国空气动力研究与发展中心空天技术研究所 | Water-entering load-reducing device and bionic cross-medium aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114001601B (en) | 2022-07-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114001601B (en) | Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof | |
| US7784732B2 (en) | Boundary-layer-ingesting inlet flow control system | |
| CN107505138B (en) | A kind of complicated distortion generator for Compressor Stability test | |
| CN106184719B (en) | A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle | |
| CN108680333B (en) | Rotary driving device for rotary aerodynamic effect wind tunnel test | |
| CN106679923B (en) | A kind of pressure decoupling device influencing dynamometry model for high speed jet | |
| CN104833476A (en) | Low Mach number system of trisonics wind tunnel | |
| CN103437911A (en) | Partition-bearing fluid control binary vector nozzle tube and vector thrust generation and control method thereof | |
| CN111175021A (en) | Device and method for testing supercavitation water holes under action of head ventilation and tail jet flow | |
| CN104986358A (en) | Stability augmentation inflation type reentry vehicle | |
| CN107021235A (en) | A kind of low-to-medium altitude aircraft driving device, driving method and low-to-medium altitude aircraft | |
| CN115436009B (en) | Jet pipe thrust measurement test system with integrally designed afterbody and jet pipe | |
| CN106441781A (en) | Flow rate measurable air intake duct throttling device | |
| CN108953231A (en) | A kind of collector air inlet device of centrifugal blower | |
| CN106697306A (en) | Secondary flow self-circulation pneumatic type adjustable air inflow passageway for in-step compression surface and control method | |
| CN206310064U (en) | A kind of air bleeding valve and water-carriage system | |
| CN203681861U (en) | Flow control device capable of reducing aerodynamic resistance of airship and improving attitude stability | |
| CN208897309U (en) | A kind of leading edge part sweepback type grid airvane and play flight device | |
| CN108248811B (en) | Wind-resistant hot air balloon | |
| CN206537467U (en) | Deep water autonomous underwater vehicle levitating device | |
| CN116046330B (en) | Three-degree-of-freedom virtual flight test device capable of ventilating | |
| CN106121706B (en) | Ventilation and dust removal integrated system for medium-length tunnel | |
| CN109733929A (en) | A kind of pneumatic air pump | |
| CN110500185A (en) | Ventilation cooling device for air entraining valve | |
| CN108163184A (en) | Air blowing circular rector self-regulation aircraft |
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 |