CN108177747B - Ship passive interference rocket projectile fixed launching deflector - Google Patents
Ship passive interference rocket projectile fixed launching deflector Download PDFInfo
- Publication number
- CN108177747B CN108177747B CN201711400421.3A CN201711400421A CN108177747B CN 108177747 B CN108177747 B CN 108177747B CN 201711400421 A CN201711400421 A CN 201711400421A CN 108177747 B CN108177747 B CN 108177747B
- Authority
- CN
- China
- Prior art keywords
- deflector
- panel
- angle
- flow
- flow guide
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G1/00—Arrangements of guns or missile launchers; Vessels characterised thereby
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B71/00—Designing vessels; Predicting their performance
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a ship passive interference rocket projectile fixed launching deflector and a design method thereof, wherein the design method of the deflector specifically comprises the following steps: acquiring a transmitting parameter of a transmitting device; simulating according to the emission parameters of the emission device to obtain the tail flame injection range; determining the size of a flow guide surface of the flow guider according to the tail flame spraying range of the launching device; determining a flow guide angle of a flow guide surface of the flow guide device; and setting a lateral flow surface, constructing a fluid director model according to the size of the flow guide surface, the flow guide angle of the flow guide surface and the inclination angle of the lateral flow surface, and optimally adjusting the structure of the fluid director. The fluid director of the invention can smoothly guide the jet flow of the jet pipe of the transmitting device to the atmospheric environment, can control the lateral diffusion influence range of the jet flow, and effectively solves the problem that the repeated scouring of the jet flow can damage the ship structure and the ship surface equipment around the ship structure.
Description
The invention relates to a divisional application of invention patent 'a ship passive interference rocket projectile fixed launching deflector and a design method thereof' with application number of 201711098007.1 on 11/9/2017
Technical Field
The invention relates to the technical field of missile launching, in particular to a fixed launching deflector for a ship passive interference rocket projectile and a design method thereof.
Background
Because of the limitation of ship surface materials and space, high-temperature and high-speed gas jet flow generated by a missile and rocket projectile thermal launching tail engine can directly act on a ship structure and surrounding equipment thereof, and severe impact and thermal ablation are generated on the ship structure and the surrounding equipment thereof.
When a small and medium-sized ship is designed, due to the restriction of the environmental conditions of the ship surface, the passive interference emitting device is usually arranged in the ship surface area with a complex environment, and the structures of nearby ships are made of aluminum alloy materials with relatively low melting points. When the passive interference launching device continuously launches, the gas flow generated by the rocket projectile engine is repeatedly flushed to the ship surface environment, so that the safety influence is generated, and therefore safety protection measures need to be taken during the overall design.
The ship surface equipment of large and medium ships is generally arranged in the ship surface area which does not influence the surrounding environment, and the ship structure has the capability of bearing repeated washing of fuel gas flow when rocket projectiles are continuously launched, so that after being launched, a common weapon only carries out repair treatment on the surface coating of the deck; for small and medium-sized ships made of aluminum alloy structural materials with relatively low melting points, only single scouring of gas flow can be resisted by brushing high-temperature-resistant paint.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, designs a ship passive interference rocket projectile fixed launching deflector and a design method thereof, and effectively solves the problem that repeated washing of a jet flow of a launching device can damage a ship structure and ship surface equipment around the ship structure.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a design method for a ship passive interference rocket projectile fixed launching deflector specifically comprises the following steps:
step 1: acquiring emission parameters and a tail flame injection angle of an emission device;
step 2: simulating according to the emission parameters of the emission device to obtain the tail flame injection range;
and step 3: determining the size of a flow guide surface of the flow guider according to the tail flame spraying range of the launching device;
and 4, step 4: determining a flow guide angle of a flow guide surface of the flow guide device;
and 5: the left side and the right side of the flow guide surface are respectively outwards folded to form a side flow surface which is inclined upwards, and the extension surface of the side flow surface is positioned above the surrounding ship surface equipment;
step 6: according to the size of the flow guide surface, the flow guide angle and the inclination angle of the lateral flow surface, a flow guide model is constructed, a tail flame jet flow of an emitting device provided with a flow guide is simulated, a temperature cloud picture and a pressure cloud picture of the ship surface environment are obtained, the temperature and pressure conditions of different areas of the ship surface are analyzed according to the temperature cloud picture and the pressure cloud picture, and the setting parameters of the flow guide surface and/or the lateral flow surface are adjusted according to the analysis result.
Preferably, the launching parameters of the launching device comprise the outlet diameter and the outlet expansion half angle of the rocket engine injection pipe; the specific steps of obtaining the tail flame injection range according to the simulation of the emission parameters of the emission device are as follows:
step 2.1: determining an arrangement scheme of the transmitting devices, wherein the arrangement scheme comprises a plurality of transmitting states, and each transmitting state corresponds to a unique transmitting angle;
step 2.2: adjusting the emission angle of the emission device, and sequentially simulating and simulating tail flame jet flows of the emission device in each emission state;
step 2.3: merging the jet flows of the tail flames in the emission states to obtain a total jet flow of the tail flames;
step 2.4: and simulating the jet cross section of the total jet flow of the tail flames on the deck, wherein the jet cross section is the tail flame jet range of the emitting device.
Preferably, the specific steps of simulating the tail flame jet flow of the emitting device in a certain emitting state in the step 2.2 are as follows:
step 3.1: determining the current emission angle of the emission device and the fixed elevation angle of each injection pipe;
step 3.2: simulating a pipe jet flow of the jet pipe by taking an extension line of an outlet expansion boundary of the jet pipe as a boundary streamline of a tail flame of the jet pipe according to a current emission angle of the emission device, and the outlet diameter, the outlet expansion half angle and the fixed elevation angle of the jet pipe;
step 3.3: repeating the step 3.2, and simulating the pipe jet flow of each jet pipe;
step 3.4: and combining the pipe jet flows of the injection pipes to obtain the tail flame jet flow of the emission device in the current emission state.
Preferably, the area of the flow guide surface is larger than the tail flame ejection range.
Preferably, the flow guide surfaces comprise a first flow guide surface and a second flow guide surface, and the first flow guide surface is connected with the second flow guide surface;
the diversion angle α of the first diversion surface satisfies the relation of α<90°-λ1Wherein α is the diversion angle of the first diversion surface, λ1The angle between the injection pipe with the maximum fixed elevation angle and the horizontal ground is the included angle between the injection pipe with the maximum fixed elevation angle of the emission device in the maximum emission angle state and the horizontal ground;
the diversion angle β of the second diversion surface satisfies the relation of β<90°-λ2Wherein β is the diversion angle of the second diversion surface, λ2The angle between the injection pipe with the minimum fixed elevation angle and the horizontal ground is the minimum angle between the injection pipe and the horizontal ground when the emission device is in the minimum emission angle state.
Preferably, the included angle between the lateral flow surface and the flow guide surface is not less than 20 °.
The utility model provides a naval vessel passive interference rocket projectile fixed emission divertor, includes the baffle, the baffle includes first diversion panel, second diversion panel, the backup pad that links up mutually with first diversion panel, first diversion panel and first diversion panel all incline the setting, and the left and right both sides of first diversion panel and second diversion panel all turn over the side flow panel of an tilt up outward, the backup pad is vertical respectively to be fixed on the side flow panel with the trailing flank of second diversion panel on.
Preferably, the support plate is provided with a plurality of lightening holes which are uniformly distributed.
Preferably, the distance between the fluid director and the outlet of the injection pipe of the emission device is 300mm-500mm, the fluid director is fixed on a deck of a ship, a transition joint is arranged between the fluid director and the deck of the ship, the transition joint is composed of an aluminum plate and a steel plate, and the aluminum plate and the steel plate are fixed through gluing.
Preferably, the diversion angle α of the diversion surface of the first diversion panel satisfies the relation α<90°-λ1Wherein α is the diversion angle of the first diversion panel, λ1The ejector tube with the largest fixed elevation angle of the emitter in the maximum emitting angle stateThe included angle between the second diversion surface and the horizontal ground, and the diversion angle β of the second diversion surface satisfy the relation of β<90°-λ2Wherein β is the diversion angle of the second diversion panel, λ2The angle between the injection pipe with the minimum fixed elevation angle and the horizontal ground is the minimum angle between the injection pipe and the horizontal ground when the emission device is in the minimum emission angle state; the included angle between the lateral flow panel and the first flow guide panel or the second flow guide panel is not less than 20 degrees.
The invention has the following positive beneficial effects:
1. the flow guide surface of the fluid director can guide the jet flow of the jet pipe of the launching device to the atmospheric environment smoothly, and the lateral flow surfaces are arranged on the two sides of the flow guide surface, so that the fluid director can control the lateral diffusion influence range of the jet flow, and the problem that the ship structure and the ship surface equipment around the ship structure are damaged due to the repeated washing of the jet flow is effectively solved.
2. The distance between the fluid director and the outlet of the injection pipe of the launching device is 300mm-500mm, and the arrangement of the fluid director does not influence the normal use of the launching device and the loading and unloading of rocket projectiles, the preparation of weapons before shooting, the equipment detection, the maintenance and the like.
3. Because the fluid director is made by steel material, the hull structure is the aluminium material, through setting up the transition joint between fluid director and hull structure, has solved the transition connection between steel fluid director and aluminium hull structure effectively.
Drawings
Fig. 1 is a perspective view of the present invention.
Fig. 2 is a side view of the present invention.
Fig. 3 is a sectional view taken along the line a-a in fig. 2.
Fig. 4 is a view from direction B of fig. 3.
Fig. 5 is a schematic view of the usage state of the present invention.
The specific meanings of the reference numbers in the figures are: 1 is a transition joint, 2 is a support plate, 3 is a first flow guide panel, 4 is a second flow guide panel, 5 is a side flow panel, and 6 is a lightening hole.
Detailed Description
In order that the objects, aspects and advantages of the invention will become more apparent, the invention will be described by way of example only, and in connection with the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
In the first embodiment, the present invention is described with reference to fig. 1 to 5, and the passive interference rocket projectile fixed launching deflector for a ship of the present invention is a safety protection device designed to solve the destructive influence of a gas flow emitted by an engine on the ship and nearby equipment during rocket projectile launching, and is particularly suitable for small and medium-sized ships with compact ship surface and light ships with aluminum alloy hull structures. The fluid director of the application can not only smoothly guide the jet flow of the jet pipe of the transmitting device to the atmospheric environment, but also control the lateral diffusion influence range of the jet flow, and simultaneously, the fluid director can not influence the normal use of the transmitting device and peripheral ship equipment when in application, and the appearance and the size of the fluid director are also integrated into the overall design of the ship.
Specifically, the fixed transmission divertor of naval vessel passive interference rocket projectile includes the baffle, the baffle includes backup pad 2, first drainage panel 3 and second drainage panel 4. The first flow guide panel 3 and the second flow guide panel 4 are obliquely arranged, the second flow guide panel 4 is connected with the first flow guide panel 1, and the left side and the right side of the first flow guide panel 3 and the second flow guide panel 4 are outwardly turned to form a side flow panel 5 which is inclined upwards. The support plate 2 is welded and fixed to the outer side of the side flow panel 5 and the rear side of the second flow guide panel 4.
The left and right side and rear side support plates 2, the first flow guide panel 3 and the second flow guide panel 4 together form a flow guide frame of the flow guide, and the flow guide angle α of the first flow guide panel 3 satisfies the relation of α<90°-λ1Wherein α is the diversion angle of the first diversion panel, λ1The angle between the injection pipe with the maximum fixed elevation angle and the horizontal ground in the maximum emission angle state of the emission device is the maximum angle, the diversion angle β of the second diversion panel 4 satisfies the relation of β<90°-λ2Wherein β is the diversion angle of the second diversion panel, λ2The angle between the injection pipe with the minimum fixed elevation angle and the horizontal ground is the minimum angle between the injection pipe and the horizontal ground when the emission device is in the minimum emission angle state. Therefore, the deflector of the present application is composed of two deflector sections.
In the process of designing the ship passive interference rocket projectile fixed launching deflector, the design method specifically comprises the following steps:
step 1: acquiring launching parameters of a launching device, wherein the launching parameters comprise parameters such as outlet diameter and outlet expansion half angle of a rocket engine jet pipe.
Step 2: and simulating according to the emission parameters of the emission device to obtain the tail flame injection range.
The specific steps of obtaining the tail flame injection range of the emitting device through simulation are as follows:
step 2.1: determining an arrangement scheme of the transmitting devices, wherein the arrangement scheme comprises a plurality of transmitting states, and each transmitting state corresponds to a unique transmitting angle; in the present embodiment, it is assumed that the transmitting device has 3 transmitting states, which are 22 °, 32 ° and 40 ° transmitting angles, respectively.
Step 2.2: adjusting the emission angle of the emission device, and sequentially simulating and simulating tail flame jet flows of the emission device in each emission state;
specifically, first, the current emission angle of the emission device and the fixed elevation angles of the emission tubes are determined, assuming that there are 3 emission tubes on the emission device, the fixed elevation angle of the first emission tube is a, the fixed elevation angle of the second emission tube is b, the fixed elevation angle of the third emission tube is c, and a < b < c, and assuming that the emission angle of the current emission device is 32 °. Then, according to the current emission angle of the emission device, the outlet diameter, the outlet expansion half angle and the fixed elevation angle of a certain injection pipe, a pipe jet flow of the injection pipe is simulated by taking the extension line of the outlet expansion boundary as the boundary streamline of the tail flame, namely, the pipe jet flow of the first injection pipe can be represented by the area formed by the extension line along the emission angle direction of the emission device and from the injection outlet of the first injection pipe according to the expansion half angle value of the first injection pipe. And then simulating the pipe jet flow of the second jet pipe and the third jet pipe in sequence. And combining the tube jet flows of the three jet tubes to obtain the tail flame jet flow of the emitting device under the state of an emission angle of 32 degrees.
Adjusting the emission angle of the emission device, and simulating the tail flame jet flow of the emission device under the emission angle states of 22 degrees and 40 degrees respectively according to the steps.
Step 2.3: merging the jet flows of the tail flames in the emission states to obtain a total jet flow of the tail flames; namely, the tail flame jet flows of the emission device under the three emission states of 22 degrees, 32 degrees and 40 degrees are combined to obtain the total tail flame jet flow.
Step 2.4: and simulating the jet cross section of the total jet flow of the tail flames on the deck, wherein the jet cross section is the tail flame jet range of the emitting device.
And step 3: the size of the guide surface of the fluid director is determined according to the tail flame spraying range of the launching device, the size of the guide surface is larger than the tail flame spraying range, the guide surface comprises a first guide surface and a second guide surface, and the first guide surface is connected with the second guide surface.
And 4, step 4: determining a flow guide angle of a flow guide surface of the flow guide device;
the flow direction track of the fuel gas flow is analyzed according to the fluid mechanics theory, and in order to smoothly guide the tail flame jet flow of the launching device to the atmospheric environment, the guide angle α of the first guide surface satisfies the relation of α<90°-λ1Wherein α is the diversion angle of the first diversion surface (i.e. the included angle between the first diversion surface and the horizontal plane), λ1The angle between the jet pipe with the maximum fixed elevation angle and the horizontal ground is the maximum angle of the launching device in the maximum launching angle state, and the diversion angle β of the second diversion surface satisfies the relation of β<90°-λ2Wherein β is the diversion angle of the second diversion surface (i.e. the included angle between the second diversion surface and the horizontal plane), λ2The angle between the injection pipe with the minimum fixed elevation angle and the horizontal ground is the minimum angle between the injection pipe and the horizontal ground when the emission device is in the minimum emission angle state.
And 5: the left and right sides of the flow guide surface are respectively folded outwards to form a side flow surface which inclines upwards.
When the tail flame of the emitting device acts on the flow guide surface of the fluid director, the flow direction of the gas flow not only moves upwards along the flow guide surface, but also carries out discrete diffusion along the flow guide surface. In order to avoid the influence of the lateral diffusion of the gas flow on the ship surface environment (namely ship surface equipment around the launching device), the flow direction locus of the gas flow is analyzed according to the fluid mechanics theory, and the smaller the lateral inclination angle of the lateral flow surface at the two sides of the flow guide surface is, the larger the lateral component force along the upwarp molded surface generated by the lateral dispersed gas flow is, so that the more smooth the lateral flow of the gas flow is. On the contrary, when the lateral inclination angle is too large, the decomposed lateral thrust is reduced, the flow of the gas flow along the lateral upwarping molded surface is reduced, and a partial accumulation phenomenon is possibly generated, so that the extension surface of the lateral flow surface is positioned above the surrounding ship surface equipment. The inventor finds out through long-time groping, research and a large number of simulation experiments that when the included angle between the lateral flow surface and the flow guide surface is not less than 20 degrees, the jet tail flame of the launching tube cannot influence ship surface equipment around the launching tube.
Step 6: according to the size of the flow guide surface, the flow guide angle of the flow guide surface and the inclination angle of the lateral flow surface, a flow guide model is constructed, a tail flame jet flow of an emitting device provided with the flow guide is simulated to obtain a temperature cloud picture and a pressure cloud picture of the ship surface environment, the temperature and pressure conditions of different areas of the ship surface are analyzed according to the temperature cloud picture and the pressure cloud picture, and the setting parameters of the flow guide surface and/or the lateral flow surface (namely the size of the flow guide surface, the flow guide angle of the flow guide surface or the inclination angle of an inclined surface) are adjusted according to the analysis result, so that the structure of the flow guide.
The second embodiment is different from the first embodiment in that a plurality of lightening holes 6 are uniformly distributed on the supporting plate 2, the lightening holes 6 do not affect the structural bearing capacity of the fluid director, and the weight of the fluid director can be lightened, so that the appearance, the weight and the size of the fluid director are integrated into the overall design of a ship to meet the design requirements of the overall weight and the bearing of the ship.
The third embodiment is different from the first embodiment or the second embodiment in that the fluid director needs to be fixed on a ship deck in the use process, and the ship structure is made of aluminum material because the fluid director is made of steel material, so that transition connection between the steel fluid director and the aluminum ship structure needs to be considered in the use process of the fluid director, and a transition joint 1 is arranged between the fluid director and the ship deck. The transition joint 1 is composed of an aluminum plate and a steel plate, and the aluminum plate and the steel plate are fixed through gluing. The aluminum panel of the transition joint 1 is fixed with the hull structure, and the steel panel is fixed with the bottom plate of the fluid director. In order not to influence the normal use of the launching device and the normal operation of loading and unloading rocket projectiles, preparation before shooting weapons, equipment detection, maintenance and the like, the flow guider is fixed at the position 300mm-500mm away from the outlet of the jetting pipe of the launching device in the using process. The other specific embodiments are the same as the first or second embodiments, and detailed description thereof is omitted.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will appreciate that; modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.
Claims (3)
1. A ship passive interference rocket projectile fixed launching deflector is characterized by comprising a deflector, wherein the deflector comprises a first deflector panel, a second deflector panel and a supporting plate, the second deflector panel is connected with the first deflector panel, the first deflector panel and the second deflector panel are obliquely arranged, the left side and the right side of the first deflector panel and the right side of the second deflector panel are respectively and outwardly turned to form an upward inclined lateral flow panel, and the supporting plate is respectively and vertically fixed on the lateral flow panel and the rear side surface of the second deflector panel;
the first flow guide panel is positioned below the second flow guide panel,
the diversion angle α of the first diversion panel satisfies the relation of α<90°-λ1Wherein α is the diversion angle of the first diversion panel, λ1For transmitting at maximum by the transmitting deviceThe included angle between the injection pipe with the largest fixed elevation angle and the horizontal ground in the angle state;
the diversion angle β of the second diversion surface satisfies the relation of β<90°-λ2Wherein β is the diversion angle of the second diversion panel, λ2The angle between the injection pipe with the minimum fixed elevation angle and the horizontal ground is the minimum angle between the injection pipe and the horizontal ground when the emission device is in the minimum emission angle state;
the included angle between the lateral flow panel and the first flow guide panel or the second flow guide panel is not less than 20 degrees.
2. The ship passive jamming rocket projectile stationary launching deflector of claim 1, wherein a plurality of uniformly distributed lightening holes are formed in the support plate.
3. The vessel passive jamming rocket projectile fixed launching deflector according to claim 1, wherein the distance between the deflector and the outlet of the launching device jet pipe is 300mm-500mm, the deflector is fixed on the vessel deck, a transition joint is arranged between the deflector and the vessel deck, the first deflector panel is in contact with the transition joint, the transition joint is composed of an aluminum plate and a steel plate, and the aluminum plate and the steel plate are fixed through gluing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711400421.3A CN108177747B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711400421.3A CN108177747B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector |
| CN201711098007.1A CN108177746B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector and design method thereof |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711098007.1A Division CN108177746B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector and design method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108177747A CN108177747A (en) | 2018-06-19 |
| CN108177747B true CN108177747B (en) | 2020-08-04 |
Family
ID=62544932
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711400421.3A Active CN108177747B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector |
| CN201711098007.1A Active CN108177746B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector and design method thereof |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711098007.1A Active CN108177746B (en) | 2017-11-09 | 2017-11-09 | Ship passive interference rocket projectile fixed launching deflector and design method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN108177747B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110131076B (en) * | 2019-04-23 | 2020-05-08 | 湖北三江航天江北机械工程有限公司 | Modularized forming method of fluid director |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1357976A (en) * | 1972-01-04 | 1974-06-26 | British Aircraft Corp Ltd | Missile launchers |
| US5127609A (en) * | 1991-02-25 | 1992-07-07 | Lynn B Stanley | Jet blast deflector fence |
| FR2934041B1 (en) * | 2008-07-17 | 2011-07-01 | Dcns | ARMS SYSTEM, IN PARTICULAR FOR MISSILES, INTENDED TO BE INTEGRATED INTO A COMBAT PLATFORM AND CORRESPONDING COMBAT PLATFORM |
| CN105971769B (en) * | 2016-07-13 | 2017-07-04 | 西安航天动力测控技术研究所 | The positive vertical test gas diversion device of small-scale solid rocket motor |
| CN106347702B (en) * | 2016-08-24 | 2018-07-27 | 东南大学 | A kind of gas-jetting flow-guiding plate |
| CN106247855B (en) * | 2016-09-13 | 2018-06-19 | 湖北航天技术研究院总体设计所 | A kind of liftable transmitting station of air deflector |
| CN107144170A (en) * | 2017-07-04 | 2017-09-08 | 北京理工大学 | A kind of big cambered surface air deflector of monoblock type for Vertical Launch duplex multiple missile |
| CN107131794B (en) * | 2017-07-04 | 2018-11-23 | 北京理工大学 | A kind of truck-mounted missile transmitting double-arc shape air deflector |
| CN107202515A (en) * | 2017-07-04 | 2017-09-26 | 北京理工大学 | One kind turns to twist research platform gas diversion device |
-
2017
- 2017-11-09 CN CN201711400421.3A patent/CN108177747B/en active Active
- 2017-11-09 CN CN201711098007.1A patent/CN108177746B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108177746B (en) | 2020-08-04 |
| CN108177747A (en) | 2018-06-19 |
| CN108177746A (en) | 2018-06-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9909829B2 (en) | Muzzle brake | |
| EP1917182B1 (en) | Armed stealth surface vessel | |
| US2998754A (en) | Missile launcher | |
| CN103183132B (en) | Launch by power source unit body and aircraft carrier combustion and steam ejector and catapult technique | |
| CN108177747B (en) | Ship passive interference rocket projectile fixed launching deflector | |
| CN109470080B (en) | Vehicle-mounted missile launching flow guide device and launching vehicle with same | |
| CN104864774A (en) | Self-catapulting launching device for guided missile | |
| US2925013A (en) | Rocket engine assembly testing and launching apparatus | |
| CN112610357A (en) | S-shaped invisible spray pipe with cooling structure | |
| CN110425057B (en) | Gas flow guiding device for vehicle-mounted rocket launching | |
| CN111156866A (en) | High-speed entry navigation body second grade head form | |
| US20170088254A1 (en) | Ultra-High-Pressure Fluid Injection Dynamic Orbit-Transfer System and Method | |
| CN105910492A (en) | Winged missile vertical thermal emission inner-round outer-square concentric cylinder structure | |
| CN102230761B (en) | Marine inflation expanding target ship with longitudinal symmetry structure | |
| CN110595276B (en) | Gas flow self-discharging structure suitable for missile launcher | |
| CN217976406U (en) | Light force transmission structure from rocket tail cabin to bottom of storage box | |
| CN118463724A (en) | Underwater emission platform based on fuel gas ejection | |
| CN106289787A (en) | Tail room for engine testsand gas extraction system | |
| CN117367214A (en) | Vehicle-mounted tail spray safety protection device | |
| KR102225571B1 (en) | Structure of ship | |
| CN111023150B (en) | Extension plate for combustion chamber | |
| CN116066258A (en) | Gao Wendu-resistant cover of solid rocket engine spray pipe | |
| KR102181031B1 (en) | A ground test device for upper-stage rocket engine | |
| CN106742025A (en) | A kind of large power shaft is to superpower trust engine, the supersonic ejection device using the engine and ejection control method | |
| CN119022718B (en) | A launch ship guide trough noise reduction and diversion device and design method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |