CN109470080B - Vehicle-mounted missile launching flow guide device and launching vehicle with same - Google Patents
Vehicle-mounted missile launching flow guide device and launching vehicle with same Download PDFInfo
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- CN109470080B CN109470080B CN201811280545.7A CN201811280545A CN109470080B CN 109470080 B CN109470080 B CN 109470080B CN 201811280545 A CN201811280545 A CN 201811280545A CN 109470080 B CN109470080 B CN 109470080B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
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Abstract
The invention discloses a vehicle-mounted missile launching diversion device and a launching vehicle with the same, wherein the vehicle-mounted missile launching diversion device comprises: the gas flow guider is used for guiding gas flow and comprises a downward sunken arc-shaped main profile and connecting surfaces which are respectively connected with the head side and the tail side of the main profile; the throttle plate is arranged above the fluid director, a plurality of through holes are formed in the surface of the throttle plate, and the surface of the throttle plate is positioned on a flow path of a gas flow, so that the technical field of missile launching equipment is related. The invention reduces the impact of the gas flow on the fluid director, further reduces the shearing force generated by the friction between the hydraulic support leg and the ground, reduces the risk of damage to the hydraulic support leg under the action of the impact of the gas flow, and improves the reliability of the whole launching system.
Description
Technical Field
The invention relates to the technical field of missile launching equipment, in particular to a vehicle-mounted missile launching diversion device and a launching vehicle with the same.
Background
The launching of the medium and short range ground tactical trajectory missile generally adopts a vehicle-mounted heat launching mode, a vehicle-mounted heat launching vehicle generally can be provided with a flow guide device, the flow guide device is used for guiding high-temperature and high-speed gas flow sprayed when the missile is launched, the gas flow is prevented from eroding and damaging launching pad facilities and equipment, and meanwhile, the missile body is prevented from being influenced by rebounding after the gas and combustion residues impact the ground.
The heat-carrying emission gas guiding device can be divided into a single-side guiding device and a double-side guiding device, wherein the single-side guiding device guides the gas to the rear of the vehicle, and the double-side guiding device guides the gas from the two transverse sides. The double-faced guide device is widely applied, for example, the double-faced guide device is used in a vehicle-mounted missile vertical launching system in the way of Huxianlian and the like, and the guide effect (Huxianlian, grand culture, high pleasure and high grade, the double-faced guide device [ J ] of the vehicle-mounted missile vertical launching system, firepower and command control, 2013, (11): 53-55), Chenjinsong and the like analyze the guide rule of the double-faced guide device (Chenjinsong, Linyu, research on the guide rule of the double-faced guide device [ J ], missile and aerospace carrying technology, 2006, (2): 11-15, DOI: 10.3969/j.issn.1004-7182.2006.02.003.) is analyzed. When the double-sided flow guide device is used, the gas diffusion range is large, the launching vehicle is easily affected under the interaction of barriers on two sides and gas during launching, and the single-sided flow guide device does not have the problem, so that the single-sided flow guide device is already applied. Great national celebration and the like provide a single-side deflector (patent number: CN201610550774.0) for upright test run gas diversion of a small solid rocket engine, the cross section curve of the deflector consists of two line segments and an arc segment, and the single-side deflector has a certain reference function on the single-side diversion design of vehicle-mounted solid missile maneuvering vertical thermal launching gas diversion.
The launching vehicle adopting the single-sided flow guide device generally fixes the flow guide device on a launching platform, the launching platform is hinged with a rear beam rotating shaft on a chassis of the launching vehicle, before launching, leveling hydraulic support legs support the launching vehicle, and the launching platform rotates to an upright state; when the missile is launched, the missile fuel gas flow is ejected, the guide device guides the downwardly ejected fuel gas flow to the rear part, the guide device receives the impact force of the fuel gas flow, the impact force has component force horizontally towards the direction of a vehicle head, and the balance is required by depending on the friction force between the hydraulic support leg and the ground.
Disclosure of Invention
The invention aims to overcome the defects of the background technology and provide a vehicle-mounted missile launching diversion device and a launching vehicle with the diversion device, wherein the vehicle-mounted missile launching diversion device can reduce the impact force of a gas flow in the horizontal direction and improve the reliability of the whole launching system.
The invention provides a vehicle-mounted missile launching diversion device, which comprises:
the gas flow guider is used for guiding gas flow and comprises a downward sunken arc-shaped main profile and connecting surfaces which are respectively connected with the head side and the tail side of the main profile;
the throttle plate is arranged above the fluid director, a plurality of through holes are formed in the surface of the throttle plate, and the throttle plate is positioned on a flow path of the fuel gas flow.
On the basis of the above technical solution, the throttle plate is arranged perpendicular to the flow path of the gas flow.
On the basis of the technical scheme, the whole throttle plate is rectangular or circular.
On the basis of the technical scheme, the through holes are equal in size and are uniformly distributed on the surface of the throttle plate.
On the basis of the technical scheme, the through holes are distributed in an annular mode, the size of the through hole located in the center of the surface of the throttle plate is small, and the size of the through hole located in the periphery of the surface of the throttle plate is large.
On the basis of the above technical solution, the connecting surfaces include a first connecting surface connected to the head of the main profile and a second connecting surface connected to both sides of the tail of the main profile, and the first connecting surface and the second connecting surface are both horizontally disposed.
On the basis of the technical scheme, the first connecting surface is in uniform transition connection with the head of the main profile through an upward convex transition surface, and the second connecting surface is arranged in a tangent mode with the tail connecting part of the main profile.
On the basis of the technical scheme, the fluid director further comprises raised flow baffles arranged on the left side and the right side of the main molded surface.
The invention also provides a launch vehicle with the vehicle-mounted missile launching diversion device, which comprises:
a vehicle body;
the transmitting device is arranged in the vehicle body and comprises a fuel gas outlet;
the gas stream outlet is arranged opposite to the flow guider of the flow guider, a throttle plate is further arranged above the flow guider of the flow guider, and a plurality of through holes are formed in the surface of the throttle plate.
On the basis of the technical scheme, the launching device can rotate to a vertical launching state, the guide device synchronously rotates along with the launching device until the main profile of the guide device faces the tail direction of the vehicle, and the guide device is ensured to be always arranged opposite to the gas outlet.
Compared with the prior art, the invention has the following advantages:
the vehicle-mounted missile launching diversion device comprises a fluid director and a throttle plate, when a vehicle-mounted missile is launched, downwardly-jetted missile gas flow is vertically jetted downwards on a main profile surface of the fluid director and is guided to the tail direction of a vehicle through the main profile surface and a connecting surface connected with the tail part of the main profile surface, so that acting force towards the vehicle head direction is generated on the fluid director, the cross section of a gas flow flowing channel is suddenly reduced due to a plurality of through holes arranged on the surface of the throttle plate on a flowing path of the gas flow, the gas flow is rubbed at the through holes, partial kinetic energy is converted into frictional heat energy, a throttling effect is generated on the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director is reduced, the shearing force generated by friction between a hydraulic support leg and the ground is further reduced, and the risk that the hydraulic support leg is damaged under the action of, the reliability of the whole transmitting system is improved.
Drawings
FIG. 1 is an isometric view of the overall construction of a vehicle-mounted missile launch diversion device of an embodiment of the present invention;
FIG. 2 is a schematic view of a throttle plate configuration according to an embodiment of the present invention;
FIG. 3 is a schematic view of a throttle plate configuration according to a second embodiment of the present invention;
FIG. 4 is a schematic view of a throttle plate structure according to a third embodiment of the present invention;
FIG. 5 is a graph of gas flow trajectory simulation at missile launch using a prior art deflector;
FIG. 6 is a diagram showing a simulation of a gas flow trajectory at the time of missile launching using a deflector in an embodiment of the present invention;
FIG. 7 is a simplified structural schematic diagram of a launch vehicle having an on-board missile launch diversion device in accordance with an embodiment of the present invention;
fig. 8 is a schematic view of the launching state of the launching vehicle with the vehicle-mounted missile launching diversion device in the embodiment of the invention.
Reference numerals: 1-a flow guider, 11-a main profile, 12-a connecting surface, 121-a first connecting surface, 122-a second connecting surface, 13-a flow baffle, 2-a throttle plate, 21-a through hole, 3-a vehicle body, 4-an emission device, 41-a gas outlet.
Detailed Description
The invention is described in further detail below with reference to the figures and the embodiments.
Example one
Referring to fig. 1, an embodiment of the present invention provides a vehicle-mounted missile launching diversion device, including:
the gas flow guider 1 is used for guiding gas flow, and the gas flow guider 1 comprises a downward sunken arc-shaped main molded surface 11 and connecting surfaces 12 which are respectively connected with the head side and the tail side of the main molded surface 11;
the throttle plate 2 is arranged above the fluid director 1, a plurality of through holes 21 are formed in the surface of the throttle plate 2, and the surface of the throttle plate 2 is positioned on a flow path of the gas flow.
The vehicle-mounted missile launching diversion device comprises a fluid director 1 and a throttle plate 2, when a vehicle-mounted missile is launched, missile gas flow which is jetted downwards is vertically jetted on a main profile 11 of the fluid director 1 downwards and is guided to the tail direction of a vehicle through the main profile 11 and a connecting surface 12 connected with the tail of the main profile 11, so that acting force towards the direction of a vehicle head is generated on the fluid director 1, the cross section of a gas flow flowing channel is suddenly reduced due to a plurality of through holes 21 which are formed in the surface of the throttle plate 2 which is arranged on a flowing path of the gas flow, the gas flow rubs at the through holes 21, partial kinetic energy is converted into friction heat energy, the throttling effect is generated on the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director 1 is reduced, the shearing force generated by friction between a hydraulic support leg and the ground is further reduced, and the risk that the hydraulic support leg, the reliability of the whole transmitting system is improved.
Referring to fig. 5 to 6, fig. 5 is a gas flow trajectory diagram of a missile using a diversion device in the prior art during missile launching, and it can be seen that the flow of the gas flow is relatively disordered and dispersed, and the impact force generated on the fluid director 1 is relatively large, so that the component force of the horizontal direction of the fluid director to the direction of the vehicle head is also large, and the risk of damage to the hydraulic legs under the action of the impact force of the gas flow is high; fig. 6 is a gas flow trajectory diagram during missile launching using the deflector in the embodiment of the invention, and it can be seen that the gas flow flows relatively smoothly and intensively, and because the impact force generated on the fluid director 1 by the throttling effect on the surface of the throttle plate 2 is relatively small, the component force of the fluid director in the horizontal direction to the vehicle head direction is also small, the risk of damage to the hydraulic support legs under the action of the gas flow impact force is correspondingly reduced, and the reliability of the launching system is high.
On the basis of the technical solutions of the above embodiments, preferably, the surface of the throttle plate 2 is arranged perpendicular to the flow path of the gas flow; the surface of the throttle plate 2 is perpendicular to the flow path of the gas flow, so that the throttle effect of the throttle plate 2 on the gas flow can be exerted to the maximum extent, and the impact effect of the gas flow on the fluid director 1 is reduced.
On the basis of the technical solution of the foregoing embodiment, preferably, the connecting surface 12 includes a first connecting surface 121 connected to the head of the main profile 11, and a second connecting surface 122 connected to both sides of the tail of the main profile 11, and both the first connecting surface 121 and the second connecting surface 122 are horizontally disposed; further, the first connecting surface 121 is uniformly transitionally connected with the head of the main profile 11 through an upward convex transition surface, and the second connecting surface 122 is tangentially arranged at the connection position of the tail of the main profile 11; the first connecting surface 121 connected with the head part of the main profile 11 and the second connecting surface 122 connected with the tail part of the main profile 11 are both horizontally arranged, and the head part and the tail part of the main profile are smoothly transited by arranging the transition surfaces, so that the appearance of the flow guide part 1 is kept attractive, the processing and the manufacturing of the flow guide part 1 are facilitated, the gas flows at the head part and the tail part of the main profile are guided to the direction of the head part and the tail part of the vehicle, and the influence on the missile body or other launching equipment after the gas and the combustion residues are splashed is avoided.
On the basis of the technical solution of the above embodiment, preferably, the fluid director 1 further includes raised flow baffles 13 disposed on the left and right sides of the main profile 11; the flow baffle 13 is arranged to prevent the gas flow from transversely diffusing to the left and right sides, and protect other equipment and personnel safety in the left and right side emission systems.
Example two
Referring to fig. 1 and 2, an embodiment of the present invention provides a vehicle-mounted missile launching diversion device, including:
the gas flow guider 1 is used for guiding gas flow, and the gas flow guider 1 comprises a downward sunken arc-shaped main molded surface 11 and connecting surfaces 12 which are respectively connected with the head side and the tail side of the main molded surface 11;
the throttle plate 2 is arranged above the fluid director 1, a plurality of through holes 21 are formed in the surface of the throttle plate 2, and the surface of the throttle plate 2 is positioned on a flow path of the gas flow.
The vehicle-mounted missile launching diversion device comprises a fluid director 1 and a throttle plate 2, when a vehicle-mounted missile is launched, missile gas flow which is jetted downwards is vertically jetted on a main profile 11 of the fluid director 1 downwards and is guided to the tail direction of a vehicle through the main profile 11 and a connecting surface 12 connected with the tail of the main profile 11, so that acting force towards the direction of a vehicle head is generated on the fluid director 1, the cross section of a gas flow flowing channel is suddenly reduced due to a plurality of through holes 21 which are formed in the surface of the throttle plate 2 which is arranged on a flowing path of the gas flow, the gas flow rubs at the through holes 21, partial kinetic energy is converted into friction heat energy, the throttling effect is generated on the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director 1 is reduced, the shearing force generated by friction between a hydraulic support leg and the ground is further reduced, and the risk that the hydraulic support leg, the reliability of the whole transmitting system is improved.
Referring to fig. 5 to 6, fig. 5 is a gas flow trajectory diagram of a missile using a diversion device in the prior art during missile launching, and it can be seen that the flow of the gas flow is relatively disordered and dispersed, and the impact force generated on the fluid director 1 is relatively large, so that the component force of the horizontal direction of the fluid director to the direction of the vehicle head is also large, and the risk of damage to the hydraulic legs under the action of the impact force of the gas flow is high; fig. 6 is a gas flow trajectory diagram during missile launching using the deflector in the embodiment of the invention, and it can be seen that the gas flow flows relatively smoothly and intensively, and because the impact force generated on the fluid director 1 by the throttling effect on the surface of the throttle plate 2 is relatively small, the component force of the fluid director in the horizontal direction to the vehicle head direction is also small, the risk of damage to the hydraulic support legs under the action of the gas flow impact force is correspondingly reduced, and the reliability of the launching system is high.
Wherein the overall shape of the throttle plate 2 is rectangular or circular; the through holes 21 are equal in size and are uniformly distributed on the surface of the throttle plate 2; in this embodiment, the throttle plate 2 is of a circular structure, a plurality of rectangular through holes 21 with the same size are uniformly distributed on the surface of the throttle plate 2, when the gas flow flows through the surface of the throttle plate 2, the cross section of the flow passage is suddenly reduced, the gas flow rubs at the through holes 21, so that part of kinetic energy is converted into friction heat energy, the throttling effect is caused to the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director 1 is reduced, and the shearing force generated by friction between the hydraulic support legs and the ground is reduced.
EXAMPLE III
Referring to fig. 1 and 3, an embodiment of the present invention provides a vehicle-mounted missile launching diversion device, including:
the gas flow guider 1 is used for guiding gas flow, and the gas flow guider 1 comprises a downward sunken arc-shaped main molded surface 11 and connecting surfaces 12 which are respectively connected with the head side and the tail side of the main molded surface 11;
the throttle plate 2 is arranged above the fluid director 1, a plurality of through holes 21 are formed in the surface of the throttle plate 2, and the surface of the throttle plate 2 is positioned on a flow path of the gas flow.
The vehicle-mounted missile launching diversion device comprises a fluid director 1 and a throttle plate 2, when a vehicle-mounted missile is launched, missile gas flow which is jetted downwards is vertically jetted on a main profile 11 of the fluid director 1 downwards and is guided to the tail direction of a vehicle through the main profile 11 and a connecting surface 12 connected with the tail of the main profile 11, so that acting force towards the direction of a vehicle head is generated on the fluid director 1, the cross section of a gas flow flowing channel is suddenly reduced due to a plurality of through holes 21 which are formed in the surface of the throttle plate 2 which is arranged on a flowing path of the gas flow, the gas flow rubs at the through holes 21, partial kinetic energy is converted into friction heat energy, the throttling effect is generated on the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director 1 is reduced, the shearing force generated by friction between a hydraulic support leg and the ground is further reduced, and the risk that the hydraulic support leg, the reliability of the whole transmitting system is improved.
Referring to fig. 5 to 6, fig. 5 is a gas flow trajectory diagram of a missile using a diversion device in the prior art during missile launching, and it can be seen that the flow of the gas flow is relatively disordered and dispersed, and the impact force generated on the fluid director 1 is relatively large, so that the component force of the horizontal direction of the fluid director to the direction of the vehicle head is also large, and the risk of damage to the hydraulic legs under the action of the impact force of the gas flow is high; fig. 6 is a gas flow trajectory diagram during missile launching using the deflector in the embodiment of the invention, and it can be seen that the gas flow flows relatively smoothly and intensively, and because the impact force generated on the fluid director 1 by the throttling effect on the surface of the throttle plate 2 is relatively small, the component force of the fluid director in the horizontal direction to the vehicle head direction is also small, the risk of damage to the hydraulic support legs under the action of the gas flow impact force is correspondingly reduced, and the reliability of the launching system is high.
Wherein the overall shape of the throttle plate 2 is rectangular or circular; the through holes 21 are equal in size and are uniformly distributed on the surface of the throttle plate 2; in this embodiment, the throttle plate 2 is of a rectangular structure, a plurality of rectangular through holes 21 with the same size are uniformly distributed on the surface of the throttle plate 2, when the gas flow flows through the surface of the throttle plate 2, the cross section of the flow passage is suddenly reduced, the gas flow rubs at the through holes 21, so that part of kinetic energy is converted into friction heat energy, the throttling effect is caused to the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director 1 is reduced, and the shearing force generated by friction between the hydraulic support legs and the ground is reduced.
Example four
Referring to fig. 1 and 4, an embodiment of the present invention provides a vehicle-mounted missile launching diversion device, including:
the gas flow guider 1 is used for guiding gas flow, and the gas flow guider 1 comprises a downward sunken arc-shaped main molded surface 11 and connecting surfaces 12 which are respectively connected with the head side and the tail side of the main molded surface 11;
the throttle plate 2 is arranged above the fluid director 1, a plurality of through holes 21 are formed in the surface of the throttle plate 2, and the surface of the throttle plate 2 is positioned on a flow path of the gas flow.
The vehicle-mounted missile launching diversion device comprises a fluid director 1 and a throttle plate 2, when a vehicle-mounted missile is launched, missile gas flow which is jetted downwards is vertically jetted on a main profile 11 of the fluid director 1 downwards and is guided to the tail direction of a vehicle through the main profile 11 and a connecting surface 12 connected with the tail of the main profile 11, so that acting force towards the direction of a vehicle head is generated on the fluid director 1, the cross section of a gas flow flowing channel is suddenly reduced due to a plurality of through holes 21 which are formed in the surface of the throttle plate 2 which is arranged on a flowing path of the gas flow, the gas flow rubs at the through holes 21, partial kinetic energy is converted into friction heat energy, the throttling effect is generated on the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director 1 is reduced, the shearing force generated by friction between a hydraulic support leg and the ground is further reduced, and the risk that the hydraulic support leg, the reliability of the whole transmitting system is improved.
Referring to fig. 5 to 6, fig. 5 is a gas flow trajectory diagram of a missile using a diversion device in the prior art during missile launching, and it can be seen that the flow of the gas flow is relatively disordered and dispersed, and the impact force generated on the fluid director 1 is relatively large, so that the component force of the horizontal direction of the fluid director to the direction of the vehicle head is also large, and the risk of damage to the hydraulic legs under the action of the impact force of the gas flow is high; fig. 6 is a gas flow trajectory diagram during missile launching using the deflector in the embodiment of the invention, and it can be seen that the gas flow flows relatively smoothly and intensively, and because the impact force generated on the fluid director 1 by the throttling effect on the surface of the throttle plate 2 is relatively small, the component force of the fluid director in the horizontal direction to the vehicle head direction is also small, the risk of damage to the hydraulic support legs under the action of the gas flow impact force is correspondingly reduced, and the reliability of the launching system is high.
Wherein the overall shape of the throttle plate 2 is rectangular or circular; the through holes 21 are equal in size and are uniformly distributed on the surface of the throttle plate 2; in this embodiment, the throttle plate 2 is of a circular structure, a plurality of through holes 21 are annularly distributed on the surface of the throttle plate 2, the size of the through hole 21 located at the center of the surface of the throttle plate 2 is smaller, the size of the through hole 21 located at the periphery of the surface of the throttle plate 2 is larger, the through holes 21 at the center of the throttle plate 2 adopting the structure are more dense and concentrated, the effect of reducing impact force is more obvious, the through holes 21 at the edge are relatively dispersed, the characteristics that the gas flow at the center is dense and the gas flow at the edge is dispersed when a missile is launched are fully adapted, the pertinence is stronger, under the same conditions, the effect of reducing impact force is more obvious, when the gas flow flows through the surface of the throttle plate 2, the cross section of a flow channel is suddenly reduced, the gas flow rubs at the through holes 21, so that part of kinetic energy is converted into frictional, thereby reducing the impact of the gas flow on the fluid director 1 and further reducing the shearing force of the hydraulic support leg caused by the friction between the hydraulic support leg and the ground.
EXAMPLE five
Referring to fig. 7 and 8, an embodiment of the present invention provides a launch vehicle with a vehicle-mounted missile launching diversion device, including:
a vehicle body 3;
a launcher 4 provided in the vehicle body 3, the launcher 4 including a gas outflow port 41;
the diversion device is arranged at the tail part of the vehicle body 3, the fluid director 1 of the diversion device is arranged opposite to the fuel gas outlet 41, the throttle plate 2 is also arranged above the fluid director 1 of the diversion device, and the surface of the throttle plate 2 is provided with a plurality of through holes 21.
The invention relates to a launch vehicle with a vehicle-mounted missile launching diversion device, wherein a fluid director 1 of the diversion device is arranged opposite to a gas flow outlet 41, a throttle plate 2 is also arranged above the fluid director 1 of the diversion device, namely the throttle plate 2 is arranged between the gas flow outlet 41 and the fluid director 1, when the vehicle-mounted missile launches, gas flow firstly flows through the surface of the throttle plate 2, the cross section of a flow channel is suddenly reduced, the gas flow is rubbed at a through hole 21, partial kinetic energy is converted into frictional heat energy, a throttling effect is caused to the gas flow, the pressure of the gas flow is reduced, then the gas flow flows through the surface of the fluid director 1 and is guided to the tail direction of the vehicle by the fluid director 1, compared with the launch vehicle in the prior art, the technical scheme of the invention can reduce the impact effect of the gas flow on the fluid director 1, further reduce the shearing force generated by the friction between a hydraulic support leg and the ground, and, the reliability of the whole transmitting system is improved.
On the basis of the technical solution of the above embodiment, preferably, the emission device 4 can rotate to a vertical emission state, the deflector device rotates synchronously with the emission device 4 until the main profile 11 of the deflector 1 faces the tail of the vehicle, and it is ensured that the deflector 1 is always arranged opposite to the gas flow outlet 41, and the surface of the throttle plate 2 is always located on the flow path of the gas flow; the flow guide device rotates synchronously with the transmitting device 4, the position and the state of the flow guide device do not need to be independently adjusted in the transmitting state, the flow guide device is ensured to be in a use state at any time, and the use is more convenient.
Various modifications and variations of the embodiments of the present invention may be made by those skilled in the art, and they are also within the scope of the present invention, provided they are within the scope of the claims of the present invention and their equivalents.
What is not described in detail in the specification is prior art that is well known to those skilled in the art.
Claims (5)
1. The utility model provides a single face guiding device of on-vehicle guided missile transmission which characterized in that includes:
the gas flow guider (1) is used for guiding gas flow, and the gas flow guider (1) comprises a downward sunken arc-shaped main molded surface (11), raised flow blocking plates (13) arranged on the left side and the right side of the main molded surface (11) and connecting surfaces (12) respectively connected with the head side and the tail side of the main molded surface (11);
the throttle plate (2) is arranged above the fluid director (1), a plurality of through holes (21) are formed in the surface of the throttle plate (2), and the throttle plate (2) is positioned on a flow path of the fuel gas flow and is perpendicular to the flow path of the fuel gas flow; the whole throttle plate (2) is rectangular or circular, the through holes (21) are equal in size and are uniformly distributed on the surface of the throttle plate (2), or the whole throttle plate (2) adopts a circular structure, the through holes (21) are distributed annularly, the size of the through hole (21) positioned in the center of the surface of the throttle plate (2) is smaller, and the size of the through hole (21) positioned around the surface of the throttle plate (2) is larger;
when the vehicle-mounted missile is launched, downward-jetted missile gas flow is vertically jetted on a main profile (11) of a fluid director (1) downwards, and is guided to the tail direction of a vehicle through the main profile (11) and a connecting surface (12) connected with the tail of the main profile to generate an acting force towards the head direction of the vehicle on the fluid director (1), the cross section of a gas flow channel is suddenly reduced due to a plurality of through holes (21) formed in the surface of a throttle plate (2), a throttling effect is generated on the gas flow, the pressure of the gas flow is reduced, the impact effect of the gas flow on the fluid director (1) is reduced, and further, the shearing force generated by friction between a hydraulic support leg and the ground is reduced.
2. The vehicle-mounted missile launching single-side flow guide device as recited in claim 1, wherein: the connecting surface (12) comprises a first connecting surface (121) connected with the head part of the main molded surface (11) and second connecting surfaces (122) connected with the two sides of the tail part of the main molded surface (11), and the first connecting surface (121) and the second connecting surfaces (122) are both horizontally arranged.
3. The vehicle-mounted missile launching single-side flow guide device as recited in claim 2, wherein: the first connecting surface (121) is in uniform transition connection with the head part of the main molded surface (11) through an upward convex transition surface, and the second connecting surface (122) is tangentially arranged at the connection part of the tail part of the main molded surface (11).
4. A launch vehicle with a vehicle-mounted missile launching diversion device is characterized by comprising:
a vehicle body (3);
a launcher (4) disposed within the vehicle body (3), the launcher (4) including a gas flow outlet (41);
the single-sided deflector of claim 1 arranged at the rear of the vehicle body (3), the deflector (1) of the deflector being arranged opposite the gas outlet (41).
5. The launch vehicle with on-board missile launch diversion device of claim 4, wherein: the emission device (4) can rotate to a vertical emission state, the single-side guide device synchronously rotates along with the emission device (4) until the main profile (11) of the fluid director (1) faces the tail direction of the vehicle, the fluid director (1) is ensured to be always arranged opposite to the fuel gas outlet (41), and the surface of the throttle plate (2) is always positioned on the flow path of the fuel gas flow.
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| CN201811280545.7A CN109470080B (en) | 2018-10-30 | 2018-10-30 | Vehicle-mounted missile launching flow guide device and launching vehicle with same |
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| CN201811280545.7A CN109470080B (en) | 2018-10-30 | 2018-10-30 | Vehicle-mounted missile launching flow guide device and launching vehicle with same |
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| CN109470080B true CN109470080B (en) | 2021-04-27 |
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| CN113606060B (en) * | 2021-07-19 | 2022-05-10 | 西安航天动力试验技术研究所 | Movable fuel gas flow guide device and using method thereof |
| CN114459286A (en) * | 2021-08-06 | 2022-05-10 | 北京天兵科技有限公司 | Rocket tail flame guiding device |
| CN113739632B (en) * | 2021-09-23 | 2023-01-10 | 湖北三江航天江北机械工程有限公司 | Box type transmitting flow guide device |
| CN114136150B (en) * | 2021-11-10 | 2023-07-14 | 湖北航天技术研究院总体设计所 | Single-sided fluid director for vertical thermal emission of guided missile |
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|---|---|---|---|---|
| JPH0539998A (en) * | 1991-08-01 | 1993-02-19 | Mitsubishi Heavy Ind Ltd | Flying object launcher |
| JPH0545093A (en) * | 1991-08-08 | 1993-02-23 | Mitsubishi Heavy Ind Ltd | Vertical launcher |
| JPH0587494A (en) * | 1991-09-30 | 1993-04-06 | Mitsubishi Heavy Ind Ltd | Missile launching device |
| JPH0593598A (en) * | 1991-10-03 | 1993-04-16 | Mitsubishi Heavy Ind Ltd | Missile launcher |
| JPH05126498A (en) * | 1991-11-01 | 1993-05-21 | Mitsubishi Heavy Ind Ltd | Missile launcher |
| 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 |
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