CN107401956B - Amphibious cruise missile based on throat offset type pneumatic vectoring nozzle and attitude control method thereof - Google Patents
Amphibious cruise missile based on throat offset type pneumatic vectoring nozzle and attitude control method thereof Download PDFInfo
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- CN107401956B CN107401956B CN201710674930.9A CN201710674930A CN107401956B CN 107401956 B CN107401956 B CN 107401956B CN 201710674930 A CN201710674930 A CN 201710674930A CN 107401956 B CN107401956 B CN 107401956B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle
Abstract
The invention discloses an amphibious cruise missile based on a throat offset type pneumatic vectoring nozzle and an attitude control method thereof, wherein the amphibious cruise missile comprises a missile body, a switching section and a throat offset type pneumatic vectoring nozzle; the advancing direction of the missile is changed and the missile jumps out of the water surface by controlling the tail throat offset type pneumatic vectoring nozzle; compared with the traditional missile, the missile cancels structures such as a rudder and the like, has smaller radar reflection area, and has better stealth performance; when the throat offset pneumatic vectoring nozzle works underwater, water is used as a working medium, and the throat offset pneumatic vectoring nozzle has the advantages of no exhaust, no flight path, low noise and good concealment; when the jet nozzle works in the air, the jet nozzle takes high-temperature gas as a working medium, and has the advantages of sensitive reaction, high navigation speed and long navigation distance.
Description
Technical Field
The invention relates to an amphibious cruise missile based on a throat offset type pneumatic vectoring nozzle, which is mainly used for improving the maneuverability of the missile, simultaneously improving the concealment of the missile and obviously improving the hit rate of the missile.
Background
The missile is developed rapidly since world war II, and the cruise missile brings great and profound influence on strategic tactics of modern war due to the characteristics of small volume, light weight, convenient maneuvering launching and the like, thereby receiving more and more general attention of various countries. In the current stage, the cruise missile usually adopts a control surface to realize the control on the direction, so that the radar reflection area of the missile is increased, the interception probability of the missile in the flight process is greatly increased, and the hit rate of the missile is greatly reduced.
Disclosure of Invention
The invention develops an amphibious cruise missile based on a throat offset type pneumatic vectoring nozzle, which can replace a rudder to realize the control of the direction of the missile, can work in water and in the air, and has smaller radar reflection area compared with the traditional missile, thereby having better stealth performance.
In order to achieve the above technical objects, the present invention adopts the following technical solutions:
the utility model provides an amphibious guided missile that cruises based on pneumatic thrust vectoring nozzle of throat skew formula, includes the guided missile body, and the afterbody of guided missile body is passed through the changeover portion and is connected with pneumatic thrust vectoring nozzle of throat skew formula, wherein:
the throat offset type pneumatic vectoring nozzle comprises a nozzle body, wherein an inner flow passage of the nozzle body is sequentially provided with a nozzle inlet, a throat front convergence section, a throat, a concave cavity and two throats along the flow direction of fluid; the nozzle body is provided with two flow channels at the position of a front convergent section of a throat, namely a main flow channel arranged along the axis of the nozzle body and a secondary flow channel positioned between the front convergent section of the throat and the wall surface of the nozzle body;
the secondary flow channel is divided into four mutually independent secondary flow channel sub-bodies along the circumferential direction of the spray pipe body, and the four mutually independent secondary flow channel sub-bodies are correspondingly a left secondary flow channel sub-body, a right secondary flow channel sub-body, a last secondary flow channel sub-body and a next secondary flow channel sub-body;
the outlet of each sub-flow passage split body is communicated with the main flow passage at the position close to the inlet of a throat of the spray pipe body, the outlet of each sub-flow passage split body is provided with a valve, and the fluid flowing out of the outlet of the sub-flow passage split body can disturb the fluid flowing into the throat of the main flow passage;
the last time of independent work of the split flow channel can generate head-up torque to the missile body and push the missile body to do head-up motion;
the next sub-channel is separately and independently operated, so that the low-head moment can be generated on the missile body, and the missile body is pushed to perform low-head movement;
the left sub-flow channel works independently and can generate left yawing moment on the missile body to push the missile body to do left yawing motion;
the right sub-channel is independently operated, so that right yawing moment can be generated on the missile body, and the missile body is pushed to do right yawing motion.
As a further improvement of the invention, the throat offset aerodynamic vectoring nozzle is a binary vectoring nozzle or an axisymmetric vectoring nozzle.
As a further improvement of the invention, the shape of the inlet of the switching section is consistent with the shape of the tail end of the missile body, and the shape of the outlet of the switching section is matched with the shape of the inlet of the throat offset pneumatic vectoring nozzle.
As a further improvement of the invention, when the throat offset pneumatic vectoring nozzle is a binary vectoring nozzle, one end of the switching section is round, the other end is square, the round end of the switching section is connected with the tail end of the missile body, and the square end is connected with the nozzle inlet of the binary vectoring nozzle; when the throat offset type pneumatic vectoring nozzle is an axisymmetric vectoring nozzle, the section of the switching section is circular.
As a further improvement of the invention, the airflow disturbance of the sub-flow channel is passive or active; when the airflow disturbance of the secondary flow channel is passive, the airflow of the secondary flow channel comes from the inlet airflow of the nozzle body; when the airflow disturbance of the secondary flow channel is active, the airflow of the secondary flow channel comes from a high-pressure part of a missile body power system.
As a further improvement of the present invention, when the throat offset pneumatic vectoring nozzle is a binary vectoring nozzle and the airflow disturbance of the secondary flow channel is active, the front convergent section of the throat includes four triangular bumps uniformly distributed relative to the axis of the nozzle body, which are respectively a first triangular bump, a second triangular bump, a third triangular bump and a fourth triangular bump; the vertex of each triangular lug is adjacent to the axis of the spray pipe body, the bottom edge of each triangular lug is adjacent to the inner wall of the spray pipe body, and the bottom edge of each triangular lug is parallel to the inner wall of the spray pipe body; a primary flow channel split body is formed between the first triangular bump and the wall surface of the spray pipe body, and a first valve capable of adjusting the opening degree of the primary flow channel split body is installed on the primary flow channel split body; a lower sub-flow passage split body is formed between the second triangular bump and the wall surface of the spray pipe body, and a second valve capable of adjusting the opening degree of the lower sub-flow passage split body is installed on the lower sub-flow passage split body; a left sub-flow passage split body is formed between the third triangular bump and the wall surface of the spray pipe body, and a third valve capable of adjusting the opening degree of the left sub-flow passage split body is installed on the left sub-flow passage split body; and a fourth valve capable of adjusting the opening degree of the right sub-flow passage split body is arranged on the right sub-flow passage split body.
As a further improvement of the invention, when the throat offset type pneumatic vectoring nozzle is an axisymmetric vectoring nozzle and the airflow disturbance of the secondary flow channel is active, the front convergent section of the throat is an annular member with a triangular section, and in the triangular section of the annular member, the vertex position is adjacent to the axis of the nozzle body, and the bottom side is adjacent to the wall surface of the nozzle body and is parallel to the wall surface of the nozzle body;
the annular component is equally divided into four mutually independent parts along the axis of the nozzle body, and the four mutually independent parts are respectively a first ring component split body, a second ring component split body, a third ring component split body and a fourth ring component split body;
a primary flow channel split body is formed between the outer wall of the first ring component split body and the wall surface of the spray pipe body, and a first valve capable of adjusting the opening degree of the primary flow channel split body is installed on the primary flow channel split body;
a next sub-flow passage split body is formed between the outer wall of the second ring member split body and the wall surface of the spray pipe body, and a second valve capable of adjusting the opening degree of the next sub-flow passage split body is installed on the next sub-flow passage split body;
a left sub-flow passage split body is formed between the outer wall of the third ring component split body and the wall surface of the spray pipe body, and a third valve capable of adjusting the opening degree of the left sub-flow passage split body is installed on the left sub-flow passage split body;
and a right sub-flow passage split body is formed between the outer wall of the fourth ring component split body and the wall surface of the spray pipe body, and a fourth valve capable of adjusting the opening degree of the right sub-flow passage split body is installed on the right sub-flow passage split body.
The invention also aims to provide an attitude control method of an amphibious cruise missile based on the throat offset type pneumatic vectoring nozzle, which comprises the following steps:
I. when the last sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, fluid is injected into the main flow channel from the last sub-flow channel at one throat so as to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects upwards to generate a head raising vector to generate a head raising moment on the missile body, and at the moment, the missile raises;
II. When the next sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, fluid is injected into the main flow channel from the next sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects downwards to generate a low head vector to generate a low head moment on the missile body, and at the moment, the missile lowers heads;
III, when the left sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened, the other sub-flow channels are closed, and fluid is injected into the main flow channel from the left sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects to the left, a left yawing moment is generated on the missile body, and at the moment, the missile yaws to the left;
IV, when the right sub-flow channel of the throat offset type pneumatic vector nozzle is opened, the other sub-flow channels are closed, and fluid is injected into the main flow channel from the right sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; and the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects to the right, a right yawing moment is generated on the missile body, and at the moment, the missile yaws to the right.
According to the technical scheme, compared with the prior art, the invention has the following advantages:
1. according to the invention, the throat offset type pneumatic vectoring nozzle is arranged at the tail part of the missile body, the working direction of the missile is adjusted by adjusting the opening degree of the secondary flow channel in the throat offset type pneumatic vectoring nozzle, and compared with the traditional missile which needs a rudder to control the direction of the missile, the missile has a smaller radar reflection area, so that the stealth performance is better.
2. The throat offset pneumatic vectoring nozzle can work in water and in the air; when working underwater, the water is used as working medium, and the advantages are no exhaust, no flight path, low noise and good concealment; when the jet nozzle works in the air, the jet nozzle takes high-temperature gas as a working medium, and has the advantages of sensitive reaction, high navigation speed and long navigation distance.
Drawings
FIG. 1 is a three-dimensional schematic view of the present invention applied to an axisymmetric throat offset aerodynamic vectoring nozzle;
FIG. 2 is a three-dimensional schematic view of the present invention applied to a binary throat offset aerodynamic vectoring nozzle;
FIG. 3 is a cross-sectional view of the throat offset aerodynamic vectoring nozzle;
in the figure: 1. a missile body; 2. a switching section; 3.a throat offset pneumatic vectoring nozzle;
wherein the pneumatic thrust vectoring nozzle of throat offset formula includes:
a, a main flow channel; 3.b, a throat front convergence section; 3, c, a throat; 3, d, a concave cavity; 3, e, a sub-stream channel; f, two throats.
Detailed Description
It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The relative arrangement of the components and steps, expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values.
As shown in fig. 1-3, the amphibious cruise missile based on the throat offset pneumatic vectoring nozzle comprises a missile body, wherein the tail part of the missile body is connected with the throat offset pneumatic vectoring nozzle through a switching section, and the amphibious cruise missile comprises:
the throat offset type pneumatic vectoring nozzle comprises a nozzle body, wherein an inner flow channel of the nozzle body is sequentially provided with a nozzle inlet, a throat front convergence section, a throat, a concave cavity and two throats along the flow direction of fluid; the nozzle body is provided with two flow channels at the position of a front convergent section of a throat, namely a main flow channel arranged along the axis of the nozzle body and a secondary flow channel positioned between the front convergent section of the throat and the wall surface of the nozzle body;
the secondary flow channel is divided into four mutually independent secondary flow channel sub-bodies along the circumferential direction of the spray pipe body, and the four mutually independent secondary flow channel sub-bodies are correspondingly a left secondary flow channel sub-body, a right secondary flow channel sub-body, a last secondary flow channel sub-body and a next secondary flow channel sub-body;
the outlet of each sub-flow passage split body is communicated with the main flow passage at the position close to the inlet of a throat of the spray pipe body, the outlet of each sub-flow passage split body is provided with a valve, and the fluid flowing out of the outlet of the sub-flow passage split body can disturb the fluid flowing into the throat of the main flow passage;
the last time of independent work of the split flow channel can generate head-up torque to the missile body and push the missile body to do head-up motion;
the next sub-channel is separately and independently operated, so that the low-head moment can be generated on the missile body, and the missile body is pushed to perform low-head movement;
the left sub-flow channel works independently and can generate left yawing moment on the missile body to push the missile body to do left yawing motion;
the right sub-channel is independently operated, so that right yawing moment can be generated on the missile body, and the missile body is pushed to do right yawing motion.
As a further improvement of the invention, the throat offset aerodynamic vectoring nozzle is a binary vectoring nozzle or an axisymmetric vectoring nozzle.
In order to achieve a better rectification effect, the shape of the inlet of the switching section is consistent with that of the tail end of the missile body, and the shape of the outlet of the switching section is matched with that of the inlet of the throat offset pneumatic vectoring nozzle. As shown in fig. 1, when the throat offset pneumatic vectoring nozzle is a binary vectoring nozzle, one end of the switching section is round, the other end is square, the round end of the switching section is connected with the tail end of the missile body, and the square end is connected with the nozzle inlet of the binary vectoring nozzle; as shown in fig. 2, when the throat offset aerodynamic vectoring nozzle is an axisymmetric vectoring nozzle, the cross-section of the adapter section is circular.
The airflow disturbance of the secondary flow channel is passive or active; when the airflow disturbance of the secondary flow channel is passive, the airflow of the secondary flow channel comes from the inlet airflow of the nozzle body; when the airflow disturbance of the secondary flow channel is active, the airflow of the secondary flow channel comes from a high-pressure part of a missile body power system. Fig. 3 discloses a schematic diagram of the structure of the sub-flow channel in the case that the disturbance of the gas flow in the sub-flow channel is active.
As shown in fig. 3, when the throat offset pneumatic vectoring nozzle is a binary vectoring nozzle, the front convergent section of the throat includes four triangular projections uniformly distributed relative to the axis of the nozzle body, which are a first triangular projection, a second triangular projection, a third triangular projection and a fourth triangular projection; the vertex of each triangular lug is adjacent to the axis of the spray pipe body, the bottom edge of each triangular lug is adjacent to the inner wall of the spray pipe body, and the bottom edge of each triangular lug is parallel to the inner wall of the spray pipe body; a primary flow channel split body is formed between the first triangular bump and the wall surface of the spray pipe body, and a first valve capable of adjusting the opening degree of the primary flow channel split body is installed on the primary flow channel split body; a lower sub-flow passage split body is formed between the second triangular bump and the wall surface of the spray pipe body, and a second valve capable of adjusting the opening degree of the lower sub-flow passage split body is installed on the lower sub-flow passage split body; a left sub-flow passage split body is formed between the third triangular bump and the wall surface of the spray pipe body, and a third valve capable of adjusting the opening degree of the left sub-flow passage split body is installed on the left sub-flow passage split body; and a fourth valve capable of adjusting the opening degree of the right sub-flow passage split body is arranged on the right sub-flow passage split body.
When the throat offset type pneumatic vectoring nozzle is an axisymmetric vectoring nozzle, the front convergent section of the throat is an annular component with a triangular section, in the triangular section of the annular component, the vertex position is adjacent to the axis of the nozzle body, and the bottom edge is adjacent to the wall surface of the nozzle body and is parallel to the wall surface of the nozzle body;
the annular component is equally divided into four mutually independent parts along the axis of the nozzle body, and the four mutually independent parts are respectively a first ring component split body, a second ring component split body, a third ring component split body and a fourth ring component split body;
a primary flow channel split body is formed between the outer wall of the first ring component split body and the wall surface of the spray pipe body, and a first valve capable of adjusting the opening degree of the primary flow channel split body is installed on the primary flow channel split body;
a next sub-flow passage split body is formed between the outer wall of the second ring member split body and the wall surface of the spray pipe body, and a second valve capable of adjusting the opening degree of the next sub-flow passage split body is installed on the next sub-flow passage split body;
a left sub-flow passage split body is formed between the outer wall of the third ring component split body and the wall surface of the spray pipe body, and a third valve capable of adjusting the opening degree of the left sub-flow passage split body is installed on the left sub-flow passage split body;
and a right sub-flow passage split body is formed between the outer wall of the fourth ring component split body and the wall surface of the spray pipe body, and a fourth valve capable of adjusting the opening degree of the right sub-flow passage split body is installed on the right sub-flow passage split body.
The invention also aims to provide an attitude control method of an amphibious cruise missile based on the throat offset type pneumatic vectoring nozzle, which comprises the following steps:
I. when the last sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, fluid is injected into the main flow channel from the last sub-flow channel at one throat so as to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects upwards to generate a head raising vector to generate a head raising moment on the missile body, and at the moment, the missile raises;
II. When the next sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, fluid is injected into the main flow channel from the next sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects downwards to generate a low head vector to generate a low head moment on the missile body, and at the moment, the missile lowers heads;
III, when the left sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened, the other sub-flow channels are closed, and fluid is injected into the main flow channel from the left sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects to the left, a left yawing moment is generated on the missile body, and at the moment, the missile yaws to the left;
IV, when the right sub-flow channel of the throat offset type pneumatic vector nozzle is opened, the other sub-flow channels are closed, and fluid is injected into the main flow channel from the right sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; and the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects to the right, a right yawing moment is generated on the missile body, and at the moment, the missile yaws to the right.
When the amphibious cruise missile works, water flow or air flow flows through the switching section from the power device in the missile body and then flows into the throat offset type pneumatic vectoring nozzle.
The missile can be thrown into water through a ship, a submarine or a plane and swim in the water, and once the missile obtains an instruction, the missile quickly jumps out of the water surface to fly to an enemy target;
the control principle is as follows:
when the last flow channel of the throat offset type pneumatic vector nozzle is opened and the other flow channels are closed, water flow or air flow is injected into the main flow channel from one throat of the last flow channel and generates disturbance on the main flow. The disturbance is amplified under the action of the concave cavity, so that the airflow deflects upwards at the outlet of the spray pipe, a head raising vector is generated, a corresponding head raising moment is generated for the missile, and the missile raises the head at the moment.
When the amphibious cruise missile works, the principle of controlling the missile to lower the head by adjusting the opening degree of the throat offset type pneumatic vectoring nozzle sub-flow channel is the same as that described above, and details are not repeated here.
When the left sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, water flow or air flow is injected into the main flow channel from one throat of the left sub-flow channel and generates disturbance on the main flow. The disturbance is amplified under the action of the concave cavity, so that the airflow deflects leftwards at the outlet of the spray pipe, a corresponding left yawing moment is generated on the missile, and the missile yaws leftwards at the moment.
When the amphibious cruise missile works, the control principle that the missile yaws rightwards by adjusting the opening degree of the throat offset type pneumatic vectoring nozzle sub-flow channel is the same as that described above, and details are not given here.
Claims (8)
1. The utility model provides an amphibious guided missile that cruises based on pneumatic thrust vectoring nozzle of throat skew formula, includes the guided missile body, its characterized in that, the afterbody of guided missile body is passed through the changeover portion and is connected with the pneumatic thrust vectoring nozzle of throat skew formula, wherein:
the throat offset type pneumatic vectoring nozzle comprises a nozzle body, wherein an inner flow passage of the nozzle body is sequentially provided with a nozzle inlet, a throat front convergence section, a throat, a concave cavity and two throats along the flow direction of fluid; the nozzle body is provided with two flow channels at the position of a front convergent section of a throat, namely a main flow channel arranged along the axis of the nozzle body and a secondary flow channel positioned between the front convergent section of the throat and the wall surface of the nozzle body;
the secondary flow channel is divided into four mutually independent secondary flow channel sub-bodies along the circumferential direction of the spray pipe body, and the four mutually independent secondary flow channel sub-bodies are correspondingly a left secondary flow channel sub-body, a right secondary flow channel sub-body, a last secondary flow channel sub-body and a next secondary flow channel sub-body;
the outlet of each sub-flow passage split body is communicated with the main flow passage at the position close to the inlet of a throat of the spray pipe body, the outlet of each sub-flow passage split body is provided with a valve, and the fluid flowing out of the outlet of the sub-flow passage split body can disturb the fluid flowing into the throat of the main flow passage;
the last time of independent work of the split flow channel can generate head-up torque to the missile body and push the missile body to do head-up motion;
the next sub-channel is separately and independently operated, so that the low-head moment can be generated on the missile body, and the missile body is pushed to perform low-head movement;
the left sub-flow channel works independently and can generate left yawing moment on the missile body to push the missile body to do left yawing motion;
the right sub-flow channel works independently and can generate right yawing moment on the missile body to push the missile body to do right yawing motion;
when the amphibious cruise missile works, water flow or air flow flows through the switching section from a power device inside the missile body and then flows into the throat offset type pneumatic vector nozzle to control the direction of the missile body, and accordingly the missile body can swim in water, jump into the air from the water or fly in the air and swim from the air to submerge in the water.
2. The amphibious cruise missile based on the throat offset pneumatic vectoring nozzle of claim 1, wherein the throat offset pneumatic vectoring nozzle is a binary vectoring nozzle or an axisymmetric vectoring nozzle.
3. An amphibious cruise missile based on a throat offset pneumatic vectoring nozzle according to claim 2, wherein the shape of the inlet of the transition section is consistent with the shape of the tail end of the missile body, and the shape of the outlet of the transition section is matched with the shape of the inlet of the throat offset pneumatic vectoring nozzle.
4. An amphibious cruise missile based on a throat offset pneumatic vectoring nozzle according to claim 2, wherein when the throat offset pneumatic vectoring nozzle is a binary vectoring nozzle, one end of the switching section is round, the other end of the switching section is square, the round end of the switching section is connected with the tail end of the missile body, and the square end is connected with the nozzle inlet of the binary vectoring nozzle; when the throat offset type pneumatic vectoring nozzle is an axisymmetric vectoring nozzle, the section of the switching section is circular.
5. The amphibious cruise missile based on the throat offset pneumatic vectoring nozzle of claim 2, wherein airflow disturbance of the secondary flow channel is passive or active; when the airflow disturbance of the secondary flow channel is passive, the airflow of the secondary flow channel comes from the inlet airflow of the nozzle body; when the airflow disturbance of the secondary flow channel is active, the airflow of the secondary flow channel comes from a high-pressure part of a missile body power system.
6. The amphibious cruise missile based on the throat offset type pneumatic vectoring nozzle of claim 5, wherein when the throat offset type pneumatic vectoring nozzle is a binary vectoring nozzle and airflow disturbance of the secondary flow channel is active, the front convergent section of the throat comprises four triangular lugs uniformly distributed relative to the axis of the nozzle body, namely a first triangular lug, a second triangular lug, a third triangular lug and a fourth triangular lug; the vertex of each triangular lug is adjacent to the axis of the spray pipe body, the bottom edge of each triangular lug is adjacent to the inner wall of the spray pipe body, and the bottom edge of each triangular lug is parallel to the inner wall of the spray pipe body; a primary flow channel split body is formed between the first triangular bump and the wall surface of the spray pipe body, and a first valve capable of adjusting the opening degree of the primary flow channel split body is installed on the primary flow channel split body; a lower sub-flow passage split body is formed between the second triangular bump and the wall surface of the spray pipe body, and a second valve capable of adjusting the opening degree of the lower sub-flow passage split body is installed on the lower sub-flow passage split body; a left sub-flow passage split body is formed between the third triangular bump and the wall surface of the spray pipe body, and a third valve capable of adjusting the opening degree of the left sub-flow passage split body is installed on the left sub-flow passage split body; and a fourth valve capable of adjusting the opening degree of the right sub-flow passage split body is arranged on the right sub-flow passage split body.
7. The amphibious cruise missile based on the throat offset type pneumatic vectoring nozzle of claim 5, wherein the throat offset type pneumatic vectoring nozzle is an axisymmetric vectoring nozzle, and when airflow disturbance of the secondary flow channel is active, the front convergent section of the throat is an annular member with a triangular section, and in the triangular section of the annular member, the vertex position is adjacent to the axis of the nozzle body, and the bottom side is adjacent to the wall surface of the nozzle body and is parallel to the wall surface of the nozzle body;
the annular component is equally divided into four mutually independent parts along the axis of the nozzle body, and the four mutually independent parts are respectively a first ring component split body, a second ring component split body, a third ring component split body and a fourth ring component split body;
a primary flow channel split body is formed between the outer wall of the first ring component split body and the wall surface of the spray pipe body, and a first valve capable of adjusting the opening degree of the primary flow channel split body is installed on the primary flow channel split body;
a next sub-flow passage split body is formed between the outer wall of the second ring member split body and the wall surface of the spray pipe body, and a second valve capable of adjusting the opening degree of the next sub-flow passage split body is installed on the next sub-flow passage split body;
a left sub-flow passage split body is formed between the outer wall of the third ring component split body and the wall surface of the spray pipe body, and a third valve capable of adjusting the opening degree of the left sub-flow passage split body is installed on the left sub-flow passage split body;
and a right sub-flow passage split body is formed between the outer wall of the fourth ring component split body and the wall surface of the spray pipe body, and a fourth valve capable of adjusting the opening degree of the right sub-flow passage split body is installed on the right sub-flow passage split body.
8. The attitude control method of the amphibious cruise missile based on the throat offset pneumatic vectoring nozzle as claimed in claim 1, wherein the attitude control method comprises the following steps:
I. when the last sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, fluid is injected into the main flow channel from the last sub-flow channel at one throat so as to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects upwards to generate a head raising vector to generate a head raising moment on the missile body, and at the moment, the missile raises;
II. When the next sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened and the other sub-flow channels are closed, fluid is injected into the main flow channel from the next sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects downwards to generate a low head vector to generate a low head moment on the missile body, and at the moment, the missile lowers heads;
III, when the left sub-flow channel of the throat offset type pneumatic vectoring nozzle is opened, the other sub-flow channels are closed, and fluid is injected into the main flow channel from the left sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects to the left, a left yawing moment is generated on the missile body, and at the moment, the missile yaws to the left;
IV, when the right sub-flow channel of the throat offset type pneumatic vector nozzle is opened, the other sub-flow channels are closed, and fluid is injected into the main flow channel from the right sub-flow channel at one throat to generate disturbance on the fluid flowing through the main flow channel; and the disturbance generated by the fluid in the main flow channel is further amplified under the action of the concave cavity, so that the fluid flowing out of the two throats deflects to the right, a right yawing moment is generated on the missile body, and at the moment, the missile yaws to the right.
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| EP4230858A1 (en) * | 2022-02-18 | 2023-08-23 | BAE SYSTEMS plc | Exhaust nozzle |
| WO2023156760A1 (en) * | 2022-02-18 | 2023-08-24 | Bae Systems Plc | Exhaust nozzle |
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