CN115434827A - Special-shaped micro-thrust eccentric spray pipe - Google Patents
Special-shaped micro-thrust eccentric spray pipe Download PDFInfo
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- CN115434827A CN115434827A CN202211052027.6A CN202211052027A CN115434827A CN 115434827 A CN115434827 A CN 115434827A CN 202211052027 A CN202211052027 A CN 202211052027A CN 115434827 A CN115434827 A CN 115434827A
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- protective layer
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses a special-shaped micro-thrust eccentric nozzle which comprises a nozzle shell, a front protective layer, a nozzle throat insert, a rear protective layer and a nozzle tail cover, wherein the nozzle shell is provided with a front protective layer and a rear protective layer; the front section of the inner cavity of the spray pipe shell is sequentially bonded with a front protective layer and a spray pipe throat lining, the rear section of the inner cavity of the spray pipe shell is bonded with a rear protective layer, and the tail cover of the spray pipe is in threaded connection with the rear end of the spray pipe shell and limits the rear end of the rear protective layer; the inner wall of the front end of the front protective layer is provided with a conical working surface which converges backwards, and the inner wall of the rear end of the front protective layer is provided with an inwards concave arc-shaped working surface which expands backwards; the front section of the inner shape of the nozzle throat insert is an outward convex arc-shaped working surface which is converged backwards, and the rear section of the inner shape of the nozzle throat insert is an outward convex arc-shaped working surface which is expanded backwards; the inner shape of the rear protective layer is a concave arc-shaped working surface expanding backwards; the front end and the rear end of the nozzle throat insert are respectively connected with the conical working surface and the concave arc-shaped working surface of the front protective layer, and the inner cavity of the rear protective layer and the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer are spliced into a working surface with the same radian. The special spray pipe improves the reliability of the spray pipe.
Description
Technical Field
The invention relates to a special-shaped micro-thrust eccentric spray pipe, and belongs to the technical field of special-shaped spray pipe design and micro-thrust eccentric spray pipe design.
Background
The function of a solid rocket engine nozzle is to accelerate the flow of fuel gas to produce thrust. The main task of the design of the aerodynamic profile of the nozzle is to reasonably select the profile geometrical structure of the convergent section, the throat section and the divergent section, so that the nozzle obtains higher efficiency.
The jet pipe is the most energy conversion device of the solid rocket engine, and converts the internal energy of high-temperature fuel gas into the kinetic energy of the fuel gas, thereby generating thrust. Meanwhile, the device is also a control device of gas flow, and can ensure that a certain working pressure is established in the combustion chamber. Because the high-temperature fuel gas in the spray pipe gradually accelerates, the working condition of the spray pipe is very bad.
A lot of researchers have conducted a lot of researches on solid rocket engine nozzles, the function of the nozzle expansion section is to accelerate fuel gas to supersonic speed and discharge the fuel gas from the nozzle outlet to generate thrust, and the inner profile of the expansion section is generally designed to be conical, so that the process is simple and the cost is low. However, because the performance requirement of the solid rocket engine is higher or the length requirement of the jet pipe is shorter, only a special type jet pipe can be adopted, and therefore, a larger expansion ratio is designed in a given length range.
The shape of the special-shaped nozzle expanding section is more complex than that of the conical nozzle expanding section, but the inner molded surface of the special-shaped nozzle expanding section is designed according to the aerodynamic characteristic line principle, so that the aerodynamic performance of the special-shaped nozzle expanding section is better than that of the conical nozzle. The outlet airflow of the special nozzle is approximately parallel to the axis, the airflow expansion loss is small, and the propellant energy is fully exerted, so that the optimization and improvement of the inner profile of the expansion section of the engine nozzle are particularly important.
Because of the asymmetric flow of the combustion surface in the expansion section of the nozzle, a certain included angle, namely an eccentric thrust angle, must exist between the thrust generated by the nozzle and the axis of the nozzle. According to the design theory of the micro-thrust deflecting spray pipe, the thrust direction generated by the spray pipe is close to the axial direction of the spray pipe by changing factors such as the inner molded surface and the length of the expansion section of the spray pipe, so that the thrust eccentric angle is reduced, and the reliability of the spray pipe is improved.
When designing the nozzle, the following basic requirements should be ensured:
(1) The efficiency is high. Therefore, the nozzle has a proper expansion ratio; the high-performance profile is required, so that the friction loss, the heat dissipation loss, the airflow expansion loss, the two-phase flow loss and the like are low.
(2) The size and the profile of the throat part of the spray pipe can be kept intact in the working process. Good thermal protection of the lance is required.
(3) Has enough strength and rigidity. The lance housing is of sufficient thickness to be protected by a layer of insulation.
(4) The structure is light. The nozzle has a proper expansion ratio and is made of proper materials and structures.
(5) The thrust eccentricity is small.
(6) The structure manufacturability is good and the economy is good.
At present, the related research on the design of the special micro-thrust eccentric nozzle is less, the special nozzle mainly comprises a double-arc nozzle and a parabolic nozzle, the structure of the special micro-thrust eccentric nozzle is more complex compared with that of a common conical nozzle, the special micro-thrust eccentric nozzle is lack of a mature design scheme, the research on the micro-thrust eccentric nozzle is more in recent years, the design research on the conical micro-thrust eccentric nozzle is mostly carried out, and the design and research on the special micro-thrust eccentric nozzle are less.
Disclosure of Invention
The invention aims to provide a special-shaped micro-thrust eccentric nozzle which can be used for reducing the thrust eccentric moment of a rocket engine, increasing the thrust of the rocket engine nozzle, reducing the deviation of a rocket projectile in the flight process to an expected trajectory and effectively improving the problem of low concentration of uncontrolled rocket projectiles.
The purpose of the invention is realized by the following technical scheme:
the invention relates to a micro-thrust eccentric special-shaped spray pipe, which comprises a spray pipe shell, a front protective layer, a spray pipe throat insert, a rear protective layer and a spray pipe tail cover, wherein the spray pipe shell is provided with a front protective layer and a rear protective layer;
the front section of the spray pipe shell is internally provided with a stepped cylindrical through hole with a large front end diameter and a small rear end diameter, and the rear section of the spray pipe shell is a cone which is connected with the front section of the spray pipe shell and expands backwards; the inner wall of the front end and the outer wall of the rear end of the spray pipe shell are both provided with connecting threads;
the front protective layer is a cylindrical part with the outer diameter matched with the small-diameter through hole at the front section of the spray pipe shell, an annular positioning table radially and outwardly extends is arranged on the outer wall of the front port part of the front protective layer, a conical working surface converging backwards is processed on the inner wall of the front port part of the front protective layer, a throat lining positioning table is arranged on the inner side of the rear port part of the front protective layer, the front end surface of the throat lining positioning table is an annular positioning surface, and the inner wall of the throat lining positioning table is an inwards concave arc-shaped working surface expanding backwards;
the outer wall of the front protective layer is adhered to the small-diameter through hole at the rear end of the inner cavity of the front section of the spray pipe shell, and the annular positioning table at the front end of the front protective layer is adhered to the stepped surface of the inner cavity of the front section of the spray pipe shell;
the front section of the inner shape of the nozzle throat insert is a convex arc-shaped working surface which converges backwards, the rear section of the inner shape of the nozzle throat insert is a convex arc-shaped working surface which expands backwards, and the axial arcs of the front section and the rear section of the convex arc-shaped working surface of the nozzle throat insert are tangent at the intersection;
the spray pipe throat lining is fixedly adhered to the inner cavity of the front protective layer, the front end and the rear end of the inner shape of the spray pipe throat lining are respectively connected with the conical working surface at the front end of the inner cavity of the front protective layer and the concave arc-shaped working surface at the rear end of the inner cavity, and the outer convex arc-shaped working surface at the rear section of the spray pipe throat lining is tangent to the axial arc line of the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer at the intersection;
the shape of the rear protective layer is matched with the inner shape of the conical barrel at the rear section of the spray pipe shell, and the inner shape of the rear protective layer is a backward-expanded concave arc-shaped working surface;
the rear protective layer is fixedly adhered to the inner wall of the conical barrel at the rear section of the spray pipe shell, and the inner cavity of the rear protective layer and the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer are spliced to form a working surface with the same radian; the spray pipe tail cover is in threaded connection with the rear end of the outer wall of the rear section of the spray pipe shell, an annular positioning table extending inwards in the radial direction is arranged at the rear end opening of the spray pipe tail cover, and the spray pipe tail cover limits the rear end of the rear protective layer through the annular positioning table; the front end of the spray pipe shell is in threaded connection with the rear end of the combustion chamber;
wherein the throat diameter Rt of the nozzle throat insert satisfies the following formula:
RL＝100Rt 2 ；
wherein R is the diameter of the engine charge and L is the length of the engine charge;
the arc radius of the arc-shaped working surface of the front section of the nozzle throat insert is 1-2 times of the throat diameter of the nozzle throat insert;
the arc radius of the outer convex arc-shaped working surface at the rear section of the nozzle throat insert, the arc radius of the inner wall of the throat insert positioning table at the rear end of the front protective layer and the arc radius of the inner concave arc-shaped working surface of the rear protective layer are all 5-10 times of the arc radius of the arc-shaped working surface at the front section of the nozzle throat insert;
the axial length of the nozzle expansion section is 4-5 times of the throat diameter of the nozzle throat insert.
Advantageous effects
The special-shaped spray pipe is simple in structure, convenient to install and reliable in work, does not need to change the structural layout of the spray pipe too much when being installed on different rocket engines or spacecrafts, can be installed after being directly upgraded and modified according to the size of the existing rocket engine, is low in cost and short in development period, and is easier to carry out experiments and put into mass production; the expansion section of the special-shaped spray pipe adopts the design of the molded surface of the double-arc spray pipe, the expansion ratio of the spray pipe can be increased on the premise of equal length of the spray pipe, the space of the expansion section of the spray pipe is increased, and fuel gas is fully expanded in the expansion section of the spray pipe so as to achieve the effect of increasing the thrust of the spray pipe. The special-shaped spray pipe of the invention designs the length of the expansion section of the spray pipe according to the thrust eccentric zero point, achieves the aim that the thrust eccentric moment of the spray pipe tends to zero, and improves the reliability of the spray pipe.
Drawings
FIG. 1 is a schematic structural view of a special nozzle of the present invention;
in the figure, 1-nozzle throat insert, 2-nozzle tail cover, 3-nozzle shell, 4-expansion section and 5-protective layer.
Detailed Description
The invention is further described with reference to the following figures and examples.
Examples
As shown in fig. 1, the special-shaped micro-thrust eccentric nozzle of the invention comprises a nozzle shell 3, a front protective layer 5, a nozzle throat insert 1, a rear protective layer 4 and a nozzle tail cover 2;
the front section of the spray pipe shell 3 is internally provided with a stepped cylindrical through hole with a large front end diameter and a small rear end diameter, and the rear section of the spray pipe shell 3 is a cone which is connected with the front section of the spray pipe shell 3 and expands backwards; the inner wall of the front end and the outer wall of the rear end of the spray pipe shell 3 are both provided with connecting threads;
the front protective layer 5 is a cylindrical part with the outer diameter matched with the small-diameter through hole at the front section of the spray pipe shell 3, an annular positioning table radially and outwardly extends is arranged on the outer wall of the front port part of the front protective layer 5, a conical working surface converging backwards is processed on the inner wall of the front port part of the front protective layer 5, the inclination angle of the conical working surface is 45 degrees, a throat lining positioning table is arranged on the inner side of the rear port part of the front protective layer 5, the front end surface of the throat lining positioning table is an annular positioning surface, the inner wall of the throat lining positioning table is a backwards-expanded inwards-concave arc-shaped working surface, and the arc radius of the inwards-concave arc-shaped working surface is 155mm;
the outer wall of the front protective layer 5 is fixedly adhered in a small-diameter through hole at the rear end of the front section inner cavity of the spray pipe shell 3, and the annular positioning table at the front end of the front protective layer 5 is fixedly adhered on the stepped surface of the front section inner cavity of the spray pipe shell 3;
the front section of the inner shape of the nozzle throat insert 1 is an outward convex arc-shaped working surface which converges backwards, the arc radius of the outward convex arc-shaped working surface is 50mm, the rear section of the inner shape of the nozzle throat insert 1 is an outward convex arc-shaped working surface which expands backwards, the arc radius of the outward convex arc-shaped working surface is 155mm, the axial arcs of the front section and the rear section of the outward convex arc-shaped working surface of the nozzle throat insert 1 are tangent at the intersection, and the throat diameter of the nozzle throat insert 1 is 12.5mm;
the spray pipe throat insert 1 is fixedly adhered to the inner cavity of the front protective layer 5, the front end and the rear end of the inner shape of the spray pipe throat insert 1 are respectively connected with the conical working surface at the front end of the inner cavity of the front protective layer 5 and the concave arc-shaped working surface at the rear end of the inner cavity, and the outer convex arc-shaped working surface at the rear section of the spray pipe throat insert 1 is tangent to the axial arc line of the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer 5 at the intersection;
the shape of the rear protective layer 4 is matched with the inner shape of the rear-section cone of the spray pipe shell 3, the inner shape of the rear protective layer 4 is an inwards concave arc-shaped working surface which expands backwards, the arc radius of the inwards concave arc-shaped working surface is 155mm, and the radius of the inner wall of the outlet end of the rear protective layer 4 is 30mm;
the rear protective layer 4 is fixedly adhered to the inner wall of the rear section cone of the spray pipe shell 3, the inner cavity of the rear protective layer 4 and the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer 5 are spliced to form a working surface with the same radian, and the axial length of a spray pipe expansion section (the throat diameter of the spray pipe throat insert 1 to the outlet end of the rear protective layer 4) is 55mm; the spray pipe tail cover 2 is in threaded connection with the rear end of the outer wall of the rear section of the spray pipe shell 3, an annular positioning table extending radially inwards is arranged at the rear end opening of the spray pipe tail cover 2, and the spray pipe tail cover 2 limits the rear end of the rear protective layer 4 through the annular positioning table; the front end of the nozzle shell 3 is in threaded connection with the rear end of the combustion chamber.
The simulation calculation is carried out on the internal flow field of the spray pipe in the embodiment, namely, the surface integral is carried out on the thrust vector of the spray pipe in different sections of the expansion section of the spray pipe, so that the main thrust Fx of each section of the expansion section of the spray pipe, which is vertical to the axis, along the axis direction and the lateral force Fy of each section of the expansion section of the spray pipe, which is vertical to the axis of the spray pipe can be obtained, and according to the calculation formula of the thrust eccentric angle alpha: tan alpha = Fy/Fx, the eccentric thrust angle of the special-shaped spray pipe obtained in the embodiment can be calculated to be 0.65 degrees, and the eccentric thrust angle of the spray pipe is 2.35 degrees under the conditions of the same expansion ratio and the same expansion section length of the spray pipe with the traditional structure, so that the influence of the eccentric thrust of the spray pipe is greatly reduced, and the thrust stability of the spray pipe is improved.
Claims (2)
1. A special-shaped micro-thrust eccentric nozzle is characterized in that: comprises a spray pipe shell, a front protective layer, a spray pipe throat insert, a rear protective layer and a spray pipe tail cover;
the front section of the spray pipe shell is internally provided with a stepped cylindrical through hole with a large front end diameter and a small rear end diameter, and the rear section of the spray pipe shell is a cone which is connected with the front section of the spray pipe shell and expands backwards; the inner wall of the front end and the outer wall of the rear end of the spray pipe shell are both provided with connecting threads;
the front protective layer is a cylindrical part of which the outer diameter is matched with the small-diameter through hole at the front section of the spray pipe shell, an annular positioning table radially and outwardly extends is arranged on the outer wall of the front port part of the front protective layer, a tapered working surface which converges backwards is processed on the inner wall of the front port part of the front protective layer, a throat lining positioning table is arranged on the inner side of the rear port part of the front protective layer, the front end surface of the throat lining positioning table is an annular positioning surface, and the inner wall of the throat lining positioning table is an inwards concave arc-shaped working surface which expands backwards;
the outer wall of the front protective layer is fixedly adhered in a small-diameter through hole at the rear end of the inner cavity of the front section of the spray pipe shell, and the annular positioning table at the front end of the front protective layer is fixedly adhered on the stepped surface of the inner cavity of the front section of the spray pipe shell;
the front section of the inner shape of the nozzle throat insert is a convex arc-shaped working surface which converges backwards, the rear section of the inner shape of the nozzle throat insert is a convex arc-shaped working surface which expands backwards, and the axial arcs of the front section and the rear section of the convex arc-shaped working surface of the nozzle throat insert are tangent at the intersection;
the spray pipe throat insert is fixedly adhered to the inner cavity of the front protective layer, the front end and the rear end of the inner shape of the spray pipe throat insert are respectively connected with the conical working surface at the front end of the inner cavity of the front protective layer and the concave arc-shaped working surface at the rear end of the inner cavity, and the convex arc-shaped working surface at the rear section of the spray pipe throat insert is tangent to the axial arc line of the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer at the intersection;
the shape of the rear protective layer is matched with the inner shape of the conical barrel at the rear section of the spray pipe shell, and the inner shape of the rear protective layer is a backward-expanded concave arc-shaped working surface;
the rear protective layer is fixedly adhered to the inner wall of the conical barrel at the rear section of the spray pipe shell, and the inner cavity of the rear protective layer and the concave arc-shaped working surface at the rear end of the inner cavity of the front protective layer are spliced to form a working surface with the same radian; the spray pipe tail cover is in threaded connection with the rear end of the outer wall of the rear section of the spray pipe shell, an annular positioning table extending inwards in the radial direction is arranged at the rear end opening of the spray pipe tail cover, and the spray pipe tail cover limits the rear end of the rear protective layer through the annular positioning table; the front end of the spray pipe shell is in threaded connection with the rear end of the combustion chamber.
2. The special nozzle for micro-thrust eccentricity as set forth in claim 1, wherein: the throat diameter Rt of the nozzle throat insert meets the following formula:
RL＝100Rt 2 ；
wherein R is the diameter of the engine charge and L is the length of the engine charge;
the arc radius of the arc-shaped working surface of the front section of the nozzle throat insert is 1-2 times of the throat diameter of the nozzle throat insert;
the arc radius of the convex arc-shaped working surface at the rear section of the nozzle throat insert, the arc radius of the inner wall of the throat insert positioning table at the rear end of the front protective layer and the arc radius of the concave arc-shaped working surface in the rear protective layer are all 5-10 times of the arc radius of the arc-shaped working surface at the front section of the nozzle throat insert;
the axial length of the nozzle expansion section is 4-5 times of the throat diameter of the nozzle throat insert.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211052027.6A CN115434827A (en) | 2022-08-31 | 2022-08-31 | Special-shaped micro-thrust eccentric spray pipe |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211052027.6A CN115434827A (en) | 2022-08-31 | 2022-08-31 | Special-shaped micro-thrust eccentric spray pipe |
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| CN115434827A true CN115434827A (en) | 2022-12-06 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116160721A (en) * | 2023-02-03 | 2023-05-26 | 武汉理工大学 | Rocket nozzle preparation system |
-
2022
- 2022-08-31 CN CN202211052027.6A patent/CN115434827A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116160721A (en) * | 2023-02-03 | 2023-05-26 | 武汉理工大学 | Rocket nozzle preparation system |
| CN116160721B (en) * | 2023-02-03 | 2024-05-14 | 武汉理工大学 | Rocket nozzle preparation system |
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