CN118228521A - Design method of solid engine composite shell adapting to aerodynamic thermal coupling internal heat - Google Patents
Design method of solid engine composite shell adapting to aerodynamic thermal coupling internal heat Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 48
- 238000013461 design Methods 0.000 title claims abstract description 39
- 239000002131 composite material Substances 0.000 title claims abstract description 35
- 239000007787 solid Substances 0.000 title claims abstract description 17
- 230000008878 coupling Effects 0.000 title claims abstract description 14
- 238000010168 coupling process Methods 0.000 title claims abstract description 14
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 14
- 238000004364 calculation method Methods 0.000 claims abstract description 18
- 238000012546 transfer Methods 0.000 claims abstract description 18
- 230000008569 process Effects 0.000 claims abstract description 13
- 230000002787 reinforcement Effects 0.000 claims abstract description 12
- 238000010438 heat treatment Methods 0.000 claims description 15
- 239000000835 fiber Substances 0.000 claims description 9
- 238000004458 analytical method Methods 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 7
- 238000000576 coating method Methods 0.000 claims description 7
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- 238000002485 combustion reaction Methods 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 6
- 238000004804 winding Methods 0.000 claims description 4
- 230000009172 bursting Effects 0.000 claims description 3
- 238000012937 correction Methods 0.000 claims description 3
- 238000005457 optimization Methods 0.000 abstract description 2
- 239000011257 shell material Substances 0.000 abstract 8
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- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
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Abstract
The invention provides a design method of a composite shell of a solid engine, which is suitable for pneumatic thermal coupling internal heat, and solves the problem of high-performance composite shell design under the condition of long-time high-speed accompanying and internal and external heat transfer in the whole process. According to the method, the optimization selection and scheme design reinforcement of the composite material shell material of the engine are carried out according to the internal and external heat transfer coupling calculation result of the engine, and the composite material shell design of the hypersonic aircraft is completed. The method mainly comprises four steps: and (3) designing the strength of the shell cylinder, calculating the internal and external heat transfer of the engine, determining a structural reinforcement area, and analyzing and confirming the rigidity and strength of the shell. The design method of the invention can realize that the structural reliability of the shell under the condition of long-time high-speed accompanying is obviously improved under the condition of limited mass increase of the composite shell.
Description
Technical Field
The invention belongs to the technical field of aircraft engine design, and particularly relates to a method for designing a solid engine composite shell.
Background
Solid rocket engines are widely used power systems in aircrafts and rockets, and composite material shells are the preferred shell scheme of the medium-and-long-range aircraft engines, so that the improvement of the quality characteristics and the overall performance of the engines is facilitated. The design of the composite material shell relates to the improvement of the quality characteristics of the engine, influences the range of the aircraft to a certain extent, and is a difficult and key problem of the design of the medium-large caliber engine.
At present, researches at home and abroad are mostly developed aiming at internal pressure and internal heat transfer conditions of an engine, mainly scheme design, material verification and performance research, and less researches are performed on the design aspect of a composite shell with long-time high-speed flight and severe heat load in the whole process. Meanwhile, the composite material shells at home and abroad are generally developed according to the working pressure and external load requirements of the engine in the scheme design stage, and the influence of temperature change caused by internal and external heat transfer coupling effect on the strength is not directly considered, so that the scheme needs to perform multi-round iterative optimization according to the overall simulation result or take measures for strengthening internal and external heat protection, on one hand, the design efficiency is lower, and on the other hand, the quality characteristics of the engine are negatively influenced.
Disclosure of Invention
In order to overcome the defects of the prior art and solve the problems of low design efficiency and poor quality characteristics of a high-performance composite shell under the conditions of long-time high-speed flight and internal and external heat transfer in the whole process, the invention provides a design method of a solid engine composite shell suitable for pneumatic heat coupling internal heat.
The technical scheme adopted for solving the technical problems is a design method of a solid engine composite shell adapting to aerodynamic heat coupling internal heat, comprising the following steps:
Step (1): the strength of the shell cylinder is designed;
step (II): calculating internal and external heat transfer of the engine;
Step (III): determining a structural reinforcement region;
Step (IV): and (5) analyzing and confirming the rigidity and the strength of the shell.
Further, in the step (one), the step of designing the strength of the shell cylinder is:
Thickness of longitudinal fiber layer of shell cylinder in internal pressure design The method comprises the following steps:
；
thickness of annular layer of shell cylinder The method comprises the following steps:
；
Wherein, To design burst pressure,/>For the radius of the shell cylinder,/>Exert strength on the fiber,/>For the winding angle,/>Calculating to obtain the thickness of the longitudinal fiber layer of the shell cylinder and the thickness of the circumferential layer of the shell cylinder as stress balance coefficients;
In the elastic stability analysis, the shell cylinder is treated as an orthotropic shell, and critical axial pressure of the shell cylinder is measured Estimated as follows:
；
Wherein, For correction factor,/>Is the wall thickness of the shell cylinder,/>For the shell cylinder longitudinal modulus,/>Is the shell cylinder circumferential modulus,/>For the collar to Poisson's ratio,/>Ring axial poisson ratio;
front joint and rear joint of shell cylinder are based on joint cross-sectional area And shoulder root thickness/>The calculation is completed:
；
；
Wherein, Is the cross-sectional area of the joint,/>Is the thickness of the root of the shoulder,/>Is the radius of the centroid circle of the joint,/>Is the bursting pressure of the end socket,/>Is the tensile strength of the joint material,/>For the end closure is/>Included angle between second curvature radius and axis,/>Poisson's ratio for linker material,/>=B/a, a is the joint shoulder outer circle radius, b is the joint shoulder inner circle radius; /(I)Is an ellipsoidal ratio.
Further, in the step (two), the specific steps of calculating the internal and external heat transfer of the engine are as follows:
the engine generates high-temperature and high-pressure gas in the working process, and is influenced by pneumatic heating in high-speed flight; therefore, the aerodynamic heating environments of the windward side and the leeward side of the aircraft are different in the flight process, and the aerodynamic heating conditions of the windward side and the leeward side are calculated respectively;
the specific calculation steps are as follows:
a. obtaining the heat flow of the windward side and the heat flow of the leeward side of the aircraft in the flight process by using a aerodynamic heat calculation method, and calculating the temperature-time curve of the outer wall of the coating by using the heat flow of the windward side and the heat flow of the leeward side;
b. Inputting the point value of the temperature-time curve of the outer wall of the coating into a heat exchange model as an outer heat boundary of the shell;
c. Applying the high-temperature gas heat flow temperature of the engine to the inner surface of the combustion chamber rubber as a boundary condition, namely taking the high-temperature gas heat flow temperature of the engine as input, and calculating the heat transfer of the inner surface of the combustion chamber rubber;
d. Calculating the total heat absorbed by the shell;
Wherein, for rocket flying in a lean transition zone, the shell of the transition zone is pneumatically heated The method comprises the following steps:
；
Wherein, For the pneumatic heating quantity of the shell/(Is the heat exchange coefficient,/>Is the free incoming flow density,/>For flying speed,/>Is the enthalpy value of standing point,/>Is the enthalpy value of the incoming flow;
total heat absorbed by the shell and rubber And structural temperature rise/>The relation of (2) is:
；
total heat absorbed by the shell and rubber,/> Is the specific heat capacity of the shell/>Is shell density/>Is shell thickness/>Is the specific heat capacity of rubber,/>Is rubber density,/>Is rubber thickness/>Is structural temperature rise;
the pneumatic heating quantity of the shell is equal to the total heat quantity absorbed by the shell and the rubber at the moment, namely Obtaining the shell/>, by utilizing the joint solution of the equation。
Further, the specific step of determining the structural reinforcement area in the step (three) is as follows:
according to the calculation in step (two) Calculating the shell wall temperature/>：
；
Wherein the method comprises the steps ofThe initial temperature of the shell is the known parameter input in design;
According to the result of heat transfer calculation, the wall surface temperature of the shell Higher than allowable temperature of the shellIs reinforced in the local area of the (c).
Further, the reinforcement is accomplished by adding localized entanglement.
Further, in the step (four) of analyzing and confirming the rigidity and the strength of the shell, the rigidity and the strength of the shell are respectively calculated by adopting a numerical analysis method.
Further, in the step (four), the step of analyzing and confirming the rigidity of the shell is as follows: when the strength or rigidity of the shell under the local high-temperature condition does not meet the safety bearing requirement, the structure is reinforced; when the strength and the rigidity of the shell under the local high-temperature condition meet the safe bearing requirement, the shell structure meeting the design target is obtained.
The beneficial effects of the invention are as follows: the design method of the composite shell of the solid engine, which is suitable for aerodynamic thermal coupling internal heat, can be used for remarkably improving the structural reliability of the shell under the condition of long-time high-speed accompanying under the condition of limited mass increase of the composite shell. In a certain engine composite shell design scheme, the design method is adopted, so that the shell scheme reduces the mass of the external heat-proof coating by 10% under the condition that the mass of a composite material layer is increased by 1.0%, the total weight of the shell can be reduced by about 0.5%, and the mass ratio requirement of an engine is met.
Drawings
FIG. 1 is a flow chart of a method of designing a solid engine composite housing that accommodates aerodynamic thermally coupled internal heat;
FIG. 2 is a schematic illustration of an initial version of an embodiment engine composite housing;
FIG. 3 is a schematic view of a front joint design part structure of an embodiment;
FIG. 4 is a schematic diagram of the result of the post-joint local enhancement design according to the embodiment;
FIG. 5 is a schematic view of the front end structure of the composite shell;
FIG. 6 is a schematic view of the rear end structure of the composite shell;
FIG. 7 is a schematic view of partial reinforcement;
FIG. 8 is an enlarged view of a portion of a partially reinforced structure;
Wherein 1 is a local stiffening region.
Detailed Description
The invention will be further described with reference to the drawings and examples.
The technical scheme adopted for solving the technical problems is a design method of a solid engine composite shell adapting to aerodynamic heat coupling internal heat, comprising the following steps:
Step (1): the strength of the shell cylinder is designed;
Thickness of longitudinal fiber layer of shell cylinder in internal pressure design The method comprises the following steps:
；
thickness of annular layer of shell cylinder The method comprises the following steps:
；
Wherein, To design burst pressure,/>For the radius of the shell cylinder,/>Exert strength on the fiber,/>For the winding angle,/>Calculating to obtain the thickness of the longitudinal fiber layer of the shell cylinder and the thickness of the circumferential layer of the shell cylinder as stress balance coefficients;
In the elastic stability analysis, the shell cylinder is treated as an orthotropic shell, and critical axial pressure of the shell cylinder is measured Estimated as follows:
；
Wherein, For correction factor,/>Is the wall thickness of the shell cylinder,/>For the shell cylinder longitudinal modulus,/>Is the shell cylinder circumferential modulus,/>For the collar to Poisson's ratio,/>Ring axial poisson ratio;
front joint and rear joint of shell cylinder are based on joint cross-sectional area And shoulder root thickness/>The calculation is completed:
；
；
Wherein, Is the cross-sectional area of the joint,/>Is the thickness of the root of the shoulder,/>Is the radius of the centroid circle of the joint,/>Is the bursting pressure of the end socket,/>Is the tensile strength of the joint material,/>For the end closure is/>Included angle between second curvature radius and axis,/>Poisson's ratio for linker material,/>=B/a, a is the joint shoulder outer circle radius, b is the joint shoulder inner circle radius; /(I)Is an ellipsoidal ratio;
step (II): calculating internal and external heat transfer of the engine;
the engine generates high-temperature and high-pressure gas in the working process, and is influenced by pneumatic heating in high-speed flight; therefore, the aerodynamic heating environments of the windward side and the leeward side of the aircraft are different in the flying process, and the aerodynamic heating conditions of the windward side and the leeward side are required to be calculated respectively;
the specific calculation steps are as follows:
a. obtaining heat flows of a windward side and a leeward side of the aircraft in the flight process by using a aerodynamic heat calculation method, and obtaining a temperature-time curve of the outer wall of the coating by using the heat flows of the windward side and the leeward side;
b. Inputting the point value of the temperature-time curve of the outer wall of the coating into a heat exchange model as an outer heat boundary of the shell;
c. Applying the high-temperature gas heat flow temperature of the engine to the inner surface of the combustion chamber rubber as a boundary condition, namely taking the high-temperature gas heat flow temperature of the engine as input, and calculating the heat transfer of the inner surface of the combustion chamber rubber;
d. Calculating the total heat absorbed by the shell;
Wherein, for rocket flying in a lean transition zone, the shell of the transition zone is pneumatically heated The method comprises the following steps:
；
Wherein, For the pneumatic heating quantity of the shell/(Is the heat exchange coefficient,/>Is the free incoming flow density,/>For flying speed,/>Is the enthalpy value of standing point,/>Is the enthalpy value of the incoming flow;
total heat absorbed by the shell and rubber And structural temperature rise/>The relation of (2) is:
；
total heat absorbed by the shell and rubber,/> Is the specific heat capacity of the shell/>Is shell density/>Is shell thickness/>Is the specific heat capacity of rubber,/>Is rubber density,/>Is rubber thickness/>Is structural temperature rise;
the pneumatic heating quantity of the shell is equal to the total heat quantity absorbed by the shell and the rubber at the moment, namely Obtaining the shell/>, by utilizing the joint solution of the equation；
Step (III): determining a structural reinforcement region;
according to the calculation in step (two) Calculating the shell wall temperature/>：
；
Wherein the method comprises the steps ofThe initial temperature of the shell is the known parameter input in design;
According to the result of heat transfer calculation, the wall surface temperature of the shell Higher than allowable temperature of the shellReinforcing a local region of the mold; the reinforcement is finished by adding local ring winding;
because the heat conductivity coefficient of the composite structure is lower, the method has the effects of reducing the heat exchange quantity and guaranteeing the strength of the internal structural layer on one hand, and increasing the thickness and the strength of the local composite on the other hand, thereby improving the overall performance of the structure;
step (IV): analyzing and confirming the rigidity of the shell;
the rigidity and the strength of the shell are respectively calculated by adopting a numerical analysis method;
The steps of the analysis and confirmation of the shell rigid strength are as follows: when the strength or rigidity of the shell under the local high-temperature condition does not meet the safety bearing requirement, the structure is reinforced; when the strength and the rigidity of the shell body under the local high-temperature condition meet the safe bearing requirement, the shell body structure meeting the design target is obtained.
The scheme of localized reinforcement of the structure is shown in FIGS. 7 and 8.
It should be noted that, the composite shell design is performed by adopting a mode of combining theoretical calculation, numerical analysis and component test verification methods, so that the feasibility of the design result can be ensured.
According to the technical scheme, the high-performance composite shell design under the condition of long-time high-speed accompanying and internal and external heat transfer in the whole process can be realized.
Claims (7)
1. A design method of a solid engine composite shell adapting to aerodynamic thermal coupling internal heat is characterized by comprising the following steps: the method comprises the following steps:
Step (1): the strength of the shell cylinder is designed;
step (II): calculating internal and external heat transfer of the engine;
Step (III): determining a structural reinforcement region;
Step (IV): and (5) analyzing and confirming the rigidity and the strength of the shell.
2. The method for designing the composite shell of the solid engine, which is suitable for aerodynamic thermal coupling internal heat, according to claim 1, is characterized in that: in the step (one), the step of designing the strength of the shell cylinder is as follows:
Thickness of longitudinal fiber layer of shell cylinder in internal pressure design The method comprises the following steps:
；
thickness of annular layer of shell cylinder The method comprises the following steps:
；
Wherein, To design burst pressure,/>For the radius of the shell cylinder,/>Exert strength on the fiber,/>For the winding angle,/>Calculating to obtain the thickness of the longitudinal fiber layer of the shell cylinder and the thickness of the circumferential layer of the shell cylinder as stress balance coefficients;
In the elastic stability analysis, the shell cylinder is treated as an orthotropic shell, and critical axial pressure of the shell cylinder is measured Estimated as follows:
；
Wherein, For correction factor,/>Is the wall thickness of the shell cylinder,/>For the shell cylinder longitudinal modulus,/>Is the shell cylinder circumferential modulus,/>For the collar to Poisson's ratio,/>Ring axial poisson ratio;
front joint and rear joint of shell cylinder are based on joint cross-sectional area And shoulder root thickness/>The calculation is completed:
；
；
Wherein, Is the cross-sectional area of the joint,/>Is the thickness of the root of the shoulder,/>Is the radius of the centroid circle of the joint,/>Is the bursting pressure of the end socket,/>Is the tensile strength of the joint material,/>For the end closure is/>Included angle between second curvature radius and axis,/>In the poisson ratio of the joint material,=B/a, a is the joint shoulder outer circle radius, b is the joint shoulder inner circle radius; /(I)Is an ellipsoidal ratio.
3. The method for designing the composite shell of the solid engine, which is suitable for aerodynamic thermal coupling internal heat, according to claim 1, is characterized in that: in the step (II), the specific steps of the internal and external heat transfer calculation of the engine are as follows:
the engine generates high-temperature and high-pressure gas in the working process, and is influenced by pneumatic heating in high-speed flight; therefore, the aerodynamic heating environments of the windward side and the leeward side of the aircraft are different in the flight process, and the aerodynamic heating conditions of the windward side and the leeward side are calculated respectively;
the specific calculation steps are as follows:
a. obtaining the heat flow of the windward side and the heat flow of the leeward side of the aircraft in the flight process by using a aerodynamic heat calculation method, and calculating the temperature-time curve of the outer wall of the coating by using the heat flow of the windward side and the heat flow of the leeward side;
b. Inputting the point value of the temperature-time curve of the outer wall of the coating into a heat exchange model as an outer heat boundary of the shell;
c. Applying the high-temperature gas heat flow temperature of the engine to the inner surface of the combustion chamber rubber as a boundary condition, namely taking the high-temperature gas heat flow temperature of the engine as input, and calculating the heat transfer of the inner surface of the combustion chamber rubber;
d. Calculating the total heat absorbed by the shell;
Wherein, for rocket flying in a lean transition zone, the shell of the transition zone is pneumatically heated The method comprises the following steps:
；
Wherein, For the pneumatic heating quantity of the shell/(Is the heat exchange coefficient,/>Is the free incoming flow density,/>For flying speed,/>Is the enthalpy value of standing point,/>Is the enthalpy value of the incoming flow;
total heat absorbed by the shell and rubber And structural temperature rise/>The relation of (2) is:
；
total heat absorbed by the shell and rubber,/> Is the specific heat capacity of the shell/>Is shell density/>Is shell thickness/>Is the specific heat capacity of rubber,/>Is rubber density,/>Is rubber thickness/>Is structural temperature rise;
the pneumatic heating quantity of the shell is equal to the total heat quantity absorbed by the shell and the rubber at the moment, namely Obtaining the shell/>, by utilizing the joint solution of the equation。
4. A method of designing a solid engine composite housing adapted to aerodynamic thermally coupled internal heat as defined in claim 3, wherein: the specific step of determining the structural reinforcement area in the step (III) is as follows:
according to the calculation in step (two) Calculating the shell wall temperature/>：
；
Wherein the method comprises the steps ofThe initial temperature of the shell is the known parameter input in design;
According to the result of heat transfer calculation, the wall surface temperature of the shell Higher than allowable temperature of the shellIs reinforced in the local area of the (c).
5. The method for designing the composite shell of the solid engine, which is suitable for aerodynamic thermal coupling internal heat, according to claim 4, is characterized in that: the reinforcement is accomplished by adding local loop wrap.
6. The method for designing the composite shell of the solid engine, which is suitable for aerodynamic thermal coupling internal heat, according to claim 1, is characterized in that: in the step (four), the step of analyzing and confirming the rigid strength of the shell is as follows: when the strength or rigidity of the shell under the local high-temperature condition does not meet the safety bearing requirement, the structure is reinforced; when the strength and the rigidity of the shell body under the local high-temperature condition meet the safe bearing requirement, the shell body structure meeting the design target is obtained.
7. The method for designing the composite shell of the solid engine, which is suitable for aerodynamic thermal coupling internal heat, according to claim 6, is characterized in that: the rigidity and the strength of the shell are calculated by adopting a numerical analysis method respectively.
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|---|---|---|---|---|
| EP0935058A2 (en) * | 1998-02-06 | 1999-08-11 | Isuzu Ceramics Research Institute Co., Ltd. | Radiators and soundproofing engine enclosure designs |
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2024
- 2024-05-24 CN CN202410650851.4A patent/CN118228521B/en active Active
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| EP0935058A2 (en) * | 1998-02-06 | 1999-08-11 | Isuzu Ceramics Research Institute Co., Ltd. | Radiators and soundproofing engine enclosure designs |
| CN108132112A (en) * | 2017-11-13 | 2018-06-08 | 北京临近空间飞行器系统工程研究所 | A kind of hypersonic aircraft surface heat flux device and design method |
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| Title |
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