Incremental aerodynamic characteristic design method for layout configuration of exposed large nozzle

Abstract

The invention discloses an incremental aerodynamic characteristic design method for an exposed large nozzle layout configuration. The incremental aerodynamic characteristic design method comprises the following steps: acquiring basic aerodynamic data of a 0-degree swing angle of a nozzle; pneumatic data of the pitching swing state of the spray pipe and pneumatic data of the yawing swing state of the spray pipe are obtained; according to the basic pneumatic data of the 0-degree swing angle of the spray pipe and the pneumatic data of the pitching swing state of the spray pipe, the pitching swing pneumatic data difference is obtained; the yaw swing pneumatic data difference is obtained according to the basic pneumatic data of the 0-degree swing angle of the spray pipe and the pneumatic data of the yaw swing state of the spray pipe; and according to the basic pneumatic data of the 0-degree swing angle of the spray pipe, the pitch swing pneumatic data difference and the yaw swing pneumatic data difference, pneumatic data of the full circumferential swing state of the spray pipe are obtained. The problem that the influence of the spray pipe cannot be considered in aerodynamic characteristic design is solved, and aerodynamic characteristic design of the large spray pipe layout configuration is efficiently and reliably completed.

Description

Technical Field

[0001] The invention belongs to the technical field of aerodynamic characteristic design, and in particular relates to an incremental aerodynamic characteristic design method for an exposed large nozzle layout configuration. Background Art

[0002] The exposed size of the nozzle of a traditional rocket is relatively small, which has little effect on the aerodynamic characteristics of the entire rocket. Whether it is a wind tunnel test or numerical simulation, the aerodynamic characteristics design generally does not consider the influence of the nozzle. With the increase in weight reduction and high thrust performance requirements, the rocket tail section becomes shorter, and the exposed size of the nozzle is larger, which significantly affects the aerodynamic characteristics of the entire rocket, thereby affecting the overall control ability of the rocket body.

[0003] After considering the influence of nozzle swing, the aerodynamic data will increase by one dimension. According to the traditional design method, the volume of aerodynamic data will increase by an order of magnitude after adding one dimension, which is a huge workload. On the other hand, since the nozzle swings 360 degrees in all directions, how to design aerodynamic data that includes all swing states is also a difficult problem. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide an incremental aerodynamic characteristic design method for an exposed large nozzle layout configuration, to solve the problem that the nozzle influence cannot be considered in the aerodynamic characteristic design, and to efficiently and reliably complete the aerodynamic characteristic design of the large nozzle layout configuration.

[0005] The objective of the present invention is achieved through the following technical scheme: an incremental aerodynamic characteristic design method for an exposed large nozzle layout configuration, comprising: obtaining basic aerodynamic data of the nozzle at a 0° swing angle; obtaining aerodynamic data of the nozzle in a pitch swing state and aerodynamic data of the nozzle in a yaw swing state; obtaining a pitch swing aerodynamic data difference based on the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle in a pitch swing state; obtaining a yaw swing aerodynamic data difference based on the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle in a yaw swing state; obtaining aerodynamic data of the nozzle in a full circumferential swing state based on the basic aerodynamic data of the nozzle at a 0° swing angle, the pitch swing aerodynamic data difference and the yaw swing aerodynamic data difference.

[0006] In the incremental aerodynamic characteristics design method of the above-mentioned exposed large nozzle layout configuration, the basic aerodynamic data of the nozzle at 0° swing angle is ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0007] In the incremental aerodynamic characteristics design method of the above-mentioned exposed large nozzle layout configuration, the aerodynamic data of the nozzle pitch swing state is ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0008] In the incremental aerodynamic characteristics design method of the above-mentioned exposed large nozzle layout configuration, the aerodynamic data of the nozzle yaw swing state is ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0009] In the incremental aerodynamic characteristic design method of the above-mentioned exposed large nozzle layout configuration, the pitch swing aerodynamic data difference is obtained by the following formula: ; in, is the pitch and swing aerodynamic data difference, is the aerodynamic data of the nozzle pitch and swing state, is the basic aerodynamic data of the nozzle at 0° swing angle, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0010] In the incremental aerodynamic characteristic design method of the above-mentioned exposed large nozzle layout configuration, the yaw swing aerodynamic data difference is obtained by the following formula: ; in, is the difference of yaw swing aerodynamic data, is the aerodynamic data of the nozzle yaw swing state, is the basic aerodynamic data of the nozzle at 0° swing angle, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0011] In the incremental aerodynamic characteristic design method of the above-mentioned exposed large nozzle layout configuration, the aerodynamic data of the nozzle in the full circumferential swing state is obtained by the following formula: ; in, is the aerodynamic data of the nozzle in the full circumferential swing state, is the pitch and swing aerodynamic data difference, is the difference of yaw swing aerodynamic data, It is the basic aerodynamic data of the nozzle with a swing angle of 0°.

[0012] An incremental aerodynamic characteristic design system for an exposed large nozzle layout configuration comprises: a first module for obtaining basic aerodynamic data of a nozzle at a 0° swing angle; a second module for obtaining aerodynamic data of a nozzle pitch swing state and aerodynamic data of a nozzle yaw swing state; a third module for obtaining a difference in pitch swing aerodynamic data based on the basic aerodynamic data of the nozzle at a 0° swing angle and aerodynamic data of a nozzle pitch swing state; a fourth module for obtaining a difference in yaw swing aerodynamic data based on the basic aerodynamic data of the nozzle at a 0° swing angle and aerodynamic data of a nozzle yaw swing state; and a fifth module for obtaining aerodynamic data of a nozzle in a full circumferential swing state based on the basic aerodynamic data of the nozzle at a 0° swing angle, the difference in pitch swing aerodynamic data and the difference in yaw swing aerodynamic data.

[0013] In the incremental aerodynamic characteristic design system of the above-mentioned exposed large nozzle layout configuration, the basic aerodynamic data of the nozzle at 0° swing angle is ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0014] In the incremental aerodynamic characteristics design system of the above-mentioned exposed large nozzle layout configuration, the aerodynamic data of the nozzle pitch swing state is ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0015] Compared with the prior art, the present invention has the following beneficial effects: The present invention solves the problem that the influence of the nozzle cannot be considered in the aerodynamic characteristic design, and efficiently and reliably completes the aerodynamic characteristic design of the large nozzle layout configuration. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings: Figure 1It is a flow chart of an incremental aerodynamic characteristic design method of an exposed large nozzle layout configuration provided by an embodiment of the present invention; Figure 2 is a schematic diagram of a coordinate system provided by an embodiment of the present invention; Figure 3 : is a schematic diagram of nozzle polarity provided by an embodiment of the present invention (viewed from the tail of the rocket to the head); Figure 4 is a schematic diagram comparing the aerodynamic characteristics of the nozzle with and without a swing angle provided by an embodiment of the present invention; Figure 5 is another schematic diagram comparing the aerodynamic characteristics of the nozzle with and without a swing angle provided by an embodiment of the present invention; Figure 6 It is a schematic diagram of the aerodynamic comparison between the actual swing angle of the nozzle circumferential swing provided by the embodiment of the present invention and the synthetic swing angle aerodynamic comparison under the decoupled design data; Figure 7 It is another schematic diagram of the comparison between the actual aerodynamics of the nozzle circumferential swing angle and the aerodynamics of the synthetic swing angle under the decoupled design data provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0017] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to be able to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0018] Figure 1 1 is a flow chart of an incremental aerodynamic characteristic design method for an exposed large nozzle layout configuration provided by an embodiment of the present invention. Figure 1 As shown, the method comprises the following steps: Obtain basic aerodynamic data of nozzle 0° swing angle; Acquire aerodynamic data of the nozzle pitch swing state and aerodynamic data of the nozzle yaw swing state; The difference of the aerodynamic data of the pitching swing is obtained according to the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle at a pitching swing state; The difference of yaw swing aerodynamic data is obtained according to the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle at a yaw swing state; The aerodynamic data of the nozzle in the full circumferential swing state are obtained based on the basic aerodynamic data of the nozzle at a 0° swing angle, the difference of the pitch swing aerodynamic data, and the difference of the yaw swing aerodynamic data.

[0019] Aerodynamic coordinate system Figure 2 As shown, the coordinate origin O is located at the vertex; the OX axis is along the axis of the arrow body, and the tail is positive when it points to the head; the OY axis is in the longitudinal symmetry plane of the arrow body, perpendicular to the OX axis, and positive upward; the OZ axis is perpendicular to the OXY plane, and the positive direction satisfies the right-hand rule.

[0020] Nozzle pitch angle and yaw angle The sign of is defined as Figure 3 As shown in the figure, when looking from the tail of the rocket to the head, the nozzle outlet swings downward (negative direction of OY axis) as the positive pitch angle, and the nozzle outlet swings to the right (positive direction of OZ axis) as the positive yaw angle.

[0021] Specifically, the method comprises the following steps: 1) Obtain basic aerodynamic data of nozzle 0° swing angle:

[0022] in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

[0023] According to the flight profile, the input parameter envelope is determined, including Mach number, angle of attack, sideslip angle, rudder deflection angle, etc. The aerodynamic model is given according to the actual nozzle profile and the non-swinging state. The basic aerodynamic data under the full parameter envelope is obtained through wind tunnel tests and numerical simulations. Since the wind tunnel test is a scaled model, the diameter of the support column section is minimized as much as possible on the basis of ensuring the tail support strength, so as to reduce the impact of the aerodynamic characteristics caused by the profile change.

[0024] 2) Obtain aerodynamic data of the nozzle pitch and swing state: ; Obtain the aerodynamic data of the nozzle yaw swing state: .

[0025] The aerodynamic data changes caused by the full-circle swing of the nozzle are decoupled into two channels: nozzle pitch and yaw swing, and the aerodynamic data of the nozzle swing state are obtained.

[0026] Determine the maximum nozzle swing angle based on the servo capability and calculate the nozzle pitch and and yaw Aerodynamic characteristics of the entire arrow under the swing angle. The data design of the full circumferential swing of the nozzle is realized by synthesizing the aerodynamic data of the nozzle pitch and yaw swing states.

[0027] 3) Based on the basic aerodynamic data of the nozzle 0° swing angle in step 1) and the aerodynamic data of the nozzle pitch swing state in step 2) Get the pitch and swing aerodynamic data difference.

[0028] Pitch and swing aerodynamic data difference for: .

[0029] According to the basic aerodynamic data of nozzle 0° swing angle in step 1) And the aerodynamic data of the nozzle yaw swing state in step 2): Obtain the yaw swing aerodynamic data difference.

[0030] Yaw swing aerodynamic data difference for: .

[0031] By subtracting the aerodynamic data in the swing state from the basic aerodynamic data, the aerodynamic data increments in the pitch and yaw swing states of the nozzle are obtained.

[0032] 4) Based on the basic aerodynamic data of the nozzle 0° swing angle in step 1) The aerodynamic data of the full circumferential swing state of the nozzle is obtained by the difference of the pitch swing aerodynamic data in step 3) and the difference of the yaw swing aerodynamic data in step 3). .

[0033] ; The aerodynamic characteristics of the nozzle swinging and non-swinging states are decoupled, and the aerodynamic data of the whole arrow is given as a state with the nozzle but without swinging. The aerodynamic data of the nozzle is given in an incremental superposition manner. Aerodynamic force / torque coefficient with swing angle CX ( CX = CA, CN, CZ, CMX, CMY, CMZ ) is calculated as: .

[0034] Among them, CA is the axial force coefficient, CN is the normal force coefficient, CZ is the lateral force coefficient, CMX is the rolling moment coefficient, CMY is the yaw moment coefficient, and CMZ is the pitching moment coefficient.

[0035] Figure 4 is a schematic diagram comparing the aerodynamic characteristics of the nozzle with and without a swing angle provided by an embodiment of the present invention; Figure 5 is another schematic diagram comparing the aerodynamic characteristics of the nozzle with and without a swing angle provided by an embodiment of the present invention; Figure 6 It is a schematic diagram of the aerodynamic comparison between the actual swing angle of the nozzle circumferential swing provided by the embodiment of the present invention and the synthetic swing angle aerodynamic comparison under the decoupled design data; Figure 7It is another schematic diagram of the comparison between the actual aerodynamics of the nozzle circumferential swing angle and the aerodynamics of the synthetic swing angle under the decoupled design data provided by an embodiment of the present invention.

[0036] The present embodiment provides an incremental aerodynamic characteristic design system for an exposed large nozzle layout configuration, the system comprising: a first module, used to obtain basic aerodynamic data of the nozzle at a 0° swing angle; a second module, used to obtain aerodynamic data of the nozzle in a pitch swing state and aerodynamic data of the nozzle in a yaw swing state; a third module, used to obtain a difference in pitch swing aerodynamic data based on the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle in a pitch swing state; a fourth module, used to obtain a difference in yaw swing aerodynamic data based on the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle in a yaw swing state; a fifth module, used to obtain aerodynamic data of the nozzle in a full circumferential swing state based on the basic aerodynamic data of the nozzle at a 0° swing angle, the difference in pitch swing aerodynamic data and the difference in yaw swing aerodynamic data.

[0037] This embodiment solves the design problem that aerodynamic characteristics cannot take into account the influence of nozzle swing. Although the data has added a dimension, it does not increase the difficulty of aerodynamic data design, and at the same time significantly improves the level of refined design of aerodynamic characteristics.

[0038] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. An incremental aerodynamic characteristics design method for an exposed large nozzle layout configuration, characterized in that include: Obtain basic aerodynamic data of nozzle 0° swing angle; Acquire aerodynamic data of the nozzle pitch swing state and aerodynamic data of the nozzle yaw swing state; The difference of the aerodynamic data of the pitching swing is obtained according to the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle at a pitching swing state; The difference of yaw swing aerodynamic data is obtained according to the basic aerodynamic data of the nozzle at a 0° swing angle and the aerodynamic data of the nozzle at a yaw swing state; The aerodynamic data of the nozzle in the full circumferential swing state are obtained based on the basic aerodynamic data of the nozzle at a 0° swing angle, the difference of the pitch swing aerodynamic data, and the difference of the yaw swing aerodynamic data.

2. The incremental aerodynamic characteristics design method of the exposed large nozzle layout configuration according to claim 1 is characterized in that: The basic aerodynamic data of the nozzle 0° swing angle is: ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

3. The incremental aerodynamic characteristics design method of the exposed large nozzle layout configuration according to claim 1, characterized in that: The aerodynamic data of the nozzle pitch swing state is: ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

4. The incremental aerodynamic characteristics design method of the exposed large nozzle layout configuration according to claim 1, characterized in that: The aerodynamic data of the nozzle yaw swing state is: ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

5. The incremental aerodynamic characteristics design method of the exposed large nozzle layout configuration according to claim 1, characterized in that: The difference in pitch and swing aerodynamic data is obtained by the following formula: ； in, is the pitch and swing aerodynamic data difference, is the aerodynamic data of the nozzle pitch and swing state, is the basic aerodynamic data of the nozzle at 0° swing angle, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

6. The incremental aerodynamic characteristics design method of the exposed large nozzle layout configuration according to claim 1, characterized in that: The difference in yaw swing aerodynamic data is obtained by the following formula: ； in, is the difference of yaw swing aerodynamic data, is the aerodynamic data of the nozzle yaw swing state, is the basic aerodynamic data of the nozzle at 0° swing angle, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

7. The incremental aerodynamic characteristics design method of the exposed large nozzle layout configuration according to claim 1, characterized in that: The aerodynamic data of the nozzle's full circumferential swing state is obtained by the following formula: ； in, is the aerodynamic data of the nozzle in the full circumferential swing state, is the pitch and swing aerodynamic data difference, is the difference of yaw swing aerodynamic data, It is the basic aerodynamic data of the nozzle with a swing angle of 0°.

8. An incremental aerodynamic characteristics design system for an exposed large nozzle layout configuration, characterized in that include: The first module is used to obtain the basic aerodynamic data of the nozzle at a 0° swing angle; The second module is used to obtain the aerodynamic data of the nozzle pitch swing state and the aerodynamic data of the nozzle yaw swing state; The third module is used to obtain the difference of the pitch swing aerodynamic data according to the basic aerodynamic data of the nozzle 0° swing angle and the aerodynamic data of the nozzle pitch swing state; The fourth module is used to obtain the difference of yaw swing aerodynamic data according to the basic aerodynamic data of the nozzle 0° swing angle and the aerodynamic data of the nozzle yaw swing state; The fifth module is used to obtain the aerodynamic data of the full circumferential swing state of the nozzle based on the basic aerodynamic data of the nozzle 0° swing angle, the difference of the pitch swing aerodynamic data and the difference of the yaw swing aerodynamic data.

9. The incremental aerodynamic characteristic design system of the exposed large nozzle layout configuration according to claim 8, characterized in that: The basic aerodynamic data of the nozzle 0° swing angle is: ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

10. The incremental aerodynamic characteristic design system of the exposed large nozzle layout configuration according to claim 8, characterized in that: The aerodynamic data of the nozzle pitch swing state is: ;in, is the Mach number, is the angle of attack, is the sideslip angle, is the nozzle pitch angle, is the nozzle yaw angle.

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