CN116266238A - Supersonic Near-Earth Parallel Interstage Separation Method with Preset Rudder Offset Feature - Google Patents

Abstract

The invention provides a supersonic near-earth parallel interstage separation method with preset rudder deflection characteristics, which comprises the following steps: s10, selecting a plurality of different rudder deflection angles to obtain a combined model of a plurality of aircrafts and boosting stages; s20, acquiring pitching moments of the aircraft in the separated initial postures under different rudder deflection angles; s30, judging whether a zero pitching moment exists, if so, turning to S50; otherwise, go to S40; s40, increasing the control surface area of the aircraft by a preset multiple, and turning to S10; s50, obtaining a rudder deflection angle corresponding to the zero pitching moment of the initial separated attitude of the aircraft, and taking the current rudder deflection angle as a preset rudder deflection angle of the aircraft; s60, performing separation simulation; s70, judging whether the aircraft meets the safety separation requirement, if so, completing separation of the aircraft and the boosting stage; otherwise, the angle of attack of the aircraft is adjusted and the flow goes to S10. The invention can solve the technical problems that the separation method in the prior art is not suitable for near-ground parallel interstage separation and cannot realize safe separation.

Description

Supersonic Near-Earth Parallel Interstage Separation Method with Preset Rudder Offset Feature

technical field

The invention relates to the technical field of electromagnetic booster launch near-earth supersonic inter-stage separation, in particular to a supersonic near-earth parallel inter-stage separation method with a preset rudder deviation feature.

Background technique

Electromagnetic launch is to use electromagnetic force to eliminate frictional resistance and vibration, and provide a strong acceleration capability to accelerate the aircraft (carrier aircraft/rocket, etc.) It is fast, easy to operate, maintain, and use ground facilities, low labor cost, and high reliability. It is an important technical approach for electromagnetic launch in the future and has broad application prospects.

According to the positional relationship between the aircraft and the skid car responsible for carrying the aircraft, electromagnetic emission is mainly divided into parallel type and serial type. Regardless of the form, there are complex flow unsteady/aerodynamic load problems in the combination of skid car and aircraft during high-speed operation near the ground. Relying on projects such as rocket sled test and electromagnetic ejection, foreign countries have carried out earlier researches on flow unsteady problems. When the speed reaches supersonic speed, a series of shock wave interference phenomena appear between the assembly and the ground, and the interference structure is greatly affected by the relative position/velocity/acceleration of the three. Therefore, the vehicle-booster stage exhibits obvious unsteady aerodynamic characteristics during the near-earth separation process. At the same time, since the near-Earth dynamic pressure environment is harsher than the traditional flight environment of the aircraft, it is very easy to cause the load of the aircraft to exceed the limit, causing serious problems such as the disintegration of the aircraft. The above problems have a significant impact on the safe separation of near-Earth supersonic speed.

In the existing separation methods, it can be mainly divided into active separation and passive separation. Ejection separation is a typical active separation. For example, plug-in ejection type, plug-in rail type, gravity drop type, submarine-launch type, and steam electromagnetic ejection are mostly used for airborne, high-altitude, light-weight or low-speed objects such as air-to-air missiles and carrier-based aircraft ejection. Passive separation is mainly represented by the way of aerodynamic free separation relying on the aerodynamic difference of its own components. For example, projectile/catapult support separation, rocket stage separation, and fairing two-lobed flat push separation, etc. Active/passive separation is used to varying degrees in serial/parallel environments.

The ejection type is mostly suitable for low-speed, light-weight, high-speed and high-altitude, and is not suitable for high-speed and heavy-load separation near the ground. The use of catapult separation poses a great challenge to the vertical structural strength of the ground booster stage/vehicle and the performance of the catapult, and there are safety risks, so it is almost difficult to achieve. In addition, due to the high mass of the catapult itself, more electromagnetic thrust is required for acceleration, and the requirements for ejection performance are strict, both of which bring negative economic benefits such as high research and development costs and long development cycles.

Passive free separation requires an accurate computational evaluation of the trajectory during separation. The accuracy of the aerodynamic force determines the safety margin of the separation, but there are large unsteady phenomena in the near-Earth stage, and it is impossible to give an accurate estimate of the state at any time, and there is a greater risk of separation failure. At the same time, due to the large separation torque, the head-up speed of the separation body is too fast, which may easily cause tail collision and rapid increase of the angle of attack, resulting in vertical overload exceeding the limit.

Contents of the invention

In order to solve the above technical problems, the present invention provides a supersonic near-earth parallel inter-stage separation method with preset rudder deviation characteristics, which can solve the problem that the separation method in the prior art is not suitable for near-earth parallel inter-stage separation and cannot achieve safety. Separation of technical issues.

According to one aspect of the present invention, a supersonic near-earth parallel inter-stage separation method with preset rudder deviation characteristics is provided, the method comprising:

S10. Select a plurality of different rudder deflection angles, and model combinations of aircraft and booster stages with different rudder deflection angles, to obtain a combination model of multiple aircraft and booster stages;

S20. Obtain the pitching moment of the aircraft at the initial separation attitude under different rudder angles based on the combined model of multiple aircraft and booster stages;

S30, judging whether there is a pitching moment of zero, if so, go to S50; otherwise, go to S40;

S40, increasing the rudder surface area of the aircraft by a preset multiple, and turning to S10;

S50. Obtain the rudder angle corresponding to when the pitching moment of the aircraft is separated from the initial attitude is zero, and use the current rudder angle as the preset rudder angle of the aircraft;

S60. Carry out separation simulation on the combination model of the aircraft with the preset rudder deflection angle and the booster stage, and obtain attitude information, force information and position information of the aircraft during the separation process;

S70. Judging whether the aircraft meets the safety separation requirements based on the attitude information, force information and position information of the aircraft during the separation process, if so, complete the separation of the aircraft and the booster stage; otherwise, adjust the angle of attack of the aircraft, and turn to to S10.

Preferably, in S20, obtaining the pitching moment of the aircraft under different rudder angles at the initial attitude of separation based on the combination model of multiple aircraft and the booster stage includes:

S21, using grid generation software to obtain the calculation grids of the combined models of multiple aircraft and booster stages;

S22. Using fluid simulation software to obtain discrete Navier-Stokes equations under each calculation grid;

S23. Obtain the pitching moment of the aircraft at the separation initial attitude under different rudder angles based on each Navier-Stokes equation.

Preferably, in S21, the calculation grid adopts an overlapping grid, a reconstructed grid or a sliding grid.

Preferably, in S21, the grid generation software adopts ICEM software or Pointwise software; in S22, the fluid simulation software adopts Fluent software or star CCM software.

Preferably, in S60, the combined model of the aircraft with the preset rudder deflection angle and the booster stage is separated and simulated, and the attitude information, force information and position information of the aircraft during the separation process are obtained, including:

S61. Obtain the flow field at the initial moment of the separation motion based on the Navier-Stokes equation of the combined model of the aircraft and the booster stage with a preset rudder deflection angle;

S62. On the basis of the flow field at the initial moment of the separation movement, the Navier-Stokes equation and the rigid body dynamics equation of the combined model of the aircraft and the booster stage with a preset rudder angle are used to pair The combined model of the aircraft with the preset rudder deflection angle and the booster stage is used for separation simulation, and the attitude information, force information and position information of the aircraft are obtained during the separation process.

Preferably, in S62, performing separate simulation on the combined model of the aircraft with the preset rudder deflection angle and the booster stage includes:

S621. After the locking device of the combined model of the aircraft with the preset rudder deflection angle and the booster stage receives a separation signal, the locking device is unlocked;

S622. The aircraft is completely separated from the booster stage. Under the action of its own aerodynamic force, its own gravity and the aerodynamic interference force of the booster stage, the aircraft performs six free movements around the center of mass until it breaks away from the aerodynamic interference of the booster stage, and the separation simulation is completed. .

Preferably, in S622, the aircraft is completely separated from the booster stage, and the aircraft performs six free motions around the center of mass under the action of its own aerodynamic force, its own gravity and the aerodynamic interference force of the booster stage until it breaks away from the aerodynamic force of the booster stage. Interference, to complete the separation simulation includes: the aircraft is completely separated from the booster stage, the aircraft performs six free movements around the center of mass under the action of its own aerodynamic force, its own gravity and the aerodynamic interference force of the booster stage, and at the same time adjusts the rudder deflection angle to Keep the pitching moment at zero until the aerodynamic interference of the booster stage is separated, and the separation simulation is completed.

Preferably, in S70, judging whether the aircraft meets the requirements for safe separation based on the attitude information, force information and position information of the aircraft during the separation process includes:

S71. Determine whether the heading angle, the pitch angle, and the roll angle in the attitude information are respectively smaller than the preset heading angle, the preset pitch angle, and the preset roll angle;

S72. Determine whether the force value in the force information is smaller than a preset force value;

S73. Obtain the separation distance between the aircraft and the booster stage based on the position information, and determine whether the separation distance is smaller than a preset separation safety distance;

S74. If both are yes, meet the safety separation requirement; otherwise, fail to meet the safety separation requirement.

Preferably, in S10, selecting a plurality of different rudder deflection angles includes: selecting a plurality of different rudder deflection angles at preset intervals within the range of the rudder deflection angle of the aircraft.

According to another aspect of the present invention, a computer device is provided, including a memory, a processor, and a computer program stored on the memory and operable on the processor. When the processor executes the computer program, any of the above-mentioned the method.

Applying the technical solution of the present invention, by selecting an appropriate rudder deflection angle in the early stage of separation, and presetting the rudder deflection angle, a certain balance moment is provided to avoid the tail of the aircraft from sinking and causing the tail to collide or rise, resulting in negative attack of the aircraft. At the same time, the static instability of the aircraft is reduced, and the attitude divergence speed during the separation process is slowed down. Compared with the prior art, the present invention has the following beneficial effects:

(1) Make full use of the effectiveness of the aircraft's own rudder surface, avoid the extra structural weight caused by the separation system, and ensure the payload of the aircraft;

(2) It not only effectively guarantees the separation stability of the ground booster stage-vehicle near-earth interference separation stage, but also ensures the stability of the flight attitude in the stage from the ground booster stage aerodynamic interference to the aircraft perigee ignition into orbit sex.

Description of drawings

The accompanying drawings are included to provide further understanding of the embodiments of the invention, and constitute a part of the specification, are used to illustrate the embodiments of the invention, and together with the description, explain the principle of the invention. Apparently, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can obtain other drawings according to these drawings without creative efforts.

Fig. 1 shows a flow chart of a supersonic near-earth parallel inter-stage separation method with preset rudder deviation characteristics provided according to an embodiment of the present invention;

Fig. 2 shows a schematic diagram of a combined model of an aircraft and a booster stage provided according to an embodiment of the present invention;

Fig. 3 shows a schematic partition diagram of an overlapping grid provided according to an embodiment of the present invention;

Fig. 4 shows a schematic diagram of the separation sequence of the aircraft and the booster stage according to an embodiment of the present invention;

Fig. 5 shows a schematic diagram of force on an aircraft provided according to an embodiment of the present invention;

Fig. 6a shows a pressure distribution diagram at separation time T=0.005s at Ma1.8 according to an embodiment of the present invention;

Fig. 6b shows a pressure distribution diagram at separation time T=0.030s at Ma1.8 according to an embodiment of the present invention;

Fig. 6c shows a pressure distribution diagram at separation time T=0.050s at Ma1.8 according to an embodiment of the present invention;

Fig. 6d shows a pressure distribution diagram at separation time T=0.070s at Ma1.8 according to an embodiment of the present invention.

Detailed ways

It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit the exemplary implementations according to the present application. As used herein, unless the context clearly dictates otherwise, the singular is intended to include the plural, and it should also be understood that when the terms "comprising" and/or "comprising" are used in this specification, they mean There are features, steps, operations, means, components and/or combinations thereof.

The relative arrangements of components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. At the same time, it should be understood that, for the convenience of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. Techniques, methods and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, such techniques, methods and devices should be considered part of the Authorized Specification. In all examples shown and discussed herein, any specific values should be construed as illustrative only, and not as limiting. Therefore, other examples of the exemplary embodiment may have different values. It should be noted that like numerals and letters denote like items in the following figures, therefore, once an item is defined in one figure, it does not require further discussion in subsequent figures.

As shown in Figure 1, the present invention provides a supersonic near-earth parallel inter-stage separation method with preset rudder deviation characteristics, the method comprising:

S10. Select a plurality of different rudder deflection angles, and model combinations of aircraft and booster stages with different rudder deflection angles, to obtain a combination model of multiple aircraft and booster stages;

S20. Obtain the pitching moment of the aircraft at the initial separation attitude under different rudder angles based on the combined model of multiple aircraft and booster stages;

S30, judging whether there is a pitching moment of zero, if so, go to S50; otherwise, go to S40;

S40, increasing the rudder surface area of the aircraft by a preset multiple, and turning to S10;

S50. Obtain the rudder angle corresponding to when the pitching moment of the aircraft is separated from the initial attitude is zero, and use the current rudder angle as the preset rudder angle of the aircraft;

S60. Carry out separation simulation on the combination model of the aircraft with the preset rudder deflection angle and the booster stage, and obtain attitude information, force information and position information of the aircraft during the separation process;

S70. Judging whether the aircraft meets the safety separation requirements based on the attitude information, force information and position information of the aircraft during the separation process, if so, complete the separation of the aircraft and the booster stage; otherwise, adjust the angle of attack of the aircraft, and turn to to S10.

The present invention provides a certain balance moment by selecting a suitable rudder deflection angle in the early stage of separation and presets the rudder deflection angle, so as to prevent the tail of the aircraft from colliding or rising due to the sinking of the tail and cause the aircraft to have a negative angle of attack, and at the same time reduce the The static instability of the aircraft slows down the attitude divergence speed during the separation process. Compared with the prior art, the present invention has the following beneficial effects:

(1) Make full use of the effectiveness of the aircraft's own rudder surface, avoid the extra structural weight caused by the separation system, and ensure the payload of the aircraft;

(2) It not only effectively guarantees the separation stability of the ground booster stage-vehicle near-earth interference separation stage, but also ensures the stability of the flight attitude in the stage from the ground booster stage aerodynamic interference to the aircraft perigee ignition into orbit sex.

In the present invention, the aircraft and the booster stage are connected in parallel through a locking device. As shown in FIG. 2 , the aircraft is arranged above the booster stage, so as to realize subsequent separation between parallel stages.

According to an embodiment of the present invention, in S10, selecting multiple different rudder deflection angles includes: selecting multiple different rudder deflection angles at preset intervals within the range of the rudder deflection angle of the aircraft.

For example, rudder deflection angles γ=-15°, -10°, -5°, 5°, 10°, and 15 can be selected for subsequent model construction.

According to an embodiment of the present invention, in S20, obtaining the pitching moment of the aircraft at the initial separation attitude under different rudder angles based on the combination model of multiple aircraft and the booster stage includes:

S21, using grid generation software to obtain the calculation grids of the combined models of multiple aircraft and booster stages;

Among them, the calculation grid can use overlapping grid, reconstruction grid or sliding grid; the grid generation software can use ICEM software or Pointwise software;

S22. Using fluid simulation software to obtain discrete Navier-Stokes equations under each calculation grid;

Among them, the fluid simulation software can use Fluent software or star CCM software;

S23. Obtain the pitching moment of the aircraft at the separation initial attitude under different rudder angles based on each Navier-Stokes equation.

According to an embodiment of the present invention, in S40, when enlarging the rudder surface area of the aircraft, the same multiple can be used each time to enlarge, or the original rudder surface area can be magnified according to 1.2, 1.5, 1.8, 2.0, 2.2 in sequence. , 2.5, 2.8 times... to zoom in.

According to an embodiment of the present invention, in S60, the combined model of the aircraft with the preset rudder angle and the booster stage is separated and simulated, and the attitude information, force information and information of the aircraft during the separation process are obtained. Location information includes:

S61. Obtain the flow field at the initial moment of the separation motion based on the Navier-Stokes equation of the combined model of the aircraft and the booster stage with a preset rudder deflection angle;

S62. On the basis of the flow field at the initial moment of the separation movement, the Navier-Stokes equation and the rigid body dynamics equation of the combined model of the aircraft and the booster stage with a preset rudder angle are used to pair The combined model of the aircraft with the preset rudder deflection angle and the booster stage is used for separation simulation, and the attitude information, force information and position information of the aircraft are obtained during the separation process.

According to an embodiment of the present invention, in S62, performing separate simulation on the combined model of the aircraft with the preset rudder angle and the booster stage includes:

S621. After the locking device of the combined model of the aircraft with the preset rudder deflection angle and the booster stage receives a separation signal, the locking device is unlocked;

Wherein, the separation signal may be an electrical signal or other types of signals;

S622. The aircraft is completely separated from the booster stage. Under the action of its own aerodynamic force, its own gravity and the aerodynamic interference force of the booster stage, the aircraft performs six free movements around the center of mass until it breaks away from the aerodynamic interference of the booster stage, and the separation simulation is completed. ; At this time, the booster stage decelerates under the action of ground electromagnetic braking force and aerodynamic force until it stops;

Among them, the rudder deflection angle is adjusted while the aircraft is separating to keep the pitching moment at zero until it breaks away from the aerodynamic interference of the booster stage to complete the separation simulation. By adjusting the rudder deflection angle in real time, the safety of separation is further improved.

According to an embodiment of the present invention, in S70, judging whether the aircraft meets the safe separation requirements based on the attitude information, force information and position information of the aircraft during the separation process includes:

S71. Determine whether the heading angle, the pitch angle, and the roll angle in the attitude information are respectively smaller than the preset heading angle, the preset pitch angle, and the preset roll angle;

S72. Determine whether the force value in the force information is smaller than a preset force value;

S73. Obtain the separation distance between the aircraft and the booster stage based on the position information, and determine whether the separation distance is smaller than a preset separation safety distance;

S74. If both are yes, meet the safety separation requirement; otherwise, fail to meet the safety separation requirement.

In order to have a further understanding of the present invention, the supersonic near-the-earth parallel inter-stage separation method with the preset rudder deviation feature of the present invention will be described in detail below with reference to FIGS. 1-6 .

In this embodiment, a supersonic near-earth parallel inter-stage separation method with preset rudder deviation characteristics is provided, the method includes:

Step 1. Select a plurality of rudder angles γ=-15°, -10°, -5°, 5°, 10°, and 15, and carry out the combination of aircraft and booster stage for each rudder angle respectively. Modeling to obtain a combined model of multiple aircraft and booster stages; wherein, the combined model of aircraft and booster stages is shown in Figure 2;

Step 2: Use the ICEM software to obtain the calculation grids of the combined models of multiple aircraft and booster stages; use the Fluent software to obtain the discrete form of the Navier-Stokes equations under each calculation grid; and based on each nanometer The Vie-Stokes equation obtains the pitching moment of the aircraft at the initial separation attitude under different rudder angles;

Step 3. The pitching moments corresponding to the above-mentioned rudder deflection angles are not zero. Therefore, the rudder surface area of the aircraft is increased to 1.2 times the original area (subsequent steps are 1.2, 1.5, 1.8, 2.0, 2.2 times the original rudder surface area , 2.5, 2.8... times to enlarge), and go to step 1 to re-model;

Step 4. When the rudder surface area of the aircraft is increased to twice the original area, and the preset rudder deflection angle γ=15°, the pitching moment is zero, which meets the design requirements of the rudder surface;

Step 5. Use ICEM software to obtain the overlapping grid of the combined model of the aircraft and the booster stage with the preset rudder angle, as shown in Figure 3; based on the combination of the aircraft with the preset rudder angle and the booster stage The Navier-Stokes equation of the model obtains the flow field at the initial moment of the separation movement; among them, the turbulence model of the flow field is the Stanκε model, and the boundary conditions are set as: the inlet is the Ma1.8 pressure far field, and the incoming flow velocity is the separation velocity , the outlet is a pressure outlet, and the ground is a non-slip wall;

Step 6. Use the following separation program to perform separation simulation on the combined model of the aircraft with the preset rudder deflection angle and the booster stage. The separation sequence of the simulation process is shown in Figure 4; and obtain the attitude of the aircraft during the separation process Information, force information and position information, the force situation of the aircraft is shown in Figure 5; in Figure 5, L represents the aerodynamic lift, D represents the aerodynamic drag, M represents the aerodynamic pitching moment around the center of mass C, and C represents the center of mass, Fx means propulsion force, Fy1 means first support force, Fy2 means second support force;

l为特征长度，一般取模型长度，V_∞为分离速度。本实施例中物理迭代时间步为/>

内迭代步数设定为20；Among them, the dynamic simulation unsteady settings are as follows: Calculate the characteristic time

l is the characteristic length, generally the model length, and V _∞ is the separation velocity. In this embodiment, the physical iteration time step is />

The number of inner iteration steps is set to 20;

The separation procedure is as follows:

Step 7. Based on the attitude information, force information and position information of the aircraft during the separation process, it is judged that the aircraft meets the safety separation requirements, and the separation of the aircraft and the booster stage is completed.

Fig. 6 shows a pressure distribution diagram at different separation moments under Ma1.8 provided according to an embodiment of the present invention. It can be seen from Fig. 6 that with the braking of the ground booster stage, under the influence of the nose-down moment generated by the preset rudder deflection angle, the pitch attitude of the aircraft does not change significantly, which effectively avoids the excessive angle of attack during separation. The resulting vertical overload exceeds the limit, which effectively increases the vertical safety distance between the stages, and realizes the supersonic near-earth safety separation of the aircraft and the ground booster stage.

The present invention is applicable to the near-surface parallel supersonic electromagnetic boosting separation environment, and adopting the method of the present invention can solve the following technical problems: First, it avoids the large mass of the separation object, and it is easy to cause damage to the aircraft/boosting stage structure by taking ejection. destructive impact; second, to avoid the separation process, the aerodynamic environment is harsher than the traditional separation environment, and the separation overload is relatively large, which is likely to cause damage to the aircraft structure; third, it avoids the main It is manifested as a small separation force and a large separation head-up moment or head-down moment, which may easily cause the tail of the aircraft to collide with the booster stage.

The present invention also provides a computer device, including a memory, a processor, and a computer program stored in the memory and operable on the processor, and the processor implements any one of the above-mentioned methods when executing the computer program.

In summary, the present invention provides a supersonic near-earth parallel inter-stage separation method with the feature of preset rudder deflection, which provides A certain balance moment can prevent the tail of the aircraft from sinking and causing the tail to collide or rise to cause the aircraft to have a negative angle of attack. At the same time, the static instability of the aircraft is reduced, and the attitude divergence speed during the separation process is slowed down. Compared with the prior art, the present invention has the following beneficial effects:

(1) Make full use of the effectiveness of the aircraft's own rudder surface, avoid the extra structural weight caused by the separation system, and ensure the payload of the aircraft;

(2) It not only effectively guarantees the separation stability of the ground booster stage-vehicle near-earth interference separation stage, but also ensures the stability of the flight attitude in the stage from the ground booster stage aerodynamic interference to the aircraft perigee ignition into orbit sex.

In the description of the present invention, it should be understood that orientation words such as "front, back, up, down, left, right", "horizontal, vertical, vertical, horizontal" and "top, bottom" etc. indicate the orientation Or positional relationship is generally based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description. In the absence of a contrary statement, these orientation words do not indicate or imply the device or element referred to. It must have a specific orientation or be constructed and operated in a specific orientation, so it should not be construed as limiting the protection scope of the present invention; the orientation words "inner and outer" refer to the inner and outer relative to the outline of each component itself.

For the convenience of description, spatially relative terms may be used here, such as "on ...", "over ...", "on the surface of ...", "above", etc., to describe the The spatial positional relationship between one device or feature shown and other devices or features. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, devices described as "above" or "above" other devices or configurations would then be oriented "beneath" or "above" the other devices or configurations. under other devices or configurations". Thus, the exemplary term "above" can encompass both an orientation of "above" and "beneath". The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptions used herein interpreted accordingly.

In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing corresponding components. To limit the protection scope of the present invention.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (10)

1. The supersonic near-earth parallel interstage separation method with the preset rudder deflection characteristics is characterized by comprising the following steps of:

s10, selecting a plurality of different rudder deflection angles, and respectively modeling a combination of the aircraft and the boosting stage with the different rudder deflection angles to obtain a combination model of the aircraft and the boosting stage;

s20, acquiring pitching moments of the aircraft in the separated initial postures under different rudder deflection angles based on a combined model of a plurality of aircraft and boosting stages;

s30, judging whether a zero pitching moment exists, if so, turning to S50; otherwise, go to S40;

s40, increasing the control surface area of the aircraft by a preset multiple, and turning to S10;

s50, obtaining a rudder deflection angle corresponding to the aircraft when the pitching moment of the separated initial attitude is zero, and taking the current rudder deflection angle as a preset rudder deflection angle of the aircraft;

s60, performing separation simulation on a combined model of the aircraft and the boosting stage with a preset rudder deflection angle, and acquiring attitude information, stress information and position information of the aircraft in the separation process;

s70, judging whether the aircraft meets the safety separation requirement or not based on the attitude information, the stress information and the position information of the aircraft in the separation process, and if so, completing separation of the aircraft and the boosting stage; otherwise, the angle of attack of the aircraft is adjusted and the flow goes to S10.

2. The method of claim 1, wherein in S20, obtaining pitch moments of the aircraft at the separated initial attitude based on the combined model of the plurality of aircraft and the boost stage at different rudder angles comprises:

s21, acquiring respective calculation grids of a plurality of combined models of the aircraft and the boosting stage by utilizing grid generation software;

s22, acquiring a Navier-Stokes equation of a discrete form under each calculation grid by using fluid simulation software;

s23, acquiring pitching moment of the aircraft in the separated initial attitude under different rudder deflection angles based on each Navier-Stokes equation.

3. The method according to claim 2, characterized in that in S21 the calculation grid is an overlapping grid, a reconstruction grid or a slipping grid.

4. A method according to any one of claims 1-3, wherein in S21, the grid generating software is implemented as ICEM software or Pointwise software; in S22, the fluid simulation software adopts Fluent software or starCCM software.

5. The method according to claim 1 or 2, wherein in S60, performing separation simulation on the combined model of the aircraft and the boosting stage having the preset rudder deflection angle, and acquiring attitude information, stress information, and position information of the aircraft during the separation process includes:

s61, acquiring a flow field at the initial moment of separation motion based on a Navier-Stokes equation of a combined model of an aircraft and a boosting stage with a preset rudder deflection angle;

s62, on the basis of a flow field at the initial moment of separation movement, separating and simulating the combined model of the aircraft with the preset rudder deflection angle and the boosting stage by using fluid simulation software based on a Navigator-Stokes equation and a rigid body dynamics equation of the combined model of the aircraft with the preset rudder deflection angle, and acquiring attitude information, stress information and position information of the aircraft in the separation process.

6. The method of claim 5, wherein in S62, performing a separation simulation on the combined model of the aircraft and the boost stage with the preset rudder deflection angle comprises:

s621, after a separation signal is received by a locking device of a combined model of the aircraft and the boosting stage with a preset rudder deflection angle, the locking device is unlocked;

s622, completely separating the aircraft from the boosting stage, enabling the aircraft to move around the mass center in six degrees of freedom under the action of self aerodynamic force, self gravity and pneumatic interference force of the boosting stage until the aircraft is separated from the pneumatic interference of the boosting stage, and completing separation simulation.

7. The method of claim 6, wherein in S622, the vehicle is completely separated from the boost stage, the vehicle is free to move six times about the center of mass under the action of its own aerodynamic force, its own gravity force, and the aerodynamic disturbance of the boost stage until the vehicle is free from the aerodynamic disturbance of the boost stage, and completing the separation simulation comprises: the aircraft is completely separated from the boosting stage, the aircraft does six-freedom motion around the mass center under the action of self aerodynamic force, self gravity and pneumatic interference force of the boosting stage, and rudder deflection angle adjustment is carried out simultaneously to keep pitching moment zero until the aircraft breaks away from the pneumatic interference of the boosting stage, so that separation simulation is completed.

8. The method of claim 1, wherein determining whether the vehicle meets the safety separation requirement based on the attitude information, the stress information, and the position information of the vehicle during the separation in S70 comprises:

s71, judging whether a course angle, a pitch angle and a roll angle in the attitude information are respectively smaller than a preset course angle, a preset pitch angle and a preset roll angle;

s72, judging whether the stress value in the stress information is smaller than a preset stress value;

s73, acquiring the separation distance between the aircraft and the boosting stage based on the position information, and judging whether the separation distance is smaller than a preset separation safety distance;

s74, if yes, meeting the safety separation requirement; otherwise, the safety separation requirement is not satisfied.

9. The method of claim 1, wherein selecting a plurality of different rudder deflection angles in S10 comprises: and selecting a plurality of different rudder deflection angles according to a preset interval in the range of the rudder deflection angle of the aircraft.

10. A computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the method of any of claims 1 to 9 when executing the computer program.

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