CN116266238A - Supersonic near-ground parallel interstage separation method with preset rudder deflection characteristics - Google Patents
Supersonic near-ground parallel interstage separation method with preset rudder deflection characteristics Download PDFInfo
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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
Technical Field
The invention relates to the technical field of electromagnetic boosting emission near-ground supersonic interstage separation, in particular to a supersonic near-ground parallel interstage separation method with preset rudder deflection characteristics.
Background
The electromagnetic emission is to utilize electromagnetic force to eliminate friction resistance and vibration, and provide strong accelerating ability, accelerate the craft (carrier-borne aircraft/rocket, etc.) to the separation speed near the ground, endow certain initial kinetic energy, have the characteristics of low emission cost, quick response, simple ground facility operation, maintenance, use, low manpower cost, high reliability, etc., and is an important technical approach of the future electromagnetic emission, and has wide application prospect.
Electromagnetic emission is mainly divided into parallel type and serial type according to the positional relationship between the aircraft and the sledge car in charge of carrying the aircraft. In either form, the combination of skid and aircraft presents a complex flow unsteady/aerodynamic loading problem during high speed operation near ground. The problems of unsteady flow are studied earlier by the foreign projects such as rocket sled test, electromagnetic ejection and the like. When the speed reaches supersonic speed, a series of shock wave interference phenomena occur between the combined body and the ground, and the interference structure is greatly influenced by the relative position/speed/acceleration of the combined body and the ground. Thus, the aircraft-boost stage exhibits significant unsteady aerodynamic characteristics during near-ground separation. Meanwhile, the near-ground dynamic pressure environment is worse than the traditional flight environment of the aircraft, so that the load of the aircraft is extremely easy to overrun, and the aircraft is easy to disassemble. The above problems have a significant impact on the safe separation of near-ground supersonic speeds.
In the existing separation mode, the separation mode mainly comprises active separation mode and passive separation mode. Catapulting is typically active. Such as externally hung catapulting, externally hung guide rails, gravity throwing type, submerged catapulting and steam electromagnetic catapulting are commonly used for airborne, high-altitude, light or low-speed objects such as air-to-air missiles, carrier-based aircraft catapulting and the like. Passive separation is mainly represented by pneumatic free separation by means of aerodynamic force difference of its own components. Such as projectile/sabot separation, rocket stage separation, fairing two-lobe translational separation, etc. Active/passive separation is employed in serial/parallel environments to varying degrees.
The ejection type device is mainly suitable for low-speed, light and high-speed high altitude, and is not suitable for ground-near high-speed heavy-load separation. The adoption of catapulting separation presents great challenges for the vertical structural strength of the ground boosting stage/the aircraft and the performance of the catapulting, presents safety risks and is hardly realized. In addition, because the catapult has large mass, more electromagnetic thrust is needed to accelerate, and the catapult has strict requirements on catapult performance, so that the catapult has the economic negative benefits of high research and development cost, long development period and the like.
Passive free separation requires accurate computational evaluation of the trajectories during separation. The accuracy degree of aerodynamic force determines the separation safety margin, but a larger unsteady phenomenon exists in the near-earth stage, accurate estimation under any moment state can not be given, and a larger separation failure risk exists. Meanwhile, as the separation moment is too large, the head lifting speed of the separation body is too high, and the vertical overload overrun is easily caused by the collision of the tail and the rapid increase of the attack angle.
Disclosure of Invention
In order to solve the technical problems, the invention provides a supersonic near-ground parallel interstage separation method with preset rudder deflection characteristics, which 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.
According to an aspect of the invention, there is provided a supersonic near-earth parallel interstage separation method with preset rudder deflection characteristics, the method comprising:
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.
Preferably, in S20, obtaining the pitching moment of the aircraft at the separated initial attitude under the different rudder deflection angles based on the combined model of the plurality of aircraft and the boosting stage includes:
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.
Preferably, in S21, the calculation grid is an overlapped grid, a reconstructed grid or a sliding grid.
Preferably, in S21, the mesh generation software is an ICEM software or a Pointwise software; in S22, the fluid simulation software adopts Fluent software or star CCM software.
Preferably, in S60, performing separation simulation on a combined model of an aircraft and a boost stage with a preset rudder deflection angle, and acquiring attitude information, stress information and position information of the aircraft in 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.
Preferably, in S62, performing a separation simulation on a combined model of an aircraft and a boost stage having a preset rudder deflection angle includes:
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.
Preferably, in S622, the vehicle is completely separated from the boosting stage, and the vehicle performs six-freedom motion around the centroid under the action of self aerodynamic force, self gravity and pneumatic interference force of the boosting stage until the vehicle is separated from the pneumatic interference of the boosting stage, and the separation simulation is completed, including: 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.
Preferably, in S70, determining whether the aircraft meets the safety separation requirement based on the attitude information, the stress information, and the position information of the aircraft during the separation process includes:
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.
Preferably, in S10, selecting a plurality of different rudder deflection angles includes: 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.
According to another aspect of the present invention there is provided a computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing any of the methods described above when executing the computer program.
By adopting the technical scheme, the proper rudder deflection angle is selected in the earlier stage of separation, and the preset rudder deflection angle is performed, so that a certain balance moment is provided, the situation that the aircraft is in a negative attack angle due to collision or rising of the tail part of the aircraft caused by sinking is avoided, meanwhile, the static instability of the aircraft is reduced, and the attitude divergence speed in the separation process is slowed down. Compared with the prior art, the invention has the following beneficial effects:
(1) The efficiency of the aircraft with the control surface is fully utilized, the extra structural weight generated by a separation system is avoided, and the effective load of the aircraft is ensured;
(2) The ground boosting stage-vehicle near-ground interference separation stage separation stability is effectively guaranteed, and the flight attitude stability at the stage from the pneumatic interference of the ground boosting stage to the position before the vehicle near-ground ignition and orbit is guaranteed.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 shows a flow chart of a supersonic near-earth parallel interstage separation method with preset rudder deflection features provided in accordance with one embodiment of the invention;
FIG. 2 shows a schematic diagram of a combined model of an aircraft and boost stage provided in accordance with an embodiment of the present invention;
FIG. 3 illustrates a partitioning schematic of an overlapping grid provided in accordance with one embodiment of the present invention;
FIG. 4 illustrates a schematic timing diagram of separation of an aircraft from a booster according to one embodiment of the invention;
FIG. 5 illustrates a schematic view of an aircraft stress provided in accordance with an embodiment of the present invention;
fig. 6a shows a pressure profile for separation time t=0.005 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6b shows a pressure profile for separation time t=0.030 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6c shows a pressure profile for separation time t=0.050 s at ma1.8 provided in accordance with one embodiment of the present invention;
fig. 6d shows a pressure profile for separation time t=0.070 s at ma1.8, provided in accordance with an embodiment of the invention.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in FIG. 1, 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, 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.
According to the invention, the proper rudder deflection angle is selected in the earlier stage of separation, and the preset rudder deflection angle is performed, so that a certain balance moment is provided, the situation that the aircraft is in a negative attack angle due to collision or rising of the tail of the aircraft caused by sinking is avoided, meanwhile, the static instability of the aircraft is reduced, and the attitude divergence speed in the separation process is slowed down. Compared with the prior art, the invention has the following beneficial effects:
(1) The efficiency of the aircraft with the control surface is fully utilized, the extra structural weight generated by a separation system is avoided, and the effective load of the aircraft is ensured;
(2) The ground boosting stage-vehicle near-ground interference separation stage separation stability is effectively guaranteed, and the flight attitude stability at the stage from the pneumatic interference of the ground boosting stage to the position before the vehicle near-ground ignition and orbit is guaranteed.
In the present invention, the vehicle and the boost stage are connected in parallel by the locking device, as shown in fig. 2, the vehicle is disposed above the boost stage, thereby achieving subsequent parallel inter-stage separation.
According to one embodiment of the present invention, in S10, selecting a plurality of different rudder deflection angles includes: 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.
For example, rudder deflection angles γ= -15 °, -10 °, -5 °, 10 °, 15 may be selected for subsequent model construction.
According to one embodiment of the present invention, in S20, obtaining pitch moments of the aircraft at the separated initial attitude at different rudder angles based on the combined model of the plurality of aircraft and the boost stage includes:
s21, acquiring respective calculation grids of a plurality of combined models of the aircraft and the boosting stage by utilizing grid generation software;
wherein, the calculation grid can adopt an overlapped grid, a reconstruction grid or a slippage grid; the grid generating software can adopt ICEM software or Pointwise software;
s22, acquiring a Navier-Stokes equation of a discrete form under each calculation grid by using fluid simulation software;
wherein, the fluid simulation software can adopt Fluent software or star CCM software;
s23, acquiring pitching moment of the aircraft in the separated initial attitude under different rudder deflection angles based on each Navier-Stokes equation.
According to one embodiment of the present invention, in S40, when the control surface area of the aircraft is amplified, the same multiple may be used each time, or the amplification may be sequentially performed according to 1.2, 1.5, 1.8, 2.0, 2.2, 2.5, and 2.8 times … … of the original control surface area.
According to one embodiment of the present invention, in S60, performing separation simulation on a combined model of an aircraft and a boost stage having a preset rudder deflection angle, and acquiring attitude information, stress information, and position information of the aircraft during separation 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.
In accordance with one embodiment of the present invention, in S62, performing a separation simulation on a combined model of an aircraft and a boost stage having a preset rudder deflection angle includes:
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;
wherein, the separation signal can adopt an electric signal or other types of signals;
s622, completely separating the aircraft from the boosting stage, enabling the aircraft to perform six-freedom movement around the mass center 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; at this time, the boosting stage decelerates under the action of the ground electromagnetic braking force and aerodynamic force until the boosting stage is stationary;
the rudder deflection angle is adjusted while the aircraft is separated, so that the pitching moment is kept to be zero until the aerodynamic interference of the boosting stage is separated, and the separation simulation is completed. The separation safety is further improved by adjusting the rudder deflection angle in real time.
According to one embodiment of the present invention, in S70, 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 process includes:
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.
For a further understanding of the present invention, the supersonic near-parallel interstage separation method with preset rudder deflection features of the present invention is described in detail below with reference to fig. 1-6.
In this embodiment, a supersonic near-earth parallel interstage separation method with preset rudder deflection characteristics is provided, and the method includes:
firstly, selecting a plurality of rudder deflection angles gamma= -15 degrees, -10 degrees, -5 degrees, 10 degrees and 15 degrees, and respectively modeling a combination body of the aircraft and the boosting stage of each rudder deflection angle to obtain a combination model of a plurality of aircraft and the boosting stage; wherein, the combined model of the aircraft and the boosting stage is shown in fig. 2;
step two, acquiring respective calculation grids of a plurality of combined models of the aircraft and the boosting stage by using ICEM software; acquiring a Navier-Stokes equation in a discrete form under each calculation grid by using Fluent software; acquiring pitching moment of the aircraft in the separated initial attitude under different rudder deflection angles based on each Navier-Stokes equation;
step three, the pitching moment corresponding to the rudder deflection angle is not zero, so that the control surface area of the aircraft is increased to 1.2 times of the original area (the aircraft is amplified sequentially according to 1.2, 1.5, 1.8, 2.0, 2.2, 2.5 and 2.8 and … … times of the original control surface area), and modeling is carried out again in the step one;
fourthly, when the control surface area of the aircraft is increased to 2 times of the original area and a preset rudder deflection angle gamma=15°, the pitching moment is zero, and the control surface design requirement is met;
step five, acquiring an overlapped grid of a combined model of the aircraft and the boosting stage with a preset rudder deflection angle by using ICEM software, wherein the overlapped grid is shown in figure 3; 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; wherein, the turbulence model of the flow field is a Stanκε model, and the boundary conditions are set as follows: the inlet is a Ma1.8 pressure far field, the incoming flow speed is a separation speed, the outlet is a pressure outlet, and the ground is a wall surface without sliding movement;
step six, adopting the following separation program to perform separation simulation on a combined model of the aircraft with a preset rudder deflection angle and a boosting stage, wherein the separation time sequence of the simulation process is shown in fig. 4; and acquiring attitude information, stress information and position information of the aircraft in the separation process, wherein the stress condition of the aircraft is shown in figure 5; in fig. 5, L denotes aerodynamic lift, D denotes aerodynamic drag, M denotes aerodynamic pitch moment around centroid C, C denotes centroid, fx denotes propulsive force, fy1 denotes first supporting force, and Fy2 denotes second supporting force;
wherein, the dynamic simulation is set as follows: calculating characteristic time
l is the characteristic length, the model length is generally taken, V ∞ Is the separation speed. In this embodiment the physical iteration time step is +.>
The number of inner iteration steps is set to 20;
the isolation procedure was as follows:
and step seven, judging that the aircraft meets the safety separation requirement based on the attitude information, the stress information and the position information of the aircraft in the separation process, and completing separation of the aircraft and the boosting stage.
Fig. 6 shows pressure profiles at different separation moments at ma1.8 provided according to an embodiment of the invention. As can be seen from fig. 6, with the ground boosting stage braking, the pitching attitude of the aircraft is not greatly changed under the influence of the low head moment generated by the preset rudder deflection angle, so that the vertical overload overrun caused by the overlarge attack angle during the separation period is effectively avoided, the inter-stage vertical safety distance is effectively improved, and the near-ground safety separation of the supersonic speed of the aircraft-ground boosting stage is realized.
The method is applicable to near-ground parallel supersonic electromagnetic boosting separation environments, and the following technical problems can be solved by adopting the method of the invention: firstly, the problem that the quality of a separated object is large is avoided, and the catapulting is easy to produce destructive influence on the aircraft/boosting stage structure; secondly, in the separation process, compared with the traditional separation environment, the pneumatic environment is avoided, the separation overload is large, and the structural damage of the aircraft is easy to cause; thirdly, the phenomenon that the aircraft mainly shows small separating force and large separating head-lifting moment or low head moment in the initial stage of near-ground supersonic speed separation is avoided, and collision between the tail of the aircraft and a boosting stage is easily caused.
The invention also provides a computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing any of the methods described above when executing the computer program.
In summary, the invention provides a supersonic near-ground parallel interstage separation method with preset rudder deflection characteristics, which provides a certain balance moment by selecting a proper rudder deflection angle in the earlier stage of separation and carrying out the preset rudder deflection angle, avoids the negative attack angle of the aircraft caused by collision or rising of the tail of the aircraft due to sinking, reduces the static instability of the aircraft, and slows down the attitude divergence speed in the separation process. Compared with the prior art, the invention has the following beneficial effects:
(1) The efficiency of the aircraft with the control surface is fully utilized, the extra structural weight generated by a separation system is avoided, and the effective load of the aircraft is ensured;
(2) The ground boosting stage-vehicle near-ground interference separation stage separation stability is effectively guaranteed, and the flight attitude stability at the stage from the pneumatic interference of the ground boosting stage to the position before the vehicle near-ground ignition and orbit is guaranteed.
In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present invention; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in 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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