CN114486158B - Quick pre-estimating method for initial throwing condition of separation compatibility of machine and bullet of embedded weapon - Google Patents
Quick pre-estimating method for initial throwing condition of separation compatibility of machine and bullet of embedded weapon Download PDFInfo
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a quick pre-estimating method for the initial throwing condition of the separation compatibility of a buried weapon machine bullet for a cavity-slender body, which mainly comprises the steps of firstly obtaining the aerodynamic lift and moment parameter expression of the missile moving outside a cabin based on the small disturbance theory of the slender body and establishing a movement equation of the separation of the buried missile machine bullet; then simplifying the missile separation motion equation of the embedded missile machine to deduce the approximate solution of the vertical displacement and pitch angle of the missile; finally, a judgment criterion of the separation compatibility of the embedded missile and the shell is provided, and an evaluation expression of the initial pitch angle speed and the vertical speed of the separation of the embedded missile is provided. The rapid evaluation method developed by the invention can provide reference for numerical simulation, wind tunnel experiments and other works in the initial stage of separation of the embedded missile machine, avoid blind input of initial throwing conditions, and has a certain value for related research in the field of separation dynamics of the embedded missile machine.
Description
Technical Field
The invention relates to a quick pre-estimating method for a separation compatible initial throwing condition of an embedded weapon machine bullet in an elongated rotation body layout, which can roughly guide the operations of numerical simulation, wind tunnel experiments and the like in an initial stage and belongs to the field of separation dynamics research of the embedded weapon machine bullet.
Background
The new generation advanced unmanned or manned fighter plane is generally configured with embedded weapons (most of air-to-air missiles in a slender spinning body layout), which can not only improve aerodynamic efficiency (such as reducing aerodynamic drag increase and radar scattering area caused by the externally hung weapons), but also improve maneuvering performance, cruising speed and survivability of the fighter plane.
When the embedded weapon is released, the embedded weapon can be regarded as typical cavity flow, and researches show that the cavity flow has unsteady flow phenomena such as boundary layer separation and reattachment, unstable shear layer, shock wave and shock wave interference and the like, and the compatibility of the embedded weapon release and separation is seriously influenced by the complex flow phenomena.
The separation of the embedded weapon from the cabin is a transient process, and reasonable initial delivery conditions (mainly initial vertical velocity and pitch angle velocity) are key parameters for determining whether the mechanical and elastic separation process is compatible. In the prior preparation work of numerical simulation or wind tunnel experiments, the initial throwing condition is generally unknown and is a parameter which needs to be input, so that scientific researchers can blindly input the initial throwing condition to perform numerical calculation or wind tunnel experiments, time is wasted, and scientific research cost is increased.
From the searched literature, the research on the evaluation method of the initial release condition of the separation compatibility of the embedded weapon machine and bullet of the slender body rotary body layout by students at home and abroad has not been carried out.
Disclosure of Invention
The invention aims to overcome the defects and provides a quick pre-estimating method for the initial throwing condition of the separation compatibility of the embedded weapon mechanical and elastic bodies of a cavity-slender body model, which mainly comprises the steps of firstly obtaining an aerodynamic lift force and moment parameter expression of the missile moving outside a cabin based on a slender body small disturbance theory and establishing an embedded missile mechanical and elastic separation motion equation; then simplifying the missile separation motion equation of the embedded missile machine to deduce the approximate solution of the vertical displacement and pitch angle of the missile; finally, a judgment criterion of the separation compatibility of the embedded missile and the shell is provided, and an evaluation expression of the initial pitch angle speed and the vertical speed of the separation of the embedded missile is provided. The rapid evaluation method can provide reference for numerical simulation, wind tunnel experiments and other works in the initial stage of separation of the embedded missile machine, avoids blind input of initial throwing conditions, and has profound significance for related research in the field of separation dynamics of the embedded missile machine.
In order to achieve the above purpose, the present invention provides the following technical solutions:
a quick pre-estimating method for initial release conditions of separation compatibility of a built-in weapon machine and bullet comprises the following steps:
s1, establishing an embedded missile separation motion equation based on aerodynamic lift and pitching moment when an embedded missile completely passes through a weapon hatch shear layer and moves in an extravehicular free flow field;
s2, simplifying and solving an embedded missile separation motion equation to obtain an expression of vertical displacement and pitch angle change along with time after the embedded missile is separated;
s3, establishing a judgment criterion of the separation compatibility of the embedded missile and obtaining an evaluation expression of the initial throwing pitch angle speed and the vertical speed of the separation of the embedded missile according to an expression of the vertical displacement and the pitch angle change along with time after the separation of the embedded missile and the judgment criterion of the separation compatibility of the embedded missile.
Further, in the step S1, the separation motion equation of the embedded missile is as follows:
wherein F and M are respectively aerodynamic lift force and pitching moment, ρ, of the embedded missile when moving outside the cabin ∞ To free incoming flow density, U ∞ V is the free incoming flow speed, omega is the missile pitching angle speed, theta is the missile pitching angle, l is the missile length, delta is the ratio of the maximum radius to the length of the missile, g 0 ,g 1 ……g 11 And h 0 ,h 1 ……h 11 Are parameters respectively related to the geometry of the embedded weapon bay.
Further, in the step S2, the expression of the vertical displacement and the pitch angle change with time after the separation of the embedded missile is as follows:
wherein b=lg 6 /|h 6 |，Z 0 And theta 0 Respectively the initial vertical displacement and pitch angle of the embedded missile machine for missile separation, t is time,i is pitch moment of inertia, g is gravitational acceleration, ω 0 And V 0 The initial pitch angle speed and the vertical speed of the separation of the embedded missile are respectively set.
Further, in the step S2, the specific method for simplifying and solving the separation motion equation of the embedded missile machine to obtain the expression of vertical displacement and pitch angle of the separation of the embedded missile machine is as follows:
s2.1 based on the free-flowing speed U ∞ And the relative size of the missile falling speed V, and main control items in a missile separation motion equation of the embedded missile are reserved:
s2.2, discarding the quadratic term in the expression obtained in the step S2.1 to obtain a two-degree-of-freedom expression of vertical displacement Z and pitch angle theta of the missile separation of the embedded missile:
wherein I is pitching moment of inertia, g is gravitational acceleration, and m is missile mass;
s2.3 reamAnd will initially drop the condition theta| t＝0 ＝θ 0 ,/>Substituted into the step S2.2And obtaining an expression of vertical displacement Z and pitch angle theta of the missile separation of the embedded missile in the two-degree-of-freedom expression.
Further, in the step S3, the criterion for separation compatibility of the embedded missile is established according to the condition for separation compatibility of the embedded missile provided by the overall design requirement.
Further, in the step S3, the criterion for separation compatibility of the embedded missile is:
t in separation process of embedded missile launcher c At moment, the pitch angle |theta| of the missile is less than or equal to theta c And the vertical displacement of the guided missile is equal to or more than Z c Wherein θ c At t c Critical pitch angle Z of missile separation compatible state at moment c At t c And critical vertical displacement in missile separation compatible state at any time.
Further, in the step S3, the vertical velocity V of the initial release of the embedded missile is separated 0 And pitch angle rate omega 0 The evaluation expression of (2) is:
wherein b=lg 6 /|h 6 |，ρ ∞ To free incoming flow density, U ∞ For free incoming flow speed, l is missile length, delta is the ratio of maximum radius to length of missile, h 6 And g 6 Is a parameter related to the geometry of the embedded weapon cabin, I is the moment of inertia of pitch, Z 0 And theta 0 And the initial vertical displacement and the pitch angle g are respectively the gravity acceleration of the initial throwing of the separation of the embedded missile.
Further, in the step S1, aerodynamic lift and pitching moment of the embedded missile when the embedded missile completely passes through the weapon hatch shear layer and moves in the free flow field outside the cabin are obtained according to the small disturbance theory of the slender body.
Compared with the prior art, the invention has at least one of the following beneficial effects:
(1) In the quick pre-estimating method of the initial throwing condition of the separation compatibility of the embedded weapon machine bullet, an embedded missile machine bullet separation motion equation is established according to the aerodynamic lift force and the pitching moment of the embedded missile machine bullet when the embedded missile machine bullet moves outside the cabin, and the assessment of the initial throwing pitch angle speed and the vertical speed of the separation of the embedded missile machine bullet is realized by combining with the judgment criterion of the separation compatibility of the embedded missile machine bullet, so that the method has important guiding significance on numerical simulation or early preparation work of wind tunnel experiments, and avoids the waste of time and labor cost;
(2) According to the quick prediction method, the embedded missile separation motion equation is reasonably simplified according to the motion characteristics of the embedded missile separation, and the evaluation efficiency is improved on the basis of ensuring the accuracy;
(3) The rapid prediction method and the obtained estimation expression of the initial pitching angle speed and the vertical speed of the separation of the embedded missile machine have universality, the related physical quantity is convenient to obtain, and the estimation process is convenient and rapid.
Drawings
FIG. 1 illustrates three motion phases of a buried missile separation.
FIG. 2 is a schematic diagram of a specific implementation procedure of a method for quickly predicting initial loading conditions of separation compatibility of a mechanical and elastic device of an embedded weapon;
FIG. 3 is a computational model of a cavity-elongated body used in example 1 of the present invention.
Detailed Description
The features and advantages of the present invention will become more apparent and clear from the following detailed description of the invention.
The word "exemplary" is used herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are illustrated in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The invention aims to provide a quick pre-estimating method for separation compatible initial throwing conditions of a built-in weapon machine bullet, which provides rough reference for evaluation works such as numerical simulation and wind tunnel experiments in an initial stage. The separation process of the embedded weapon machine bullet is divided into three movement stages (in a cabin, crossing a shear layer and outside the cabin), aerodynamic force and moment parameter expressions of the missile moving outside the cabin are firstly obtained based on a slender body small disturbance theory, and a movement equation of two degrees of freedom (vertical displacement and pitch angle) of the separation of the embedded weapon machine bullet is established; then simplifying the missile separation motion equation of the embedded missile machine to deduce the approximate solution of the vertical displacement and pitch angle of the missile; finally, a judgment criterion of separation compatibility of the embedded weapon machine and the embedded missile is provided, and an evaluation expression of initial pitch angle speed and vertical speed of the separation of the embedded missile is provided.
The process of the invention will be further described below with reference to the accompanying drawings:
the embedded missile separation process is divided into three stages by referring to the idea of shataev et al: stage I: movement of the missile in the flow field in the missile pod; stage II: the missile moves through the hatch shear layer; stage III: the missile passes completely through the weapon hatch shear layer and moves in the free flow field outside the cabin, as shown in fig. 1.
Referring to fig. 2, the method for quickly estimating the initial release condition of separation compatibility of the mechanical and elastic bodies of the embedded weapon according to the invention comprises the following specific steps:
step 1: based on the theory analysis of small disturbance of the slender body, the aerodynamic lift and pitching moment which act when the embedded missile moves outside the cabin (namely the stage III) are obtained, and based on Newton's second law, a motion equation with two degrees of freedom (vertical displacement Z and pitch angle theta) of the separation of the embedded missile is established, and the expression is as follows:
wherein: f and M are respectively aerodynamic lift force and pitching moment when the embedded missile moves outside the cabin, and ρ is ∞ And U ∞ The free incoming flow density and the speed are V is the missile falling speed, omega is the missile pitch angle speed, theta is the missile pitch angle, l is the missile length, delta is the ratio of the maximum radius of the missile to the length, g 0 ,g 1 ……g 11 And h 0 ,h 1 ……h 11 Is a parameter related to the geometry of the embedded weapon cabin, and the specific parameter expression is as follows: .
Wherein: q=0.5 a/D is a small amount, a is the elongate body diameter, is a function of the elongate body axial position x, x 0 And x e The distance between the head and tail of the missile and the mass center is D, and the height of the cavity is the height of the cavity.
Step 2: simplifying the separation motion equations (1) and (2) of the embedded missile and obtaining an approximate solution expression of the vertical displacement and the pitch angle in the separation process of the embedded missile. The method comprises the following specific steps:
step 2.1 due to the free incoming flow speed U outside the cabin of the embedded missile ∞ The missile falling speed V and the cabin outer free incoming flow speed U are relatively large ∞ Normal component U at missile surface ∞n The comparison is small, so that when the missile moves outside the embedded missile cabin, simplified processing can be performed, and main control items in expressions (1) and (2) are reserved:
(2) Discarding the quadratic term of the pitch angle in equation (3) to obtain the following two-degree-of-freedom equation of motion expression:
wherein: i is pitching moment of inertia, m is missile mass, g is gravitational acceleration.
(3) Order theAnd substituting the second term of equation (4) (a) into the first term yields a linear quadratic ordinary differential equation with respect to the pitch angle θ as:
(4) Solving a linear quadratic ordinary differential equation (5) and putting the initial putting condition theta| t＝0 ＝θ 0 ,Substituting, the vertical displacement Z and pitch angle theta expression of the missile falling can be obtained as follows:
wherein: b=lg 6 /|h 6 |，Z 0 And theta 0 Generally known.
And establishing a judgment criterion of the separation compatibility of the embedded missile machine and the bullet according to the separation compatibility condition of the embedded weapon machine and the bullet provided by the overall design requirement. Such as t of mechanical and elastic separation c Moment, the missile pitch angle is required: the theta is less than or equal to theta c Vertical displacement: z is not less than Z c In t c 、θ c And Z c Is a known quantity. Substituting the criterion conditions of separation compatibility of the embedded missile machine into (6) and (7)And (3) obtaining an expression of initial release conditions of the separation compatibility of the embedded missile machine and the missile:
the initial pitching angle speed omega required by the separation of the embedded missile is estimated by inequality (8) and (9) 0 And vertical velocity V 0 Is not limited in terms of the range of (a).
The physical quantities are all stage III: the missile passes completely through the weapon hatch shear layer and moves in the free flow field outside the cabin.
Example 1:
in this embodiment, the cavity-elongated body model shown in fig. 3 is adopted for evaluation calculation, and flow field parameters and quality characteristic parameters of the model can be seen in table 1; the criterion of compatibility of the built-in missile separation is as follows c Time=0.5, missile pitch angle is required: the theta is less than or equal to theta c =9°, vertical displacement: z is not less than Z c ＝2.5m；
TABLE 1 flow field and quality characterization parameters
| Parameters (parameters) | Value of |
| Missile length l/(m) | 3.85 |
| Missile mass m/(kg) | 156.8 |
| Moment of inertia I/(kg.m) 2 ) | 199.59 |
| Fly height H/(km) | 10 |
| Mach number M of flight ∞ | 2.0 |
| Cavity height D/(m) | 0.525 |
The expression of the initial release condition of the missile separation compatibility of the embedded missile obtained by the invention is as follows:
the initial throwing pitch angle speed omega required by the separation of the embedded missile launcher can be obtained 0 And vertical velocity V 0 The following are provided:
the invention has been described in detail in connection with the specific embodiments and exemplary examples thereof, but such description is not to be construed as limiting the invention. It will be understood by those skilled in the art that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, and these fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (6)
1. A quick pre-estimating method for initial release conditions of separation compatibility of a built-in weapon machine and bullet is characterized by comprising the following steps:
s1, establishing an embedded missile separation motion equation based on aerodynamic lift and pitching moment when an embedded missile completely passes through a weapon hatch shear layer and moves in an extravehicular free flow field;
s2, simplifying and solving an embedded missile separation motion equation to obtain an expression of vertical displacement and pitch angle change along with time after the embedded missile is separated;
s3, establishing a judgment criterion of the separation compatibility of the embedded missile and the missile, and obtaining an evaluation expression of the initial throwing pitch angle speed and the vertical speed of the separation of the embedded missile according to an expression of the vertical displacement and the pitch angle along with the time change after the separation of the embedded missile and the judgment criterion of the separation compatibility of the embedded missile;
in the step S3, the criterion for separation compatibility of the embedded missile is as follows:
t in separation process of embedded missile launcher c At moment, the pitch angle |theta| of the missile is less than or equal to theta c And the vertical displacement of the guided missile is equal to or more than Z c Wherein θ c At t c Critical pitch angle Z of missile separation compatible state at moment c At t c Critical vertical displacement in missile separation compatible state at any time;
in the step S3, the vertical velocity V of the initial throwing of the embedded missile is separated 0 And pitch angle rate omega 0 The evaluation expression of (2) is:
wherein b=lg 6 /|h 6 |，ρ ∞ To free incoming flow density, U ∞ For free incoming flow speed, l is missile length, delta is the ratio of maximum radius to length of missile, h 6 And g 6 Is a parameter related to the geometry of the embedded weapon cabin, I is the moment of inertia of pitch, Z 0 And theta 0 And the initial vertical displacement and the pitch angle g are respectively the gravity acceleration of the initial throwing of the separation of the embedded missile.
2. The method for quickly estimating the initial release condition of separation compatibility of the embedded weapon machine bullet according to claim 1, wherein in the step S1, the separation motion equation of the embedded missile machine bullet is as follows:
wherein F and M are respectively aerodynamic lift force and pitching moment, ρ, of the embedded missile when moving outside the cabin ∞ To free incoming flow density, U ∞ V is the free incoming flow speed, omega is the missile pitching angle speed, theta is the missile pitching angle, l is the missile length, delta is the ratio of the maximum radius to the length of the missile, g 0 ,g 1 ……g 11 And h 0 ,h 1 ……h 11 Are parameters respectively related to the geometry of the embedded weapon bay.
3. The method for quickly estimating the initial release condition of the separation compatibility of the embedded weapon machine bullet according to claim 2, wherein in the step S2, the expression of the vertical displacement Z and the pitch angle θ with time after the separation of the embedded missile machine bullet is as follows:
wherein b=lg 6 /|h 6 |，Z 0 And theta 0 Respectively the initial vertical displacement and pitch angle of the embedded missile machine for missile separation, t is time,i is pitch moment of inertia, g is gravitational acceleration, ω 0 And V 0 The initial pitch angle speed and the vertical speed of the separation of the embedded missile are respectively set.
4. The method for quickly estimating the initial release condition of the separation compatibility of the embedded weapon machine bullet according to claim 2 or 3, wherein in the step S2, the method for simplifying and solving the separation motion equation of the embedded missile machine bullet to obtain the expression of the vertical displacement and the pitch angle of the separation of the embedded missile machine bullet is as follows:
s2.1 based on the free-flowing speed U ∞ And the relative size of the missile falling speed V, and main control items in a missile separation motion equation of the embedded missile are reserved:
s2.2, discarding the quadratic term in the expression obtained in the step S2.1 to obtain a two-degree-of-freedom expression of vertical displacement Z and pitch angle theta of the missile separation of the embedded missile:
wherein I is pitching moment of inertia, g is gravitational acceleration, and m is missile mass;
s2.3 reamAnd will initially drop the condition theta| t＝0 ＝θ 0 ,/>Substituting the vertical displacement Z and the pitch angle theta of the embedded missile separation into the two-degree-of-freedom expression obtained in the step S2.2.
5. The method for quickly predicting the initial release condition of the separation compatibility of the embedded weapon machine bullet according to claim 1 or 3, wherein in the step S3, the criterion of the separation compatibility of the embedded missile machine bullet is established according to the separation compatibility condition of the embedded missile machine bullet provided by the overall design requirement.
6. The method for quickly predicting the initial release condition of the separation compatibility of the embedded weapon machine bullet according to claim 1, wherein in the step S1, the aerodynamic lift and the pitching moment of the embedded missile when the embedded missile completely passes through the weapon hatch shear layer and moves in the free flow field outside the cabin are obtained according to the small disturbance theory of the slender body.
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