CN114486158A - Quick estimation method for initial launching condition of separation compatibility of machine projectile of embedded weapon - Google Patents

Quick estimation method for initial launching condition of separation compatibility of machine projectile of embedded weapon Download PDF

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CN114486158A
CN114486158A CN202111651683.3A CN202111651683A CN114486158A CN 114486158 A CN114486158 A CN 114486158A CN 202111651683 A CN202111651683 A CN 202111651683A CN 114486158 A CN114486158 A CN 114486158A
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宋威
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China Academy of Aerospace Aerodynamics CAAA
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Abstract

The invention discloses a method for quickly estimating the missile separation compatible initial launching condition of an embedded weapon aiming at a cavity-slender body, which mainly comprises the following steps of firstly obtaining the pneumatic lifting force and moment parameter expression of the missile moving outside a cabin based on the small disturbance theory of the slender body, and establishing the motion equation of the missile separation of the embedded weapon; then simplifying the buried missile-missile separation motion equation, and deducing approximate solutions of vertical displacement and pitch angle of the missile; and finally, providing a judgment criterion for separation and compatibility of the buried missile and aircraft missile, and providing an evaluation expression of initial launching pitch angle speed and vertical speed of separation of the buried missile and aircraft missile. The rapid evaluation method developed by the invention can provide reference for numerical simulation, wind tunnel experiment and other work of the initial separation stage of the buried missile, avoids blind input of initial throwing conditions, and has certain value on related research in the field of buried weapon machine-bullet separation dynamics.

Description

Quick estimation method for initial launching condition of separation compatibility of machine projectile of embedded weapon
Technical Field
The invention relates to a method for quickly estimating initial launching conditions of machine-bullet separation compatibility of an embedded weapon in a long and thin rotating body layout, which can roughly guide the work of numerical simulation, wind tunnel experiment and the like in an initial stage and belongs to the field of research on machine-bullet separation dynamics of the embedded weapon.
Background
A new generation of advanced manned or unmanned fighter aircraft is generally provided with embedded weapons (mostly hollow missiles in a slender and rotary body layout), so that not only can the aerodynamic efficiency be improved (such as the increase of aerodynamic resistance and the radar scattering area caused by external weapons are reduced), but also the maneuvering performance, the cruising speed and the viability of the fighter aircraft can be improved.
The cavity flow can be regarded as typical cavity flow when the buried weapon is released, and researches show that the cavity flow has the unsteady flow phenomena of boundary layer separation and reattachment, shear layer instability, shock wave and shock wave interference and the like, and the complex flow phenomena seriously influence the compatible characteristic of the buried weapon release separation.
The release and separation of the buried weapon from the cabin is a transient process, and reasonable initial release conditions (mainly initial vertical velocity and pitch angle velocity) are key parameters for determining whether the separation process of the machine and the bomb is compatible. In the early preparation work of numerical simulation or wind tunnel experiment, the initial launching condition is generally unknown and is a parameter which must be input, so that scientific researchers can blindly input the initial launching condition to carry out numerical calculation or wind tunnel experiment, time is wasted, and scientific research cost is increased.
From the search literature, the research on the evaluation method of the internal weapon separation compatible initial throwing condition of the slender body rotation body layout by scholars at home and abroad has not been carried out.
Disclosure of Invention
The invention aims to overcome the defects and provides a method for quickly estimating the separation compatibility initial launching condition of the built-in weapon aircraft ammunition aiming at a cavity-slender body model, which mainly comprises the following steps of firstly obtaining the pneumatic lifting force and moment parameter expression of the missile moving outside a cabin based on the small perturbation theory of the slender body and establishing a separation motion equation of the built-in missile aircraft ammunition; then simplifying the buried missile-missile separation motion equation, and deducing approximate solutions of vertical displacement and pitch angle of the missile; and finally, providing a judgment criterion for separation and compatibility of the buried missile and aircraft missile, and providing an evaluation expression of initial launching pitch angle speed and vertical speed of separation of the buried missile and aircraft missile. The rapid evaluation method can provide reference for numerical simulation, wind tunnel experiment and other work of the initial separation stage of the buried missile, avoids blind input of initial throwing conditions, and has profound significance for relevant research in the field of buried weapon machine-projectile separation dynamics.
In order to achieve the above purpose, the invention provides the following technical scheme:
a quick estimation method for initial launching conditions of separation compatibility of a machine projectile of an embedded weapon comprises the following steps:
s1, establishing a missile-missile separation equation of the buried missile based on aerodynamic lift and pitching moment of the buried missile when the buried missile completely passes through a weapon hatch shear layer and moves in a free flow field outside a cabin;
s2, simplifying and solving an embedded missile separation motion equation to obtain an expression of time-varying vertical displacement and pitch angle after the embedded missile separation;
s3, establishing a criterion for judging the separation compatibility of the buried missile warplane, and obtaining an evaluation expression of the initial launching pitch angle speed and the vertical speed of the separation of the buried missile warplane according to the expression of the time variation of the vertical displacement and the pitch angle after the separation of the buried missile warplane and the criterion for judging the separation compatibility of the buried missile warplane.
Further, in step S1, the buried missile separation equation of motion is as follows:
Figure BDA0003446720860000021
Figure BDA0003446720860000022
wherein F and M are respectively the aerodynamic lift force and the pitching moment of the buried missile when moving outside the cabin, and rho∞For free incoming density, U∞Is the free incoming flow velocity, V is the missile falling velocity, omega is the missile pitch angle velocity, theta is the missile pitch angle, l is the missile length, delta is the missile maximum radius to length ratio, g0,g1……g11And h0,h1……h11Are parameters relating to the geometry of the buried weapons bay, respectively.
Further, in step S2, the expressions of the time-dependent vertical displacement and the pitch angle of the separated buried missile are as follows:
Figure BDA0003446720860000031
Figure BDA0003446720860000032
wherein B ═ lg6/|h6|，Z0And theta0The initial throwing vertical displacement and the pitch angle which are respectively the separation of the buried missile and the missile, t is time,
Figure BDA0003446720860000033
i is the pitching moment of inertia, g is the acceleration of gravity, omega0And V0The initial throwing pitch angle speed and the vertical speed of the separation of the embedded missile are respectively.
Further, in step S2, the method for obtaining the expressions of vertical displacement and pitch angle of separation of the buried missile is specifically as follows:
s2.1 based on free incoming flow velocity U∞And the relative size of the missile falling speed V, main control items in the buried missile separation equation of motion are reserved:
Figure BDA0003446720860000034
Figure BDA0003446720860000035
s2.2, abandoning the quadratic term in the expression obtained in the step S2.1, and obtaining a two-degree-of-freedom expression about the vertical displacement Z and the pitch angle theta of the separation of the embedded missile:
Figure BDA0003446720860000036
Figure BDA0003446720860000037
in the formula, I is pitching moment of inertia, g is gravity acceleration, and m is missile mass;
s2.3 order
Figure BDA0003446720860000038
And the initial charging condition theta ist＝0＝θ0,
Figure BDA0003446720860000039
And (5) substituting the two-degree-of-freedom expression obtained in the step (S2.2) to obtain expressions of vertical displacement Z and pitch angle theta for separation of the embedded missile and missile.
Further, in step S3, a criterion for determining separation compatibility of the missile of the buried missile is established according to the separation compatibility condition of the missile of the buried missile provided by the overall design requirement.
Further, in step S3, the criterion for determining the compatibility of separation of the missile from the buried missile is as follows:
t in separation process of buried missilecAt the moment, the missile pitch angle theta is less than or equal to thetacAnd the missile vertical displacement | Z | ≧ Z |cWherein, thetacIs tcCritical pitch angle, Z, at a moment in the missile-missile separation compatible statecIs tcThe critical vertical displacement of the missile-missile separation compatible state is at the moment.
Further, in the step S3, the buried missile separates the initial launching vertical velocity V0And pitch angle velocity ω0The evaluation expression of (1) is:
Figure BDA0003446720860000041
Figure BDA0003446720860000042
wherein B ═ lg6/|h6|，
Figure BDA0003446720860000043
ρ∞For free incoming density, U∞Is free incoming flowSpeed, l is the missile length, delta is the missile maximum radius to length ratio, h6And g6I is the pitch moment of inertia, Z for parameters related to the geometry of the buried weapons bay0And theta0The initial throwing vertical displacement and the pitching angle of the separation of the embedded missile are respectively, and g is the gravity acceleration.
Further, in the step S1, the aerodynamic lift and the pitching moment of the buried missile when the buried missile completely passes through the weapon hatch shear layer and moves in the extravehicular free flow field are obtained according to the slender body small disturbance theory.
Compared with the prior art, the invention has at least one of the following beneficial effects:
(1) according to the method for quickly estimating the initial launching condition of the separation compatibility of the machine and the bomb of the buried weapon, a separation motion equation of the machine and the bomb of the buried missile is established according to the aerodynamic lift force and the pitching moment of the buried missile when the buried missile moves outside the cabin, and the evaluation of the pitch angle speed and the vertical speed of the initial launching of the separation of the machine and the bomb of the buried missile is realized by combining the judgment criterion of the separation compatibility of the machine and the bomb of the buried missile, so that the method has important guiding significance on numerical simulation or early preparation work of a wind tunnel experiment, and avoids the waste of time and labor cost;
(2) according to the rapid estimation method, the embedded missile separation motion equation is reasonably simplified according to the motion characteristics of the embedded missile separation, and the estimation efficiency is improved on the basis of ensuring the accuracy;
(3) the quick estimation method and the obtained estimation expression of the initial launching pitch angle speed and the vertical speed of the separation of the machine and the missile of the buried missile have universality, the related physical quantity is convenient to obtain, and the estimation process is convenient and quick.
Drawings
Fig. 1 shows three motion stages of separation of an embedded missile.
FIG. 2 is a diagram illustrating the steps of the method for quickly estimating the initial launching conditions for the separation and compatibility of the machine and the cartridge of the buried weapon;
figure 3 is a computational model of the 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 appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively 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. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The invention aims to provide a quick estimation method for the initial launching condition of the separation compatibility of the machine and the bomb of an embedded weapon, which provides rough reference for the evaluation work of numerical simulation, wind tunnel experiment and the like in the initial stage. The separation process of the embedded weapon aircraft ammunition is divided into three motion stages (in a cabin, across a shear layer and outside the cabin), firstly, a pneumatic force and moment parameter expression of the missile moving outside the cabin is obtained based on a slender body small disturbance theory, and a motion equation of two degrees of freedom (vertical displacement and pitch angle) for separating the embedded weapon aircraft ammunition is established; then simplifying the buried missile-missile separation motion equation, and deducing approximate solutions of vertical displacement and pitch angle of the missile; and finally, providing a judgment criterion for separation compatibility of the buried weapon aircraft ammunition, and providing an evaluation expression of initial launching pitch angle speed and vertical speed of separation of the buried weapon aircraft ammunition.
The process of the present invention will be further described with reference to the accompanying drawings:
referring to the concepts of Shalaev et al, the buried missile separation process is divided into three stages: stage I: the movement of the missile in the flow field in the missile cabin; stage II: the missile moves through the hatch shear layer; and stage III: the missile completely crossed the weapon hatch shear layer and moved in the extravehicular free flow field as shown in fig. 1.
Referring to fig. 2, the method for quickly estimating the initial launching condition for the separation compatibility of the machine and the cartridge of the buried weapon comprises the following specific steps:
step 1: the aerodynamic lift force and the pitching moment acting on the buried missile during the outboard movement (namely the stage III) are obtained based on the analysis of the slender body small disturbance theory, and a two-degree-of-freedom (vertical displacement Z and pitching angle theta) motion equation for the separation of the buried missile and the missile is established based on the Newton's second law, wherein the expression is as follows:
Figure BDA0003446720860000061
Figure BDA0003446720860000062
in the formula: f and M are respectively the aerodynamic lift force and the pitching moment of the buried missile when moving outside the cabin, and rho∞And U∞V is the falling speed of the missile, omega is the pitch angle speed of the missile, theta is the pitch angle of the missile, l is the length of the missile, delta is the ratio of the maximum radius to the length of the missile, g0,g1……g11And h0,h1……h11The parameters are respectively related to the geometric shape of the buried weapon bay, and the specific parameter expression is as follows: .
Figure BDA0003446720860000063
Figure BDA0003446720860000064
Figure BDA0003446720860000065
Figure BDA0003446720860000066
Figure BDA0003446720860000067
Figure BDA0003446720860000068
Figure BDA0003446720860000069
Figure BDA00034467208600000610
Figure BDA00034467208600000611
Figure BDA0003446720860000071
Figure BDA0003446720860000072
Figure BDA0003446720860000073
Figure BDA0003446720860000074
Figure BDA0003446720860000075
Figure BDA0003446720860000076
Figure BDA0003446720860000077
Figure BDA0003446720860000078
Figure BDA0003446720860000079
Figure BDA00034467208600000710
Figure BDA00034467208600000711
Figure BDA00034467208600000712
Figure BDA00034467208600000713
Figure BDA00034467208600000714
In the formula: q-0.5 a/D is a small quantity, a is the diameter of the elongated body and is a function of the axial position x of the elongated body, x0And xeThe distance between the head and the tail of the missile and the center of mass, and D is the height of the cavity.
Step 2: simplifying the buried missile separation motion equations (1) and (2) to obtain approximate solution expressions of vertical displacement and pitch angle in the buried missile separation process. The method comprises the following specific steps:
step 2.1 since the buried missile is outside the cabin free stream velocity U∞Relatively large, missile falling speed V and extravehicular free incoming flow speed U∞Normal component U at missile surface∞nCompared with the small amount, therefore, when the missile moves outside the cabin of the buried missile, simplified treatment can be carried outThe main control items in expressions (1) and (2) are retained:
Figure BDA0003446720860000081
(2) discarding the quadratic term of the pitch angle in equation (3) can obtain the following two-degree-of-freedom motion equation expression:
Figure BDA0003446720860000082
in the formula: i is pitching moment of inertia, m is missile mass, and g is gravity acceleration.
(3) Order to
Figure BDA0003446720860000083
And 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:
Figure BDA0003446720860000084
(4) solving a linear quadratic ordinary differential equation (5), and enabling the initial charging condition theta to be non-zerot＝0＝θ0,
Figure BDA0003446720860000085
Substituting, the expressions of the vertical displacement Z and the pitch angle theta of the falling missile are obtained as follows:
Figure BDA0003446720860000086
Figure BDA0003446720860000087
in the formula: b ═ lg6/|h6|，Z0And theta0Are generally known.
And establishing a criterion for judging the separation compatibility of the buried weapon projectile according to the separation compatibility condition of the buried weapon projectile proposed by the general design requirements. E.g. t at separation of bombcMoment, required missile pitch angle: theta is less than or equal to thetacAnd vertical displacement: z | ≧ ZcIn the formula, tc、θcAnd ZcIn known amounts. Substituting the judgment criterion conditions of the separation compatibility of the buried missile warplane into the judgment criterion conditions (6) and (7) to obtain an expression of the initial launching condition of the separation compatibility of the buried missile warplane:
Figure BDA0003446720860000091
Figure BDA0003446720860000092
the initial launching pitch angle speed omega required by the separation of the buried missile can be estimated by inequalities (8) and (9)0And a vertical velocity V0In (c) is used.
The above physical quantities are all stage III: physical quantity when the missile completely passes through a weapon hatch shear layer and moves in an extravehicular free flow field.
Example 1:
in this embodiment, the cavity-elongated body model shown in fig. 3 is used for evaluation and calculation, and the flow field parameters and the quality characteristic parameters of the model are shown in table 1; the criterion for the compatibility of separation of the missile and the embedded missile is, for example, t of separation of the missile and the embedded missilecAnd (5) requiring missile pitch angle at 0.5 moment: theta is less than or equal to thetac9 °, vertical displacement: z | ≧ Zc＝2.5m；
TABLE 1 flow field and Mass characterization parameters
Parameter(s) Value of
Missile length l/(m) 3.85
Missile mass m/(kg) 156.8
Pitching moment of inertia I/(kg m)2) 199.59
Flying height H/(km) 10
Flight Mach number M∞ 2.0
Cavity height D/(m) 0.525
According to the expression of the embedded missile separation compatible initial launching condition obtained by the invention:
Figure BDA0003446720860000093
Figure BDA0003446720860000094
the initial throwing pitch angle speed omega required by the separation of the buried missile can be obtained0And a vertical velocity V0The following were used:
Figure BDA0003446720860000095
the invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the embodiments and implementations of the invention without departing from the spirit and scope of the invention, and are within the scope of the invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.

Claims (8)

1. A quick estimation method for initial launching conditions of separation compatibility of a machine projectile of an embedded weapon is characterized by comprising the following steps:
s1, establishing a missile-missile separation equation of the buried missile based on aerodynamic lift and pitching moment of the buried missile when the buried missile completely passes through a weapon hatch shear layer and moves in a free flow field outside a cabin;
s2, simplifying and solving an embedded missile separation motion equation to obtain an expression of time-varying vertical displacement and pitch angle after the embedded missile separation;
s3, establishing a criterion for judging the separation compatibility of the buried missile warplane, and obtaining an evaluation expression of the initial launching pitch angle speed and the vertical speed of the separation of the buried missile warplane according to the expression of the time variation of the vertical displacement and the pitch angle after the separation of the buried missile warplane and the criterion for judging the separation compatibility of the buried missile warplane.
2. The method for rapidly estimating the separation-compatible initial launching condition of the buried weapon aircraft and the bomb according to claim 1, wherein in the step S1, the separation equation of motion of the buried weapon aircraft and the bomb is as follows:
Figure FDA0003446720850000011
Figure FDA0003446720850000012
wherein F and M are respectively the aerodynamic lift force and the pitching moment of the buried missile when moving outside the cabin, and rho∞For free incoming density, U∞Is the free incoming flow velocity, V is the missile falling velocity, omega is the missile pitch angle velocity, theta is the missile pitch angle, l is the missile length, delta is the missile maximum radius to length ratio, g0,g1……g11And h0,h1……h11Are parameters relating to the geometry of the buried weapons bay, respectively.
3. The method for rapidly estimating the separation-compatible initial launching condition of the buried weapon aircraft ammunition according to claim 2, wherein in the step S2, the vertical displacement Z and the pitch angle θ of the separated buried weapon aircraft ammunition are expressed as follows along with the time variation:
Figure FDA0003446720850000013
Figure FDA0003446720850000021
wherein B ═ lg6/|h6|，Z0And theta0The initial throwing vertical displacement and the pitch angle which are respectively the separation of the buried missile and the missile, t is time,
Figure FDA0003446720850000022
i is the pitching moment of inertia, g is the acceleration of gravity, omega0And V0The initial throwing pitch angle speed and the vertical speed of the separation of the embedded missile are respectively.
4. The method for rapidly estimating the separation-compatible initial launching condition of the buried weapon aircraft ammunition according to claim 2 or 3, wherein in the step S2, the buried missile aircraft ammunition separation motion equation is simplified and solved, and the specific method for obtaining the expressions of the vertical displacement and the pitch angle of the separation of the buried missile aircraft ammunition is as follows:
s2.1 based on free incoming flow velocity U∞And the relative size of the missile falling speed V, main control items in the buried missile separation equation of motion are reserved:
Figure FDA0003446720850000023
Figure FDA0003446720850000024
s2.2, abandoning the quadratic term in the expression obtained in the step S2.1 to obtain a two-degree-of-freedom expression about the vertical displacement Z and the pitch angle theta for separating the buried missile:
Figure FDA0003446720850000025
Figure FDA0003446720850000026
in the formula, I is pitching moment of inertia, g is gravity acceleration, and m is missile mass;
s2.3 order
Figure FDA0003446720850000027
And the initial charging condition theta ist＝0＝θ0,
Figure FDA0003446720850000028
And (5) substituting the two-degree-of-freedom expression obtained in the step (S2.2) to obtain expressions of vertical displacement Z and pitch angle theta for separation of the embedded missile and missile.
5. The method for rapidly estimating the separation compatibility initial delivery condition of the buried weapon aircraft missile according to the claim 1 or the claim 3, wherein in the step S3, the criterion for the separation compatibility of the aircraft missile is established according to the separation compatibility condition of the aircraft missile proposed by the general design requirements.
6. The method for rapidly estimating the separation-compatible initial delivery condition of the missile of claim 5, wherein in step S3, the separation-compatible decision criteria of the missile are as follows:
t in separation process of buried missilecAt the moment, the missile pitch angle theta is less than or equal to thetacAnd the missile vertical displacement | Z | ≧ Z |cWherein, thetacIs tcCritical pitch angle, Z, at a moment in the missile-missile separation compatible statecIs tcThe critical vertical displacement of the missile-missile separation compatible state is at the moment.
7. The method for rapidly estimating the separation-compatible initial launching condition of the buried weapon aircraft ammunition according to claim 6, wherein in the step S3, the separation-initial launching vertical velocity V of the buried weapon aircraft ammunition0And pitch angle velocity ω0The evaluation expression of (1) is:
Figure FDA0003446720850000031
Figure FDA0003446720850000032
wherein B ═ lg6/|h6|，
Figure FDA0003446720850000033
ρ∞For free incoming density, U∞For free incoming flow velocity, l is guideThe length of the missile, delta is the ratio of the maximum radius to the length of the missile, h6And g6I is the pitch moment of inertia, Z for parameters related to the geometry of the buried weapons bay0And theta0The initial throwing vertical displacement and the pitching angle of the separation of the embedded missile are respectively, and g is the gravity acceleration.
8. The method for rapidly estimating the separation compatibility initial launching condition of the buried weapon aircraft ammunition according to claim 1, wherein in the step S1, the aerodynamic lift force and pitching moment of the buried missile when completely crossing the shearing layer of the weapon hatch and moving in the extravehicular free flow field are obtained according to the slender body perturbation theory.
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118484028A (en) * 2024-07-16 2024-08-13 中国空气动力研究与发展中心计算空气动力研究所 Control method for mechanical-elastic separation compatibility based on preset rudder deflection

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109238636A (en) * 2018-10-30 2019-01-18 中国航天空气动力技术研究院 A kind of stage separation wind tunnel free flight test model separation trace predicating method
CN110398340A (en) * 2019-06-28 2019-11-01 中国航天空气动力技术研究院 The simplified wind tunnel test parameter determination method of the class wind tunnel free flight test law of similitude is separated based on launching
CN110610065A (en) * 2019-10-31 2019-12-24 中电工业互联网有限公司 Aircraft multi-body separation CFD simulation method and system based on hybrid dynamic grid technology
CN111964861A (en) * 2020-07-15 2020-11-20 中国航天空气动力技术研究院 Experimental device for compensating insufficient vertical acceleration of light model method
CN111964862A (en) * 2020-07-20 2020-11-20 中国航天空气动力技术研究院 Similar wind tunnel test method for separation dynamics of machine and projectile
CN112629815A (en) * 2020-12-10 2021-04-09 中国航天空气动力技术研究院 Series-parallel multi-degree-of-freedom machine-projectile separation trajectory capture test system
WO2021098886A1 (en) * 2019-11-19 2021-05-27 蓝箭航天空间科技股份有限公司 Pitching moment coefficient and center-of-pressure coefficient correction method for rocket projectile, and storage medium

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109238636A (en) * 2018-10-30 2019-01-18 中国航天空气动力技术研究院 A kind of stage separation wind tunnel free flight test model separation trace predicating method
CN110398340A (en) * 2019-06-28 2019-11-01 中国航天空气动力技术研究院 The simplified wind tunnel test parameter determination method of the class wind tunnel free flight test law of similitude is separated based on launching
CN110610065A (en) * 2019-10-31 2019-12-24 中电工业互联网有限公司 Aircraft multi-body separation CFD simulation method and system based on hybrid dynamic grid technology
WO2021098886A1 (en) * 2019-11-19 2021-05-27 蓝箭航天空间科技股份有限公司 Pitching moment coefficient and center-of-pressure coefficient correction method for rocket projectile, and storage medium
CN111964861A (en) * 2020-07-15 2020-11-20 中国航天空气动力技术研究院 Experimental device for compensating insufficient vertical acceleration of light model method
CN111964862A (en) * 2020-07-20 2020-11-20 中国航天空气动力技术研究院 Similar wind tunnel test method for separation dynamics of machine and projectile
CN112629815A (en) * 2020-12-10 2021-04-09 中国航天空气动力技术研究院 Series-parallel multi-degree-of-freedom machine-projectile separation trajectory capture test system

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
李菁;陈帮;胡俊香;: "三维内埋式航弹与载机分离非定常流场数值模拟", 兵器装备工程学报, no. 04, pages 125 - 129 *
雷娟棉;牛健平;王锁柱;周奇;: "初始分离条件对航弹与载机分离安全性影响的数值模拟研究", 兵工学报, no. 02, pages 357 - 366 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118484028A (en) * 2024-07-16 2024-08-13 中国空气动力研究与发展中心计算空气动力研究所 Control method for mechanical-elastic separation compatibility based on preset rudder deflection

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