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Effectiveness-Oriented Missile Weapon System Design Method Based on Performance Index

A system design and missile weapon technology, applied in the direction of weapon types, guidance methods, weapon accessories, etc., can solve the problem of lack of accurate description of performance indicators and efficiency indicators, and achieve the effect of saving manpower and material resources

Active Publication Date: 2017-06-13
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the current problem of lacking an accurate description of the relationship between the performance index and the effectiveness index, and propose a performance-oriented missile weapon system design method based on the performance index

Method used

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  • Effectiveness-Oriented Missile Weapon System Design Method Based on Performance Index

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specific Embodiment approach 1

[0047] The efficiency-oriented missile weapon system design method based on the performance index of this embodiment, combined with figure 1 Shown flow chart, described method is realized through the following steps:

[0048] Step 1. Determine the components of performance indicators, including: overall ballistic flight indicators, fragmentation warhead system, propulsion system, projectile shape and aerodynamic layout, and ballistic guidance and control system; among them,

[0049] The overall performance index of ballistic flight, including: range, flight speed, altitude, required overload, available overload, and maximum flight time;

[0050] Fragmentation warhead system performance indicators, including: fragmentation initial velocity, fragmentation angle, fragmentation direction angle, total number of fragments, unconditional killing radius, power radius;

[0051] Propulsion system performance indicators, including: working time, total impulse, thrust, specific impulse, ...

specific Embodiment approach 2

[0072] The difference from Embodiment 1 is that in the design method of the effectiveness-oriented missile weapon system based on performance indicators in this embodiment, the design process of the combat part system in Step 3 involves the quantity of the fragment killing combat part, wherein the quantity of the fragment killing combat part also includes Fragment initial velocity and fragment flying direction angle,

[0073] Fragment initial velocity is v 0 said, v 0 The calculation formula is:

[0074]

[0075] In the formula, Q e Indicates the detonation heat of explosives, the unit is J / kg;

[0076] m f Indicates the mass of the shell used for blasting to form fragments;

[0077] m e Indicates the charge quality;

[0078] like Figure 14 As shown, the fragment scattering direction angle refers to the average scattering direction of the fragment group; the fragment scattering direction angle is represented by φ 0 Indicates that it is equal to the angle between t...

specific Embodiment approach 4

[0093] The difference from the third specific embodiment is that in the design method of the effectiveness-oriented missile weapon system based on performance indicators in this embodiment, the shape and aerodynamic layout of the missile body described in step 1 are reflected in the missile wing area, hinge moment, static stability and The control efficiency of the rudder surface; through the control of the missile wing area, hinge moment, static stability and control efficiency of the rudder surface, the process of adjusting the shape of the missile body and the aerodynamic layout is as follows:

[0094] First, the missile wing area mainly depends on the requirements for missile maneuverability. The missile mobility is represented by the available overload of the missile. Then the correlation between the missile wing area and the available overload of the missile is:

[0095]

[0096] In the formula, q represents the flight dynamic pressure, v represents the flight speed ...

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Abstract

The invention discloses a missile weapon system design method aiming at efficiency on the basis of performance indexes, relates to the field of missile weapon system overall design and aims to solve the problem that the relation of the performance indexes and efficiency indexes is not accurately described in the existing missile weapon system design process. The missile weapon system design method aiming at the efficiency on the basis of the performance indexes definitely comprises the performance indexes of a fragment killing combating part, a propulsion system, a missile body shape, aerodynamic layout, the trajectory guidance control capacity and definitely comprises the efficiency indexes of the defense penetration capacity, the damage capacity, the hit probability, the survivability, the maneuvering capacity, the anti-interference capacity, the maintainability and the reliability; and finally the relation of components of the performance indexes and components of the efficiency indexes is built, and missile overall design is carried out. By means of the missile weapon system design method, the efficiency indexes of a missile are improved overall, so that the actual combat capacity of the missile achieves the best.

Description

technical field [0001] The invention relates to an efficiency-oriented missile weapon system design method based on performance indicators; Background technique [0002] The design of traditional missile weapon systems is mainly a serial design method for performance; such a method is not only inefficient, but also its design purpose is only to improve the performance index of the missile. Obviously, such a design method can no longer meet the increasingly stringent requirements of the current stage operational requirements; if the missile design needs to be improved because it cannot meet the mission requirements, the designer must start from the original performance index to revise the design again, which consumes both time and manpower; [0003] In order to better meet the requirements of high-tech warfare, it is necessary to use an efficiency-oriented design method for design; Contents of the invention [0004] The purpose of the present invention is to solve the curr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F41G3/32F42B15/01G06F17/50
CPCF41G3/32F42B15/01G06F30/20
Inventor 郭继峰关英姿荣思远
Owner HARBIN INST OF TECH
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