Missile weapon system design method aiming at efficiency on basis of performance indexes
A system design, 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.
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
specific Embodiment approach 1
[0046] The effectiveness-oriented missile weapon system design method based on the performance index of this embodiment, combined with figure 1 As shown in the flow chart, the method is realized through the following steps:
[0047] 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,
[0048] The overall performance index of ballistic flight, including: range, flight speed, altitude, available overload, and maximum flight time;
[0049] Fragmentation warhead system performance indicators, including: fragmentation initial velocity, fragmentation angle, fragmentation direction angle, total number of fragments, unconditional killing radius, power radius;
[0050] Propulsion system performance indicators, including: working time, total impulse, thrust, specific impulse, mass ratio, ...
specific Embodiment approach 2
[0070] 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,
[0071] Fragment initial velocity is v 0 said, v 0 The calculation formula is:
[0072] v 0 = 1.236 Q e M f M e + 1 2 ;
[0073] In the formula, Q e Indicates the detonation heat of expl...
specific Embodiment approach 4
[0090] 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:
[0091] 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:
[0092] S w = K m ...
PUM
Abstract
Description
Claims
Application Information
- R&D Engineer
- R&D Manager
- IP Professional
- Industry Leading Data Capabilities
- Powerful AI technology
- Patent DNA Extraction
Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.
© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com