0065. Hypersonic Aeroballistic Missile Flight Analysis

A calculation sheet for the analyses of the speed characteristics on different sections of the flight trajectory of hypersonic airbased missiles. The analysis is based on differential equations of the dependence of the course velocity of a hypersonic aeroballistic missile KH-47M2 “Dagger”, taking into account the aerodynamic resistance of the atmospheric layers, on the duration of the flight.

The calculation methodology is based on the paper ANALYSIS OF THE FLIGHT TRAJECTORY OF HYPERSONIC MISSILES CONCERNING THEIR EFFECTIVE INTERCEPTION BY ANTI-AIRCRAFT DEFENSE SYSTEMS (O. Karpenko & A. Kiiko, 2024, 5 p.,https://doi.org/10.30748/nitps.2024.57.06 ).

Automated calculations and analysis

The software solution implements automated calculation of dynamic flight parameters based on differential equations of body motion in the atmosphere.

• Dynamic speed calculation: The system automatically calculates the current speed for any period of free flight.
• Environmental impact analysis: Automated determination of correction factors that take into account air density and aerodynamic drag.
• Predicting time to explosion: Based on the total flight time entered, the system calculates the remaining time until impact.

Practical application

The solution is designed for specialists in aerodynamics, military engineering, and air defense system analysts. It can be used for:

• Interception effectiveness assessment: Calculating the missile speed at the terminal stage (Terminal Dive) to determine the window of opportunity for Patriot PAC-3 MSE-type systems.
• Trajectory design: Simulating the behavior of an object during launch from a carrier (e.g., MiG-31K) at speeds exceeding Mach 1.
• Scientific research: Studying the aeroballistic characteristics of hypersonic weapons in the upper and dense layers of the atmosphere.

Features & Document Logic

The document is structured according to the logic of sequential engineering calculations:

• Input data: Ability to enter the mass of the missile, the drag coefficient for a symmetrical aerodynamic body, the average air density, the cross-sectional area, and the initial velocity of the missile (e.g., Mach 6).
• Mathematical model: Use of the refined methodology of O. Karpenko and A. Kiyka (2024), based on the quadratic dependence of drag force on velocity.
• Control: Using a slider, the user can instantly jump to the desired moment in time.
• Visualization: Automatic generation of a graph showing the relationship between speed and time, clearly demonstrating the process of rocket deceleration in the atmosphere (using the example of the Kh-47M2 “Kinzhal” air-launched missile).

Technical Specifications & Standards

File Format: .tec (TechEditor Project).

Document Language: English (Technical).

Output: On-screen review, report printing, export to PDF, RTF, DOCX, or image.

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