Ballistics
Application 1
Started - 25.02.2025.
Actuality and motivation - The war of 22.02.2022; the war of 07.10.2023
[A] On the Air Resistance to a Projectile Flight
Abstract
There is a great deal of experience in the field of evaluation of the air resistance to projectile flight within the atmosphere. Although, the common tendency to increase the object velocity beyond the sonic barrier challenges the traditional methods of evaluation.
The following analysis is performed according to the direct motion model, by the methods of classical mechanics.
The approximated theoretical dependences were achieved, allowing to determine the direction of structural improvement, to lower the resistance for supersonic speeds.
[B] Projectile Flight: The Problem Formulation, Solution, Predictions
Abstract
This report is dedicated to the issue of calculating air resistance to the flight of projectiles. The method used was previously developed in the work "On the Air Resistance to a Projectile Flight".
The same examples as in the soars are used to determine additional flight parameters. Their numerical values can be used for the selection of appropriate means to solve the problem – air removing from the trajectory.
Formulas have been developed to determine the flight design functions.
A computational assessment has been carried out for range and speed performance in the presence of air resistance two times lower than existed.
The obtained data can be used for both functional and commercial evaluation of solutions.
Boris Nudelman
Prepared 25/04/2025
Full file may be provided by request.
[C] 155 mm Projectile Flight Design Function
Abstract.
This work defines the flight characteristics of the 155 mm projectile with enhanced aerodynamic properties. The optimization of properties was carried out based on an original physical flight model with atmospheric air resistance.
An example of comparative calculations of projectile flight along an overhead trajectory is provided.
As a result, the impact (damage) radius, compared to the standard projectile shape, can be increased by more than one and a half times.
Boris Nudelman
Prepared 17/06/2025
Full file may be provided by request.
Application 2
Started - 09.08.2025.
Base Bleed (Base Burn) projectile
Abstract
TThis study examines the base bleed (base burn) projectile with a view to its potential application in the design of a hybrid protective system (Defense Aerial Device). The practical effectiveness of using a gas generator is well established and undisputed [1]. However, the conventional explanation of the effect is physically inadequate. Filling the base cavity with gas does not influence the hypothetical vortices outside that volume. Disregarding myths about vortices and air friction, only two physical elements remain: the projectile’s base surface and the flow of hot gases emerging from the generator. These constitute the subject of the present analysis.
Boris Nudelman
Prepared 01/09/2025
Application 4
Started - 23.12.2025.
Advanced method of space rocket launch, flight and descent.
Abstract
In the present work, the launch, flight, and descent of a spacecraft in the atmosphere are considered as one of the applications of previous works. The modern configuration of rockets for entering space is traditional and has existed since time immemorial. Its main functional attributes—a cylindrical body; a jet engine located at the lower end; and, as a rule, a nose fairing—are invariably present in every design. The cylindrical body provides maximum internal volume for fuel and systems. The jet engine creates the necessary thrust. The nose fairing reduces drag. At the same time, there is a possibility of substantially reducing motion resistance through simple modifications. A possible improvement in flight characteristics is shown by example. Data from the Falcon 9 project, SpaceX, were used as the prototype. Calculations of flight characteristics were performed for the first stage up to separation. The possibility of reducing the propellant mass of the first stage to 240 t has been demonstrated, provided that the characteristics of the second stage remain unchanged. In addition, through more complex modifications, the possibility of solving the problem of body overheating during descent and landing in the atmosphere has been identified. Prospects for further improvement of the design and flight characteristics have been determined.
Boris Nudelman
Prepared 31/03/2025