Коганицкий Григорий. Medium and long range tactical strike weapons Part One

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medium and long range tactical strike weapons

PART ONE - CRUISE MISSILE OF VARIABLE GEOMETRY, HAVING RAMJET ENGINE WITH ADDITIONAL INJECTING/FEEDING OF INLET AIR FLOW

PART TWO - ANTI-SHIP MISSILE, HAVING RAMJET ENGINE WITH ADDITIONAL INJECTING/FEEDING OF INLET AIR FLOW

PART THREE - GUIDANCE ALONG SPIRAL AND OVERCOMING MULTILEVEL MISSILE DEFENSE USING THE VIRTUAL MIRROR METHOD

Generals are always preparing for the past war.

Words from British Prime Minister Winston Churchill

A good example of this was giving by the Ukraine war.

The discrepancy between military-technical thought and modern realities has reached such an extent that military experts and politicians are increasingly to incline to think that the war (military thought) has reached a positional dead end.

Only superiority in technology and superiority in flexible firepower will be able to compensate for the transition to "stalemate" situation of positional warfare as it was in the First World War and which now is further complicated by the inability to conduct a covert accumulation of forces due to the action of space and aviation reconnaissance.

This is very clearly visible when analyzing the state of modern tactical strike weapons. I have already spoken on this topic in the selection - IMPACT TACTICAL GROUPS[8].

In this work/selection I want to raise the topic of medium- and long-range tactical strike weapons. I want to show one of the possible development options for medium-range tactical missiles and long-range cruise missiles, which, in present day froze at the level of V-1 and V-2, which was modernized (to the level of modern technologies in the field of electronics and control), mainly by immigrant scientists or through the theft of alien intellectual property, ideas and technologies.

Now the flows of the immigrant-scientists which are got from: Russia; China and India to US are minimized. Western national education has been commercialized and collapsed, so western countries, in military-technical terms, began to turn into "third world" countries

Why did I emphasize "... or through the theft of alien intellectual property, ideas and technologies"!?

I've myself already be confronted by this problem twice .

First time - Koganitsky G.A " ;Warning of violation of the right of "intellectual property" Размещен: 17/03/2015

It was ended by a classy African-American man arriving, presumably as a representative of DARPA, and together with a stupid member of the "Canadian Mountain Police", which tried to threaten and to blackmail me.

The second time, as I assume, I caught in theft of my intellectual property certain Matt Walker, head of the Air breathing Propulsion division at NAWCWD.

(C) "...engineers want to combine it with the main rocket into a single system with a common combustion chamber. Walker believes that in 3-4 years a working model will be ready and will go into mass production..." This statement was done approximately in 2017

https://www.techinsider.ru/weapon/344202-rapjet-inzhenery-ssha-postroili-raketu-s-pomoshchyu-modelnogo-dvigatelya-i-kreditki/

https://www.sciencedirect.com/topics/engineering/combined-cycle-engine

As I assume, it was copied from the Internet, based on a drawing from my article "Anti-ship and tactical missiles of short and medium range" (Posted: 11/14/2011) and " Overcoming of missile defense part one " (Posted: 16/10/2011), after that, it was stated in press as advertising matter, in the level and in the style of a brave cowboy who successfully stole chickens from a neighbor's ranch.

(C) "...The United States conducted another successful test of a hypersonic missile prototype as part of the HAWC program, reports the US Department of Defense Advanced Research Projects Agency (DARPA).

"... Done .... successful flight test of the prototype under the HAWC (hypersonic ramjet rocket) program" -

The rocket is being developed by Lockheed Martin. During testing, it reached a speed of Mach 5 (6.1 thousand km per hour) at an altitude of more than 18 km and flew about 483 km.." - announced in September 2021

US successfully tests Mach 5 missile - DW - 09/28/2021

Combined-Cycle Engine - an overview | ScienceDirect Topics 2021 год

Based on the advertising statements of Mr. Matt Walker and the design features of the hypersonic missile in the picture from the advertising topic above, I have reason to assume that this missile was designed based on an idea stolen from me ...

Press-clipping of Internet searching by a given picture and topic

HEREBY - MEDIUM AND LONG RANGE TACTICAL STRIKE WEAPONS

Both options are united by an engine design, which is based on my idea of 'cruised missile of variable geometry, having ramjet engine with additional injection/feeding of inlet air flow.'

The difference is that in an anti-ship missile (operating range up to 150-250 km) as an injection gas generator is used a powder rocket engine, and in a longer-range cruise missile (operating range up to 1500-2000 km), an injection gas generator based on a liquid-propellant rocket engine working by hydrogen peroxide is used.

THIS PARAGRAPH DISCUSSES A VARIABLE GEOMETRY CRUISE MISSILE BASED ON SUCH AN ENGINE.

What is the difference between a "variable geometry wing" of cruise missile and "a cruise missile of variable geometry "?

A cruise missile having "a variable geometry wing" changes the wing configuration, while a "variable geometry cruise missile" changes in flight its operating aerodynamic configuration.

1 - detachable arched wing; 2 - winglet; 3 - hypersonic wings; 4 - homing head; 5 - fuel tank in which the gyroscopic module is installed; 6 - air intake; 7 - hydrogen peroxide tank in which the propulsion system is installed.

Hereinafter, the cruise missile is presented without a nose cone, which must be selected on the results of complex purges in an aerodynamic tunnel

Such cruise missile airframe has artificially unstable aerodynamic in both heading and pitch.

Position of the center of air pressure -12 and center of gravity - 13 on the cruising section of flying

The wings do not have controlling surfaces.

Control of the cruise missile position in space and its stabilization is carried out by positioning the body relative to the gyroscopic module and mutual/interrelated changes in the rotation speed of the gyroscopes.

The flight can be roughly divided into four stages:

Climbing altitude up to 6000 meters and speed up to 500 km/h, which is carried out in a full aerodynamic configuration using powder accelerators;

Climbing to an altitude of 12-16 thousand meters and a speed of more than 1000 km/h, which is carried out in a full aerodynamic configuration, due to an injectiing direct-flow engine;

Cruising mode at an altitude of up to 16 thousand meters with a cruising speed of more than 2000 km/h, which is carried out in a full aerodynamic configuration, due to an injecting direct-flow engine;

It is quite possible that at this stage it would be rational to shooting out winglets

Performing an attack in a shallow dive, that carried out from a distance of 100-150 km to the target.

At this stage, the cruise missile changes its geometry and aerodynamic configuration by shooting off the arched wing.

The cruise missile attacks target along a spiral trajectory with speed that increase, due to an injecting direct-flow engine, up to 3-4 thousand kilometers per hour as it approaches the target and altitude losing.

Picture of cruise missile in attacking configuration

In principle, a third configuration of a cruise missile is possible. It is the transport-launch configuration, in which the arched wing and winglets are folded.

The cruise missile in such configuration be able not only to have a minimum area during transportation, but because it has the forced stabilization of the body, it can to start from the container and rapidly pick up speed on the initial phase of trajectory.

How it is possible and expedient, may be said only after a series of aerodynamic blowdowns and an assessment of the weight of the hydraulic drive of the wing mechanics after strength tests.

The gyroscope module are located inside the fuel tank.

The gyroscopic module consists of two gyroscope-charges, each of its are located inside own pressure tight housing and are fixed at an angle to each other inside a power gimbal, controlled in two planes as by roll and by pitch.

Heading control is carried out by redistributing energy between gyroscopes and by roll controlling.

10 - pressure tight gyroscope housing; 11- powering (executive) cardan suspensions.

Gyroscopes should be rotate at a speed up to 12-20 thousand revolutions per minute.

The strength of a gyroscope-charges is ensured by their design.

Gyroscopes are a honeycomb structure, wound from a composite tape (carbon fiber on a metal binder), in which, for example, high-purity magnesium is used as a a binding agent.

During the process of winding into a spherical, honeycomb structure, layers of composite tape are welded layer by layer by means of a roller welding.

After winding, tape-8 is filled into honeycomb-9 by TNT or other suitable plastic explosive, by vacuum or centrifugal casting, forming a monolithic sphere of high strength.

Each of such gyroscope-charge contains 150-180 kg of explosive matter.

According to my estimate, the weight coefficient of filling the gyroscope-charge with an explosive substance will be at least 0.7.

As result of action of: high attack speed that sufficient for impact destruction of the take-off armored deck; large area spread of burning fragments of the tape and its high thermal impact (more than 2000 * C), "butterfly" effect will be being.

As result of that, when it will be doing a simultaneous, "star strike" carry out by three missiles (optimal application scheme) modern an aircraft carrier, of any type will be completely incapacitated, simultaneously with heavy losses of personnel and flight crews.

LET'S CONSIDER RAMJET ENGINE WITH ADDITIONAL INJECTING/FEDDENG OF INLET AIR FLOW, BY A GAS GENERATOR RUNNING ON HYDROGEN PEROXIDE.

For the first time such an engine diagram was published by me

in the article - " Overcoming of missile defense - part one (samlib.ru)" 16/10/2011

http://samlib.ru/img/k/koganickij_g_a/overcoming_1/overcoming_1-12.jpg

1 - air intake; 2 - spiral air flow transformer; 3 - toroidal gas generator; 4 - injector of jet of flame; 5 - fuel injector; 6 - flame chamber; 7 - soft tank for oxygen peroxide; 8 - cavity with excess pressure

The catalyst panels and hydrogen peroxide piping are not shown in this view

8 - cellular panel of turbolator having a catalyst coating; 9 - hydrogen peroxide pipeline; 10 - perforated section of the gas generator wall; 11 - fuel pipeline

The air flow enters through air intake_1 into a spiral diffuser, in which it accelerates and twists into a vortex (possibly pulsating) structure.

Three flows interact in the air injection zone:

1. Vortex flow from a toroidal chamber_4 of a gas generator running on hydrogen peroxide.

Hydrogen peroxide is supplied to the toroidal chamber through hollow inclined plates-turbolator_8, one side of which has a honeycomb structure and a coating of catalyst.

2. Vortex of air that is outgoing from a spiral diffuser.

3.Linear jet of flame that is outgoing from the fuel torch former.

Jet of flame and vortex air flow from the toroidal gas generator have a higher speed relative to the engine axis than the air flow off the air intake and they inject it into the flame chamber.

The engine input resistance has a negative value as a result of forsed air injection of the input air flow in the injection zone.

The vortex flow of products of decomposition hydrogen peroxide which are enriched by oxygen from the toroidal chamber of the gas generator and the vortex air flow from the input diffuser have the opposite direction of rotations.

A linear Jet of flame is fed between two oppositely directed vortex flows of the oxidizer and mixed with them.

Presumably (I do not have the opportunity to carry out experimental work), pulsating spiral strings are formed in the contacting zone of a fuel mixture compressed and heated to a high temperature, and combustion can be occurring according to a detonation mode.

I assume that such a ramjet engine can be operate effectively starting from a cruise missile speed of 400-450 km/h and the transition to supersonic and hypersonic flight modes will not cause disruption to its operation (transition to an unplanned pulsing stall of flame).

I carry out mailings the articles into these addresses

Ministry of Defense	research organizations of Ministry of Defense
Canada - information@forces.gc.ca https://buyandsell.gc.ca/contact-us	DND.IDEaS-IDEeS.MDN@forces.gc.ca
the British Ministry of Defense no email address	centralenquiries@dstl.gov.uk AuroraProviderNetwork@QinetiQ.com https://www.qinetiq.com/en/contact-us
Ministry of Defense of Iran + info@mfa.gov.ir	research organizations of Ministry of Defense of Iran https://www.iranwatch.org/contact int@irost.ir
Ministry of Defense of China + mod@mod.gov.cn	research organizations of Ministry of Defense of China heidi.mcgregor@ithaka.org https://support.publishers.jstor.org/hc/en-us/requests/new?ticket_form_id=360003403994
Ministry of Defense of Poland kontakt@mon.gov.pl	The National Centre for Research and Development (NCRD, Polish) info@ncbr.gov.pl https://www.gov.pl/web/ncbr-en/information-point
Ministry of Defense of Sweden exp-hkv@mil.se	research organizations of Ministry of Defense of Sweden registrator@foi.se
Ministry of Defense of Norway postmottak@fd.dep.no	research organizations of Ministry of Defense of Norway info@ffi.no hanne.bjork@ffi.no firmapost@ffi.no *runderland@mil.no*
Ministry of Defense of Finland kirjaamo.plm@gov.fi registratorskontoret.fsm@gov.fi	research organizations of Ministry of Defense of Finland registry.plm@gov.fi
Ministry of Defense of India indiaportal@gov.in	research organizations of Ministry of Defense of India ws-dst@gov.in
Washington no email address	contact@nti.org DARPA - https://contact.darpa.mil/ Lockheed Martin - CSSCustPortalSuppt@sikorsky.com community.relations@lmco.com
Ministry of Defense of United Pakistan datacenter.mlc@gmail.com sotodgmlc@outlook.com	research organizations of Ministry of Defense of Pakistan issra@ndu.edu.pk
Ministry of Defense of South Africa pgvdb@sanavy.co.za Senior Staff Officer info@dod.mil.za secdef@dod.mil.za Director-General: Sonto Kudjoe, Ms	research organizations of Ministry of Defense of South Africa no email address
Ministry of Defense Italy udc@postacert.difesa.it	research organizations of Ministry of Defense of Italy udc@gabmin.difesa.it segrecapo.sm@casd.difesa.it
Ministry of Defense of North Korea dpr.korea@verizon.net admou@mil.gov.ua
Ministry of South Korea webmaster@pmo.go.kr

Contact

Koganitsky Grigory

koganitskyg@gmail.com or k_gert99@yahoo.ca

сell 1 514 8899875

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Аннотация: The discrepancy between military-technical thought and modern realities has reached such an extent that military experts and politicians are increasingly to incline to think that the war (military thought) has reached a positional dead end .... .... Now the flows of the immigrant-scientists which are got from: Russia; China and India to US are minimized. Western national education has been commercialized and collapsed, so Western countries, in military-technical terms, began to turn into "third world" countries

Коганицкий Григорий : другие произведения.

Medium and long range tactical strike weapons Part One