Коганицкий Григорий. Part two - anti-ship missile, having ramjet engine with additional injecting/feeding of inlet air flow

All innovations declared here are the property of the author and cannot be used without his consent.

medium and long range tactical strike weapons

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

http://samlib.ru/k/koganickij_g_a/turnskin_2.shtml

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

"ANTI-SHIP MISSILE, HAVING RAMJET ENGINE WITH ADDITIONAL INJECTING/FEEDING OF INLET AIR FLOW" was developed by me in the early 2000s and posted on the Internet 14/11/2011

Then, as I teel wrote in the previous article - PART ONE - CRUISE MISSILE OF VARIABLE GEOMETRY, HAVING RAMJET ENGINE WITH ADDITIONAL INJECTING/FEDDENG OF INLET AIR FLOW , 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, all of that was stated as the innovation by Mr. Matt Walker - head of Air breathing Propulsion at NAWCWD, and it was represented 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.

Based on the advertising statements of Mr. Matt Walker and on 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 intellectual property stolen from me ...

(C) "Matt Walker, head of Air breathing Propulsion at NAWCWD, told Naval Aviation News that his team went for a trick ...''

.... Walker declared - "Instead of making the launch-vehicle as a part that splitting away after launch, engineers want to combine it with the main rocket into a single system united by a common combustion chamber".

Walker believes that in 3-4 years a working model will be ready and will go into mass production...

He can, of course, call it as cunning, but, in my opinion, it's just stealing.

Moreover -

(С) "In July 2021, the US (....) announced that Australia had become a partner in the PrSM Program with the Australian Army signing a memorandum of understanding for Increment 2 of the program with the US Army's Defense Exports and Cooperation and had contributed US$54 million. [10] [11]

The United Kingdom, as part of an upgrade to the British Army's M270 MLRS to the M270A2 standard, has hinted that it may possibly acquire PrSM.^[12]

On December 8, 2023, the US Army announced that the first PrSM has been delivered.^[13]

Future operators

Australia

Australian Army

United Kingdom

British Army - Not confirmed

United States

United States Army

United States Marine Corps

Apparently, for an American cowboy it is important not only to being able to steal someone else's property, but also to sell the stolen property profitably.

I have read Mr. Matt Walker's self-promotion and, with interest, scrutinized at what he was able to "understand" from my work and what He offers now into market as own idea.

In my opinion, "his" hypersonic missile, controlled by aerodynamic planes, looks like a "steam locomotive driven by legs" - well, what can you do, the intelligence of the American cowboy has deep historical roots

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

All drawings and drafting used in the article are simplified and are intended for demonstration purposes only.

The differences of unit that is represented in the "part one" and unit represented below are that in an anti-ship missile (operating range up to 150-250 km) as an injection gas generator is used a solid-propellant 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 as an example by hydrogen peroxide is used.

Such distinction is motivated by: different flight ranges; target features at which missiles operate; the type of air defense of a particular enemy and the differinses of tactics of passing this air defense.

Both options are united by an engine design, which is based on my idea of "ramjet engine with additional injection/feeding of inlet air flow."

So far as the rocket does not have any type of external aerodynamic planes; the body and main elements are made of carbon fiber - its effective radar scattering cross-section is minimal.

The main targets of the short and medium-range anti-ship missile described below are heavy aircraft carriers, which, in addition to the armored take-off deck, have an inner a full or focal carapace deck that protects the internal, most critical components.

Ships of this type are protected not only by their own layered air defense, but also by the anti-aircraft systems of an escorting convoy.

Currently, anti-aircraft systems based on high-power lasers are being developed and field tested. To date, such systems are effective only for classic cruise missiles and unmanned attack drones that have: a relatively thin-walled duralumin body; poorly protected controlling airfoils and downward-looked external optic matrixes.

The engines of a hypersonic short and medium-range anti-ship missiles is designed to provide the highest hypersonic speed throughout the entire flight trajectory (approximately 200-400 km), which will be being limited only by the thermal barrier that is specific at an air density on this flight altitude.

Such engines must provide the ability of maneuver to deviation from long-range air defense interceptors and, in the passage of a mid- and short-range air defense fire barrage, provide the ability to constantly maneuver, with high angular speed and high overloads, without of a surging of the engine.

I think, when the missiles must be passes through middle or nearby echelon of air defense of an escorted heavy atomic aircraft carrier, it will be optimum to attack along spiral by a group of three missiles that capable to misinform air defense systems, by forming of a virtual mirror.

A hypersonic anti-ship missile structurally consists of two bodies - outer (2) and inner (1), rotating at high speed in opposite directions relative to each other on a common axis.

The following are installed in the inner case: 3A, 3B - impact core; 4 - thermobaric charge; 10 - control compartment

The following are installed in the outer casing: 5A, 5B - gas generator; 7A; 7B - liquid fuel tanks; 6 - combined engine

The impact core consists of: 3A - a hollow, trimmed cone of rotation, made of depleted uranium; 3B - explosive charge, which has a detonation characteristic nonlinear in volume, and a cumulative funnel at the front end which has a liner (9) inside

The control compartment (5) does not rotate, since it is stabilized in two planes relative to the rocket axis by a gyroscopic module containing gyroscopes (8A); (8B).

The control compartment can be to forсe deviate from the central axis of the inner housing in two planes, relative to the gyroscopic module.

The control compartment contains the main hardware modules (not shown in the figure)

For heading and pitch control (roll control, due to the absence of aerodynamic planes on a symmetrical body, is not necessary), the control compartment is deflected by a power drive in the desired direction and causes precession of the body, with a controlled angle, relative to the course.

The oncoming flow of air, flowing around the rocket body that rotating at an angle to it, creates a transverse component of aerodynamic force and deflects the trajectory of the rocket.

In the picture below is an explanation (from a school textbook) of this process, for the cowboys of Loughheed Martin and others ... (C) "Magnus Effect" - phenomenon commonly associated with a spinning object moving through a fluid or a gas"

As a result of these influences, the rocket moves along of a desired spiral in the air.

Since the missile (three missiles as part of the attacking "wolf pack") moves at hypersonic speed and their angular and circular velocity of projection of movement in a spiral is presumably higher than the effective scanning speed of modern air defense radars, the sensors see instead of the real point of the location of the rocket, several of its avatars.

Optical guidance of interceptor missiles of escort ships and usage by powerful lasers by these ships for intercepting of missiles is also complicated as result of the effect of multiple shock waves and lensing targets by it during the spiral movement of a hypersonic missiles (three missiles in attacking "wolf pack").

The missile carries a composite warhead.

In front (in the direction of impact) is located: impact core (3), consisting of: 3A - a hollow, truncated cone of rotation made of depleted uranium; (3B) - explosive charge, which has a detonation characteristic nonlinear in volume, and a cumulative funnel at the front end which has a liner (9) inside

Cone of rotation that is made of depleted uranium (3A). Section view.

The truncated cone of rotation made of depleted uranium (3A) is the main penetrating element of the warhead, the task of which is to penetrate the armored take-off deck and, acting in conjunction with the charge (3B), to destroy a section of the carapace deck, for an allowing of the penetration of the high-temperature jet and burned fragments of the spin cone into the interior volume of the aircraft carrier - storage fuel, weapons and energy generating compartments.

Charge (3B). To simplify of the figure, the honeycomb structure is shown conventionally

To form the directional characteristic of explosion, part of the outer cells of the charge (3B) is filled with an explosive having a higher speed of propagation of the detonation wave than the main part of the charge (such cells, in the figure above, are shown in ocher color)

The charge (3B) is a wound by honeycomb structure made of composite tape (carbon fiber that is impregnated with molten magnesium), the cells of which are filled with molten explosives.

At the front end of the charge there is a lined cumulative funnel (9).

/ Charge (4). To simplify of the figure, the honeycomb structure is shown conventionally/

The tapes from which charges (3B) and (4) are formed are wound parallel to the main axis of the rocket. The honeycomb structure also runslocaited in parallel to this axis.

/charges with a honeycomb structure are described in more detail in the charter "Part One"/

11 - cells filled by explosives; 12 - composite tape of carbon fiber (honeycomb structure), impregnated with magnesium melt.

The initiators of charge (4) are installed so that its detonation occurs at the moment preceding the penetration of the impact core (3) through the take-off deck.

Its main effect on the environment is carried out by a shock wave and by fragmentations of honeycomb structure, which are burning in the air and, in its effect, is close to the effect of volumetric explosion ammunition or high-explosive bombs having an additional a white phosphorus charge.

The initiators of charge (3B) are installed so that its detonation should be occur at the moment of the impact core (3) penetrates through the carapace deck. Its impact on the environment is distributed between the spaces above and below the carapace deck.

LET'S CONSIDER THE STRAIGHT FLOW, AIR JET ENGINE OF DESCRIBED ABOVE HYPERSONIC ROCKET.

It principle, in general terms (injection of the input air flow due to the energy of the gas generator) repeats the principle of the engine described in the article of "Part One - cruised missile of variable geometry, having ramjet engine with additional injecting of an inlet air flow."

The principle of such a ramjet engine was first stated by me in the article "Short- and medium-range anti-ship and tactical missiles" and Posted: 11/14/2011.

Its main difference from the engine described in the Part One is the usage of a solid propellant rocket engine as an injection gas generator, which is also a structural component of the combined ramjet engine of this rocket.

1- Inlet air flow; 2 - injection zone; 4 - afterburner chamber; 5 - gas generator

The gas flow producted by the solid fuel modules (5) through the buffer mixer (7) is supplied by tangential nozzles (6) to the injection zone (2), forcing the input air flow and the burning, over-enriched fuel mixture into the afterburner chamber (4)

(fuel torch formers and fuel fittings are not shown in the figure)

3 - rotation turbine of the internal casing; 5A - solid fuel module of cruising mode; 5B - solid fuel module of acceleration mode; 6 - tangential nozzle block; 7 - buffer mixer

The gas generator shown in this figure is formed by two solid propellant modules working on a common buffer-mixer (an earlier version of the description of this Know-How used one module, made by winding or a standard, by central-axial powders' cartridge).

In the version shown in the figure, two types of solid fuel modules, having different combustion diagrams are used:

5A is a slow-burning module that provides input air injection for a relatively long hypersonic cruise flight mode and 5B is a fast-burning module with high energy output that provides starting acceleration.

It is possible that usage solid fuel modules fulfilled of a material that has a positive oxygen balance together with supplying by them a catalyst into the gas stream, will give an additional positive effect.

A gas jet from tangential nozzles is supplied to the combustion chamber, simultaneously injecting the input flow and rotating both the internal housing and the inlet flow twirlers by acting on the impeller (3)

(the inlet flow twirlers are not shown in the figure).

In the fire chamber, two coaxial, counter-rotating gas flows interact, between which overrich fuel mixture is supply by a flame torches.

The gas flow from tangential nozzles has a relatively low temperature, so there is no need to make an impeller (3) from expensive and difficult-to-process materials.

As I already wrote in Part One -

(С) ".... 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
Ministry Saudi Arabia hostmaster@moda.gov.sa	research organizations of Ministry of Defense of Saudi Arabia https://www.psdsarc.org.sa/about-us/

P.S.

I want to address at -

(С) " Future operators

Australia

Australian Army

United Kingdom

British Army - Not confirmed

United States

United States Army

United States Marine Corps "

Do these gentlemen understand that they are being offered to buy stolen goods!?

Of course and I also understand that it is pointless to go to an American court - theft, as in this case, of someone else's intellectual property, has deep historical traditions in the United States and is encouraged and protected by the state in every possible way.

But do these and other gentlemen understand that those to whom I will agree to cede by legally way my "right to intellectual property" will bring million-dollar claims against them!?

Contact

Koganitsky Grigory

koganitskyg@gmail.com or k_gert99@yahoo.ca

cell 1 514 8899875

Оставить комментарий © Copyright Коганицкий Григорий (gert99@mail.ru) Размещен: 19/12/2023, изменен: 20/12/2023. 37k. Статистика. Статья: Изобретательство IMPACT TACTICAL GROUPS Иллюстрации/приложения: 14 шт. Скачать FB2		Ваша оценка:
Аннотация: So far as the rocket does not have any type of external aerodynamic planes; the body and main elements are made of carbon fiber - its effective radar scattering cross-section is minimal... The main targets of the short and medium-range anti-ship missile described below are heavy aircraft carriers.

Коганицкий Григорий : другие произведения.

Part two - anti-ship missile, having ramjet engine with additional injecting/feeding of inlet air flow