So, "... the main phase of WIG were:

1) 1942-1962 years - to obtain experimental data that led to the idea of ​​using an air wing that runs near the surface (the screen), the study of physical principles and characteristics, the creation of mathematical models, construction and testing of the first self-propelled models, WIG;

2) 1962-965 years - designing and construction of full-scale ekperimentalnogo winged "KM" - still the largest in size and mass of all build the world's WIG;

3) 1965-1979 years - construction and testing of experimental WIG (only been established for over ten WIG takeoff weight from 1,5 up to 500 tons), the work on designing and building for the Navy WIG different purposes: "Eaglet", "Lun", " Kite;

4) 1980-1991 years - work on implementation of WIG first generation in operation, development efforts (OCR) to create a second generation WIG;

5) 1991 - present - the cessation of work on ekranoplans for the Navy in connection with the conversion, consider issues of backlog created for commercial purposes to create a civilian WIG.

The resulting backlog allow CDB to SEC to develop various applications WIG displacement up to 5000 tons "

However, as time has shown, this potential is realized not removed, because Russia in order WIG was already no one, and America, removing scum, in on itself, classify their work in this area.

This is another example of our Russian credulity and simplicity, which, indeed, worse than stealing.

So what was the purpose of our cooperation with NPO Energia?

Goal - the creation of a mobile rocket-space complex (RSC) using the WIG.

Projected performance criteria of the complex.

1) There is no need for expensive facilities for ground training.

2) The possibility of landing winged almost not equipped lowland areas, including the absence of the airfield.

3) Ability to conduct starting from any area, including the equatorial regions.

4) Improving energy performance of launch vehicles (LV) due to start from a height of 8-10 km.

The objectives of the joint research work (research) were:

1. Determine the fundamental possibility of the Prince of WIG to create a mobile rocket-space complex.

2. To identify possible structural layout of the complex space rockets (ILV) on ekranoplans.

3. Determine preliminary constructive shape, specifications WIG to create mobile RAC.

4. Determine the phasing, cost and timing of a winged, indicating the alleged co-enterprises subcontractors.

5. Determine the major issues in creating WIG mobile RSC and the expected solutions.

Technical requirements for ekranoplans stated in the terms of reference has four directions of WIG for RCM .

The use of WIG in the aerospace complex (WCC). WCC based WIG must ensure delivery of ILV with the coastal base (eg, near Vladivostok) in the waters of the desired start and holding it launching RCN at a height of 12.9 km and the speed of 700-900 km / h.

WCC should include:

- Winged vehicle,

- Launch Vehicle (ILV),

- The container with the necessary equipment to ensure the filling of ILV and its launch. Removal of the district starting from the base of RCN may be 3, 6, 9 and 12 thousand kilometers.

The total mass of RKN container and equipment may be 300, 500 and 900 tons. During transportation, and launch preparation should be provided to maintain temperature and humidity RKN container and equipment, as well as their power output to 20 kilowatts.

Start filling ILV - 5 minutes before its start.

RCN launch angle relative to the horizon at least 25 degrees (to study the possibility of increasing the angle of launch).

Branch of the winged space rocket - the hot, ie, With the engine running ILV. In the process of elaboration to consider the possibility of cold branch of winged space rocket, followed by the inclusion of its engines.

The use of WIG in the mobile space-rocket complex (MRKK).

MRKK based on a series of WIG provides delivery to the desired launch area (with access to the shelving shore) ILV required ground launch equipment deployment in the area starting position, preparation and launches space rocket.

Weight of dry ILV - 55 m, 450 tons of seasoned.

Mass transported modules MRKK - 300, 500, 1000 tons.

Removal of the launch area from the main base ILV MRKK may be 3, 6, 9 and 12 thousand kilometers.

The use of WIG for oversize cargo - blocks ILV with manufacturing plants in Samara and Moscow and Baikonur cosmodrome Plesetsk, as well as the ports of St. Petersburg, Novorossiysk, Severodvinsk and Vladivostok.

Characteristics of goods:

- Single cylinder, diameter 8 m, length 60-80 m, weight 100 tons;

- Two cylinders, the diameter of 4 m, length 40 m, weight of 50 tons each;

- Front-docking unit (Unit I), dimensions 10x20x5, 2 m, weight 150 tons when carrying out design study for ekranoplans for these oversized loads

should be considered options for both seasonal and year-round transportation.

The use of WIG for delivery ILV "Energy" "Energy M" and other cargo from shore technical complex at the floating launch platform in a space-rocket complex sea-based (RKKMB). Weight carried by RCN and other loads of up to 600 tons, and in view of the enclosure (container) - up to 800 tons.

For all areas of WIG should be elaborated question the need for large-scale models with regard to their possible use in advertising and commercial purposes for the transportation of goods.Determination of shape WIG, their technical characteristics and diagrams of aerodynamic layout and geometric dimensions were based on years of experience of the firm and the author.

Of the variety of schemes of arrangements of a wind (AGDK) WIG developed and examined previously, winged vehicle ILV was chosen and accepted as a basis the scheme of "composite wing" with the center-Small, X = 0.6, elongation, and V -shaped tail.

The chosen scheme WIG allows you to:

- To obtain higher values ​​of aerodynamic control in cruise flight at the screen;

- A winged takeoff weight up to 5000 tons;

- Ensure the creation of a dynamic air cushion (blowing under the wing) on ​​the conditions of launch and landing and in amphibious mode of motion;.

- Used in the amphibious landing of the complex soft bellows-mounted side-skeg hulls;

- To provide hot start ILV (start with the engine running) on board the WIG in flight through the use of diversity on ekranoplane V -shaped tail, not getting into the jet ILV;

- Provide convenient placement and loading and unloading of ILV and other bulky cargo in transit to both the external load, and within the winged;

- To ensure a comfortable stay on board the WIG as his own crew and service personnel launches space rocket;

- To provide flight winged vehicle out of the screen at an altitude of 12 km.

For all three sizes of winged selected in this elaboration, adopted a scheme of arrangement Aerohydrodynamic.

Powerplant WIG consisted of main and auxiliary facilities, and systems to ensure operation of the main and auxiliary engines: fuel, air systems, control systems and control SS.

As part of the main propulsion unit used bypass turbofan engines NK-44, proposed SSPE Samara Trud. The company has 50 years experience in the creation and finishing of aircraft engines is a great resource, developed under the leadership of General Designer Kuznetsova, ND, as well as 25 years of experience in development and improvement of engine modifications for WIG "Eaglet" and "lun."

WIG flight characteristics were determined on the basis of test models in wind tunnel WIG Siberian Research Institute of Aviation (SibNIA). Results of model testing (aerodynamic coefficients) have been converted to full-scale dimensions of each option taking into account existing differences in the model and nature of the procedure adopted in the aviation industry (RDK TsAGI Guide for designers to design aircraft that I, Book 3, Number 2, 1978)

The initial polar model for the five operating altitudes near the screen, as well as the flight out of the screen were converted to nature.

....

During the flight of winged off-screen aerodynamic quality drops sharply and is necessary to work all the engines, especially in the beginning of the flight, when the mass of winged close to the maximum.

Typically, a flight to high altitudes should be done at the end of the horizontal flight at the screen after the main supply is depleted fuel. Masses WIG climb will be on 18-22% less than the maximum takeoff weight.

After the task at altitude produces winged decrease with the angle of inclination of the trajectory is not more than 4 ° at a speed of 650-700 km / h. The decline of the screen will be approximately 7 minutes.

The winged includes center-low aspect ratio (k = 0,6), equipped with flaps deflected by an angle -10 °, +20 °.

On each side of the center-located housing-skeg fitted bottom elastic bellows, soften the blow when moving winged over land and rough water surface in the amphibious landing modes. In the fore part of the WIG, the shell-skeg mounted pylons, which are the main propulsion engines, equipped with nozzles, directing the jet engines horizontally at cruising flight, and obliquely in the sand - on the landing and amphibious mode.

Struck by a center-console and a space bounded on the sides of buildings, skegs and end washers, and rear - downward deflection flaps, gas engines under the wings form a zone of high pressure - a dynamic air cushion that lifts winged to a certain height and reduces its resistance to movement.

The sides of the skeg-mounted console, composite wing aspect ratio X = 3.5, equipped with ailerons, flaps and end plate. End plate from the bottom, as well as body-skeg, equipped with flexible bellows. On the external side of the console composite wing, on their upper surface, front flaps, provides the installation of interceptors for directional control WIG.

In the rear of the hull, skeg mounted console, a separate V -shaped tail, equipped with elevators.

Fuel capacity is located in sealed tanks, caissons wing panels, in the center of mass along the length of the WIG.

In sealed caissons consoles tail provides ballast fuel tanks to ensure the necessary alignment with winged flight without a payload.

Corpus skeg provides accommodation of the crew, equipment and personnel to service the space rocket launches.

In the center section provides accommodation of bulky equipment and payload. The main way to accommodate bulky cargo, under terms of reference - on external sling.

The winged number 1 take-off weight of 1100 tons, can carry the following loads:

- Block "C" rocket "Energia", weighing about 100 tons, 60 m long with a diameter of 8 m, located on the upper surface of the central plane. By providing the necessary position of the center of mass WIG (alignment) and taking into account the location of its main engines, block "C" appropriate place, as shown in Fig. 65, ie, nose in the direction of flight and with a shift in the stern of WIG.

At the tail of the block "C" provides installation stekatelya to reduce drag during flight;

- ILV-3 missile with a 25 m, diameter 3,9 m, with two containers of a length of 22 m, diameter 3,6 m, total weight of cargo - 300 tons. The missile was placed over the container with the rocket fuel and starting equipment;

- Two blocks of "A" RCN "Energy", weighing 50 tons, a length of 40 m, a diameter of 4 m blocks located on the upper surface of the central plane, symmetrically about the center plane winged, bow in the direction of flight. At the tail end of the block provides installation stekateley to reduce drag during flight and engine protection;

- Front-connecting block (block "I"), size 10x20x5, 2 m long, weighing about 150 tons.

The winged № 2 takeoff weight 1,900 tons can carry goods listed above for WIG number 1 and, moreover, following goods:

-Launcher "Energia-M 50 m, width 16 m and a height of ~ 8 m, the mass together with the starting-block, - 280 m. The launcher" Energia-M was located on the upper surface in the center plane , nose in the direction of flight, winged. On the aft missile provides installation stekatelya.

- Booster ILV-2 35 m, diameter 3,9 m, with two containers of a length of 30 meters, diameter of 3,6 m, which is fuel for missiles and equipment to run it. The total mass - about 500 tons. The launcher was placed over the container so as to ensure its passage on engines with winged state, and unauthorized launch. At the bow of containers the fairing and the tail parts of the container and missiles to be installed stekateli to reduce resistance during transportation.

The winged № 3 take-off mass of 3500 tons can carry goods listed above for ekranoplaknov number 1 and number 2, and apart from them:

- Booster "Energy" with power "cn" and starting-the block "I" of the total mass of about 600 tons, a length "60 m, a width" 18 m, height "17 m.

Under the terms of alignment and to reduce aerodynamic drag, RN "Energy" was installed on the upper surface of the winged, "backwards". To reduce drag in flight and engine protection during transportation provided for the installation of the fairing on the tail of the rocket.

- Rocket ILV-1 (Zenit), 60 m long, 3.9 m in diameter, with two containers of a length of 45 m, diameter of 3.6 m. The total weight of the load - 900 tons.

In containers placed fuel for missiles and equipment to run it.

The launcher was placed over the containers to ensure its passage on engines with winged state, and unauthorized launches. In the bow of containers and provides installation of missile radomes, and aft - stekateley to reduce resistance. Launch Zenit mounted nose in the direction of flight, winged.

Mounting missiles and their modules ekranoplans provided for their regular shipping sites by clicking on ekranoplans foreseen response units, installation area on which ekranoplans intensified.

Handling of launch vehicles and other equipment could produce specially designed for this purpose compact loading and unloading means, carried on ekranoplans together with a missile, or separately from it.

The main characteristics of the WIG three sizes (geometric, mass, aerodynamic and operational) are defined on the basis of calculations and expert estimates made on the basis of experience in the design, construction and operation of WIG gained NGO CDB to SEC and listed in the table:

The technology of using WIG in the space-rocket complexes, or for the transport of RKN and their modules, with respect to the directions of use set forth in the specifications, will be next.

Direction I . Use WIG in the aerospace complex (WCC), which should ensure the delivery of ILV to the coastal base (for example, in Novorossiysk and Vladivostok) in the required launch area and launch space rocket carrying it at an altitude of 12.9 km and a speed of 700 -900 km / h.

Prior to the operation of delivery is the exploration and laying of tracks, its navigation software and computing range. It should seek to make the most of the route passes over the sea that ensure the greatest possible range, because flight will take place in screen mode.

Loading ILV and its docking with the container and the WIG-bearer should be made in the coastal shore-based facilities. Then start with a winged produces water with blowing and flies at the screen or outside at a height of 6000 meters, depending on the range and nature of the terrain (sea, mountains, plains).

If the launch area ILV removed from the launch area to a distance greater than the winged its range (4500-7000 km), an intermediate dressing.

Intermediate filling WIG can be made with the vessel afloat refueling tanker, or WIG, or in flight - from aircraft or winged-tanker.

The latter method is preferable to fill for many reasons, primarily because during refueling in flight from the screen, airfoil can carry significantly more fuel than afloat. Because his flight weight to a much lesser extent, limited strength, and thrust-weight ratio than the take-off weight at the start of a rough water surface.

In the area of ​​missile launch, which can be located both at sea and on land, winged leaves, picking up a given height in the final segment of the flight.

Under its own engine airfoil number 1 and number 2 can recruit the ceiling and provide a start at an altitude of 6000 m. The winged number 3 has a ceiling of 5000 m.

When underworking LRE mounted on containers or on RCN, airfoil can perform launches from a height of 12,000 m.

Filling ILV fuel placed in containers made at the final stage of the climb for 5 minutes before the start.

Branch of the winged space rocket carrier seems appropriate superintendent, a thief in two flavors: hot, ie, with the engine running ILV, and cold, when engines are started ILV after its separation from the WIG. Because technically very difficult to pitch in the WIG 25 ° or more, it seems appropriate to study the rotation of ILV in a vertical position in the separation process or after it. Rotate ILV in flight can be accomplished using aerodynamic surfaces (lattice wings) mounted on it, or using a parachute system, fire back after the launch rocket engines.

In both cases, should be excluded effects on winged jet engines ILV and significant longitudinal moments, breaking balance and stability of winged flight.

Start by parking winged space rocket on the ground can be performed under the condition that the total mass and size of the ILV will not exceed the allowable for this type of WIG. It will probably be possible to start on the ground RCN-3 with a WIG number 2 and number 3 and the launch of ILV-2 with a winged number 3. Possible and an option when a device for verticalization and start-up (eg, ILV-1 with a winged number 3) is delivered to the launch area or other WIG vehicle.

Direction II. Use of WIG in the mobile space-rocket complex (MRKK), when a series of WIG provides delivery to the desired area with access to the shelving shore, launch vehicle, launch the necessary ground equipment deployment in the area starting position, preparation and launches ILV. For this pre-explored and selected flight path, to make its navigation software, the place of intermediate fuel and gas stations WIG landfall. In this case, the starting point of the flight may be water or a water area of relatively flat land surface length of 3-5 km (including those covered by ice and snow) in the vicinity of the manufacturers or near shore technical complex.

Terminals flight in near-equatorial zone must have a water area of ​​3-5 km in length to seat WIG and explored the site for landfall. The site should have a slope of no more than 5 ° and not have sharp rocky inclusions that can damage the elastic bellows WIG. The best type of soil at the site exit - loam, clay, supeschanik.

The proposed three sizes WIG weight of 1100, 1900, and 3500 tons will provide solution to the problem: a year-round transportation of modules weighing 300, 500, and 1000 m from the main base MRKK in the launch area, a remote at a distance of 12000 km with intermediate dressing.

Direction III. The use of WIG for year-round transportation of goods - RCN blocks with factory - in Samara and Moscow to Baikonur and Plesetsk launch site, as well as the ports of St. Petersburg, Novorossiysk, Severodvinsk and Vladivostok. Landing and takeoff of WIG in the factory in Samara can be made: in the summer - the waters of the Kuibyshev Reservoir, and in winter - in the surrounding steppes of Samara.

Takeoff and landing WIG in the areas of sea ports can be made on the water. Landing in the WIG Baikonur must be done to spy out fairly flat area adjacent to the spaceport steppe, 3.5 km in length, both winter and summer.

The main route WIG in this case the use will take over the land at a height of 4-5 km. The average length of runs is 2000 km, excluding the route Samara - Vladivostok.

Direction IV. Use of WIG for delivery ILV (Energia, Energia-M), and other goods from the shore and technical complex, for example, in Novorossiysk and Vladivostok, a floating launch platform in a space-rocket complex sea-based (RAC MB) will include the loading on the winged space rocket tools onshore technical system (such as gantry cranes), breaking-in ekranoplans, delivery to the floating platform, and unloading means mounted on the platform.

Much of the route will pass over the sea in a screen of the flight.

Upon delivery of ILV with onshore technical complex, located, for example, in Novorossiysk, on the floating launch platform located in the equatorial Indian Ocean, the length of the flight path will be 5500-6000 km, 3300-4000 km of which will be held over the sea mode, the display of flight .

Time of flight in this case is 8-10 hours. Require an interim dressing in the Gulf region.

Following points were made on the possible use of WIG in the proposed "national economy"

Transport problems:

- Transport of large chemical reactors, petrochemical equipment with a high degree of readiness of manufacturers to their areas of assembly and installation, including delivery of bulk petroleum equipment in place of the construction of oil platforms offshore;

- Delivery of fresh fish from remote areas of fishing on fish processing plants.

Rescue tasks:

- Rescue crews and passengers of ships in distress in remote areas of the world's oceans;

- Providing emergency humanitarian assistance, including medical supplies, food, rescue equipment and prefabricated temporary housing in areas of major natural and environmental disasters;

- Spill containment and collection of oil from the sea surface.

Working with NPO Energia to study the feasibility and advisability of using large WIG to create a space-rocket complex mobile home was a good opportunity to evaluate the effectiveness of the vortices for creation of start-lander of the WIG. According to the same requirements specification, by which, carried out study the "three heroes", the fourth study was performed WIG weighing 5000 tons with a vortex blowing.

Side skeg winged, they are also - the center-wing end plate, they are the same, housing for the crew and equipment included in its central part, the vortex tube. Near these pipes in the center section, has six starting bypass turbofan engines NK-44 thrust of 40 tons exhaust gases and compressed air from both the contours of these engines were sent to the nozzle of the vortex tube through the ejector mixer. Ejection of air provided to increase consumption and reduce the temperature supplied to the vortex tube gas-air mixture. The total pressure of the mixture should not exceed the pressure in the air cushion - the specific load on the center section.

Starter motors and ejector mixing chamber were eliminated in the center section, and have individual air vents, closed in flight and opened at the start and landing.

In the figure, this launch system is not shown because drawing was intended for preliminary contacts with potential customers and had to keep the know-how.

Buoyancy provided WIG achieved through displacement of the central plane. Skeg in its creation almost did not participate, except for the planing of the extremities.

Even with the visual comparison of the two displacement WIG 5000 and 3500 tons, it is evident that the resistance to be significantly different in favor of the first, not to mention the quality blowing.

The location of the main engines on the wing, top, provided the discharge of consoles from the bending moments in the flight and can organize the airflow of the upper bow of the consoles in order to increase the lift coefficient at launch and landing, the same AN-72 and AN-74.

In general, this arrangement was more concise in terms of aerodynamics, and had a smaller bending moments on the shell-skeg than moments from the staggered to the pylons of the masses engines. Because it start the engines were located inside the center section so that they create massive force unloaded center-and not load it through the pylons and the shell-skeg like WIG № № 1-3.

Aerodynamic quality of the flight, excluding the positive impact of lateral vortices, the WIG with vortex blowing was equal to 20.3 against 16.5 in WIG № 3 with the same payload, located in the center section, which provided 22% more range.

Intakes of starting motors and ejector located on the upper surface of the center section, it would have sucked the air, increasing dilution and, thus, increasing the lift on the transition and the starting and landing. Boundary layer suction that occurs when the engine contributes to prolonging the regime of laminar flow over the center-to large-angle and speed.

The location of the aileron, flaps and spoilers on the ends of the console more scope for WIG № 4 enhances directional stability and handling, including the roll over ekranoplans № № 1-3.

Exemption-skeg hull of the pylons with engines improves visibility from the cockpit.

However, one of the main advantages Aerohydrodynamic layout (AGDK) WIG № 4, apart from improving the aerodynamic qualities, was the elimination of the destabilizing actions pylons large area, located on № № 1-3 ekranoplans far ahead of the center of mass, which required a significant increase in the area of ​​horizontal tail.

Another advantage was, as already said, removal of the longitudinal bending and torsional moments of the separated mass of engines and pylons.

Improved alignment of WIG and its handling and eliminates the need for pumping fuel in the aft (in the tail) when flying empty.

Here is a winged number 4 and the proposed 5 January 1993 the Director General of SEC CDB Chubikovu BV as a basis for joint development with the U.S. military cargo WIG. Further events are already known to the reader. Followed by an order of reprimand and the threat of dismissal.

However, publications in foreign press about ekranoplans, initiated by the leadership of CDB, continued, and Americans writing to me went unanswered.