WO2024054197A1

WO2024054197A1 - Rocket plane (embodiments)

Info

Publication number: WO2024054197A1
Application number: PCT/UA2023/000042
Authority: WO
Inventors: Володимир ЯРОШОК; Александра ЯРОШОК
Original assignee: Володимир ЯРОШОК
Priority date: 2022-09-05
Filing date: 2023-08-18
Publication date: 2024-03-14
Also published as: UA153114U

Abstract

The invention relates to space engineering and can be used in the creation of a suborbital rocket plane with substantially vertical takeoff and landing. A rocket plane comprises a body (1), movable front and rear aerodynamic control surfaces (2 and 3, respectively) attached to the sides of the body, and controllable rocket engines (9). Extending along the entire length between the movable aerodynamic control surfaces (2, 3), in an amount of one on each side of the body (1), is a controllable narrow lateral longitudinal wing (4) which is movably attached by its leading part and which has an aerodynamic supersonic bump (5) attached along the entire length of the underside thereof. In a second design embodiment, the rocket plane comprises a body (1) with controllable rocket engines (9), wherein extending along the entire length of the body (1), in an amount of one on each side thereof, is a controllable narrow lateral longitudinal wing which is movably attached by its leading part and which is transversely divided in the middle into a front and rear controllable narrow longitudinal wing (12 and 13, respectively), each having an aerodynamic supersonic bump (5) attached along the entire length of the underside thereof.

Description

ROCKET PLAN (options).

A group of new technical solutions relate to space technology and they can be used to create a suborbital rocket plane with predominantly vertical take-off and landing.

Analogues are the well-known reusable space planes - rocket planes "Space Shuttle", "Buran", and others (Google: Wikipedia, Raketoplan), the disadvantages of which are the large weight and complexity of the design of rocket planes made according to an airplane design, the wings of which have a heavy structure due to power spars and these wings have a large load-bearing surface, and their lower part requires expensive thermal protection. All these disadvantages reduce the weight of the payload for launching a rocket plane into space and create the need for expensive launch vehicles for its takeoff from the surface of the Earth, and also create the need to use long landing strips to land it on Earth.

Elon Musk's STARSHIP rocket plane was taken as the prototype (Google: visual capitalist social media ROCKETS of the world), (Google: Wikipedia-SpaceX Starship (at the end of the text - notes: 106. Tarig Malik. SpaceX Test fires Starchip SN11 rocket prototype again aheod of next launch (English) Another video on the page)). Google: Aerodynamic control areas for rockets and rocket planes ... RU254670C1, 04/10/2015-guided rocket- ... in this patent look: RU185698U1, 12/14/2018 ... and type: RU2291381C1, 01/10/2007. The disadvantages of the prototype are: 1. Only vertical flight after launch from Earth to enter space, which requires a large consumption of rocket fuel components and does not allow increasing the weight of the payload for

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CORRECTED SHEET (RULE 91) launch into space; 2. Ineffective aerodynamic braking by the body of a rocket plane when descending in the Earth’s atmosphere.

A new positive technical result is an increase in the aerodynamic quality and a highly effective increase in the aerodynamic lift of the rocket plane, which reduces the consumption of rocket fuel components when the rocket plane takes off in a mixed mode - vertical take-off from the Earth, and further flight in the rocket plane mode in the Earth's atmosphere! (almost like an airplane). And also, this declared new layout of the rocket plane allows for highly effective braking with an aerodynamic body, instead of braking with rocket engines when descending in the atmosphere. All this makes it possible to further increase the weight of the payload for launch into space thanks to the new highly efficient aerodynamic layout of the rocket plane.

A new positive technical result is achieved by the fact that: 1. A rocket plane, which has a body with movable aerodynamic control planes attached to its sides at the front and rear and controllable rocket engines in the rear part of the body, which differs in that along the entire length between the movable aerodynamic control planes , one on each side of the body, a controlled narrow lateral longitudinal wing is movably attached to the front part, to the lower surface of which, along the entire length, an aerodynamic supersonic protrusion is attached; 2. A rocket plane, which has a body and guided rocket engines in the rear part of the body, is characterized in that along the entire length, along one on each side of the hull, a controlled narrow lateral longitudinal wing is movably attached to the front part, which in the central part is divided transversely into front and rear controlled narrow lateral longitudinal wings, to the lower surface of which one aerodynamic supersonic protrusion is attached along the entire length.

The declared new positive technical result is achieved because along the entire length between the movable aerodynamic control planes, fixed at the front and rear on the sides of the body, new controllable narrow lateral longitudinal wings are declared, which are movably fixed at the front along the sides of the rocket plane body.

At the same time, the claimed movable, controlled narrow side longitudinal wings, one on each side of the body, are provided with aerodynamic supersonic protrusions attached to their lower surface along the entire length, one under each wing. Such new wings in flight in rocket plane mode (almost like an airplane) create a powerful lifting force by placing them along the sides of the cylindrical body of the rocket plane in the zone of double the speed of the oncoming air flow, and when the double speed of the oncoming air flow increases to more than 1200 kilometers per hour, then on the longitudinal aerodynamic supersonic protrusions, located one under each wing, useful longitudinal air supersonic shock waves are formed, which compress and hold the incoming air flow, thereby creating an air cushion under the body, which further increases the overall aerodynamic lifting force of the rocket plane and turns all this into an ordinary rocket plane into a highly efficient rocket plane with increased payload and making it more economical and more environmentally friendly. With this new aerodynamic configuration, in airplane flight mode, the rocket plane does not go into a tailspin even during a vertical descent, so it is able to quickly change flight modes to more economically beneficial ones.

Fig.l shows a rocket plane viewed from above. Fig.2 shows section A-A in Fig.l. Fig.3 shows a rocket plane with controllable narrow lateral longitudinal wings, which are movably fixed in the front part, one on each side of the hull and along the entire lateral length of the hull, which in the central part are divided transversely into front and rear controlled narrow lateral longitudinal wings, to the lower surface of which one aerodynamic supersonic protrusion is fixed along the entire length. Fig.4 shows the B-B section in Fig.3. Fig.5 shows a rocket plane equipped with a wheeled landing gear with which it takes off and lands on the airfield runway. Fig.6 shows the rear view of Fig.5.

Fig.l shows a rocket plane in a top view, which has a body 1, movable aerodynamic control planes attached to its sides at the front 2, at the rear 3, and guided rocket engines 9 in the rear part of the rocket plane body 1. Along the sides of the body 1, the front part is movably fixed with the help of axes 11, which are indicated in Fig.2, controlled narrow side longitudinal wings 4 are fixed, to the lower surface of which, along the entire length, one aerodynamic supersonic vista 5 is attached. Pos. 10 indicates unguided rocket engines large power. H is the length of body 1. Fig.2 shows section A-A in Fig.l, on which along the sides of body 1 symmetrically on the right and left, one on each side of body 1, the front part is movably fixed with the help of axis 11. longitudinal wing 4, to the specially aerodynamically profiled lower surface of which, along its entire length, an aerodynamic supersonic wing 5 is attached. Pos. 7-zone of double speed of air flow flowing onto body 1 eo. When, when wrapping around the bottom of the housing 1 in zone 7, the air flow velocity Voo increases almost to the speed of sound, air supersonic shock waves 6 appear on aerodynamic supersonic shocks 5. Air supersonic shock waves 6 act as side ridges or winglets lowered down, which slow down the flow through them the incoming air flow Vco, thereby condensing the incoming air flow Vco, increasing its pressure and creating an air cushion 8 under the body 1. Designation b - width of the wings 4. Designation h - height of the wing 5. Moreover, the structurally aerodynamic supersonic wing 5 can be made of a longitudinal plate, which is attached to the lower surface of the narrow side longitudinal wing 4 at a right angle, or at a large angle. Also, the vistup 5 can be made as shown in Fig.2 and Fig.4, or the shape of its cross-section follows the narrow part of the Loval nozzle. Also, aerodynamic supersonic vistas 5 are attached to the lower surface of the narrow side longitudinal wings 4, or 12 and 13, at a distance from the outer edge of the wings, mainly in the range from 0 to 0.75b - its width. Fig.3 shows a rocket plane to the body 1 of which, one on each side, movably along the entire length a controlled narrow lateral longitudinal wing is attached to the front part, which in the central part is divided transversely into front 12 and rear 13 controlled narrow lateral longitudinal wings, to the lower surface of which along the entire length one aerodynamic supersonic vista 5 is attached. Also, to the lower rear part of the body 1 a supersonic aerodynamic vista 5 is attached for the appearance of air supersonic shock waves 6 on it. Fig.4 shows a section B-B in Fig.3, on which elevator shafts 14 are attached to the sides of the body 1 for the movement of cargo and people into the nose of the rocket plane, to which with the help of axes 11, controlled narrow lateral longitudinal wings 12 and 13 are movably secured, which, like the lower surface of the body 1, are provided with ceramic thermal protective plates 15. And position 16 shows the range of deflection of the controlled lateral longitudinal wings 12 and 13. At the same time, the movable controlled narrow lateral longitudinal krills 4, which are shown in Fig.l and 2, and pos. 12 and 13 in Fig.3, 4, 6, width b, no more than 0.01...1.OH of body 1, and supersonic aerodynamic projections pos.5, height h no more than 0.001...0.01N of body 1 and these size ranges are interconnected, from initial to initial, to final to final. But in general, the maximum values of the width of the krills around the values of b = 1.0H will be used very rarely; basically, it is necessary to use movable, controlled narrow lateral longitudinal wings 4, as well as 12 and 13, the width of which is close to half the radius of the body 1. In Fig.5 shows the layout of a rocket plane with a body 1 on a wheeled chassis 17 and 18, and indicates the angle 19 of inclination of the body 1 relative to the earth's surface 20 in the range of 15...35 degrees during takeoff and landing of the rocket plane. Also, takeoff can be performed using an additional wheel

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CORRECTED SHEET (RULE 91) platform, which remains on the ground after the rocket plane takes off. Fig.6 shows View A in Fig.5, where the controlled narrow side longitudinal wings 13, 12 and 4 in cross-section can have the shape of a body 1, and also shows the placement of controlled mobile rocket engines 9, unguided high-power rocket engines 10, and air jet engines 21.

The rocket plane works as follows. From the launch pad it takes off vertically and accelerates to a speed of 300-600 km/h, and the movable, controlled narrow side longitudinal wings 4 are installed almost perpendicular to the side surface of the body 1, as in Fig.2. Then, with the help of the controlled jet thrust of the engines 9, the rocket plane tilts the body 1 relative to the transverse axis to an angle of attack relative to the horizon of 15-60 degrees, like an airplane, and continues acceleration. And at this moment the oncoming air flow, having a speed Voo of more than 600 km/h, as in Fig. 2, in zone 7 on the sides of the cylindrical body 1 of the rocket plane, this air flow speed doubles to 1200 km/h ((Google: 2016_297_kaverinakm. pdf) in Table 2.1) reaching almost the speed of sound. And a further increase in the speed Voo ensures the appearance on the aerodynamic supersonic longitudinal protrusions 5 of the appearance of air supersonic shock waves 6, which slow down the flow of the incoming air flow through them, having a speed Voo, and act as ridges or E nglets, lowered down, which condense this oncoming air flow Voo, and increase its pressure under the body 1 of the rocket plane and on the lower surfaces of the controlled narrow side longitudinal wings 4 or 12, 13 and create

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CORRECTED SHEET (RULE 91) air cushion 8, as in Fig.2, which also increases the total aerodynamic lift. All this provides the rocket plane with an increase in load-bearing capacity and an increase in aerodynamic quality by 2-3 units, which reduces the consumption of rocket fuel components by half during flight stages in the atmosphere. This example is taken for the right angle of inclination of the air flow Voo , which impinges on the body 1 in Fig. 2, because it is most characteristic of a vertical descent in the atmosphere, when the cylindrical body 1 of the rocket plane lies almost parallel to the surface of the Earth. For smaller angles of attack of the air flow Vco , which impinges on body 1 in the flight mode of a rocket plane (almost like an airplane), the appearance of air supersonic shock waves 6 will occur at high speeds of the air flow Vco , which impinges on body 1.

The declared innovative layout of the rocket plane ensures the emergence and beginning of mastering the technical application of a new unique physical phenomenon - the creation of longitudinal air supersonic shock waves 6, which contribute to the creation and retention of an air cushion 8 under the body 1 of the rocket plane, and this air cushion 8, with its increased pressure, increases the effective aerodynamic load-bearing forces The quality of the rocket plane is doubled, and this is without any additional significant real heavy large load-bearing aerodynamic structural areas (wings), as required by rocket planes that are made according to the traditional aircraft design. In this case, longitudinal air supersonic shock waves 6 behave like useful phantoms and do not have any a rocket plane has no harmful weight and no harmful aerodynamic drag; when the flight speed increases, they appear, do their useful work, and when the flight speed decreases, they disappear into nowhere, until the next useful need...!

The low weight of the design of the claimed movable controlled narrow side longitudinal wings 4 is ensured by the fact that they do not require a heavy power element-spar, because they are narrow and directly with their front parts-spouts the movable controlled narrow side longitudinal wings 4 are attached to the power body 1 of the rocket plane. And reducing the weight of the rocket plane structure increases the payload, and allows the rocket plane to fly in the atmosphere and into near space independently without the help of a heavy, expensive first stage launch vehicle. At the same time, the movable, controlled narrow side longitudinal wings 4 create a large lift force, due to the fact that they are located in the zone of doubling the speed of the oncoming air flow V©©, pos. 7 in Fig. 2, and taking into account the fact that in the formula the aerodynamic lift force increases on the speed of the incoming air flow squared, then the required aerodynamic area of the wings decreases several times and at the same time these small wings provide a large lift force sufficient for the flight of a rocket plane.

List of advantages of a rocket plane with new krills:

1. The wings are technologically very simple to manufacture, have small dimensions and very light weight.

2. Krills almost do not increase the drag of the rocket plane. 3. An air cushion under the body reduces the thermal load on the body when the rocket plane enters the Earth’s atmosphere from space.

4. The rocket plane does not go into a tailspin during a vertical descent.

5. During takeoff and landing, these new wings are lowered down and pressed against the body of the rocket plane, thereby protecting the thermal protection tiles on the body from damage by the “sticks” of the launch tower.

6. Significantly saves rocket fuel components when flying in rocketplane mode (like an airplane), as well as when braking the body with new wings in the Earth’s atmosphere.

7. Increases volatility by increasing the aerodynamic quality to 2-3 units, which reduces the consumption of rocket fuel components in flight in the atmosphere in rocket plane mode (like an airplane) by up to two times.

8. During the flights of thousands of such rocket planes, the savings will amount to millions of tons of rocket fuel components.

9. If you look at the rocket plane from above or below, during its flight in humid air, then the lower longitudinal air supersonic shock waves near it have a variable color with a torn edge (like the feathers of a bird), this makes it look like the PHOENIX bird.

Claims

FORMULA

1. A rocket plane containing a body, movable aerodynamic control planes attached to its sides at the front and rear, and controlled rocket engines in the rear part of the body, is characterized in that along the entire length between the movable aerodynamic control planes, one on each side of the body, is movably fixed at the front a partially controlled narrow lateral longitudinal wing, to the lower surface of which, along its entire length, an aerodynamic supersonic protrusion is attached.

2. A rocket plane containing a body with controllable rocket engines in the rear part of the body, which is characterized in that along the entire length, one on each side of the body, a controlled narrow side longitudinal wing is movably fixed at the front, which in the central part is divided transversely into the front and rear controlled narrow lateral longitudinal wings, to the lower surface of which one aerodynamic supersonic protrusion is attached along the entire length.