RU2568630C1 - Space rocket and method of its landing (versions) - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: claimed space rocket comprises rocket engine and payload. Note here that shuttle rocket features the ogive cone shape with the blunt refractory part at the cone base while fins, or pylons, or engines are secured to the payload by controlled detachable attachment. Space rocket comprises shuttle payload with wings which double, as-folded, as the cargo compartment covers. Cargo hatch on the payload one side is closed by two covers sliding toward each other and turning relative to relative to the axes crossing the lengthwise axis to make the wings. Rocket landing process consists in landing on the water at "cone downward" position. Note here that gas pressure is increased inside the payload by, particularly, water evaporation.

EFFECT: better controllability of payload at landing.

7 cl, 2 dwg

Description

The invention relates to missiles, mainly space and strategic combat.

Known space rocket, consisting of an engine / engines and payload, US Pat. №РФ 2233772. However, some design solutions are not optimal.

The objective and technical result of the invention is to save the mass of the rocket and the descent vehicle.

OPTION 1. With the invention of the open-frame engineless engine, the need for reusable systems has practically disappeared, since there is nothing to save for reuse - there are no expensive missile stage bodies, there are no complex, powerful and expensive liquid engines. And of the disposable parts - only a simple and small (approximately 0.3-0.5% of the volume of the rocket) tank for liquid fuel of the auxiliary engine and, possibly, a fabric fairing. The main engine, which consists of 99-99.9% solid propellant fuel, as it should be, burns down (this is another advantage of such an engine - space is not contaminated with space "debris"), and fuel also burns from a taxi tank or taxiing solid fuel engine .

But darker less, if the payload is returned, then you should first determine the location of the reusable device. The present invention proposes an arrangement that is unconventional for reusable devices: a reusable device has the shape of a lively cone with a blunt, heat-resistant part at the base of the cone (practically the shape of a projectile). That is, in such an apparatus it is impossible to name where - before, where - back. The device takes off with a sharp end forward and upward, flowing well aerodynamically (which, by the way, compares it favorably with the Shuttle, Buran and other existing and planned devices). In space, "front" and "rear", of course - no. And the apparatus lands, exposing an almost flat thermally protected base of the cone - a kind of shield, and preferably replaceable (disposable). And from these considerations, the PGO (front horizontal tail, in the terminology of aviation), it is convenient to place in the front (along the flight of the rocket) part of the payload. That is, when landing, it will become a ZGO (posterior horizontal plumage). The fact is that the aerodynamic scheme "Regressive weathervane duck" according to US Pat. No. RF 2410286 has one feature - it works equally well when flowing around both “front” and “rear” - the all-turning plumage, obeying the slip sensor command, simply rotates 180 degrees and continues to work as if nothing had happened. Only the control action must be changed from “+” to “-“, which is easy to do with remote control using a toggle switch.

That is, such an apparatus, if covered with a heat-shielding composition and steering pylons (for example, pyrographite modified by neutron irradiation), will be easily controlled when descending at high temperatures in pitch, roll and, in terms of pitch and roll, in direction. You don't even need a keel or its semblance. Although if you apply three or four steering, then one or two of them will be just keels. The device can enter the atmosphere, heat up, and then leave it in order to cool. And so several times. Or, having put two feathers a little with scissors, you can twist the device for stabilization when descending on a “hot” section of the trajectory.

OPTION 2. For all available and designed reusable devices, wings are provided, moreover, they can not be retractable or changeable in geometry. This affects the streamlining and increases the mass of the device. The proposed rocket reusable payload (MKK) has wings that serve when folded lids of the cargo compartment. Moreover, two sub-options are possible here:

OPTION 2a. The missile has a cargo hatch on one side of the payload, which is closed by two moving covers, rotating relative to the axes, intersecting with the longitudinal axis and serving as wings.

OPTION 2b. The missile has two cargo hatches opposite each other (that is, a through compartment), and each of them is closed by one lid that rotates about an axis that intersects or is perpendicular to the longitudinal axis of the missile, and serves as wings. At the same time, the wings become in an unusual position - one wing - as the upper wing, and the other - as the low wing, but this, with appropriate tuning, will not interfere with their stable operation. But the area of the wing (“wings”, as inaccurately said by non-specialists) in this sub-option doubles. True, the stiffness of the fuselage of the IWC is slightly reduced.

Since the cargo compartment at the same time becomes a well without a bottom, then if there is something large in it, then it is tied to the lodgements, and small objects are cleaned in lockers.

OPTION 2c. At the same time, the rear end of the cargo compartment slows down the incoming flow, so its parts between the flaps are fixed with the ability to deviate into the compartment, and the compartment itself is closed with a shutter made of high-strength material (for example, zylon, dima, spectra, vectran, carbon fiber).

OPTION 3. However, the parachute system having an unconventional soft landing device (see the separate invention “Parachute landing system”), a resettable heat-shielding brake shield and landing in water in the “cone down” position will have the smallest “dead” load. The Americans are not fools to put their Apollo into the water - so they saved on a soft landing rocket device. It is necessary to select 2-3 places with small shipping and good weather in the waters of the globe and put ships there.

In order to prevent the cone from being crushed by a shock of water, it is necessary to raise the pressure inside the MCC to 2.25 atmospheres before landing (it is this drop that the human body can easily transfer when the apparatus is depressurized). If a person is not inside, then more. Moreover, the pressure can be increased by evaporation of water, if the descent payload can withstand a temperature of about 150 ° C.

When landing with a “cone into the water”, rudders, keels, pylons and brake engines are in the bow of the MKK and therefore can destabilize the entrance to the water. To avoid this, they must be resettable, that is, attached to the payload by a controlled detachable mount.

In FIG. Figure 1 shows the landing of the MKK on two wings 1, which make up one upper lid of the cargo compartment of the ship 2. The wings are shown in the unfolded state with a sweep angle of about 85 degrees along the leading edge, the weathervane duck 3 is turned in the opposite direction and plays the role of a rear V-shaped plumage. By adjusting the sweep of the wings, you can change the position of the aerodynamic focus. Ailerons are desirable on the wings.

In FIG. 2 shows the parachuting landing in water, where 2 is the IWC with the heat shield shielded.

The rocket works according to option 1 as follows: after entering the orbit, the IWC performs a flight program, then it brakes and enters the atmosphere with its blunt end. Reducing the speed below the temperature barrier, wings 1 are released, and the IWC goes into a horizontal or decreasing flight, followed by a horizontal landing.

According to option 3, the IWC during landing after testing brake engines resets them in space. As it decreases after a decrease in speed below the thermal barrier, the IWC makes a cabling and resets the heat shield and rudders and keels. Then it releases a parachute, preferably adjustable, which allows smoothly increasing the braking force from zero to 100% (see US Pat. No. RF 2343090), and approaches the water. Before entering the water, on the command of the radio altimeter, a soft landing device should work (a separate invention - application No. 2013136180), which will slow down the MCC to zero speed 1 m from the water and then lower it at a speed of 1-2 m / s until it comes into contact with water.

An abnormal case is provided - the soft landing system did not work. Then the IWC will crash into the water at a relatively high speed. But if the astronauts will be in anti-boot devices, US Pat. No. 2400403, then they will not suffer. It remains only to prevent them from drowning in the broken IWC, for which they should use individual breathing apparatus and, of course, arrange quick help. Before parachuting, anti-overload devices (chairs, lodgements) should be deployed 180 degrees from the take-off position to the landing position (in zero gravity this is easy).

Claims (7)

1. A space rocket containing a rocket engine and a payload, characterized in that the reusable device has the shape of a life cone with a blunt heat-resistant part at the base of the cone, and the rudders, or pylons, or engines are connected to the payload by a controlled detachable mount. 2. A space rocket containing a rocket engine and a payload, characterized in that the reusable payload has wings that serve when folded lids of the cargo compartment. 3. The rocket according to claim 2, characterized in that it has a cargo hatch on one side of the payload, which is closed by two moving covers that rotate relative to the axes intersecting with the longitudinal axis and serving as wings. 4. The rocket according to claim 2, characterized in that it contains two cargo hatches opposite each other, and each of them is closed by one lid that rotates about an axis that intersects or is perpendicular to the longitudinal axis of the rocket, and serves as wings. 5. The missile under item 2, characterized in that the parts of the rear end of the cargo compartment between the wings are fixed with the ability to deviate into the compartment, and the compartment itself is closed with a shutter made of high-strength material. 6. A method of landing a rocket, characterized in that it lands in water in the "cone down" position. 7. The method according to p. 6, characterized in that the gas pressure rises inside the payload before landing, in particular by evaporation of water.

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