RU2749908C1 - Step space rocket - Google Patents

Abstract

FIELD: rocket and space technology.SUBSTANCE: invention relates to rocket and space technology and can be used in interplanetary flights including the stages of releasing the stages of the rocket and delivering payloads (PL) to passing celestial bodies. The space rocket comprises a last stage (1) with a sustainer engine (2), two or more stages separated therefrom, e.g., the first stage (3) for launching from a planet (7) and the second stage (4) with sustainer engines, respectively (5) and (6), and at least one landing module for delivering the PL to a celestial body. The detachable stages (excluding the first stage) are made structurally and functionally combined with the landing modules into traction and landing complexes with engines common for the stages and the modules, e.g. (4) - (6). At least some of the described complexes are made non-returnable.EFFECT: technical result of the invention is aimed at improving the technical and operational characteristics of multistage space rockets.1 cl, 3 dwg

Description

The invention relates to rocket and space technology and can be used in interplanetary flights, including long expeditions with intermediate stages of dropping rocket stages and delivery of a payload to "intermediate" celestial bodies as they move along the trajectory.

Known stepped missiles, as a rule, two- and three-stage, in which additional (in addition to the last in the block with the landing module) stages are exclusively accelerating, i.e. equipped with additional engines, while as the rocket moves along the route (trajectory), "spent" booster stages are sequentially separated [1. Grabin B., V., Davydov O.I., Zhikharev A.A. and others. Fundamentals of designing spacecraft carrier rockets. - M .: Mechanical Engineering, 1991, Ch. I "Methodological foundations for the design of launch vehicles." - P. 14; 2. RU 176695 U1, VGR F42B 15/12, 25.01.2018; 3. RU 2013148842 A, IPC B64G 1/12; В64С 39/00, В64В 1/30, 06/07/2013; 4. RU 2595092 C1, IPC B64G 1/00, 08/20/2016; 5. RU 2643082 C1, IPC B64G 1/10, B64G 1/14, B64G 1/64, 30.01.2018].

A typical example of such a rocket is a stepped space rocket adopted as the closest analogue (prototype) of the claimed invention, containing the last stage with the main engine, at least one detachable stage with an additional engine and a landing module with its own engine [6. Feodosiev V.I. Fundamentals of rocket flight techniques. - M .: Ch. ed-tion fiz.-math. Literature "Science", 1979, ch. II B64G 1/16 devices for long-range ballistic missiles and launch vehicles ”. - S. 64-65].

In them, the last (as a rule, the head) stage, in principle, can act as a descent module (vehicle), if this is provided for by the purpose and program of the expedition.

However, as in the analogs listed above, the "spent" booster stages (first, second, etc.) are essentially thrown away. The first stage, as a rule, upon separation from the second, falls to the Earth, at best burning up in the dense layers of the atmosphere. The second and further stages, with a multi-stage (N stages) scheme, for an indefinite period turn into "space debris", sowing threats to spacecraft. At the same time, the descent vehicles carrying the payload (crew, instruments, etc.) are equipped with their own engine designed, at least, for maneuvering and braking in the gravitational field of the final or "intermediate" (along the trajectory of the rocket - the route of the expedition ) of a celestial body (planet, satellite, asteroid). This leads to the overestimated mass and dimensions of the rocket as a whole: the "ejected" stage is no longer used body, engine, fuel tank (containers) and other equipment. This means - insufficiently high technical and operational characteristics (capabilities) - TEH (V) - stepped rocket. Moreover, the more steps and descent vehicles (long-term expeditions), the more these disadvantages are manifested.

The task (problem) solved by the claimed invention is to develop a device (stepped rocket) with increased TEH (B).

The technical result, in accordance with the task, is achieved by the fact that in a stepped space rocket containing the last stage with the main engine, at least two detachable stages - the first and the second, each with an additional engine and at least one landing module with its own engine, in accordance with the claimed invention, the detachable stage of the rocket, with the exception of the first, and the landing module are structurally and functionally combined into an indivisible traction and landing complex with a common engine for them, with the possibility of sequentially performing the functions of the said detachable stage and the landing module.

A particular set of essential features of the device is also aimed at solving the problem posed within the framework of the main set of its features, formulated in the previous paragraph and in the claims, namely:

- with the number of N stages, the rocket can contain N-2 landing modules (this optimizes the technical result by adopting the traditional scheme with the early, at the Earth, separation of the first stage, which makes no sense to combine with the descent module);

- the lander can carry a payload for its delivery to the surface or orbit of celestial bodies (this gives additional advantages in two special cases of using descent modules-vehicles - according to the "maximum program" with pronounced scientific and other equipment, up to habitability, with alternative passive - for "disposal" of the spent stage);

- at least part of the mentioned traction and landing complexes can be made non-returnable (this is rational in terms of “fuel efficiency and is recommended mainly for multi-stage, long-term expeditions).

Thus, the main idea inherent in the declared project is the dual functionality of intermediate stages, the use of not only as intermediate (located behind the last stage) sustainer stages, but also (with incomplete fuel production in the specified mode) as descent modules (vehicles) at intermediate stages of the flight of the entire rocket-"train" (expedition).

Among the array of known devices, such devices have not been found, the set of essential features of which would coincide with the declared one. At the same time, it is due to the latter that a new technical result is achieved, which determines the presence of the qualification feature of the claimed device “world level of novelty”.

For all its brevity of the wording, the set of distinctive essential features of the claimed device is not a simple sum of the known technical results of using separately known system components. There is a "supereffect" (in the patent meaning of this term), which is not obvious to a specialist from the state of the art achieved (of course, before considering the proposed technical solution). With the above spectrum of TEV. This convincingly demonstrates the inventive step of development as the second of the triad of qualifying features of the invention.

The third qualification feature - industrial applicability - is also indisputable and follows, first of all, from the same rich experience in creating products for the rocket and space complex.

The essence of the invention is disclosed in more detail in the example of implementation given below - for a three-stage rocket with one descent module.

The device is illustrated by drawings (diagrams) of FIG. 1-3:

in fig. 1 shows a simplified design of a three-stage rocket (an example of a stepped rocket with the number of stages N = 3), side view, where F1 is the thrust generated by the first stage traction motor (not combined with the descent module);

in fig. 2 schematically shows the process of transition of thrust functions from the "exhausted" first stage to the second stage (combined with the descent module);

in fig. 3 - the process of separating the second stage and its autonomous movement due to its own engine with traction force F2 * (possibly corrected in magnitude and direction) as a descent module with a payload to the "intermediate" celestial body, and meanwhile continuing the movement of the first (main ) the rocket stage further under the action of the traction force F3 of its engine.

The stepped space rocket contains the last stage 1 with the main engine 2, at least two detachable stages - the first 3 and the second 4 with additional engines, each - 5 and 6, respectively, and at least one landing module (apparatus) with its own engine.

The second detachable stage 4 of the rocket (and others between it and the last stage 1, if any) and the landing module (s) are structurally and functionally combined into an indivisible traction and landing complex (respectively, under positions 4, 6) with a common engine (6), with the possibility of sequentially performing the functions of the mentioned detachable stage 4 and the landing module (also under position 4).

The further description applies to particular, recommended as rational, cases of implementation of the claimed device.

With the number of N stages, the rocket can contain N-2 landing modules. In the depicted three-stage rocket example, there is only one (3-2 = 1) landing module (apparatus) 4.

Lander 4 can carry a payload for its delivery to the surface or orbit of celestial bodies.

At least part of the mentioned traction and landing complexes (4) can be made non-returnable.

The inventive device operates as follows (method of operation of the device).

The rocket, having started on the surface of the Earth 7, "traditionally" rises with acceleration, overcoming the gravity of the Earth and the resistance of atmospheric air, due to the thrust F1 of the engine of the first stage of the rocket (see Fig. 1).

Having spent the fuel, the first stage 3 is separated from the rocket and passively falls on the surface of the Earth 7, partially or completely burning up in the atmosphere. Also "traditional" (not shown).

The second stage of the rocket movement is characterized by the thrust effect F2 of the additional engine 6 installed on the second stage 4 (it is also the descent module (4), and the mentioned engine 6 is the engine (6) of the descent module (4)). But while this structural part of the rocket performs the function of the second, traction stage 4 of the rocket (see Fig. 2).

When the rocket moves near the "intermediate" according to the flight program, the celestial body 8, the second stage 4 is separated and directed towards it (automatically, by the commands of the crew in the first stage 1 or in manual mode by the crew of the second stage 4, if available), when corrected ( in magnitude and direction) traction force F2 * and the first (main) stage 1 of the rocket moves further along the trajectory due to traction force F1 of the main engine 2 (see Fig. 3).

When the number of rocket stages is greater than N = 3, two, three, etc., are possible, in the image and likeness, respectively. separation and dispatch "to the left", - to celestial bodies on the example of body 8, - descent modules (vehicles) 4, etc. in the amount of N-2.

The technical result consists in improving the TEC (B), including reducing the total weight and dimensions, increasing the fuel efficiency of the rocket. Thus, the use of the proposed device solves the problem.

Claims (1)

A stepped space rocket containing N stages, of which one is the last, and the rest are detachable, while N-2 detachable stages, with the exception of the first, are structurally and functionally integrated into traction and landing complexes with landing modules for delivering the payload to the surface celestial bodies with common engines for the steps and modules, and at least part of the mentioned traction and landing complexes are made non-returnable.

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