RU2219464C1 - Tubular booster - Google Patents

Abstract

FIELD: mechanical engineering, in particular, propulsion units for rapid propelling of rigid bodies. SUBSTANCE: the propulsion unit is positioned in combustion chambers formed by interchamber partitions and made for changing of their volume. The combustion chambers are connected an electric circuit. The means for initiation is made in the form of electric primers installed in the propellant charge. The combustion chamber closest to the outlet from the body is designed for dynamic locking of the latter and is provided with a locking partition. EFFECT: enhanced mass of the propelled body and the range of its flight. 3 cl, 3 dwg

Description

 The invention relates to the field of engineering, namely, devices for throwing by simultaneous "simulation" combustion of a combustible substance intended for high-speed throwing of solids, and can be used to create propulsion systems in designs for both sharply increasing dynamic loads (shells, missiles), and for smoothly increasing dynamic loads (space transport systems).

In determining the level of technology, publicly available information was used that is provided in the following sources of information:
published descriptions of title documents, applications for inventions;
Soviet and other publications available in the library;
messages transmitted via radio, television, cinema, etc.

 As a prototype adopted a tubular accelerator according to patent RU 2072501.

 An analysis of this information showed that the well-known, widely used propulsion systems (rocket-propelled jet propulsion systems) make it possible to accelerate solids in space to speeds of 7.9-16.67 km / s (1st, 2nd, 3rd I am cosmic speed). In the lower atmosphere up to 3000 m / s (up to 10 M).

 The disadvantages of such propulsion systems should include a fairly large fuel consumption, therefore, a large mass of the structure as a whole. So, to achieve space speeds, the ratio of the charge weight to the weight of the propelled body (payload) is up to 1 \ 500, which significantly increases the complexity of the design (weight, volume, overall dimensions), significantly increases the time of manufacture and maintenance, and, accordingly, the overall the cost of the product with the entire infrastructure. In addition, the types of fuels and oxidizing agents used have a strong effect on humans, including maintenance staff and environmental ecology, which, accordingly, complicates their production, use and disposal.

 The objective of the invention is the creation of a tubular accelerator (TU), which will allow you to smoothly run the product, increase the weight and volume of the payload and reduce the weight of the propellant charge in relation to the weight of the propelled, simplify the design as a whole, use a type of fuel that is gentle for humans and the environment. Increase the range and flight speed of products corresponding to the payload of existing analogues. Reduce the cost of products at all stages of manufacturing and operation in the performance of tasks similar to those existing at this time.

 The technical result that can be obtained by using it is that the fuel energy efficiency per unit of payload is increased, thereby reducing the characteristics (weight, volume) of the structure as a whole to perform similar tasks, which makes it possible to build products on a compact basis.

 The solution to this problem is achieved by the fact that in a tubular accelerator, which contains a housing with a payload placed in it, a propulsion charge and initiating means, the propulsion charge is placed in the combustion chambers formed by inter-chamber partitions and configured to change their volume, while the combustion chambers are connected electric circuit, the means of initiation is made in the form of electric igniters installed in the propulsive charge, and the combustion chamber, which is extreme to the exit mentioned The casing is designed for dynamic locking of the latter and is equipped with a locking partition.

 In addition, the number of combustion chambers is two or more.

 The casing of the tubular accelerator is made in the form of a cylindrical glass with an increase in its outer diameter to the location of the propulsion charge.

 The essence of the proposed specifications is shown in FIG. 1 and 2. TU consists of a casing, which is a hollow metal pipe with a bottom (glass) (1), a fuel tank for a moving charge (5), a combustion chamber (6a, 6b, 6c) with a volume regulator (12) in the working cavity (4), propulsion charge (8) in the shell (9) with adjustable electric igniters (7) complete with an ignition regulator (11) connected to the electric circuit, the locking partitions (2) and the payload (3) in the housing (1); the combustion chambers (6a, 6b, 6c) are separated by inter-chamber partitions (10).

 The casing (1) with a payload (3) is accelerated using a propulsion charge in the casing (5), the design of which ensures the sequential actuation of the propulsion charge (8) in the working cavity (4) and, accordingly, the gradual acceleration of the casing (1) and the complete combustion of a combustible substance propellant charge (8) from adjustable igniters (7), placed in adjustable combustion chambers (6a, 6b, 6c), in which the device is not yet destroyed due to explosion from pressure overload.

The propellant charge placed in volume-controlled combustion chambers with adjustable electric igniters corresponds to the condition of the burning rate:
n <n (s); n (s) = V / V (m); n = n (s) -n (s) K, where:
n is the number of adjustable electric igniters;
n (s) is the number of electric igniters corresponding to the explosion;
s is the burning rate corresponding to the explosion,
V (m) is the ignition volume of the propellant charge from one electric igniter per unit time;
V is the volume of the entire shell of the propellant charge;
K - coefficient from 0.4 ~ 0.9 is set depending on the tasks to be solved, divided among themselves by inter-chamber partitions and connected by an electric circuit; a missile body, consisting of a payload and a body in the form of a pipe, with a bottom (glass) of metal, the length of which corresponds to the condition
L = L (d.sar) + P L (burnout), where
L is the total length of the pipe channel (depth of the glass);
L (d.zar) is the maximum length of the shell of the motive charge;
L (combustion) is the channel length corresponding to the complete combustion of a combustible substance of maximum charge;
P - coefficient from 2 to "C" to stabilize the flight of a missile;
"C" - pressure of the products of complete combustion of a combustible substance from igniters in an amount n, corresponding to the pressure during complete combustion of a given combustible substance from one igniter;
L (d.sar) = L (c.sgor) n + L (mp) n, where
L (combustion) - the maximum length of the combustion chamber;
n is the number of combustion chambers from 2 to n - depending on the tasks;
L (mp) is the thickness of the interchamber partition.

 To simultaneously initiate electric igniters with an ignition regulator are connected to an electrical circuit. The characteristics of technical specifications vary depending on the tasks to be solved, by changing all structural elements tied into a single whole.

 In the proposed TU, the acceleration of the missile body is carried out by filling the tube (cup) with a propulsive charge divided into adjustable combustion chambers with several adjustable igniters, which made it possible to smoothly increase the velocity of the propelled body when compressing the propulsion charge (decreasing the ratio of the charge weight of the combustible substance to body weight), reduce the length of the acceleration channel, reduce the total weight of the structure, increase the size and weight of the missile body, increase the length of the flight path after exiting the acceleration channel.

 The proposed device operates as follows.

 After the electric power is supplied through the ignition controller (11) to the “TUSS K” with the help of series-connected adjustable electric igniters (7), the combustible substance of the propellant charge (8) is simultaneously ignited in the adjustable combustion chambers (6a, 6b, 6c) installed through the volume regulator ( 12) for the minimum volume. Inside the controlled combustion chambers (6a, 6b, 6c) a pressure is created corresponding to the condition of the burning rate. The products of combustion of a combustible substance (gas compressed to a high density), expanding in the working cavity (4), press on the bottom of the body cup (1) and inter-chamber partitions (10). Under the gas pressure in the controlled combustion chambers (6a, 6b, 6c), the interchamber partitions (10) come into motion, while in the combustion chamber (6a) the gas pressure pushes the engine block in front of it (1), the interchamber partition (10) presses on the chamber combustion (6b); in the combustion chamber (6b), one inter-chamber partition (10) presses on the combustion chamber (6a), another inter-chamber partition (10) of the combustion chamber (6b) presses on the combustion chamber (6c); in the combustion chamber (6c), part of the gases through the interchamber partition (10) presses on the combustion chamber (6b), the other part of the gases of the combustion chamber (6c) pushes the locking partition (2) out of the working cavity (4) of the pipe body (1) to the outside. The combustion chamber extreme to the outlet (6c) works as a locking mechanism, thereby ensuring the corresponding operation of the gases of the remaining combustion chambers (6a, 6b, ... 6n), providing pressure to the bottom of the housing cup (1), setting the whole structure in motion in motion (1). The working cavity (4) with adjustable combustion chambers (6a, 6b, 6c) installed through the volume regulator (12), by the amount of volume following the minimum value, is again filled with a propulsion charge from the fuel tank in the housing (5), electricity is supplied to adjustable electric igniters (7) installed to ignite the propulsive charge in the corresponding changed (from the minimum) volume of the controlled combustion chambers (6a, 6b, 6c) using the ignition regulator (11). Further, the cycle of actions repeats in increasing order.

Claims (3)

1. A tubular accelerator comprising a housing with a payload placed therein, a propulsion charge and initiating means, characterized in that the propulsion charge is located in the combustion chambers formed by inter-chamber partitions and configured to change their volume, while the combustion chambers are connected by an electric circuit, the means of initiation is made in the form of electric igniters installed in a propulsive charge, and the combustion chamber, which is extreme to the exit of the said housing, is designed to Response Dynamic closing the latter and provided with locking wall. 2. The tubular accelerator according to claim 1, characterized in that the number of combustion chambers is two or more. 3. The tubular accelerator according to claim 1, characterized in that the said housing is made in the form of a cylindrical glass with an increase in its outer diameter to the location of the propulsion charge.

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