RU2478536C2 - Rocket-propelled vehicle - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to rocketry. Proposed vehicle comprises body, rocket engine with axially symmetric supersonic nozzle and truncated cone-shaped jacket made of soft thin-wall material, closed on body side and exposed on nozzle side to fold along lengthwise axis. Cone smaller exposed base extends beyond nozzle edge. Case is made form heatproof dense fabric. Fabric of smaller exposed base is connected with heatproof rigid ring. Jacket larger closed base has annular tubular channel communicated on one side with flexible tubular channels from heat-resistant dense fabric bound with jacket fabric and located along jacket one generatrix extending from larger base to smaller one and provided with gauged outlets in rigid ring area and, on the other side, with high-temperature gas source. Folded jacket is attracted to body by cords from thermally unstable material jointed with jacket smaller base rigid ring and located opposite flexible tubular channel outlets.

EFFECT: decreased weight and increased thrust.

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Description

The invention relates to rocket and space technology and can be used in the construction of rocket aircraft (RLA) and rocket engines (RD).

The effectiveness of the radar depends on the specific impulse of the propulsion system (DE), the value of which is determined by the specific impulse of the taxiway, and also, at low environmental pressure, corresponding, in particular, to the conditions of outer space, in which the outflow from the nozzle of the taxiway can be characterized as “outflow with underexpansion ", Bottom pressure - pressure acting on the radar casing or, in particular, the remote control in the taxiway location zone and arising due to the braking of freely expanding jets of the supersonic air flowing from the taxiway nozzle a flow control structure and elements RLA in general (this is known, the boundary supersonic jet, according to the model Prandtl-Meyer flow at vacuum nozzle can turn on edge by an angle of> 90 degrees). Thus, an increase in the effective specific impulse of the remote control is possible not only due to an increase in the specific impulse of the taxiway, but also due to an increase in the bottom pressure and the effective area of interaction of the boundary jets of a freely expanding stream flowing from the nozzle of the taxiway with structural elements of the control (RL), which is defined as "Bottom effect".

It is known to increase the bottom effect of a radar device comprising a radar housing, a rocket engine with a combustion chamber and an axisymmetric supersonic nozzle, and a casing mounted on the housing around the engine; wherein the nozzle cut edge is placed inside the casing with a gap relative to the inner surface of the casing (US patent No. 4896848, B64G 1/40 from 10.30.90). The disadvantage of this device is the relatively high mass with a slight increase in specific impulse due to the bottom effect, which virtually eliminates the increase in the effectiveness of the radar.

The closest analogue (prototype) of the invention is a rocket apparatus and a rocket engine according to the patent of the Russian Federation No. 2094333 priority from 10.27.97, B64G 1/40, comprising a housing, a rocket engine with a combustion chamber and an axisymmetric supersonic nozzle; mounted on a casing outside the engine, closed on the casing side and open on the nozzle side, a casing in the form of a truncated cone folding along the longitudinal axis of the RLA, with a smaller open base placed on the nozzle side, made of gas-tight elastic material, a mechanism for deploying the casing so so that the nozzle cut is located inside the casing at a distance from the open base of the casing, not less than the half difference in the diameters of the cut of the nozzle and the open base of the casing.

The design of the prototype can significantly increase the bottom effect and thereby increase the effective specific impulse of the remote control radar: depending on the diameter of the casing and the distance from the nozzle exit to the open base of the casing, the increase in specific impulse can be up to 7%.

The disadvantages of the prototype include a significant additional mass of radar (up to 60 kg - according to the authors of the prototype), due to the mass of the 2-layer shell of the casing, including a shell of a gas-tight material, such as a polyamide film, and the mass of the deployment mechanism of the casing, which involves the use of a deployment drive that reinforces rings, rods, hinges, fasteners, etc.

The present invention is aimed at reducing the additional mass due to the introduction of the casing in the design of the radar while maintaining a significant increase in the effective specific impulse of the remote control due to the creation of the bottom effect, and, therefore, to increase the mass perfection of the radar. The result is achieved by the following technical solutions:

Mounted on the radar casing around the taxiway, closed from the casing side and open from the nozzle side, folding along the longitudinal axis of the radar casing is made single-layer from a soft, dense and heat-resistant fabric, for example, based on silicon or carbon fibers. A dense fabric is not completely gas-tight, however, at pressures of the order of 10 ^-3 kg / cm ^{2 of a} gaseous medium formed inside the casing due to the interaction of a freely expanding gas stream flowing from the RD nozzle with the edge of the open casing base, leakages through its leaks are negligible.

An assessment carried out with respect to a casing with a length and diameter of 2000 mm made of dense fabric with a relative porosity of ~ 0.1%, designed to shield a jet flowing out of a nozzle with a diameter of 400 mm taxiway with a thrust of 2000 kgf in the absence of counterpressure of the surrounding radar environment, shows that when the pressure inside the casing is ~ 0.0015 kgf / cm ² and the flow rate through the open casing base is ~ 6 kg / s, the leakage through its side surface is 0.0018 kg / s or ~ 0.03% of the flow rate through the open casing casing.

Accordingly, the loss of specific impulse due to leaks is ≤0.1 s when it increases due to jet shielding ~ 7.5 s. In this case, the reduction in mass due to the exclusion of the sealed shell will be ~ 20 kg in addition, the manufacturing technology of the casing is greatly simplified, in particular, the problems of choosing a heat-resistant material of a gas-tight film are eliminated (the casing shell in the prototype is supposed to be heat-resistant up to ... 450 ° C, which is not enough).

In a smaller open base, the casing fabric is connected to a rigid ring made of heat-resistant material, for example, from CCCM, which defines the shape of the edge of the open base, and in a larger base adjacent to the radar casing, an annular tubular channel is made of a heat-resistant material, for example, a carbon-carbon composite material (CCCM) or dense heat-resistant fabric, which on the one hand is equipped with a pipeline including a throttle washer, with a source of high-temperature gas, for example, based on gunpowder or azides, and on the other hand - with flexible tubular channels of heat-resistant fabric, bonded to the fabric of the casing, located along its generators from a larger closed base to a smaller open base and having calibrated outlet openings at the exits. In the folded (transport) position, the casing is pulled to the casing by cords of heat-resistant material, such as nylon, connected to a rigid ring of an open base and located opposite the outlet openings of flexible tubular channels located along the generatrices of the cone of the casing. The specified design of the casing does not require mechanisms for its deployment, which allows to reduce the weight of the radar due to the exclusion of the specified mechanism by another 18 ... 20 kg with an additional mass of the igniter ~ 0.2 kg and an increase in the mass of the casing due to parts from the CCM by 1 ... 1.5 kg and channels of fabric at ≤1 kg.

The invention is illustrated by the graphic images presented in figures 1-7.

The figure 1 presents a General view of the radar with a casing in the deployed working position;

figure 2 presents a cross section of a casing;

figure 3 presents on a large scale the design of a smaller, open base of the casing after its deployment;

figure 4 presents a view of the radar with a casing in the folded (pulled to the body of the radar) transport position;

the figure 5 presents on a large scale the design of the open base of the casing in the folded (transport) position;

the figure 6 presents on a large scale the design of the mounting of the casing to the body of the radar cords, in the folded (transport) position;

the figure 7 presents a large scale view of the mutual arrangement of the exit from the tubular located along the casing of the channel and the cord attaching the casing to the body of the radar in the folded (transport) position.

A conical casing 3 is fixed on the casing 1 around the taxiway 2 with a large base. The connection between the casing and the casing tissue is tight; while the surface of the housing 1 closes the casing 3 in its larger base, forming the bottom of the casing; a smaller open base of the casing in the working position protrudes beyond the nozzle exit RD 2 (see figure 1).

The casing is made of heat-resistant dense fabric. In the larger base of the casing 3, near the casing 1, an annular tubular channel 4 of heat-resistant material, for example, CCCM or heat-resistant fabric, is built into its fabric (see Figs. 4, 6). The annular tubular channel 4 is connected by a pipe 5 containing a throttle washer 6, with a source of high-temperature gas - a squib 7 (see Fig. 1) and flexible tubular channels 8 made of heat-resistant fabric and attached to the fabric of the casing 3 along its generatrices from the annular tubular channel 4 to the lower open base of the casing 3 (see figures 1, 2). At the exits of the tubular channels 8 in the area of the open base of the casing, inserts 9 are made of heat-resistant material, for example, УУКМ, with calibrated outlet openings and lodges intersecting these holes (for cords 11, Figs. 3, 5, 7). To ensure the rigidity of the open base, the edge fabric of the casing is connected to a ring 10 (see Figs. 1, 3) made of a heat-resistant material, for example, CCCM.

Figure 4 shows the casing 3 in a folded position: its fixation is provided by cords 11 made of heat-resistant material, for example, nylon, connected to the ring 10 (see Figs. 5, 7) and located in the lodgements of the inserts 9 opposite the outlet openings of the tubular channels 8 (see Fig.7). In the transport position (before undocking the radar from the launch vehicle), the casing 2 is folded and pulled to the casing 1 by cords 11 fixed to the ring 10, the number of which corresponds to the number of tubular channels 8; while the cords are located opposite the outlet in the lodgment of the inserts 9 of the tubular channels 8.

Before starting the taxiway, a command is issued to the squib 7. The charge of the squib 7 is ignited and the gaseous products of its combustion enter through the pipe 5 through the throttle washer 6 into the annular tubular channel 4 and then into the tubular channels 8 folded together with the casing to calibrated holes made in the inserts 9, through which they flow into the peripheral space, while the pressure in the tubular channels 8 increases. Hot combustion products flowing through the openings in the inserts 9 burn out nylon cords located in the lodges of the inserts 9 opposite the calibrated output openings, attracting the ring 10 to the housing 1, which fix the casing fabric in the folded state, after which, under pressure, the tubular channels 8 are fastened to the casing fabric 3, straighten, turning the casing 3 in the working position. After the launch of the taxiway, the high-temperature gaseous products of fuel combustion coming from the nozzle of the taxiway fill the space inside the casing 3 with a pressure corresponding to the static pressure at the boundary streamline of the jet passing through the edge of the open base of the casing.

In this case, the projection onto the longitudinal axis of the radar as a result of the pressure acting on the side surface of the conical casing 3 is directed from its larger base to a smaller open base, which ensures stable casing 3 in the open operating position. The same pressure, acting on the closing larger base of the surface of the radar housing 1, creates additional thrust force of the remote control radar (bottom effect), which increases the specific impulse of the propulsion system.

Claims (1)

A rocket aircraft comprising a housing, a rocket engine with an axisymmetric supersonic nozzle, and mounted on the housing around the engine, closed on the side of the body and open on the side of the nozzle, folding along the longitudinal axis of the casing of soft thin-walled material in the form of a truncated cone, the smaller open base of which stands for the nozzle cut, characterized in that the casing is made of heat-resistant dense fabric, for example, based on silicon or carbon fibers, in a smaller open base fabric, the brazing casing, at its edge, is connected to a rigid ring made of heat-resistant material, for example, carbon-carbon composite material; in a larger closed base of the casing, an annular tubular channel is made, communicating on one side with flexible tubular channels of heat-resistant dense fabric bonded to the casing fabric located along the generatrices of the cone of the casing from a larger base to a smaller one and having calibrated outlet openings in the area of the rigid ring of the smaller base of the casing, and on the other hand, chnikom high-temperature gas, e.g., based on powders or azides and folded casing is pulled to the body cords of termonestoykogo material such as nylon, rigid ring coupled with a smaller housing base and disposed opposite the outlet openings flexible tubular channels.

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