RU2572014C1 - Reduction of fall area for carrier rocket first-stage units in case of their parallel coupling - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: rocket first-stage units are equipped with the flexible rope-type mechanical linkage. Said rocket units are detached from the carrier rocket second stage to launch the parachute system. The rocket units are stabilized to suppress their hypersonic speeds. The rocket units are descended with the help of space parachute system to surface them at the fall area.

EFFECT: reduced distance between fall area and launching site and fall area proper.

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Description

The invention relates to a method for reducing the areas of incidence of spent rocket blocks (RB) of the first stage of the carrier rocket with their parallel connection.

When the spacecraft (SC) is launched, fall zones of spent parts of the launch vehicle stages are automatically formed in the form of areas with an area of hundreds of square kilometers. Placing any objects in these areas is prohibited, except for protected bunkers. The presence of personnel in such an area is also not allowed, especially on the day of launch. When the inclination of the orbit of the spacecraft changes, these regions move accordingly. The seriousness of resolving issues on the identification of areas of incidence of rocket launches is visible on the example of a note dated May 29, 2012 in the Cosmonautics News.

A number of Russian media reported on May 27 that Russia would not be able to complete the three planned space launches in the summer due to the fact that Kazakhstan does not allow its territory to be used as a fall area for the first stage of the Soyuz launch vehicle. Due to the ban of the Kazakh side, three Russian and four foreign satellites are waiting for orbit. We are talking about the launch of the MetOp-B European meteorological spacecraft, which was planned for May 23, about the group launch of the Russian Canopus-V and MKA-PN1 satellites, the Belarusian BKA, the Canadian ADS-1B and the German TET-1, which is scheduled for 7 June, and the launch of the Russian apparatus Resource-P, which was to be held in August.

"The launches of the spacecraft referred to in the article were not agreed by the Kazakh side at the end of 2011, since their implementation requires the use of a new fall area for the separating parts of launch vehicles, not provided for in the lease agreement for the Baikonur complex dated December 10, 1994 of the year. The Russian side was notified about this in a timely manner, "the Kazkosmos message posted on the company's official website said.

In accordance with the land legislation of Kazakhstan, in order to allocate new land plots as a falling area of the separated parts of missiles, it is necessary to conclude an international agreement, which must be ratified by the parliament of the republic. According to Kazkosmos, in 2008 the parties began work on the preparation of the corresponding draft intergovernmental agreement, but so far the text of the agreement has not been agreed upon by the parties, RIA Novosti reports.

Similar problems arise when the spacecraft launches into orbits with a different inclination at the cosmodromes (Plesetsk, Vostochny) with areas of impact on the earth's surface in Russia and China.

At present, for cosmodromes whose fall regions are located on the earth's surface, a method is known of damping the kinetic energy of the Republic of Belarus due to braking by their own body in dense layers of the atmosphere, followed by fragmentation from thermal and aerodynamic loads at an altitude of less than 15-20 km and falling parts RB in designated areas.

The officially allocated area of the fall area for the first stage RB of the Soyuz-2 rocket carrier for one launch track is an ellipse with axes of 42 × 22 km and an area of 693 km ² for the Baikonur Cosmodrome and 50 × 30 km (1125 km ² ) for the Cosmodrome "Oriental".

The area of the fall area of spent RB of the first stages of the launch vehicle (ILV) is determined by the following factors:

instrumental deviations of the onboard control system from the given values: RB separation time, trajectory angle, speed and direction (azimuth) of the flight path;

seasonal and daily changes in atmospheric density, wind direction and speed at different heights;

the initial impulse and expansion of the separated RB relative to each other when they are parallel to the second stage. The separation of the Republic of Belarus takes place on an ascending branch of the trajectory (45-80 km), followed by free flight in an atmosphere of high vacuum at an altitude of 70-150 km. Under these conditions, there is practically no counteraction to the initial impulse of the RB expansion from each other, and they fly apart over a considerable distance.

The parallel layout of the first stage RB is used on domestic Soyuz-type launchers. So, on the Soyuz rocket carrier there are four side blocks of the first stage, and their calculated expansion in the areas of incidence in the direction of flight is up to 6 km, and the transverse expansion is up to 3 km.

The officially allocated area of the fall area for the first stage RB of the Soyuz-2 rocket carrier for one launch track is an ellipse with axes of 42 × 22 km and an area of 693 km ² for the Baikonur Cosmodrome and 50 × 30 km (1125 km ² ) for the Cosmodrome "Oriental".

Prevention of the relative expansion of the RB from each other after separation for the Soyuz rocket launcher will reduce the axis of the ellipse of the fall region to (42-6) 36 km and (22-3) 19 km, and accordingly, reduce the area of the fall region from 693 to 513 km ² , i.e. 26% for the Baikonur Cosmodrome. For the Vostochny Cosmodrome, these axes will decrease to (50-6) = 44 km and (30-3) = 27 km — an area of up to 890 km ² , i.e. by 21%.

Consequently, for only one launch path, the decrease in the area of the fall area due to the prevention of the relative expansion of the first stage RB will be up to 180 km ² for the Baikonur Cosmodrome and up to 235 km ² for the Vostochny Cosmodrome.

The exception of the relative expansion of the RB of the first stage of the Soyuz-type rocket launcher is provided by the introduction of a constructive flexible cable connection between the bow of the blocks, which, without interfering with their separation from the second stage of the rocket launcher, provides a strict restriction of the rotation angles of the blocks in the range from 0 to 35 degrees to the incident velocity vector flow, and preservation of the constructive connection of the blocks in the future flight with the exception of their relative expansion when falling into a given area.

The fall areas for the Baikonur Cosmodrome are located in an open, flat terrain of the steppe type and are readily accessible for road transport tow trucks of the remnants of the Republic of Belarus. In contrast, the fall areas of the Vostochny cosmodrome are located both on rugged and mountainous, taiga terrain and are very inaccessible or generally inaccessible for automobile and tracked vehicles of RB evacuators. Therefore, for the Vostochny cosmodrome, it is also important to ensure the possibility of regulation (downward) of the center of the ellipse of the fall region. The center of the fall area of the first steps of the Republic of Belarus is located at a distance of 350 km from the start. A ballistic assessment of the use of substations for braking and stabilized flight of the Republic of Belarus showed that it is possible to reduce this distance to 250 km, provided that the station is entered immediately after separation of the Republic of Belarus and its operation along the entire trajectory of decline. In this case, the fall of the RB to the mountainous areas is practically eliminated and the absence of defragmentation of the RB from thermal and aerodynamic loads is ensured. The removal of unfragmented RB significantly reduces the labor costs of tow trucks and reduces the total cost of launching an ILV.

To minimize weight in the design of single-use RBs, thin sheets of aluminum alloys are used with the minimum possible reinforcement with a longitudinal and transverse power frame and the maximum possible internal overpressure. It is for these reasons that the hulls of the Republic of Belarus are stochastically destroyed under the combined influence of thermal and aerodynamic loads at the entrance to the dense layers of the atmosphere at altitudes of 15–20 km.

The introduction of traditional PS from kapron textile materials at an altitude of 7-10 km for the landing of the Republic of Belarus is also impossible due to intensive rotation from aerodynamic forces. The introduction of such substrates (with a working temperature of the material up to 60 ° C) immediately after separation of the RB, provided that they are stabilized, is excluded due to exposure to a hypersonic high-temperature flow (1200-1500 ° C).

The only possible application for this in the first stage RB is the aerospace parachute system (VKPS) made of heat-resistant and heat-resistant textile materials (patent No. RU 113240 U1 with priority dated 03/17/2011) when entering from the upper rarefied atmosphere with landing on the earth's surface of spent RBs in pre-designated areas (according to patent RU 2495802 C2). To enter the VKPS into operation, it is necessary to prevent rotation and ensure the oriented position of the aerodynamically unstable empty RB housings, which is also provided by a constructive flexible cable connection between the RB. Thus, the inventive method of reducing the areas of areas of incidence of spent RBs of the first stage when they are parallel to the ILV provides:

- the use for its implementation of VKPS from heat-resistant fabrics with the introduction of PS immediately after their separation from the second stage at the time of limiting the rotation of the Republic of Belarus due to the work of a flexible cable connection.

- reduction of the area of the fall region to 20% due to the implementation of a group flight of the RB to the PS by introducing a constructive connection between the RB of the first stage, which does not interfere with the separation of the side blocks of the first stage from the second stage of the ILV and eliminates their discrepancy when flying the formulated ligament of the RB into the specified area ( see Fig. 2);

- reducing the distance from the start to the center of the dispersion ellipse of the RB landing area by not less than 30% due to the use of VKPS for braking and parachuting starting from the ascending section of the trajectory and the subsequent implementation of the RB group flight due to the operation of constructive cable communication along the entire flight path and landing of the RB at an acceptable speed, ensuring their integrity for subsequent evacuation.

Reducing the distance from the landing point of the Republic of Belarus to the start from 350 km to 240 km is essential for the implementation of transportation of the Republic of Belarus. In addition, a decrease in the area of the fall area from the start by 30% or more for the Vostochny Cosmodrome leads to their landing on the plain terrain.

The listed advantages of the invention, in comparison with the prototype - ballistic flight of RBs to selected ground areas for falling fragments of RBs, are provided by the introduction of constructive communication of RBs of the first stage when they are parallel placed on the second stage of the ILV, which does not prevent their free separation from the second stage of the ILV, but excludes the relative expansion and rotation of the RB in free fall to the rear region and the application for each RB VKPS made of heat-resistant materials for braking and stabilizing the RB with active communication along the entire flight path and landing of the RB with an acceptable speed, ensuring their integrity for subsequent evacuation.

Implementation of the proposed method in carrier rockets of the SOYUZ type with a parallel arrangement of RBs of the first stage is carried out by introducing into the RBs a system of flexible cable mechanical communication in accordance with FIG. 1 (item 3) of the attached drawings.

The invention is illustrated by drawings.

In FIG. 1. shows the mutual positions of the RBs of the first and second stages of the Soyuz-2 rocket carrier when they are separated with a time interval of 0.5 s from the RB of the first stage - 1, RB of the second stage -2, structural connection of the blocks of the first stage - 3, VKPS - 4. Communication - 3 does not prevent separation of the first stage RB - 1 from the second stage RB - 2 in the first two seconds of the flight, but limits their divergence and rotation by the time the VKPS - 4 is put into operation by the third second.

In FIG. Figure 2 shows the fall area of the RB of the first stage of the Soyuz rocket carrier for the Baikonur cosmodrome with the free separation of RB-5 with superimposed on it a reduced fall region of the RB of the first stage with constructive communication - 6. Area S _{2 of the} reduced fall region - 6 is about 80% from area S ₁ of the fall area with free separation of RB - 5.

In FIG. Figure 3 shows the calculated fall areas of the RB of the first stage of the Soyuz rocket for the Vostochny spaceport, indicating the distance of the center of the dispersion ellipse from the launch and mapping the terrain without constructive connection between RB-7 and the fall regions with each RB - VKPS minimum possible area (500 m ² ) and constructive connection between each other - 8.

In FIG. 4 shows a system of four RB - 1 with VKPS - 4 in the area of decline before landing, connected by a structural connection - 3.

Claims (1)

The method of launching Soyuz-type launch vehicles with parallel arrangement of the first-stage rocket blocks (RBs) for which stabilization, quenching of hypersonic speeds and reduction due to the use of the aerospace parachute system (VKPS) are provided, starting from the upper rarefied atmospheric layers with landing to the earth’s surface in the fall areas, characterized in that to create conditions for putting the parachute system into operation immediately after separation of the RB, the missile units are equipped with a flexible cable mechanical communication system, not preventing their regular separation from the second stage in the active flight section, but limiting their turn, and preserving the mechanical connection of the RB in the area of parachute descent, thereby ensuring group landing of the RB with a reduction in the size of the fall areas.

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