RU2571890C1 - Light-class space rocket with high ready-to-use availability for launching and with shuttle-type first stage - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: claimed space rocket runs on non-toxic propellant components and features high degree of readiness for launching with definite composition, weight and overall dimensions and operating performances required for air transportation of completely factory assembled and tested space rocket. This space rocket has reusable rocket unit or the first-stage power plant, and aerospace parachute system.

EFFECT: accelerated pre-launch jobs.

5 dwg

Description

The invention relates to rocketry and is intended to solve the problem of creating a light carrier of high class readiness (ILV VZG) with multiple use of the rocket block of the first stage (RB 1 st.). The LV rocket launcher provides the launch of light and ultralight class spacecraft weighing from 100 kg to 1,500 kg in circular orbits with a height of N _cr from 200 km to 1,500 km without restrictions on launch paths, with the exception of the landing areas of the RB 1st, with its organized descent to air -the space parachute system (VKPS) with helicopter interceptor or soft landing (patents RU 113240 U1 and RU 2495802 C2 with priority dated March 17, 2011).

Salvation of Belarus 1st. for its subsequent reuse, it is realized due to parachute descent to VKPS along the entire trajectory of descent with a final speed of not more than 8 m / s, providing helicopter interception or soft landing at landing sites. Salvation of Belarus 1st. allows you to ensure its completion with reusable rocket engines and solve the problem of reusable use of its modular part consisting of: tanks, dry compartments, fittings, switching devices and other elements.

Design parameters of the rocket launcher VZG LC are selected taking into account the restrictions imposed on the trajectory of the active section of the RB 1st. the conditions of reliable operation of the APSU when entering large domes at hypersonic speeds and the temperature loading of their elements. At the same time, the task of ensuring the energy characteristics of the ILV to bring payloads of the required mass to the given orbits is solved.

The integrated solution of these tasks for the VZG LV rocket launcher determined their weight and size parameters, which are favorably combined with the tactical and technical characteristics (TTX) of Il-76-MDF and AN-124-100 Ruslan transport aircraft.

Thus, air transportation of the fully assembled ILV VZG LV from the manufacturer after its comprehensive acceptance tests at the spaceport with direct delivery to the launch complex for carrying out only the launch cycle (2-3) days is provided. At the same time, the traditional stage of the ILV preparation technology at the technical complex of the cosmodrome lasting 10-15 days is excluded.

Currently, all spacecraft created and operated are delivered to spaceports by rail or sea (Zenit - 3SL, Soyuz-ST at the GKK-Kura) for a long time. Such a delivery scheme, in addition to the additional load during loading and unloading of the LV, exposes its elements to long cyclic loads during railway or sea transportation. After that, it is necessary to conduct a full range of electrical and pneumatic and hydraulic tests and take into account additional safety factors when calculating the structural elements of the LV for strength for cases of railway transportation and loading and unloading operations.

Currently, the aviation delivery of spacecraft (SC) to spaceports is widely used. In addition to ensuring prompt delivery, this method of transportation implements the calculated loading parameters necessary for optimizing the characteristics of the spacecraft.

ILV of the light class with the use of VKPS is characterized by the following parameters.

Weight and overall parameters of the rocket launcher VZG

The length of the rocket carrier ≈24-28 m

ILV diameter≈2.7-3 m

Mass design ILV≈13-15 t

The performance characteristics of heavy transport aircraft:

IL-76-MDF

The mass of the transported payload ≈56 t

Overall dimensions of loading the fuselage: length - 24 m, diameter - 3.4 m

Flight range with a cargo of 52 tons of at least 5000 km.

Flight altitude up to 11 km.

AN-124-100

The mass of the transported payload is ≈120 t.

Overall dimensions of loading the fuselage: length - 36 m, height -4 m, width up to 6.5 m.

Flight range with a load of 80 tons of at least 7500 km. Flight altitude up to 11.6 km.

An assessment of the characteristics of the rocket launcher of the VZG LC and transport aircraft shows that it is guaranteed that the ILV with the necessary control equipment is delivered to launch cosmodromes (the Yubileny aerodrome of the Baikonur Cosmodrome provides reception of these aircraft and their maintenance for unloading and loading of such bulky goods.)

Analogs for the rescued RB 1CT. ILV VZG ILV are:

salvaged entirely RB 1st. weighing 36 tons rocket launcher "Energy" "Technical design of OJSC RSC" Energy ";

salvaged entirely RB 1st. weighing 10 tons of rocket carrier "Angara" "Design studies of the GNP RSC named after Khrunichev (" Cosmonautics News "in 2002 No. 3).

In these analogues, to perform the main task of parachuting RB 1st. from a height of about 5 km, a parachute system of traditional textile nylon materials with a temperature range of -60 ° C to 60 ° C is used. To ensure the safety of the casing of the Republic of Belarus 1 st., Made of thin-sheet aluminum alloy, its thermal insulation with thermal protection elements is required, protecting it from the thermodynamic effects of the incoming flow and aerodynamic stabilization to ensure an oriented entry into the dense layers of the atmosphere. The use of thermal protection and aerodynamic stabilization elements in addition to the main substation of rescue RB 1st. degrades the weighty design perfection and, as a result, reduces the value of the main target parameter of the rocket launcher - its energy capabilities in terms of the mass of the cargo put into orbit.

Due to the use of various elements, each of which performs its narrow function, the rescue system, as a whole, has an increased mass and dimensions compared to that used in the declared ILV LC VZG - VKPS. The VKPS equipped RBs of the first stage do not need additional external thermal insulation of the body and means of aerodynamic stabilization, since the VKPS parachutes are made of heat-resistant and heat-resistant textile materials, have a working temperature range from -60 ° C to 1300 ° C and perform target functions on the same parachutes, both for stabilizing the RB immediately after separation from the ILV at altitudes of 60-80 km, and for braking at hypersonic speeds in rarefied upper layers of the atmosphere on the ascending and descending parts of the trajectory (decrease Ia trajectory angle from + 25 ° to -90 °) with access to a vertical descent to an altitude of 40 km at subsonic speeds and vertical drop RB 1st. within about 30 minutes before a helicopter catch or landing at a speed of not more than 8 m / s (RU 113240 U1 and RU 2495802 C2 with priority dated 03/17/2011).

The practical time interval for the helicopter to reach the pick-up point according to the action plan for rescue RB 1st. The Angara ILV is very small and lasts no more than 7 minutes, which causes great difficulties for the crew of the pick-up helicopter by visual contact and its exit to the pick-up point.

The specialists of the Mil Helicopter Plant, the conditions for picking up the RB 1st for the rocket launcher with VKPS: namely, a vertical speed of not more than 10 m / s at an altitude of 3 km, a mass of not more than 5 tons and, especially, a long time interval of about 30-35 minutes of visual tracking from heights of the order of 30-40 km to the heights of helicopter pickup of 2-3 km - are estimated as parameters that uniquely ensure the technical implementation of the pickup mode on existing serial MI-8T helicopters.

The low rate of vertical decrease allows you to apply the proven technology of visualizing the position of the object with the beacon ("tracker") of the GLONASS - GPS location systems with determining the position of the RB 1st. - VKPS in conditions of limited visibility of helicopter interception and ground search.

As an option, a separation of RB 1st is possible. after its separation into the engine compartment (DO) and the tank compartment (BO) to reduce the speed and load on the APSU while reducing the most expensive part - DO. A less critical part - BO can decrease with increased speed on a single-square VKPS of a smaller area. With such a separate descent, the total mass and the area of the VKPS also decreases.

Thus, the essence of the invention and the achievement of the claimed differences and advantages of ILV LC VZG in comparison with these analogues are as follows:

- rescue of the first stage or its propulsion system (DU) due to the use of the rescue system as part of the Republic of Belarus on the basis of the VKPS;

- Creation of a high factory readiness RCP by optimizing the configuration and weight and size parameters of the LV rocket launcher for air transportation;

- ensuring the implementation of ILV from the manufacturer directly to the launch site of the spaceport;

- Carrying out only prelaunch launch for launch.

The implementation of the proposed differences and advantages of this invention is realized in the design and creation of launchers of launchers instead of disposable launchers of the type "Cosmos", "Rokot", "Dnepr" operating on toxic components of rocket fuels and having limitations on the technical resource of their use.

The invention is illustrated by drawings.

In FIG. 1 presents a General view of the ILV LC VZG. RB 1st. - 1, tank compartment RB 1 tbsp. (BO) - 2, the engine compartment of the Republic of Belarus 1st. (DO) - 3, containers with main parachutes VKPS - 4, a container with a small parachute VKPS and a pickup system by helicopter - 5, RB 2 st. - 6, KGCh- (GO - 7, apogee-adjustable tank and payload - 8).

In FIG. 2 shows the layout of the containers with the main parachutes VKPS - 4 on the RB RB 1st. - 3 LV VZG launcher, a container with a small parachute VKPS and a helicopter pickup system - 5.

In FIG. 3 presents the scheme of work of the APSU with RB 1st. ILV LC VZG. RB 1st. - 1, RB 2 tbsp. - 6, KGCh- (GO - 7, apogee-and-draw unit and payload - 8), parachute of the VKPS support system - 9, the main parachute of the multi-dome VKPS - 10, the support helicopter - 11. For information, the design parameters of the ILV movement variant at the time are indicated separation of steps. The time for the separation of the stages coincides with the beginning of the introduction of the VKPS into operation and is conditionally taken for 0 s.

In FIG. 4 presents the scheme of work of the All-Union Central Council of Trade Unions with the division into BO and DO for RB 1st. ILV LC VZG. Division of the Republic of Belarus 1 tbsp. - 1 on BO-2 and DO-3 occurs after separation from the second - 6 and third stages - 7, 8 ILV LC VZG. The VKPSS interception system parachute - 9, the multi-dome VKPS multi-dome parachute - 10, the interception helicopter - 11, the single-wing VKPS with the main VKPS parachute - 10 BO-2. For information, the design parameters of the ILV at the time of separation of the steps are indicated. The time for the separation of the stages coincides with the beginning of the introduction of the VKPS into operation and is conditionally taken for 0 s.

In FIG. Figure 5 shows a general view of the VKPS from a helicopter interception to the RB of the 1st stage of the VZG LV launcher. To RB 1st - 3, a parachute of the VKPSS pick-up system with an area of 20-50 m ² - 9, a main parachute with an area of 500 m ^{2 of a} multi-dome VKPS - 10, a helicopter cable loop catcher - 12, a power link for transporting a helicopter to the helicopter - 13, automatic couplers - 14 main parachutes from DO (when transferring the main load from DO-3 to the catcher of the cable loop of the helicopter - 12 and 13).

Claims (1)

A light class space rocket (ILV) on non-toxic fuel components with a high degree of factory readiness for launch operations at the launch site of the cosmodrome, with a salvage rocket unit (RB) of the first stage or its propulsion system, characterized in that to fulfill the requirements of a high degree of factory the readiness, the composition, weight and technical parameters of the Launcher Launcher, which provide air transportation of the fully assembled and factory-tested Launcher from the factory, are determined For the spaceport with its subsequent delivery directly to the launch complex, and to save the first stage RB or its propulsion system, the ILV is equipped with an aerospace parachute system.

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