RU2495802C2 - Method of parachute system application for salvation of carrier rocket burned out stages or their parts and descent spacecraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to space equipment and can be used for salvation of burned out rocket stages in de-orbiting. In detachment of rocket unit at altitude over 70 km space parachute system of heat-resistant materials, passive orientation, stabilisation, braking and heat resistance means are used, at altitude below 10 km parachute system is used. At altitude below 3 klm, helicopter pickup is used.

EFFECT: lower aerodynamic and thermal load.

2 dwg

Description

The invention relates to a method for rescuing spent stages of launch vehicles or parts thereof. It can also be used to decelerate spacecraft (SC) in a relatively mild temperature mode, followed by a decrease in the atmosphere and landing at a low speed. For convenience of presentation and coincidence with the terminology of rocket science - the stage of the launch vehicle is designated as the missile unit (RB), and its engine compartment (DO) RB.

There is a method of quenching the kinetic energy of RB and spacecraft due to braking by their own body in dense layers of the atmosphere, followed by the introduction of a parachute system (PS) at an altitude of less than 10 km, described in the journal "Cosmonautics News" No. 3 of 2002

In the article "The steps of the" Angara "will pick up in the air?" Describes the closest analogue to the claimed method of saving Belarus. The way to save the spent first stages of the launch vehicle, which at an altitude of ≈80 km and a speed of ≈3 km / s due to the stabilizing shields are oriented in a certain way in the stream and begin to quench hypersonic speeds due to friction in dense layers of the atmosphere by means of an organized RB input and by applying special means of active and passive orientation, stabilization, braking and thermal protection, followed by the introduction of a standard multi-dome parachute system (PS) at altitudes below 10 km. Helicopter interception is provided at altitudes below 3 km. When the RB is caught by a helicopter, the PS is separated from the RB. The specified method, in principle, with proper thermal protection of the housing, ensures complete safety of the RB. However, the article ignored a significant point related to the large amount of thermal and aerodynamic loads on the body of the Republic of Belarus during free flight with hypersonic speed.

Since the midship of the RB and the spacecraft’s hulls is rather small (compared to the SS midship), when they are immersed in the atmosphere, from the altitude of 60 km to an altitude of 20 km, the frontal part of the spacecraft is intensively heated (Engineering Manual for Space Technology, ed. A.V. Solodova, Moscow, Military Publishing House of the Ministry of Defense of the USSR, 1977). The temperature on the front of the descending spacecraft reaches 3000 ° C, and the overload during ballistic descent (without using aerodynamic quality) is 8 units or more. Therefore, the heat shield protecting the descent spacecraft from destruction has high strength and mass. So, on the Vostok and Voskhod spacecraft, the mass of the heat shield was more than 250 kg, while the mass of the spacecraft was 2 tons. The mass of the PS, introduced at an altitude of less than 10 km, had a value of ≈150 kg.

When saving the Republic of Belarus or before the Republic of Belarus, similar problems arise of thermal heating and aerodynamic effects. As practice has shown, the first stages of launch vehicles at a speed of ≈3 km / s are separated by 90 km, reach a height of 120-150 km and, in the absence of proper thermal protection, their aluminum bodies are destroyed almost completely to a height of 10 km.

Calculations of the ballistics of braking and lowering of the RB of Soyuz show that when a substation (the same area as for safe landing) is entered at an altitude of more than 80 km, the overload is reduced to 8 units, the main braking occurs up to an altitude of 50 km and thermal and aerodynamic loads. The aluminum case before RB is stored without thermal protection and, when picked up by a helicopter, does not receive damage.

The main obstacle to this method of using PS is the temperature under the dome, reaching 1800 ° C. Standard PS, as a rule, are made of nylon fabric and tapes with a temperature range of application from minus 60 to plus 60 ° C. In the manufacture of substrates from heat-resistant materials - carbon fiber cloth and carbon fiber, its mass will remain at the same level, and during short-term operation the temperature range will expand to 1800 ° C. (Carbon fabric remains operational up to 2000-2300 ° C).

The use for rescue of RB - an aerospace parachute system (VKPS), capable of operating both in dense surface air layers and in high rarefied atmospheric layers more similar to outer space, and with aerodynamic heating - solves the problem of multiple use of RB or RB .

The main cost of the Republic of Belarus is a liquid rocket engine, capable of, in its reliability, to carry out multiple use. Repeated use of RBs or their parts, in turn, can significantly reduce the cost of spacecraft launches. Thus, the inventive method of using VKPS for rescue spent RB or detachable BS RB provides: oriented RB entry into dense atmospheric layers while damping hypersonic speed, braking from a height of more than 70 km with a large parachute, blanking RB speed up to 2-3 M at a decrease in the upper rarefied atmosphere to an altitude of 50 km and landing of the RB at a low speed; a decrease, by more than 2 times, of the thermal protection mass for the spacecraft and its practical absence for the RB compared with their ballistic descent and braking by the RB (SC) body in dense atmospheric layers — by the prototype.

Calculations of the ballistics of the movement of the Republic of Belarus after separation from the launch vehicle show that when the VKPS is put into operation at an altitude of 90 km or more, the velocity head is no longer enough for the domes to fill themselves. At the same time, it is very important to open the domes and use their braking properties as early as possible. In this case, compulsory disclosure is ensured through the use of special design solutions (elements) for shooting systems, input, formation and maintenance of the VKPS domes.

It should be noted that with a mass of up to 8 tons of RB, it is advisable to save it as a compartment separated from the RB. At the same time, the weight of the APSS and the loading of the helicopter during interception and transportation to the Republic of Belarus are reduced. For the specified mass before RB, it is rational to use a multi-dome VKPS. The multi-dome VKPS always has a non-simultaneous filling of the domes, leading to an increase in the swinging angles of the RB. In this case, in order to reduce fluctuations in the DO from non-simultaneous filling of the VKPS domes, the DO is separated from the Republic of Belarus after the VKPS domes are put into operation.

To ensure maximum inhibitory effect in rarefied atmospheric layers, the APSS is put into operation with a minimum time delay after separation of the RB from the launch vehicle.

The listed advantages of the invention, in comparison with the prototype method of salvation of the RB “Angara” (“Cosmonautics News” No. 3 of 2002) are provided by the introduction of the APSS, made of heat-resistant materials, at high altitude with a small velocity head, and then the reduction along the entire trajectory is performed by open main parachute or parachute bundle with a mass of RB (DO RB) of more than 2 tons. At an altitude of less than 3 km a helicopter intercept is made.

The invention can also be used when returning to spacecraft.

The invention is illustrated in the drawing. Figure 1 shows: DO RB - 1, VKPS - 2, commissioning VKPS - 3, the conditional boundary of the dense atmosphere at an altitude of 90 km - 4, the stage of braking DO - 5, lowering and catching by helicopter DO RB with the uncoupling VKPS - 6 .

Figure 2 shows: KA - 7, VKPS - 2, commissioning of the VKPS at an altitude of 120 km - 8, the conventional boundary of a dense atmosphere at an altitude of 90 km - 4, the stage of orbit and deceleration of the KA - 9, the decrease and landing of the KA - 10.

Claims (1)

The way to save the spent stages of launch vehicles - rocket blocks (RB), which by the time the parachute system (PS) is introduced at altitudes below 10 km, complete the quenching of hypersonic speeds due to friction in dense layers of the atmosphere without destroying the structure due to the organized entrance of the RB using onboard active and passive orientation systems, stabilization, braking and thermal protection, followed by the introduction of a standard substation with helicopter pick-up at altitudes below 3 km, characterized in that, in order to provide orientation After the super-high-altitude parachute descent of the Republic of Bashkortostan, starting with rarefied layers of the atmosphere at an altitude of more than 70 km, realizing the exclusion of intensive aerodynamic and thermal loading on the structure of the RB, and up to a height of helicopter support of ~ 3 km, an aerospace parachute system (VKPS) made of heat-resistant materials, with the introduction in the upper rarefied atmosphere.

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