RU2355607C1 - Rocket-carrier ascent unit - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to space engineering and can be used in developing and producing rocket-carrier ascent unit. In compliance with this invention, the proposed ascent unit comprises a nose cone, spacecraft made up of, at least, one compartment with its surface furnished with vacuum thermal shield insulation. Additionally, it comprises the device that ensures required durability and thermal properties of aforesaid insulation and represents a set of through draining holes uniformly arranged on the insulation surface to communicate interlayer spaces of gas medium of the said insulation and, under it, with gas medium spaces below the nose cone. Reflecting shields are mounted above the said draining holes with a clearance with respect to aforesaid insulation. The nose cone is furnished with drain holes, at least, one of which communicates gas medium space under the said nose cone with atmosphere.

EFFECT: reduced pressure differences acting on vacuum thermal shield insulation and nose cone and provision of required thermal properties of insulation.

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Description

The invention relates to rocket and space technology and can be used in the design and creation of a space head part (KCH) as a part of a spacecraft (KA) equipped with a screen-vacuum thermal insulation (EVTI) and a launch vehicle (RN) into outer space .

The invention is intended to protect the fairing KGCH, the spacecraft body, its elements, systems and assemblies located in the spacecraft, from the aerodynamic and thermal effects of the environment.

Known and widely used in rocket science are devices for protecting a fuel tank with cryogenic fuel and its pipelines, containing a protective shell from environmental influences [1], [2]. On the surface of the fuel tanks to reduce losses due to evaporation of cryogenic fuel install EVTI [3].

EVTI, having high thermal insulation properties, is a package consisting of successively arranged interlayer screens with a minimum degree of blackness, thermally insulated from each other by spacer strips. Reflective shields limit most of the heat flux due to radiation, and dividing shields reduce thermal conductivity between adjacent shields.

The effectiveness of such insulation, in addition to the properties of the materials of the screens and gaskets, is determined by the pressure in the heat-insulating layer, as well as the technology of its manufacture and installation on the elements (fuel tanks, spacecraft) of the rocket-space system (CS). Moreover, for the regular functioning of the EVTI requires the creation of a deep vacuum (up to 10 ^-4 mm Hg), since when it decreases, the thermal conductivity increases sharply [4].

According to the technical solution [1], EVTI is installed on a fuel tank with cryogenic fuel, intended for long-term storage of cryogenic fuel and its refueling in LV tanks. In this case, the fuel tank with EVTI is enclosed in a casing (thermal shell) installed with a gap with the fuel tank forming a closed sealed heat-insulating cavity between the fuel tank and the casing. To evacuate this cavity to a predetermined residual pressure, a corresponding vacuum tooling and pressure control in the cavity are provided, which significantly complicates the design of this device, which is functionally designed to operate it in ground conditions.

According to the technical solution [2], the EVTI is installed on the fuel line, also enclosed in a casing with the formation of a heat-insulating cavity, evacuated to a predetermined residual pressure and also intended for operation of the line in ground conditions.

It is also known and widely used in rocket science KGH RN, containing a dumped fairing, spacecraft, made in the form of a spacecraft (SC). QC is performed in the freight and cargo ("Progress") [5] and manned ("Soyuz") [6] options.

KGCh fairing is designed to protect the Soyuz spacecraft and the Progress spacecraft from the force and heat of the aerodynamic flow.

The Soyuz and Progress spacecraft consist of a system of interconnected frame and truss compartments, on the surface of which an EVTI is installed, designed to heat protect the shell of the compartments, systems and units of the spacecraft from the thermal effects of the aerodynamic flow on the active part of the LV flight, as well as during operation Spacecraft in autonomous flight under conditions of prolonged stay in outer space.

The disadvantages of these technical solutions include the increased aerodynamic loads acting on the EVTI spacecraft, and the possibility of its damage in the process of launching the spacecraft into outer space. As shown by a visual inspection of the surface of the Soyuz spacecraft in outer space, the EVTI has local "swellings" and even exfoliation of its individual elements. This reduces the reliability of the operation of the EVTI and, therefore, systems and assemblies located in the compartments of the spacecraft.

The technical solution [6] is the closest to the proposed and accepted by the authors as a prototype.

The objective of the invention is to ensure the structural strength of the fairing KGCH and EVTI KA, the LV launched into outer space, as part of the KGCH.

The problem is solved in such a way that in the KGH LV containing a fairing, a spacecraft consisting of at least one compartments on the surface of which an EVTI is installed, according to the invention, a device is introduced into it to provide strength and thermophysical characteristics of screen-vacuum thermal insulation in the form of through drainage holes evenly spaced on the surface of said insulation, communicating interlayer volumes of the gaseous medium of this insulation and under the insulation with the volume of the gaseous medium under the cowling, while above the drain openings Reflective screens are installed with gaps with respect to insulation, and at least one drainage holes are made in the fairing with a given total effective area, which informs the volume of the gas medium under the fairing with the atmosphere, and the specified total effective areas of the insulation drainage holes, the gaps between the reflective screens and fairing and drainage holes are determined from the ratios

Where

S, S ₁ , S ₂ [cm ² ] - the total area of the drainage holes of the insulation, the gaps between the reflective screens and insulation and the drainage holes of the fairing, respectively;

µ, µ ₁ , µ ₂ - flow coefficient of the drainage holes of the insulation, the gaps between the reflective screens and insulation and the drainage holes of the fairing, respectively;

V, [m ³ ] is the total volume of the gas medium in the insulation and under the insulation;

V ₂ , [m ³ ] is the total volume of the gaseous medium under the fairing;

ΔР, [kgf / cm ² ] is the maximum differential pressure of the gaseous medium acting on the insulation along the flight path of the LV;

ΔP ₂ , [kgf / cm ² ] - the maximum along the flight path of the LV differential pressure of the gas medium acting on the fairing;

a, c - coefficients depending on the parameters of the LV flight path that approximate the curves of the effective area of the drainage holes of the insulation and fairing as a function of the maximum differential pressure acting on the flight path acting on the insulation and fairing.

The technical results of the invention are:

- reduction of pressure drops acting on the elements of EVTI KA due to through drainage holes made in EVTI;

- providing the thermophysical characteristics of EVTI with through drainage holes due to screens reflecting from radiation heat flux screens installed above the through drainage holes of EVTI;

- ensuring admissible pressure differences acting on the KGCh fairing, as part of a spacecraft equipped with a device for ensuring the strength and thermophysical characteristics of EVTI, due to drainage holes made in the fairing with a given effective area;

- determination of the total effective area of the drainage openings of the KGCH, EVTI spacecraft fairing and the gaps between the reflective screens and EVTI, which ensure the flow of the gas medium from the interlayer volumes of the EVTI and the volumes under the EVTI into the atmosphere.

The essence of the invention is illustrated by the example of solving the problem with reference to the KGCh PH as part of the spacecraft, made in the form of spacecraft "Union"

Figure 1 shows a diagram of the KGCH PH as part of a spacecraft consisting of a system of compartments of a frame and truss structure, on the surface of which an EVTI is installed.

Figure 2 shows a fragment of the EVTI KA with the shell of the frame compartment.

In these figures:

1 - fairing;

2 - spaceship (spacecraft);

3 - frame compartment;

4 - shaped compartment;

5 - drainage holes;

6 - device separation of the aerodynamic flow;

7 - a spring-loaded cover;

8 - screen-vacuum thermal insulation (EVTI);

9 - shell frame compartment;

10- rods of the shaped compartment;

11 - drainage holes;

12 - reflective screens;

13 - interlayer screens;

14 - heat-insulating gaskets.

Figures 1 and 2 also illustrate the flow pattern of the gaseous medium from the volume under the EVTI and from the EVTI into the volume under the fairing and further into the atmosphere (shown by arrows).

Figure 3 shows the dependence of the maximum along the flight path of the PH differential pressure of the gas medium ΔP acting on EVTI, on the relative effective area µ · S / V of its drainage holes.

Figure 4 shows the dependence of the maximum along the flight path of the PH differential pressure of the gaseous medium ΔP ₂ acting on the fairing, on the relative effective area µ ₂ · S ₂ / V _{2 of} its drainage holes.

KGCH PH (figure 1, 2) contains a fairing 1, KK 2, consisting of frame compartments 3 and the shaped compartment 4.

In the fairing 1 there are made drainage holes 5, at least one. Drainage holes 5 can be made in the local area of the fairing 1 (Node I, a) with a negative overpressure over the atmospheric pressure along the flight path of the LV, or behind the device for separating the aerodynamic flow 6 (Node I, c), or together with a spring-loaded cover 7 (Node I, s). The choice of cowling drainage option is determined by the permissible operational loads acting on the cowling along the LV flight path, taking into account the design features of the cowling.

On the surface of KK 2 installed EVTI 8. It is made in roll form or in separate panels and attached to the shell of the frame compartment 9 and the rods of the shaped compartment 10. The joints of its individual elements are sealed.

In EVTI 8, a device for ensuring its strength and thermophysical characteristics in the form of through drainage holes 11 with reflective screens 12 installed above the drainage holes 11 with a gap relative to EVTI 8 is made.

The drainage holes 11 communicate the volume of the gaseous medium in the EVTI 8 located between its interlayer screens 13 and the heat-insulating gaskets 14, as well as the volume of the gaseous medium beneath it with each other with the volume under the cowling 1.

Through drainage holes perform uniformly on the surface of EVTI 8, which ensures uniform or close to uniform distribution of pressure in the interlayer volumes of EVTI 8 and, consequently, pressure drops acting on its elements.

Thus, stress concentrations in its individual elements are excluded from non-uniform pressure drops in the presence of hidden local non-flow of the gas medium in the interlayer volumes of EVTI 8. At the same time, reflection screens 12 exclude thermal heating of KK 2 elements through drainage holes 11 of EVTI 8 from radiation from space objects.

Thus, the pressure drops acting on the elements of the EVTI 8 are reduced, and its thermophysical characteristics are retained.

The total effective area µ · S of the drainage holes 11 EVTI 8 for a given flight path is determined from relation (1), using the dependence shown in figure 3, taking into account the maximum allowable (from the strength condition) pressure drops ΔP _add acting on EVTI 8 and the coefficients a, b included in this ratio, depending on the parameters of the pH trajectory (see the valid region "A" of the definition of μ · S). In this ratio, the total volume V of the gaseous medium for the frame compartment 3 is taken as the volume consisting of the volume of the gaseous medium in the EVTI 8 and the volume between the EVTI 8 and the shell of the frame compartment 9, and for the truss compartment 4 as the volume consisting of the volume of the gaseous medium in EVTI 8 and the volume of the gaseous medium in the truss compartment 4.

The total effective area µ ₁ · S _{1 of the} gaps between the reflective screens 12 and EVTI 8 is determined from the relation (2).

The total effective area μ ₂ · S _{2 of the} drainage holes 5 of the fairing 1 for a given flight path is determined from relation (3) using the dependence shown in Fig. 4, taking into account the maximum allowable (from the strength condition) pressure drops _{ΔР 2dop} acting on the fairing 1, and the coefficients a, b included in this ratio, which also depend on the parameters of the pH trajectory (see the valid region "B" of the definition of μ ₂ · S ₂ ). In this ratio, the total volume V _{2 of the} gaseous medium is taken as the volume consisting of the volume of the gaseous medium under the EVTI 8, in the EVTI 8 and the volume between the fairing 1 and the surface of the EVTI 8.

Formulas (1) and (3) contain a mathematical description of the dependences of the total effective area of the drainage holes of the insulation and fairing on the maximum pressure differences ΔP and ΔP ₂ acting along the flight path of the PH, acting on the insulation and fairing, respectively, and are obtained by analyzing the flow of the gas medium in the volume , consisting of a gasdynamically interconnected volume located under the EVTI in the EVTI, and the volume located under the fairing KGCh.

In rocket science, interlayer screens 13 are made of aluminum foil several microns thick or aluminized polymer film, and heat-insulating linings 14 are made of various fiberglass materials (glass paper, fiberglass, fiberglass, etc.). Reflective screens 12 are made of a material with a minimum degree of blackness, for example aluminum foil.

The functioning of the KCH in the composition with KK, on the surface of which is installed EVTI, as follows.

Since, in contrast to the prototype, through drainage holes 11 are uniformly made on the surface of EVTI 8, during the flight of the spacecraft as a part of the KGCH, the gas medium flows from the volume under the EVTI 8 and its interlayer elements through the through drain holes 11 into the volume under the cowl 1 and then through its drainage holes 5 into the atmosphere (Fig.1, 2).

The outflow of the gaseous medium into the atmosphere occurs at subsonic speeds with non-locking in the drain holes 11 and 5, since the total effective area µ ₁ · S _{1 of the} gaps between the reflection screens 12 and EVTI 8 is made greater than or equal to the total effective area µ · S of the drain holes 11 (µ ₁ · S ₁ ≥µ · S) in accordance with relation (2), and the total effective area µ ₂ · S _{2 of the} drainage holes 5 is made greater than or equal to the total effective area of the gaps (µ ₂ · S ₂ ≥ µ ₁ · S ₁ ) in accordance with relation (3).

In the interlayer volumes of EVTI 8, a pressure is established close to the pressure under the KGC fairing. This ensures almost zero (taking into account the delay in pressure equalization) pressure differences acting on the interlayer screens 13 and heat-insulating gaskets 14 EVTI 8 along the flight path of the LV.

In the autonomous flight of the spacecraft, after the dumping of the fairing 1 KGH, the gas medium flows from the volume under the EVTI 8 and its interlayer elements into the surrounding atmosphere (figure 2). In the interlayer volumes of EVTI 8 and under it, an internal pressure close to atmospheric is established. The pressure drops acting on the interlayer screens 13 and heat-insulating gaskets 14 EVTI 8 are also close to zero. In this case, the reflective screens 14 installed above the through drainage holes 11 exclude the influence of the heat flux on the spacecraft elements from the radiation of space objects.

Thus, they provide the structural strength of the KGCh fairing, increase the structural strength and maintain the thermophysical characteristics of the EVTI KK, which leads to the fulfillment of the task. This increases the reliability of the operation of devices, systems and assemblies located in the compartments of the spacecraft, the LV launched into outer space as part of the KGCH.

Currently, the technical solution has been tested experimentally and is being implemented on one of the alternatives of the KGCh RN as part of the Soyuz spacecraft.

The technical solution can be used for various types of spacecraft launched by spacecraft into space as a part of the spacecraft: near-Earth, interplanetary, cargo, manned and other spacecraft.

Information sources

1. The spaceport. Ed. prof. A.P. Volsky, VI of the Ministry of Defense of the USSR, M., 1977, pp. 160-161, Fig. 5.3, 5.4.

2. Ibid., P. 164, Fig. 5.6.

3. Cosmonautics: Encyclopedia. / Ed. V.P. Glushko. M .: Soviet Encyclopedia, 1985, p. 394.

4. Handbook of the physical and technical foundations of cryogenics / Ed. prof. M.P. Malkova, Moscow: Soviet Encyclopedia, 1973, p. 236-237.

5. Cosmonautics: Encyclopedia. / Ed. V.P. Glushko. M .: Soviet Encyclopedia, 1985, pp. 304-305.

6. Ibid., Pp. 369-370.

Claims (1)

The space head part of the launch vehicle containing a radome, a spacecraft consisting of at least one compartments, on the surface of which screen-vacuum thermal insulation is installed, characterized in that a device for providing strength and thermophysical characteristics of screen-vacuum thermal insulation in the form of through drainage holes evenly spaced on the surface of said insulation, communicating interlayer volumes of the gaseous medium of this insulation and under isolation with the volume of the gaseous medium a fairing, while reflective screens are installed above the drainage openings with gaps relative to the insulation, and at least one drainage openings are made in the fairing, communicating the volume of the gaseous medium under the fairing with the atmosphere, and the total effective area of the insulation drainage holes, the gaps between the reflective screens and fairing and drainage holes are determined from the ratios:
μ · S≥a · ΔP ^-to · V, μ ₁ · S ₁ ≥μ · S;
μ _{2 2} · S ₁ · S ≥μ ≥a · ΔP ₁ ^-to ₂ · V _2,
where S, S ₁ , S ₂ [cm ² ] is the total area of the drainage holes of the insulation, the gaps between the reflective screens and insulation and the drainage holes of the fairing, respectively;
µ, µ ₁ , µ ₂ - flow coefficient of the drainage holes of the insulation, the gaps between the reflective screens and insulation and the drainage holes of the fairing, respectively;
V [m ³ ] - the total volume of the gas medium in the insulation and under the insulation;
V ₂ [m ³ ] - the total volume of the gas medium under the fairing;
ΔР [kgf / cm ² ] is the maximum differential pressure of the gaseous medium acting on the insulation along the flight path of the LV;
ΔP ₂ [kgf / cm ² ] - the maximum along the flight path of the LV differential pressure of the gas medium acting on the fairing;
a, c - coefficients depending on the parameters of the LV flight path that approximate the curves of the effective area of the drainage holes of the insulation and fairing as a function of the maximum differential pressure acting on the flight path acting on the insulation and fairing.

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