RU2700150C1 - Method for minimization of exclusion zones for carrier rocket separating parts and device for its implementation - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: group of inventions relates to aerospace engineering and can be used to reduce areas of falling parts of carrier rocket stages. Method consists in the fact that at the pre-flight preparation stage of the carrier rocket the parameters of the motion of the separating parts – SP are determined to their falling to the ground. Based on the results of calculations, sections are determined on escapement path for impact on SP. Signal is generated during autonomous flight of SP and additional structure is subjected to impact on structure. When forming SP from polymer composite materials, a combustion system consisting of several modules is installed on the structure of SP, providing for thermal loading of extracted masses of the structure of SP by supplying heat contained in combustion products of a mixture of oxygen and propane gases. Amount of heat released by each module is determined from the condition for heating the selected mass of the SP structure to the combustion temperature. Ratio of mass seconds flow of oxygen and propane in a specific module of the combustion system, direction of movement of jets of combustion products is determined from the condition of ensuring operability of the module structure on the interval of heating time, minimum reserves of oxygen and propane. Number of modules - points of thermal loading of structure of SP for providing heating of selected mass of structure of SP to combustion temperature is selected from condition of combustion of structure SP at specified time interval.

EFFECT: reduction of areas of falling of separating parts by their burning at atmospheric section of descent trajectory.

2 cl, 3 dwg

Description

The invention relates to rocket and space technology and can be used to reduce the areas of incidence of the separating parts (OCH) of the stages of launch vehicles. The PH stages include: spent stages, interstage transition compartments, head fairing flaps.

One of the main problems associated with the reduction of the technogenic impact of LV launches on the environment is the presence of PF, which leads to the need to allocate significant areas of exclusion zones in the territories and water areas of the Earth's surface for areas of PF incidence.

The well-known "Method of minimizing exclusion zones for the detachable parts of a multi-stage launch vehicle" (RF patent No. 2464526 IPC F42B 15/36), according to which at the stage of pre-flight preparation of the LV, the parameters of the movement of the IF are calculated until they fall to Earth and the necessary the exclusion zone, in the construction of the OCh, elements are distinguished that differ in the degree of their destruction in the dense layers of the atmosphere after separation from the LV, for these separately flying elements of the OCh, zones of the necessary alienation are calculated and, after separation, О P from the LV during the autonomous flight of these parts on the trajectory until the moment they enter the dense layers of the atmosphere, they form a signal on the means of division and influence the design of the optical elements for their physical separation into selected elements.

The prototype of the proposed technical solution is the "Method of minimizing the exclusion zones of the separated parts of the launch vehicle" (RF patent No. 2626797 IPC F42B 15/00, B64G 1/64) according to which the minimization of the exclusion zones for OCh, for example, head fairing flaps, transition compartment PH, consists in the fact that at the stage of pre-flight preparation of the LV, the parameters of the VL movement are calculated until they fall to the ground and the results of the calculations determine the sections on the descent trajectory for impact on the VL, the formation of a signal during an autonomous flight О H and carry out the impact on the design of the HF, the pyrotechnic composition (PS) is placed on the HF, which ensures, when it is burned, the HF is heated to the temperature at which the HF is burned in the incoming air flow, when the altitude reaches 25-30 km, the HF is ignited, for example , using the ignition train, a signal to activate the ignition train is formed from the moment of separation of the RF from the LV, when generating a signal to activate the PS, the ignition train ignition delay and combustion of the PS, size Substitution of PS along the surface of the OCh is carried out taking into account the surface temperature of the OCh at the beginning of the engagement of the PS, the placement of the incendiary composition is carried out in several places, based on increasing the probability of ignition, minimizing the combustion time of the PS and OCh, as a PS, compositions are used, for example, mixtures of powdered metals, for example , magnesium, aluminum, titanium or their alloys (for example, a mixture of aluminum and titanium powders), the compositions used, for example, are Fe ₂ O ₃ + Mg (69:31), BaO ₂ + Mg (78:22) as an incendiary composition.

When applying this method to the burning of OChs such as modern head fairings (GO), which are structures made of polymer composite materials such as carbon fiber and aluminum honeycomb between them, a number of problems arise:

- during the combustion of PS placed in the GO structure, the aluminum honeycomb core is melted and does not enter into further reaction with the oncoming flow oxygen;

- the heat received from the combustion of the PS mass placed inside the GO structure is not enough to heat the carbon fiber to the combustion temperature in the oncoming air flow, including due to the low thermal conductivity of the carbon fiber being stratified during heating, the entrainment of heat by the oncoming air flow, etc.

The technical result of the proposed technical solution is to reduce the areas of fall of the PF by burning it in the atmospheric section of the descent trajectory.

The specified technical result is achieved due to the fact that in the known method of minimizing exclusion zones for PF, for example, head fairing flaps, transition compartment of the LV, which consists in the fact that at the stage of preflight preparation of the LV, the parameters of the movement of the IF are calculated until they fall to the ground and according to the results of the calculations, the sections on the descent trajectory are determined for impact on the PF, the signal is formed during the autonomous flight of the PF and the design of the PF is impacted by additional thermal loading, The following actions are added to the claimed technical solution:

a) install on the OCh combustion system, consisting of several modules that provide thermal loading of the selected masses of the shell structure of the OCh by supplying heat contained in the combustion products of a mixture of oxygen and propane gases;

b) the amount of heat generated by each module is determined from the condition of heating the selected mass of the construction of the HF to the combustion temperature;

c) the ratio of the mass second consumption of oxygen and propane in a particular module of the combustion system is determined from the condition of ensuring the operability of the module design over the heating time interval, the minimum fuel supply (oxygen and propane).

d) the number of modules and, correspondingly, the points of thermal loading of the optical component to ensure heating of the selected mass of the optical component to the combustion temperature, is selected from the combustion condition of the optical component for a given time interval.

The implementation of the method

The action of the method is illustrated by the graphic material:

- in FIG. 1 shows the traditional design of the element of the three-layer head fairing with aluminum honeycomb (patent RF №2581636 F42B 10/46, B64G 1/64), where 1 is an aluminum honeycomb, 2, 3 - carbon fiber plate (UP);

- in FIG. 2 shows a diagram of the design and installation of the module of the combustion system at the high frequency;

- in FIG. Figure 3 shows a diagram of thermal loading of the wall of the construction of the OF and module.

The rationale for the actions of the method

a) install an incineration system on the design of the PF, consisting of several modules that provide thermal loading of the selected masses of the PF shell structure by supplying heat contained in the combustion products of a mixture of oxygen and propane gases;

Several modules are introduced into the composition of the PM burning system, for example, for the transition compartment (PO) of the Soyuz launch vehicle, which after separation is further divided into 3 parts, respectively, the number of modules for heating the separated PO fragments must be at least three. The composition of each module includes: fuel reserves (fuel, oxidizer), a fuel supply and mixing system in the nozzles, an ignition system, and a module mounting structure for software.

In FIG. 2 shows a diagram of the module and its installation on the OF, where 4 is a container with oxygen, 5 is a container with propane; 6 - shut-off valves on the supply lines; 7 - mixer; 8 - ignition system; 9 - nozzles; 10 - a protective screen against reverse heat flow; 11 - a protective screen from the effects of torch jets of the mid-flight engine of the upper stage; 12 - shell OCh (for the case of ON - a single-layer carbon fiber, for the case of the head fairing three-layer shell of Fig. 1); 13 - power set OCh.

b) the amount of heat released by each module is determined from the condition of heating the selected mass of the construction of the HF to the combustion temperature;

The amount of heat, respectively, the supply of fuel (fuel and oxidizer) in each module is determined from the condition of heating the allocated mass of the structures of the HF to the combustion temperature, taking into account all the components of the heat acting on the HF (ablation by the oncoming aerodynamic flow, heat transfer to other structural elements of the HF, radiation heat into the surrounding space, the heat of radiation from the Sun, Earth, re-radiation from the Earth).

c) the ratio of the mass second consumption of oxygen and propane in a particular module of the combustion system, the direction of movement of the jets of combustion products is determined from the condition of ensuring the operability of the module design over the heating time interval, the minimum fuel supply;

The temperature of the products of combustion of oxygen and propane depends on the ratio of mass second flow rates and can vary over a wide range.

Heat flows from the combustion products fall on the nozzles, heat them, as well as the gas supply system, which, when a certain temperature is reached, can disrupt their performance. To ensure the health of the module, a screen 10 is installed, and the use of the ability to control the temperature of the combustion products due to the ratio of the mass second consumption of oxygen and propane in a specific module of the combustion system will allow to extend the time interval of the health of the module as a whole.

In FIG. Figure 3 shows a diagram of the thermal loading of the wall of the construction of the OCh and the module during the expiration of the combustion products 14: convective Q _k and conductive Q _λ heat fluxes from the products of combustion to the OCh; Q _a - radiation and heat transfer to the environment; U _∞ is the incident flow.

d) the number of modules and, correspondingly, the points of thermal loading of the optical component to ensure heating of the selected mass of the optical component to the combustion temperature, is selected from the combustion condition of the optical component for a given time interval.

The rate of burning of the OCh depends on a number of factors: the mass of the OCh, the burning rate of the material of the OCh, which in turn depends on the ambient pressure, the presence of oxygen, etc. In connection with the need to burn OCh for a given time interval, for example, when moving in the altitude range from 15 km to 1 km in the time interval, for example, 200-250 sec (depending on the speed of the OCh), it is proposed to start burning the OCh in several parts, accordingly, placing modules on these parts.

Detachable part

As a prototype of the HF, the HF system is adopted in the form of a head fairing (GO) according to the patent of the Russian Federation No. 2581636 F42B 10/46, B64G 1/64), the GO is a three-layer structure of polymer composite materials in the form of a bivalve shell of variable curvature containing an external bearing layer made of carbon fiber and the inner carrier layer with a filler between them, the filler contains a termite-igniting mixture (TSS), which is flammable when the surface of the GO shell structure reaches the ignition temperature of the TSS, and the mass of the TSS is determined by the shapes ole

where: m _go , m _TZS is the mass of the shell structure GO, TZS, respectively, kg;

Q is the heat released during the combustion of the heating element, kJ / kg;

ΔT = T ₁ -T ₀ , deg .;

T ₀ is the average temperature of the GO shell structure at the moment it enters the dense layers of the atmosphere, where the GO combustion process should begin, K;

T ₁ is the temperature necessary to ensure the beginning of the spontaneous combustion process of the structure of the shell GO, K.

The composition of TLC includes an oxidizing agent, for example, salts or metal oxides (KClO3, KClO4, CuO, etc.) mixed with a powdered metal, one or more, for example, powders of magnesium, aluminum, titanium or their alloys, and also, possibly, and a binder, for example, colloxylin.

TZS is applied on the inner surface of the GO or in the honeycomb of the shell, based on the condition of uniformity of heating of the shell structure of the GO during combustion of the TSS and maintaining the position of the center of mass of the GO.

The use of this technical solution is difficult in the following positions:

- placement in the honeycombs of a metal honeycomb core, located between the outer and inner bearing layers of the GO shell, of a termite-incendiary mixture is associated with significant changes in the technology of manufacturing shells, leading to a significant increase in the cost of the process of their manufacture;

- the used solid fuel TZS have significantly lower calorific value compared to the calorific value of the oxygen-propane fuel pair;

- the mass of TCC is calculated from the condition of heating the entire mass of GO to the combustion temperature and ensuring combustion in the minimum time, and not from the condition of heating a separate part of the GO, which during the combustion process releases heat to maintain its own combustion, which increases the combustion time of the entire mass of the GO structure;

- the mass of TZS was calculated without taking into account losses of entrainment of heat, etc.

These disadvantages are eliminated due to the fact that in the known device, which is a separating part of the launch vehicle, for example, head fairing flaps, transition compartments, which includes a structure of polymer composite materials in the form of a shell made of carbon fiber reinforced plastic, a power set, a combustion system, are additionally introduced to each module of the combustion system:

a) a gas supply system through nozzles with their subsequent combustion and subsequent exposure of combustion products directly to the design of the OCh,

b) tanks with compressed gas, oxidizing agent (oxygen) and gaseous fuel (propane),

c) the fastening of the module of the combustion system is carried out to the power set of the OF, using detachable connections.

d) a protective shield against the thermal effect of the torch on the module of the combustion system.

Other components can be used as a fuel and an oxidizing agent, for example, hydrogen peroxide, hydrogen, acetylene, liquid self-igniting components of rocket fuel, etc.

The proposed device operates as follows.

Before separation of the OCh, the main engine of the upper stage of the launch vehicle is launched, the protective screen 11 protects the combustion system module from heat loading over the interval of this heat exposure. After separation of the HF, the combustion system is activated: in each module, by opening the valves of 6 cylinders with oxygen gases 4 and propane 5, the gases are mixed in the mixer 7, then the gas mixture enters the nozzles 9, electric ignition is performed in the ignition system 8 and combustion in the nozzles 9 The combustion products flowing out from the nozzles 9 provide heating of the selected masses of the shell 12, which during the combustion process will give off heat to the combustion temperature of the HF to the combustion temperature in a given time, for example, in 50 seconds; during this time, the OCh enters the atmospheric layers, where the necessary amount of oxygen is already present for burning the material of the OCh design. When the OCh moves in the atmosphere, its further combustion occurs over a time interval of the order of 200-250 sec.

The technical feasibility of the proposed method and device is ensured by the existing level of development of rocket and space technology, including the borrowing of existing and proven technology for the creation and operation of modules for the combustion system containing heat-resistant nozzles, protective screens, fuel supply system, etc.

Example: for burning the Soyuz launch vehicle weighing 450 kg, when divided into 3 parts of 150 kg each, one combustion module is installed, the required amount of heat for heating to the combustion temperature (~ 1100 ° C) is 41.4 MJ, respectively, the mass of oxygen and propane will be 0.9 kg.

Claims (2)

1. The method of minimizing exclusion zones for the separating part of the stage in the form of flaps of the head fairing of the launch vehicle, which consists in the fact that at the stage of pre-flight preparation of the launch vehicle, the motion parameters of the separating part — OC are calculated until they fall to the ground and determined by the calculation results sections on the descent path for impact on the PF, form a signal during the autonomous flight of PF and affect the design of the PF with additional thermal loading, characterized in that when When OCh is made from polymer composite materials, an OG system is installed on the OG structure, consisting of several modules that provide thermal loading of the extracted mass of the OCh structure by supplying heat in the products of combustion of a mixture of oxygen and propane gases, the amount of heat generated by each module is determined from the heating condition the selected mass of the construction of the HF to the combustion temperature, and the ratio of the mass second consumption of oxygen and propane in a specific module of the combustion system I of the jets of combustion products is determined from the condition of ensuring the operability of the design of the module over the interval of the heating time, the minimum supply of oxygen and propane, the number of modules and, correspondingly, the thermal load points of the design of the HF to ensure that the selected mass of the HF structure is heated to the combustion temperature, is selected from the condition for the combustion of the HF design at a given time interval. 2. A detachable part of the launch vehicle, in the form of flaps of the head fairing, which includes a modular combustion system, characterized in that when performing the RF from polymer composite materials, a system including a compressed gas mixer is introduced into each module of the combustion system, from which gas mixture is supplied to nozzles designed for burning a gas mixture and supplying its combustion products to the inner shell of the filter, containers with compressed gases of an oxidizing agent - oxygen and fuel - propane, fixing the module with Combustion systems for the power set of the HF, protective shields from the thermal effects of flares on the module of the combustion system.

Images