RU2223202C2 - Method of control of transportation of articles with thin-walled reservoirs charged with gas by aviation means - Google Patents

Abstract

FIELD: aeronautical engineering and space engineering. SUBSTANCE: proposed method includes change of altitude and speed of flight in route and monitoring of supercharging of thin-walled reservoir. Supercharging of reservoirs depends on their strength and resistance of envelope. Change in flight altitude is performed by ratio taking into account limiting altitude of this aircraft, certified data on cargo to be transported and present magnitude of pressure in reservoir. Change in flying speed is performed by ratio taking into account initial ground temperature of air, flying altitude, temperature change linear coefficient depending on altitude, certified data on cargo, present magnitude of pressure in reservoir and present magnitude of barometric pressure in cargo compartment. EFFECT: enhanced reliability of transportation. 3 cl, 6 dwg

Description

 The invention relates to aerospace engineering to ensure the delivery by air of products to the assembly or operation of space rocket complexes (RKK).

 As a rule, products can be a separate structure made in the form of thin-walled containers (fuel tanks) or have a complete assembly unit in the form of stages of missiles (blocks). Known transportation of rocket blocks (RB), fuel tanks and other containers in the cargo compartments of wide-body transport aircraft, while transporting both fully assembled products and technological parts, since the production cycle can be completed directly at the launch complex (SK). For such transportation, new wide-body aircraft are being created, for example, the US Supergappi aircraft, and in the CIS countries Ruslan, Mriya and others [1].

 However, the capabilities of wide-body aircraft have a limit due to the dimensions of the transported products, and products with a diameter of more than 6 m are more profitable to transport on the external suspension of the aircraft. Delivery of such products by water is possible, but not all waterways from the manufacturer to their destinations are available, and such dimensional products are not allowed to be transported by rail according to existing standards (more than 4.2 m).

 Known methods of controlling the transportation of products with inflated gas with thin-walled containers of a launch vehicle (LV) by aviation means, which consists in changing the height and speed of flight when transporting them inside a transport container located on top of the fuselage of the carrier aircraft [2, 3].

This method of transportation has a number of significant disadvantages, namely:
the dimensions of the transported goods are limited by the dimensions of the container;
due to the significant mass of the container, either the mass of the transported products or the flight range decreases;
the flight range is complicated due to additional operations of loading and unloading the container, its opening and closing.

 It should also be noted that the creation of a transport container is a complex engineering task commensurate with the creation of a new fuselage for a wide-body transport aircraft.

 Partially, the disadvantages of the aforementioned method were eliminated in the technical solution, which proposed a method for controlling the transportation of products with thin-walled containers with pre-inflated thin-walled containers with nose and stern cowls equipped with air intakes, through which they are in flight due to the speed of the incoming flow inflated internal cavities under the fairings from the condition of ensuring their stability against collapse [4].

 In this way, various ampouled air-to-air, air-to-ground missiles and other oversized industrial cargoes are transported by external helicopters.

 Closest to the claimed method of air transportation of thin-walled LV containers, adopted as a prototype, is a method for controlling the transportation of products with blown gas with a thin-walled capacity (fuel tank "LV" Energy) using the carrier aircraft "Atlant" [5]. A product with pressurized gas (air) with a thin-walled tank - an airtight fuel tank (cargo) - is placed on the "back" of an aircraft - an Atlant aircraft, which makes a change in the altitude and flight speed path during ascent and descent before landing, while simultaneously controlling the charge thin-walled capacity. Transportation is carried out under conditions limited by temperature and barometric pressure at the points of departure and reception of cargo, so as not to violate the high-altitude flight levels of aircraft.

 The disadvantage of the method adopted for the prototype is the limitation of air transportation of products with pressurized gas with thin-walled containers between zones with different climatic conditions, i.e. having a noticeable difference in temperature and pressure of the environment with the relevant requirements for its sealing.

 This is explained by the fact that any sealed thin-walled container has a well-defined pressure drop on the walls of the shell from the side of the inner (inflated) cavity and the outer surface washed by the external flow, limited by the strength of the structure of the thin-walled container (tank), as well as a completely allowable difference on the shell wall, limited tank stability.

 The boundaries of this range are selected from the condition of the tank for its intended purpose, i.e. when working as part of the launch vehicle.

In the graph of FIG. 1 shows a typical range of permissible pressures in the tanks of the first stages of the launch vehicle (shaded area), where:
R _{B MAX} - the maximum allowable boost pressure of a thin-walled tank when working as part of a product;
R _{B PR} - ultimate pressure, based on ensuring the strength of thin-walled containers;
P _N - environmental pressure (external static);
R _BU - the maximum pressure inside a thin-walled tank, based on the condition of maintaining stability;
ΔP _MIN - the minimum allowable differential pressure (P _N -P _BU ), based on the conditions for ensuring the stability of the shell of a thin-walled tank;
ΔP _MAX - the maximum allowable pressure drop (R _{B PR} - R _N ), based on the conditions for ensuring the strength of the shell of a thin-walled container;
R _BNO - initial pressure in a thin-walled container;
R _BUO - the initial pressure in a thin-walled tank, based on the stability condition of the shell of a thin-walled tank.

 When transporting a thin-walled container - a tank - from the manufacturer to the technical complex where the final assembly of the product takes place, the pressure inside the tank should be within acceptable values at all stages of transportation.

 In the case of transporting products from a warm climatic zone to a cold one from South to North (see the graphs of Figs. 1-4) at a low pressure of the pressurization of the tank, the gas cools and, when planted in the cold climate zone, buckling of the tank shell may occur, and vice versa when transporting the product from a cold climatic zone at a relatively high boost pressure, a loss of strength of the tank after landing in the warm zone due to a further increase in pressure inside the tank due to heating of the boost gas can occur.

 Thus, the choice of the initial gas boost in the tank from the range of acceptable values does not yet ensure the safety of the tank during air transportation between zones with different climatic conditions in temperature and pressure, and it is also possible to lose stability during the flight of end shells closed by aerodynamic cowls due to growth pressure under the fairings, depending on the altitude and speed of flight with strong cooling of the boost gas (see the graph of FIGS. 5-6).

 The problem solved by the present invention is the development of a method for controlling the air transportation of products with thin-walled containers (tanks), especially large-sized products, to ensure reliable transportation both within the same and between different climatic zones.

где Н_{П МАХ} - предельно допустимая высота полета, м;
V_{П МАХ} - предельно допустимая скорость полета, км/ч;
Н_{П ПРЕД} - предельная высота Н_{П ПРЕД} = 12000 м;
ΔP_MAX и ΔP_MИН - паспортные данные на транспортируемое изделие;
Р_Б - текущее значение давления в тонкостенной емкости, кгс/см²;
Р_Н - текущее значение барометрического давления в грузовом отсеке (в контейнере или атмосферы за бортом на высоте полета), кгс/см²;
Т₀ - начальная (земная) температура воздуха, К;
К₁ - линейный коэффициент изменения температуры с высотой, одновременно с изменением высоты и/или скорости полета регулируют по данным контроля наддув тонкостенной емкости на трассе.The technical result can be achieved by the fact that in the method of controlling the transportation of products with inflated gas by thin-walled containers by aviation means, which consists in changing the altitude and speed of the aircraft with the transported product on the track and controlling the pressurization of thin-walled containers in the product, in contrast to the prototype of thin-walled pressurization containers are made based on the requirements of strength and stability of the shell of a thin-walled container, a change in the height of N _P and / or speed V _P flight dividing their value from the relations:

where N _{P MAX} - the maximum permissible flight height, m;
V _{P MAX} - the maximum permissible flight speed, km / h;
N _{P PRED} - maximum height N _{P PRED} = 12000 m;
ΔP _MAX and ΔP _MIN - passport data for the transported product;
R _B - the current value of pressure in a thin-walled tank, kgf / cm ² ;
P _N - the current value of the barometric pressure in the cargo compartment (in the container or atmosphere overboard at flight altitude), kgf / cm ² ;
T ₀ - initial (terrestrial) air temperature, K;
To ₁ - a linear coefficient of temperature change with altitude, simultaneously with a change in altitude and / or flight speed, is controlled according to the control of supercharging a thin-walled tank on the track.

 At the same time, it is proposed that, as one of the options, at the same time as the altitude and flight speed is changed, thin-walled tank pressurization be adjusted by bleeding the pressurization gas or supplying an additional mass of gas to it due to the pressure head and, as another option, by changing the pressurization gas pressure due to a change in its temperature.

 The above formulas, significantly removing restrictions, make it possible to significantly expand the range of adjustable flight parameters - altitude and / or speed - due to additional changes in both the initial and current values of gas pressure and temperature in the tank of the transported product, despite the fact that not on the whole route it is possible to change both height and speed at the same time.

An example of the implementation of one of the options for providing air transportation of a product with a thin-walled capacity - a fuel tank for a space rocket (ILV) "Energia", having the shape of a cylinder with a diameter of 7.8 m and a volume of 535 m ³ , was carried out using a carrier aircraft from the dispatch aerodrome to Delivery aerodrome (Baikonur Cosmodrome) with a transportation duration of up to two hours.

The initial boost pressure was selected from the condition of ensuring the safety margins and stability of the tank shell for the maximum set temperature difference Т _НО in the range from -20 ^o С (sending aerodrome) to +20 ^o С (receiving aerodrome). In the limiting case ΔP _MIN = -0.05 atm (external pressure greater than the pressure P _H P supercharging _B) and ΔP _MAX = 1.2 atm (boost pressure P _BO greater than the external pressure P _H from the condition of the tank shell strength).

A further decrease in ΔP _MAX and ΔP _{MIN is} unacceptable in terms of strength and stability and is not used in rocketry.

During the flight at a given height N _{P MAX} (the maximum height provides the maximum flight range), the charge gas is cooled in a thin-walled tank, therefore, when the carrier aircraft decreases in the climatic zone with T _НО = +20 ^o С, the permissible limit for ΔP _MIN can be exceeded .
There is a need for accurate calculation of the regulation of altitude and speed of flight and control of boost parameters (pressure, temperature) of a thin-walled tank to prevent violation of the integrity of the transported product. The control of the boost parameters is carried out using pressure and temperature sensors, the values of which are displayed on the operator’s console of the carrier aircraft. The speed and altitude are visually controlled by the pilot on the instruments of the carrier aircraft.

A significant new distinguishing feature of the claimed method of aviation transportation is the regulation of flight altitude and speed depending on the pressure and temperature of the boost gas in a thin-walled vessel according to empirical dependences (according to the formulas N _P and V _P ), obtained experimentally during testing in the course of flight tests of carrier aircraft with mock-ups of tanks and during the transportation of cargo of flying products.

 The proposed method for controlling the transportation of products with large-sized thin-walled containers (tanks) by aviation means to ensure the reliability of transportation both within the same or between different climatic zones can be implemented using Atlant carrier aircraft (Il-76, Ruslan, Mriya et al. ) with the cargoes of the Energia rocket, the Buran airframe and the Aurora rocket blocks, space accelerating blocks (RB) of the Corvette, DM3, DM-SL, etc. type, as well as when transporting products without aerodynamic fairings, if the shape tank not with flax degrades the aerodynamic system "plane + load" when transporting goods on the external load of the aircraft or transportation of goods in the cargo hold in the shipping container, placed in the cargo compartment of the aircraft.

где Р_НО - барометрическое атмосферное давление на поверхности Земли в районе аэродрома вылета, мм рт.ст.;
К_t - безразмерный термический коэффициент, учитывающий влияние температуры окружающей среды;
ΔP_MИH,ΔP_MAX - минимальный и максимальный допустимые перепады давления между полостью тонкостенной емкости и окружающей средой, кгс/см².Regarding the initial pressure (R _BNO ), it can be clarified that this dependence is empirical, determined on the basis of processing a series of field tests with various transported thin-walled containers and represents the following dependence:

where R _HO - barometric atmospheric pressure on the Earth's surface in the vicinity of the departure aerodrome, mm Hg;
To _t is a dimensionless thermal coefficient that takes into account the influence of ambient temperature;
ΔP _MИH , ΔP _MAX - minimum and maximum allowable pressure drops between the cavity of a thin-walled container and the environment, kgf / cm ² .

Since in most cases on the territory of Russia the barometric pressure P _НО in the area of aerodromes does not go beyond P _НО = 710-770 mm Hg. , then with a sufficient degree of accuracy we can take P _HO / 737, equal to ~ 1.

The number 735 is a conversion factor for the dimension of pressure from mmHg. Art. in kgf / cm ² , since 735 mm Hg corresponds to one atm and at the same time represents the arithmetic mean pressure obtained in specific tests.

The thermal coefficient K _t is an empirical dependence of the form
K _t = a + b • T ₀ ;
where a = 0.7 is a dimensionless coefficient;
b = 0.01 - coefficient having a dimension of 1 / ^o C.

Формула для определения Р_БНО примет вид

При крейсерском полете сравнивают известными методами текущие значения давления в тонкостенной емкости Р_Б и давления за бортом Р_Н, выдерживают безопасный их перепад таким образом, что при уменьшении избыточного давления Р_Б - Р_Н увеличивают высоту полета, а при увеличении избыточного давления высоту полета уменьшают.Thus, the thermal coefficient will have the form

The formula for determining P _BNO will take the form

When cruising, the current values of pressure in the thin-walled vessel Р _B and pressure overboard Р _{Н are} compared by known methods, they are kept safely in such a way that, with a decrease in overpressure Р _B - Р _Н , the flight altitude is increased, and when the excess pressure is increased, the flight altitude is reduced .

To narrow the range of flight altitudes during climb, the cruising flight speed and with a decrease in the decrease in excess pressure Р _B - Р _{Н are} regulated by increasing the pressure in the thin-walled vessel Р _B due to the supply of compressed air to it from the side of the carrier’s aircraft, and the increase in excess pressure is compensated by bleeding thin-walled capacity.

 It is proposed to regulate the supercharging of a thin-walled tank during the flight simultaneously with a change in altitude and / or speed by bleeding the supercharging gas or supplying an additional mass of gas to it due to the pressure head or from the aircraft’s onboard means. However, another option is also possible - adjustment of the supercharging of a thin-walled vessel is carried out by changing the pressure of the supercharging gas by increasing or decreasing its temperature.

In cruise flight mode, it is possible to compensate for the decrease in excess pressure in the product R _B - R _{N by} heating the air filling it without violating the tightness due to the pumping of hot air supplied from the side of the carrier aircraft, and the increase in excess pressure is compensated by cooling the air in the product by pumping cold air from the carrier aircraft.

They carry out combined transportation control, combining, while reducing excess pressure in the product Р _B - Р _Н, increasing flight altitude, additional pressurization of the thin-walled tank with air while increasing its temperature, and when increasing excess pressure in the product, they reduce the flight altitude and bleed air from the thin-walled tank to obtaining the required difference.

The formula for calculating the flight altitude (N _P ) is derived from the inequality
H _P • (1 + P _B -ΔP _MAX ) ≤12000 • (1 + ΔP _MAX -P _B ),
determined empirically from the dependence shown in figure 1.

где Н_П - текущее значение высоты полета, м;
Н_{П МАХ} - предельно допустимая высота полета, м;
Р_Б - текущее значение давления в тонкостенной емкости, кгс/см²;
ΔP_MAX - максимально допустимый перепад (со знаком минус) давление между внутренней полостью тонкостенной емкости и внешней средой, а также средой в контейнере или в грузовом отсеке самолета из условия обеспечения устойчивости оболочки тонкостенной емкости, кгс/см².With increasing flight altitude, the external pressure (P _N ) decreases, therefore, the maximum permissible pressure in a thin-walled vessel decreases, the intersection of which with P _MAX should not be. This determines the inequality and the maximum height of 12,000 m, whence

where N _P - the current value of the flight altitude, m;
N _{P MAX} - the maximum permissible flight height, m;
R _B - the current value of pressure in a thin-walled tank, kgf / cm ² ;
ΔP _MAX is the maximum allowable pressure difference (with a minus sign) between the internal cavity of the thin-walled container and the external environment, as well as the medium in the container or in the cargo compartment of the aircraft, from the condition of ensuring the stability of the shell of the thin-walled container, kgf / cm ² .

где V_ПР - приборная скорость, км/ч;
ρ₀ - плотность воздуха при высоте Н = 0;
ρ_H - плотность воздуха при высоте полета (Н_П до 12 км).The formula for calculating flight speed (V _P - air speed) is derived from the Vetchinkin formula for a flight altitude (N _P ) of less than 12 km and has the form

where V _PR - instrument speed, km / h;
ρ ₀ - air density at a height of H = 0;
ρ _H - air density at flight altitude (N _P up to 12 km).

After converting and introducing empirical coefficients 24, 6, and 0.0065, the flight speed (V _P ) will take the form described in the text.

Thin-walled container before loading onto a carrier aircraft is pressurized with boost gas to a pressure determined by the formula (P _BNO ) and ensuring the stability of its shell with a minimum mass of boost gas, and the flight altitude is limited by the formula (N _P ). Choose a flight speed depending on the height of the cruise flight according to the formula (V _P ).

The essence of the invention will be explained using figures 1-6:
in FIG. 1 shows the dependence of the ultimate pressure in the product depending on the external pressure associated with the flight altitude of the carrier aircraft;
in FIG. Figures 2-4 show changes in altitude, temperature, and pressure in a thin-walled product container during flight in different climatic zones over the flight time;
figure 5 shows the dependence of the flight altitude on the maximum allowable differential pressure in a thin-walled container;
figure 6 shows the dependence of the flight speed on the minimum allowable differential pressure in the thin-walled capacity of the product.

Implementation of the proposed method is carried out as follows: a thin-walled container inflated with gas is raised using an aircraft (for example, a carrier aircraft), changing the height and speed of the flight along the route, and control the boost pressure inside the product’s thin-walled container. In the take-off, cruising, and lowering sections during boost control, the pressure in the product P _B and the pressure outside P _{N are} compared by known methods, ensuring a safe pressure drop P _B - P _N , determined by the strength of the tank and the stability of the blown shells of the product, corresponding to a change in flight height on the cruiser mode and change in flight speed during climb and decrease, for which the corresponding pressure readings in a thin-walled tank are displayed on the control panel in the cockpit. Simultaneously with a change in altitude and flight speed, thin-walled capacity pressurization is controlled by bleeding off the supercharging gas or supplying an additional mass of gas to it, for example, from balloons with supercharging gas supplied through a reducer using start-and-shut valves or intake of supercharged gas (air) to create the necessary pressure from the compressor of the aircraft engine. In the proposed method, the gas supply is proposed to be carried out due to the high-pressure head with the help of an air intake directed towards the oncoming flow. The diameter of the air intake, which is a circular hole in the center of the front fairing, depends on the volume of the thin-walled container of the transported product.

 In this case, emergency maneuvers are also possible, for example, with a sudden increase in pressure in the compartment or its sudden depressurization.

The presence of conditions ensuring the possibility of the above actions, the combination of which makes up this method — indicates the modes of temperature and pressure inside a thin-walled container and the speed of the surrounding environment, pressure and ambient temperature, and to clearly specified limits on the height of transportation of the product, the speed of flow around it with an external stream, the initial boost pressure, the range of temperature and pressure regulation in the product. All these parameters are connected by empirical and thermodynamic relations, which make it possible to introduce calculated dependences (formulas R _BNO , N _P , V _P ).

 The development of rocket blocks of the first and second stages of the Aurora rocket launcher and the Corvette space rocket booster blocks and the second stage of the Air Launch are carried out taking into account the proposed method of air transportation with the delivery of both individual parts of the rocket launcher and fully assembled missile blocks from the factory the manufacturer to the place of launch by transport aircraft An 124, IL 76 or Mriya, which are in operation.

 Currently, the use of the invention is possible to ensure the transport by air of RSC Energia products, for example, Aurora, Soyuz, Progress rocket launchers, as well as 11D861 type rocket booster units and its modifications, 11C824F, DM1-4, LM , 314GK (Sea Launch), etc.

Sources of information:
1. The journal "Science and Life", Pravda Publishing House, Moscow, 1990, V. Burdakov's article "Cargo on the back of an airplane."

 2. The newspaper "Evening Moscow" from 10.27.88, the article by D. Guy "Saddle for the" Buran ".

 3. The newspaper "Socialist Industry" on 10.29.88, an article by V. Korchagin and others. "Buran" flies to Baikonur.

 4. "Encyclopedia of Aviation", TsAGI publishing house (p. 322, 365, 525), 1994

 5. Newspaper "Red Star" on 04/12/89, article by V. Burdakov "On the back of the aircraft."

Claims (3)

1. The method of controlling the transportation of products with gas inflated by thin-walled containers with gas by means of aviation, which consists in changing the altitude and speed of the flight of an aviation vehicle with a transported product and controlling the pressurization of a thin-walled container as part of the product, characterized in that the thin-walled container is pressurized based on strength requirements and a thin-walled container shell stability change of height H _n and / or the velocity V _P of aircraft flight producing means, determining their value from the relationship

where N _P.MAX - maximum permissible flight altitude, m; V _P.MAX - maximum permissible flight speed, km / h; H _{P. PRED} - maximum height H _{P. PRED} = 12000 m;

P _MAX and

R _min - passport data on the transported product; R _B - the current value of pressure in a thin-walled tank, kgf / cm ² ; P _N - the current value of the barometric pressure in the cargo compartment (in the container or atmosphere overboard at flight altitude), kgf / cm ² ; T ₀ - initial (terrestrial) air temperature, K; To ₁ - a linear coefficient of temperature change with altitude simultaneously with a change in altitude and / or flight speed is controlled according to the control of supercharging a thin-walled tank on the track. 2. The method of controlling the transportation of products with pressurized gas by thin-walled containers by aviation means according to claim 1, characterized in that the adjustment of the supercharging of the thin-walled container is performed by venting the supercharging gas or supplying additional mass to it due to the high-speed pressure. 3. The method of controlling the transportation of products with pressurized gas by thin-walled containers by aviation means according to claim 1, characterized in that the adjustment of the supercharging of the thin-walled container produces changes in the pressure of the supercharged gas due to a change in its temperature.

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