Method of arrangement of stationary earth man-made satellite

FIELD: space engineering.

SUBSTANCE: proposed method consists in using a vessel aboard the satellite with a required constant area of the liquid phase location on the said vessel wall surface. The Earth satellite lengthwise axis, in operating conditions, is constantly directed along the current radius-vector of the orbit mass centre. The aforesaid vessel is placed at a maximum possible distance from the satellite mass centre along the direction parallel to the said lengthwise axis. The vessel should be placed so that the normal at the point of the vessel wall surface opposite the working medium outlet was directed towards the satellite mass centre. The said point should be located at a minimum possible distance from the satellite lengthwise axis.

EFFECT: simpler design and smaller weight of service satellite systems.

2 dwg

 

The invention relates to space technology, in particular to a stationary artificial satellites of the Earth, and created by the authors in order to perform their tasks.

As part of the spacecraft, such as telecommunication satellites, used capacity, in which during orbital operation is stored a certain stock of a working body:

in the attitude control system and motion control (SOUD) (spacecraft./Under the General editorship Ceptionist. M, Military publishing house, 1983, p.54, 56 [1]) is the capacity for storing the working fluid, an internal cavity which is initially charged, for example, a xenon under pressure ≈200 kgf/cm2; during the active life of the satellite, the number of xenon gradually decreases and at pressures below the critical pressure (≈59,45 kgf/cm2) and temperatures below the critical temperature (≈289,7K) (see Nbhrhieq. Handbook of thermophysical properties of gases and liquids. M., Nauka, 1972 str [3]) in the tank is formed of a two-phase environment. From the point of view of the functional purpose of the tank into the pressure reducer, then a jet nozzle for the normal functioning of the xenon must come in the form of vapour, or in the case of supply from the tank the liquid phase, the flow rate of xenon will be significantly overestimated and therefore the conserve mass xenon her to the gearbox must be converted into steam, i.e. in SOUD there is an additional device is quite powerful heater (for example, at a flow rate of xenon ≈2 g/with the power of the heater is equal to ≈120 watts, which is engaged in work on the job SOUD in case of presence of the liquid phase near the holes for the supply of xenon in-line reducer);

in thermal control system (P) (according to the author's certificate of the USSR No. 2117891 [2]) is a device for maintaining the pressure of the fluid in the circuit P of the SPACECRAFT (SC), the inner cavity of which is filled by a certain number of two-phase working fluid (coolant), for example, ammonia; from the point of view of a functional purpose in terms of orbital operation should be capable of delivering (or receiving) the liquid phase ammonia in the line P and to maintain a certain vapor pressure of ammonia in the gas cavity of the container.

As can be seen from the above, in containers of both satellite systems for normal and optimal functioning of the liquid phase of the working heat in the tanks must be in a certain permanent zones on the inner surface of the vessel wall:

- in capacity SOUD - opposite holes for supplying the vapor of the working fluid in the supply line to the gearbox;

- capacity P - near the outlet for flow of the liquid phase of the capacity is in line P and near heaters.

Currently known technical solutions to ensure the normal functioning of the above systems during orbital operation:

in SOUD provide a heater system for its automatic inclusion in the starting feed reducer liquid phase xenon or, in the absence of electric heaters provide an additional supply of xenon in the vessel with greater capacity to provide health SOUD within a specified period of operation, which complicate the design and increase the weight, the power consumption of the above systems;

- capacity PAGE within its total volume and the area of the outlet set the capillary structure and the heaters complex designs (such a complex and massive structure is provided on the assumption that during orbital operation position of the liquid phase ammonia in the tank undefined).

In the known technical solutions heaters incorporated in the work periodically (for example, 0.5 h included, then at least 2-2 .5 h off) to create (and maintain) a certain operating pressure of the vapor phase of the working fluid in the valid range. When the radiator is boiling of the liquid phase wetting the surface of the vessel wall, in the zone opposite the location of the heaters. In the boiling (vaporization) of the liquid phase, the particles of the liquid and vapor are released into the Central zone of the vessel. After turning off the heater fluid particles according to known physical law (VII. The motion of an artificial satellite about the center of mass. M., Nauka, 1965, page 24, figure 2 on p.25, p.26 (paragraphs 1 and 2 below), p.27 (the formula for the components of the centrifugal force: z and FG, Fu) [4]) will have a certain direction - they will move parallel to the radius-vector of the center of mass of the satellite in the direction of the center of mass of the satellite.

Because it is not currently known technical solution, which stipulates the specific placement of the above capacity on the satellite, these fluid particles may move in the direction opposite to the desired direction - this means that the liquid phase will gradually collect on the inner surface of the container opposite from the desired, i.e. in this case, the constructive arrangement of the capacity on the satellite is not conducive to the concentration of the liquid phase in a certain fixed area on the inner surface of the vessel wall, and this technical problem currently requires permission.

Analysis of sources of information - the patent and scientific-technical the Russian literature showed that the closest to the technical nature of the prototype of the proposed technical solution is the way to build capacity SOUD for storing the working fluid - xenon onboard the satellite [1].

Currently, the requirements specified by the layout of the containers used, for example, on a stationary artificial Earth satellite, not specified (see figure 2, where C is the center of the Earth (center of gravity); the center of mass (center of inertia) of the satellite; Oxyz - right rectangular orbital coordinate system (ACI. The motion of an artificial satellite about the center of mass. M., Nauka, 1965, p.17 (3rd paragraph from the bottom), 23 (3rd paragraph from the top); r is the current radius-vector of the satellite's orbit; A - stationary satellite orbit (the orbit of the center of mass of the satellite); 1 - the payload module of the satellite; 2 - module service systems satellite; 3 - capacity SOUD; 3.1 - hole for exhaust vapor of the working fluid from the tank; 4 - pipe selection the vapors of the working fluid; 5 - pairs of the working fluid; 6 - liquid phase working fluid; 7 - electric heater; 8 - longitudinal axis of the satellite).

As indicated above, a significant disadvantage of the known device is increased weight due to the need to carry an additional supply of the working fluid and power consumption is to turn the liquid phase of the working fluid in the vapor state.

The purpose of accom is amago the authors of the technical solution is to eliminate the above-mentioned significant disadvantages.

This goal is achieved by the arrangement of the satellite in such a way that the specified capacity is set at the greatest possible distance from the center of mass of the satellite in a direction parallel to a specified longitudinal axis with the container so that the normal at the point of the surface of the wall opposite the hole for the exhaust vapor of the working fluid from the tank, was directed toward the center of mass of the satellite, and this point was at the minimum possible distance from the longitudinal axis of the satellite, which is, according to the authors, significant distinctive features proposed by the authors of the technical solution.

The analysis conducted by the authors of the famous patent and scientific literature, the proposed combination of significant distinguishing features of the proposed technical solution in the well-known sources of information are not detected and, therefore, the known technical solutions do not exhibit the same properties as in the present method, the composition of the artificial satellite.

The layout of the satellite according to the authors, the method is as follows (see figure 1, where C is the center of the Earth; center of mass; Oxyz - right rectangular space coordinate system; r is the current radius-vector of the satellite's orbit; A - stationary orbit satellite is; 1 - the payload module, 2 - module service systems; 3 - capacity SOUD; 3.1 - hole for exhaust vapor of the working fluid from the tank; 4 - pipe selection the vapors of the working fluid; 5 - pairs of the working fluid; 6 - liquid phase working fluid; 7 - heater; 8 - longitudinal axis of the satellite):

- conducted requirements analysis for the arrangement of stationary artificial Earth satellite, the longitudinal axis 8 axis of least moment of inertia or the most Central axis of the ellipsoid of inertia) which must always be directed along the current radius vector of the orbit r between the center of the Earth With the center of mass Of the satellite;

- analyze functional purpose of the vessel 3 the given construction, seasoned two-phase working fluid (working fluid), and define the desired constant area location of the liquid phase 6 on the surface of the wall;

- determine the location on the satellite, which as much as possible removed from the center of mass Of the direction parallel to the aforementioned axis 8;

- establish the capacity of the 3 on-Board the satellite in vysovyvanii zone so that the normal n at the point C of the surface of the wall opposite the hole for the exhaust vapor of the working fluid from the tank, was directed toward the center of mass of the satellite, and the specified point C was located at the minimum possible distance about the longitudinal axis 8 of the satellite.

Conducted on the basis of [4] calculations for the capacity of the particular telecommunication stationary satellites on Board the satellite according to the new proposed technical solution, show that the acceleration of fluid particles is not less than 3·10-8m/s2and for ≈40 minutes these particles are the distance between the mutually opposite areas of capacity, i.e. to the time of the next switching of the heater liquid phase will be in the zone capacity, thereby ensuring normal operation.

Thus, as a result of this arrangement the liquid phase 6 of the coolant during orbital operation will always be required in the area: as a result of combined effects of the gravitational and centrifugal forces (which by the magnitude and direction relatively stable in stationary orbit) on fluid particles they will move parallel to the radius-vector r of the center of mass Of the satellite in the direction of the center of mass Of the satellite and will be concentrated on the surface of the vessel 3 in the area in front of her holes 3.1 for removal of vapor of the working fluid from the tank 3 and is pressed to the surface in the zone of the point C, and at the same time under the influence of disturbances (the influence of the moon and Sun, the nonspherical character of the Land, intermittent periodic work SOUD) liquid phase th the media, with slight fluctuations, to be in this zone capacity [4], thus, by providing the exhaust vapor of the working fluid in the pipeline selection.

It should additionally be noted that in the case of maintaining the temperature of the wall, located in the area opposite said hole, below the temperature of the rest of the aspiration of the liquid phase to the above area will be further enhanced by the high degree of wettability over a cold fluid compared with warm - to do this they need this amount of capacity to insulate insulation with a lower thermal resistance than the rest of the insulation.

Thus, as can be seen from the above, in the layout KA according to the technical solution of the reduced mass SOUD as a result of filling its capacity with the optimal amount of the working fluid, and a heater for converting the liquid phase into vapor is backing element and, consequently, the power consumption of it within the operation of the minimum possible, i.e. thereby achieved the objectives of the invention.

Currently proposed by the authors of the technical solution are reflected in the technical documents of the company for the development of the newly created telecommunications satellites.

The positioning of the stationary artificial Earth satellite, the longitudinal axis of which must be constant the NGOs are directed along the current radius vector of the orbit, connecting the center of the Earth with the center of mass of the satellite, including installation on Board the vessel, filled two-phase working fluid, the desired permanent location area of the liquid phase on the surface of the vessel wall, characterized in that the specified capacity is set at the greatest possible distance from the center of mass of the satellite in a direction parallel to a specified longitudinal axis with the container so that the normal at the point of the surface of the wall opposite the hole for the exhaust vapor of the working fluid from the tank, was directed toward the center of mass of the satellite, and this point was at the minimum possible distance from the longitudinal axis of the satellite.



 

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1 dwg, 1 tbl

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3 cl, 2 dwg

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