Module of spacecraft engine plant (versions)

FIELD: spacecraft engine plants, mainly geostationary communication satellites; orientation of satellite and correction of its orbit.

SUBSTANCE: proposed module of spacecraft engine plant includes low-thrust engine (or engine package) mounted in biaxial suspension on rod and components of engine plant pneumatic system. Engine is mounted on one end of rod and pneumatic system components are mounted on other end of rod. Articulation securing the rod to spacecraft case is located between engine (or engine package) and pneumatic system components. Biaxial suspension makes it possible to perform independent rotation of engine (or engine package) relative to rod at two perpendicular axes through 90° around each axis. Rod securing articulation makes it possible to rotate the rod through 360° relative to spacecraft case. Provision is made for shaping correcting pulse during operation of low-thrust engine (or engine package) in any direction for maintenance of point of sight of spacecraft on orbit and creating required control moment around center of mass of spacecraft for its orientation.

EFFECT: enhanced efficiency.

4 cl, 2 dwg

 

The invention relates to rocket and space technology, in particular to devices propulsion of space vehicles, namely geostationary communication satellites (hereinafter SC)used for orientation of the satellites in space through the creation of control points around the center of mass of the SPACECRAFT for orbit correction, i.e. changing the position of the center of mass of the SPACECRAFT.

An example of the propulsion system geostationary communications can serve as the propulsion system KA Yamal-100" (see, for example, the magazine cosmonautics news", No. 11 (238) for 2002, p.44-45). This handset has the propulsion system, which uses the same engines for orbit correction, and to generate control moments about the center of mass. The propulsion system KA Yamal-100" is composed of eight fixed thrusters (electric propulsion engines LDS-70) and 12 of the gas nozzles. Gas nozzles have a low specific impulse and are used only to enable electric propulsion engines and in emergency situations. Eight engines LDS-70 provides correction of the orbit of the SPACECRAFT and the creation of the required moments about the center of mass of the SPACECRAFT.

The disadvantages of this propulsion system is the large number of engines, as well as what to perform any dynamic operation simultaneously engages the VA engine of eight or frequently need to switch engines in the respective pair, there is no possibility to change the direction of the total thrust vector of the propulsion system.

A device propulsion SPACECRAFT containing placed on the rod, pivotally attached to the chassis KA, the thruster and the elements of the pneumatic system of the propulsion system (see RF patent №2021170, class B 64 G 1/00, from 10.06.91 year).

However, such devices of the propulsion system has a number of shortcomings, such as to control the orientation of the SPACECRAFT you need to use multiple engines, torque from the engine can be changed on only one axis.

It is also known device propulsion SPACECRAFT containing a thruster placed in the biaxial suspension rod, pivotally attached to the body of the spacecraft, and the elements of the pneumatic system of the propulsion system (see patent US 6565043 A (THE BOEING CO); 20.05.2003, CL 244/169)

However, the device of the propulsion system does not allow to solve the problem of maintaining the SPACECRAFT in the stand point with only one such device: for example, you want a single device to support the points of observation in the direction of "North-South" and a second device for maintaining the point of standing in the "West-East". This device allows you to direct the thrust vector through the center of mass in only two ODA is divided positions of the rod relative to the body of the SPACECRAFT, for example: in the "North" and "South". The specified device propulsion system also provides for measures to reduce the change in the position of the center of mass of the SPACECRAFT when moving the rod from one extreme position to the other, which would require a more complex device stabilization and control the orientation of the SPACECRAFT.

The objective of the present invention is a device of the propulsion system, which allows to achieve a technical result in the creation of a corrective pulse when one thruster along any direction, you need to maintain points of observation SPACECRAFT in orbit, and create the required control torque around the center of mass of the SPACECRAFT for attitude control of a SPACECRAFT, including the issuance of corrective impulse.

The solution to this problem is achieved by the fact that the device of the propulsion system of the spacecraft contains pivotally attached to the body of the spacecraft rod placed in the biaxial suspension on the barbell thruster and the elements of the pneumatic system of the propulsion system, in accordance with the invention:

the thruster is mounted on one end, the elements of the pneumatic system of the propulsion system, including the tank with a working medium, installed on the other end of the rod (this location allows better balance arm is smart in order to make changes to the nominal position of the center of mass of the spacecraft during rotation of the rod relative to the body of the spacecraft);

the hinge mounting rod to the body of the spacecraft is located between the thruster and the elements of pneumatic systems and made with the possibility of rotation of the rod relative to the body of the spacecraft 360 degrees, providing the possibility of issuing corrective impulse not only along one direction, such as North-South, but also across the first direction, for example along the direction of the "West-East" (this allows one device to maintain the point of standing KA in all the required areas);

- dual axle suspension is made with the possibility of independent rotation of the thruster relative to the rod in two mutually perpendicular axes by 90 degrees around each axis.

The maximum deviation of the thruster relative to the nominal position relative to the rod on each of the axes of the biaxial suspension is at an angle of 45 degrees in both directions. The nominal position of the thruster relative to the rod corresponds to the passage of the nominal thrust vector of the engine of small thrust through the nominal center of mass of the spacecraft at least in one position of the rod relative to the body of the spacecraft. The direction and placement of the hinge mounting rod to the body of the spacecraft relative to the housing is the spacecraft provides at any position of the rod relative to the body of the spacecraft and the nominal position of the thruster relative to the rod deviation of the nominal vector direction thrust of a thruster from the direction to the nominal center of mass of the spacecraft at an angle up to 40 degrees.

Installation of a thruster in the biaxial suspension with the specified nominal position relative to the rod, possible deviations relative to the rod and the specified position of the attachment point and the direction of the axis of rotation of the rod relative to the body of the spacecraft and its center of mass provides in any position of the rod relative to the body of the SPACECRAFT, the possibility of granting impulse directed through the center of mass of the SPACECRAFT (for issuing corrective pulse), and with the necessary "penalty" to create the control point around the center of mass of the SPACECRAFT (for offload engines-flywheels in the system attitude control of the SPACECRAFT), including on the background of the issuance of corrective impulse.

In addition, near the thruster additionally installed backup thruster in the same biaxial suspension of a thruster on the same bar, running parallel to the main thruster.

In addition, the elements of the pneumatic system including a cylinder with a working medium, together with a thruster connected with the system conversion and management, placed in the body of the spacecraft.

The solution to the above problem is achieved by the fact that the device motor is stop spacecraft contains the block thrusters, posted in the biaxial suspension rod, pivotally attached to the body of the spacecraft, and the elements of the pneumatic system of the propulsion system, in accordance with the invention:

block thrusters installed on one end, the elements of the pneumatic system of the propulsion system, including the tank with a working medium, installed on the other end of the rod;

the hinge mounting rod to the body of the spacecraft is located between the block thrusters and elements of pneumatic systems and made with the possibility of rotation of the rod relative to the body of the spacecraft 360 degrees, providing the possibility of issuing corrective impulse not only along one direction, such as North-South, but also across the first direction, for example along the direction of the "West-East"; it allows one device to maintain the point of standing KA in all required areas;

- dual axle suspension is made with the possibility of independent rotation block thrusters relative to the rod in two mutually perpendicular axes by 90 degrees around each axis.

The maximum deviation of the block thrusters relative to the nominal position relative to the rod on each of the axes of the biaxial suspension is at an angle of 45 degrees in both art the Rhone. The nominal position of the block thrusters relative to the rod corresponds to the passage of the nominal total thrust vector of the block thrusters through the nominal center of mass of the spacecraft at least in one position of the rod relative to the body of the spacecraft. The direction and placement of the hinge mounting rod to the body of the spacecraft relative to the body of the spacecraft provides at any position of the rod relative to the body of the spacecraft and the nominal position of the block thrusters relative to the rod deviation of the nominal direction of the resultant vector thrust block thrusters from the direction to the nominal center of mass of the spacecraft at an angle up to 40 degrees.

Next, the data of the invention are explained in detail using schematic drawings (figures), where figure 1 shows the proposed device in the first embodiment, and figure 2 - the second option.

The device of the propulsion system of the spacecraft contains a low-thrust engine 1 installed in the biaxial suspension 2 relative to the rod 3. The bar itself is attached to the body of the spacecraft 4 with the center of mass 5 by means of the hinge 6. The rod is made of l-shaped, one end of which is fixed in the biaxial suspension mount (on LW is Chairman frame) thruster, and at the other end of the rod mounted elements of the pneumatic system including a cylinder with a working body 7 for a thruster. Biaxial suspension engine consists of two hinge 8 and 9 mounted mutually perpendicular so that they implement relative to the boom similar gimbal for motor frame on which are mounted thrusters.

In General, relative to the body of the spacecraft obtained three axes of rotation can be implemented using three hinges, and the first hinge is a hinge 6 which pivots the rod 360° relative to the body of the spacecraft, and the second and third hinges, the components of the biaxial suspension placed on one end of the rod in such a way that they implement relative to the rod independent of the rotation of the thruster in two mutually perpendicular axes at 90° in respect of each axis. The rotation of the hinges 8 and 9 is the angle to 45 degrees in both directions relative to the nominal position of these hinges.

For reservation failure of a thruster suitable for motor frame to install two engines: one primary and one backup, disaster in parallel with the main thruster, at the same time (in the absence of the accident) will run only one engine.

In addition on the rod between the engine and the tank has four gas nozzles. The elements of the pneumatic system including a cylinder with a working medium, together with the thrusters and gas nozzles associated with the conversion system and control placed in the hull of a spacecraft.

The second option on the motor frame is not one main operating thruster, and the block a few basic thrusters, not counting emergency backup.

The operation of the propulsion system of the spacecraft is as follows.

For the correction of the geostationary orbit emit pulses of thrust along two mutually perpendicular axes only in four directions relative to the center of mass of the SPACECRAFT. With the help of hinges, the thrust vector is directed exactly through the center of mass of the SPACECRAFT, in order to avoid disturbances from the engines.

For example, when issuing a corrective pulse in a northerly direction to maintain the point latitude standing KA bar rotates relative to the body of the SPACECRAFT in such a position, when the rod end with a two-axis suspension is directed to the South. Then, using a two-axis suspension thrust of the engine is directed through the center of mass of the SPACECRAFT and is issued a corrective impulse.

To create control points around the goal is tra mass total thrust vector by means of hinges direct line, not passing through the center of mass, i.e. past the center of mass. This selects the desired amount of "slip"to minimize the consumption of the working fluid. The control device generates the control point of any sign on any of the three axes of the SPACECRAFT.

At the same time the creation of control points and the creation of thrust pulses for correction produced ONLY one work thruster. (second - include backup only in case of an accident or failure of a thruster).

The second option is the creation of control points and create pulses of thrust produced including both a block of two or more working thrusters (leaving again backup engine not included).

When the device propulsion SPACECRAFT as in the first embodiment and the second option, compared to the propulsion system with a fixed set engines or multiple mobile engines, the proposed device propulsion for geostationary communications satellites has the following advantages:

- a small number of engines (at least enough of one thruster (e.g., SPD-70) allows you to reduce weight and cost control AC, and lots of hardware power and management control;

- the ability to direct the thrust vector along the desired directions for p is djergenia point standing KA as latitude, and longitude;

- ability to change the direction of the thrust vector during operation of the propulsion system (the ability to direct the thrust of the engine or in the center of mass, or to create the desired control point) allows you to minimize disturbances from the operation of the engine, which minimizes inventory (mass) additional fuel to parry these perturbations;

- balance the rod with the controls it contains DN relative to the rotary mechanism provides a reduction changing the position of the center of mass of the SPACECRAFT during rotation of the rod relative to the body of the SPACECRAFT;

- run in a separate module, which can autonomously collect and spend cycle preflight checks, and completely install and remove without modification or disassembly of other spacecraft.

In addition to the above advantages, we get both versions when the device of the propulsion system, the first option has the advantage that the need to include only one engine reduces system requirements power supply AC for the power supply of the propulsion system. For example, one SPD-70 to about 750 watts of power instead of 1500 watts for two SPD-70. The advantage according to the second variant of the device is that the unit of several is the space of a few engines, installed on one motor frame and turn at the same time, it reduces the operating time of the propulsion system for the issuance of momentum correction and/or unloading engines-flywheels.

The propulsion device according to the second option may or may not contain additional, emergency engine in addition to the two basic operating thrusters. In this case failure (accident) one of the working engines of the propulsion device moves to work on the first version.

1. The device of the propulsion system of a spacecraft containing a thruster placed in the biaxial suspension rod, pivotally attached to the body of the spacecraft, and the elements of the pneumatic system of the propulsion system, characterized in that the thruster is mounted on one end of the rod, the elements of the pneumatic system of the propulsion system, including the tank with a working medium, installed on the other end of the rod, and a hinge attaching the rod to the body of the spacecraft is located between the thruster and the elements of the pneumatic system with dual axle suspension of a thruster performed by enabling independent rotation of the engine relative to the rod in two mutually perpendicular axes 90° around each axis, and the specified Sha the research fastening rod is made with the possibility of rotation of the rod relative to the body of the spacecraft on the 360° .

2. The device according to claim 1, characterized in that near the thruster on the same rod and parallel to it additionally fitted in the same axle suspension redundant emergency thruster.

3. The device according to claim 1, characterized in that the elements of the pneumatic system including a cylinder with a working medium, together with a thruster connected with the system conversion and management, placed in the body of the spacecraft.

4. The device of the propulsion system of a spacecraft containing block thrusters placed in the biaxial suspension rod, pivotally attached to the body of the spacecraft, and the elements of the pneumatic system of the propulsion system, characterized in that the block thrusters mounted on one end of the rod, the elements of the pneumatic system of the propulsion system, including the tank with a working medium, installed on the other end of the rod, and a hinge attaching the rod to the body of the spacecraft is located between the specified block thrusters and elements of the pneumatic system with dual axle suspension unit thrusters done with enabling independent rotation of the block relative to the rod by two mutually perpendicular axes at 90° around each axis, and the hinge mounting rod is made to ensure the receiving capabilities of rotation of the rod relative to the body of the spacecraft on the 360° .



 

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The invention relates to the field of space technology and can be used for delivery of communications satellites in geostationary orbit

The invention relates to space technology and more specifically to methods control the relative motion of spacecraft in near-circular orbit

The invention relates to the field of joint management orientation and movement of the center of mass of the SPACECRAFT (SC)

The invention relates to space technology and can be used on a space object (KO) in the event of the urgent need of his leaving

The invention relates to rocket and space technology, namely the device propulsion spacecraft

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