Patent Description:
The cost to launch spacecraft such as satellites into orbit is extraordinarily expensive. The launch cost per satellite can be reduced by launching multiple satellites with one launch vehicle. In one technique, multiple spacecraft are arranged in a stack with the lowest spacecraft attached to a launch vehicle adaptor. Thus, the satellites are sometimes oriented during launch one above another with respect to the gravitational force of the earth. The launch phase of a launch vehicle is the period in which the launch vehicle powers the flight to raise the launch vehicle above the Earth's atmosphere and accelerate to at least an orbital velocity. In some cases, the launch phase raises the launch vehicle to a transfer orbit. When the launch vehicle is in the transfer orbit, the spacecraft are dispensed from the launch vehicle.

In some techniques, after the multiple spacecraft are dispensed from the launch vehicle orbit raising maneuvers are performed. An orbit raising maneuver transfers a spacecraft from one orbit to another orbit. The orbit raising maneuver increases the size and energy of the orbit, which is referred to herein as orbit raising. One example of an orbit raising maneuver is to transfer (or raise) a spacecraft from a low-altitude transfer orbit (or "parking orbit") to a higher-altitude mission orbit (or "operational orbit"), such as a geosynchronous orbit. For example, after the launch vehicle reaches the launch vehicle transfer orbit, the multiple spacecraft are dispensed from the launch vehicle. Then, the spacecraft are raised to their respective mission orbits such as a geosynchronous orbit. A spacecraft may have an onboard propulsion subsystem to effect such orbit raising.

Spacecraft propulsion subsystems generally include thrusters, which may be broadly categorized as either "chemical" or "electric" based on the respective primary energy source. Chemical thrusters, for example bi-propellant thrusters, deliver thrust by converting chemical energy stored in the propellant to kinetic energy delivered to combustion products of the chemical propellant, e.g., a fuel such as monomethyl hydrazine and an oxidizer such as dinitrogen tetroxide. In general, chemical based propulsion subsystems have higher thrust than electric based propulsion subsystems. For example, a relatively high thrust chemical thruster may have a nominal thrust rating of, for example, <NUM> N or greater. Some chemical thrusters have a lower nominal thrust ratings closer to <NUM> N. In contrast, electric based propulsion subsystems may have a nominal thrust rating of about 1N or less. Electric thrusters normally use a high atomic number, easily ionized, inert gas, frequently xenon, as a propellant.

There are numerous technical challenges to overcome when launching multiple spacecraft with one launch vehicle, while providing for orbit raising maneuvers of the spacecraft. One technical challenge is dealing with the structural bending moment on launch. A structural bending moment occurs when force applied to a structure causes the structure to bend. The structural bending moment that occurs during the launch phase can damage the spacecraft. One possible solution is to fortify the spacecraft and/or the structure that supports the spacecraft on launch to limit the impact of the structural bending moment. However, such fortifications typically undesirably add mass.

The time of flight is a term used to refer to the time it takes to raise the orbit of a spacecraft from a parking orbit to its mission orbit. The time of flight can be reduced by using high thrust chemical thrusters for orbit raising. For example, chemical orbit raising typically has a time of flight of two weeks, whereas electric orbit raising could take up to <NUM> days. However, such high thrust chemical thrusters and their propellent typically are more massive than lower thrust electric thrusters. Moreover, the candidate payload designs in a stack may lead to an excessively high center of mass if chemical propulsion is used, which may force a switch to electric propulsion. However, electrical propulsion leads to long orbit raising time that may be undesirable to the candidate customers. Electric orbit raising can be shortened by firing more electric thrusters simultaneously, but this requires a larger than normal power subsystem. Some types of commercial payloads require larger power subsystems so that they can also support a larger electric propulsion subsystem. Therefore, there is a trade-off between time of flight and mass. <CIT> discloses cross-feeding propellant between stacked spacecraft. <CIT> discloses a satellite system comprising two satellites attached to each other and a method for launching them into orbit. <CIT> discloses a method and system for transferring a satellite from an initial orbit into a mission orbit.

Technology is disclosed herein for orbit raising of multiple spacecraft that were launched with a single launch vehicle. Two or more spacecraft are configured in a stacked launch configuration in which a lower spacecraft is mechanically coupled with a payload adapter of a launch vehicle with one or more upper spacecraft above the lower spacecraft. Propellant that is stored in the lower spacecraft during a launch phase is transferred to an upper spacecraft in the stack after the launch phase. The propellent may be used by the upper spacecraft for an orbit raising maneuver that raises the orbit of at least the upper spacecraft from a first orbit to a second orbit. Storing the propellant in the lower spacecraft lowers the center of mass of the stack during launch. Lowering the center of mass reduces the structural bending moment of the stack during launch. A lower center of mass at launch allows a larger total launch mass. The larger total launch mass allows the spacecraft and/or the structure that supports the spacecraft on
launch to be fortified. Therefore, the risk of damage to the spacecraft during launch is reduced. Alternatively, lowering the center of mass of the propellent allows the dry mass of the payload to be placed higher in the stack, which may improve payload operation.

The system deploys an upper spacecraft and a lower spacecraft from a launch vehicle into a parking orbit following the launch phase. The system transfers propellant by way of a propellant line arrangement, subsequent to the launch phase, from a first propellant storage of the lower spacecraft to a second propellant storage of the upper spacecraft. The system operates a thruster of the upper spacecraft using the propellant that the system transferred to the upper spacecraft subsequent to the launch phase. The thruster of the upper spacecraft may be used for an orbit raising maneuver that raises the orbit of at least the upper spacecraft. In one embodiment, the orbit raising maneuver raises at least the upper spacecraft to a higher orbit (e.g., mission orbit) than the parking orbit. Many other orbit raising maneuvers using the propellant that was transferred from the lower spacecraft to the upper spacecraft are disclosed herein.

<FIG> is a block diagram of a spacecraft system. The system of <FIG> includes spacecraft <NUM>, subscriber terminal <NUM>, gateway <NUM>, and ground control terminal <NUM>. Subscriber terminal <NUM>, gateway <NUM>, and ground control terminal <NUM> are examples of ground terminals. In one embodiment, spacecraft <NUM> is a satellite; however, spacecraft <NUM> can be other types of spacecraft. Spacecraft <NUM> may be in a mission orbit, such as a geostationary or non-geostationary orbital location. Technology disclosed herein may be used for launching the spacecraft <NUM> with at least one other spacecraft <NUM> in the same launch vehicle and raising the orbit of the spacecraft <NUM>.

Spacecraft <NUM> is communicatively coupled by at least one wireless feeder link to at least one gateway terminal <NUM> and by at least one wireless user link to a plurality of subscriber terminals (e.g., subscriber terminal <NUM>) via an antenna system. Gateway terminal <NUM> is connected to the Internet <NUM>. The system allows spacecraft <NUM> to provide internet connectivity to a plurality of subscriber terminals (e.g., subscriber terminal <NUM>) via gateway <NUM>. Ground control terminal <NUM> is used to monitor and control operations of spacecraft <NUM>. Spacecraft can vary greatly in size, structure, usage, and power requirements, but when reference is made to a specific embodiment for the spacecraft <NUM>, the example of a communication satellite will often be used in the following, although the techniques are more widely applicable, including other or additional payloads such as for an optical satellite.

<FIG> illustrates an embodiment of two spacecraft mechanically coupled together in a stack to be launched within a common fairing <NUM> of a launch vehicle (not illustrated). The configuration in <FIG> may be referred to as a launch configuration. A lower spacecraft <NUM>(<NUM>) includes an adapter <NUM>(<NUM>) that is mechanically coupled, in the launch configuration, with a primary payload adapter <NUM> that may be part of an upper stage (not illustrated) of the launch vehicle. The lower spacecraft <NUM>(<NUM>) includes an inter-spacecraft coupling arrangement <NUM> (also referred to as an inter-satellite coupling arrangement) that is mechanically coupled, in the launch configuration, with an adapter <NUM>(<NUM>) of an upper spacecraft <NUM>(<NUM>). The stack may have more than two spacecraft mechanically coupled together. For example, there could be a third spacecraft that is above and mechanically coupled to the upper spacecraft <NUM>(<NUM>). Herein, the phrase "spacecraft mechanically coupled together in a stack" means that each spacecraft will be mechanically coupled to at least one other spacecraft. However, it is not required that each spacecraft be mechanically coupled to every other spacecraft in the stack.

Each spacecraft <NUM> includes one or more on-board propulsion subsystems. In one embodiment, the on-board propulsion subsystem of a spacecraft may be used for orbit raising from, for example, a parking orbit. This orbit raising could raise the orbit of one or both of the spacecraft <NUM>(<NUM>), <NUM>(<NUM>). In one embodiment, an on-board propulsion subsystem may also perform station-keeping to maintain an orbit of a spacecraft. In one embodiment, an on-board propulsion subsystem may also be used for attitude control/momentum management purposes. The on-board propulsion subsystems of the lower spacecraft includes propellant storage <NUM>(<NUM>) and a thruster <NUM>(<NUM>), which are connected by a propellant line <NUM>(<NUM>). The on-board propulsion subsystem of the upper spacecraft <NUM>(<NUM>) includes propellant storage <NUM>(<NUM>) and a thruster <NUM>(<NUM>), which are connected by a propellant line <NUM>(<NUM>).

Technology is disclosed herein for configuring and operating the on-board propulsion subsystems so as to lower the center of mass of the stack in the launch configuration. In an embodiment, propellant is distributed unequally between the two spacecraft so as to lower the center of mass of the stack. In one embodiment, most or all propellant, at the time of launch, is stored in the lower spacecraft <NUM>(<NUM>). Subsequent to launch, at least some of the propellant is transferred from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) so that each spacecraft has an amount of propellant needed to complete its respective mission. In an embodiment, sufficient propellant is transferred to the upper spacecraft <NUM>(<NUM>) for orbit raising of the upper spacecraft <NUM>(<NUM>), as well as maintaining the orbit the upper spacecraft <NUM>(<NUM>). In an embodiment, at least a portion of the orbit raising of the lower spacecraft <NUM>(<NUM>) is performed using the on-board propulsion subsystem of the upper spacecraft <NUM>(<NUM>) using propellant that was transferred to the upper spacecraft <NUM>(<NUM>) from the lower spacecraft <NUM>(<NUM>). In an embodiment, at least a portion of the orbit raising of the upper spacecraft <NUM>(<NUM>) is performed using the on-board propulsion subsystem of the lower spacecraft <NUM>(<NUM>).

Referring to <FIG>, propellant from the lower spacecraft <NUM>(<NUM>) may be transferred to the upper spacecraft <NUM>(<NUM>) by way of propellant lines and propellant line coupling devices. More particularly, propellant line <NUM>(<NUM>), coupling device <NUM>, and propellant line <NUM>(<NUM>) couple a port of propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) with a port of propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>). Therefore, propellant from the propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) is transferred to the propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) subsequent to launch and prior to orbit raising. Thus, at least some of the propellant that will be used by upper spacecraft <NUM>(<NUM>) is stored at launch in propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>). According to the invention, the propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) is empty at launch. Therefore, the center of mass of the spacecraft stack, in the launch configuration, may be lowered significantly thereby reducing structural bending moment. Reducing the structural bending moment at launch allows a higher overall spacecraft launch mass.

In some implementations, the coupling device <NUM> may be or include a line disconnect. An example of a line disconnect appropriate for use cases contemplated by the present disclosure is described in<NPL>). In some implementations, the coupling device <NUM> may include a line disconnect including a proximal portion and a distal portion, each of the proximal portion and the distal portion including a respective valving element. The valving elements may be configured to permit propellant flow when the distal portion and the proximal portion are mutually engaged and prevent propellant flow when the distal portion and the proximal portion are detached.

In some embodiments, the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>) each have an electric propulsion subsystem. <FIG> illustrates an example of an electric propulsion subsystem that may be used in a spacecraft <NUM>. The electric on-board propulsion subsystem may include any number of electric thrusters <NUM> manifolded by way of a propellant management assembly (PMA) <NUM> with propellant tanks <NUM>. Propellant such as Xenon (Xe) stored in tanks <NUM> at a high pressure may be reduced in pressure by the PMA <NUM> and delivered to the electric thrusters <NUM>. In an embodiment, propellant storage <NUM>(<NUM>) includes one or more Xe tanks <NUM>, and propellant storage <NUM>(<NUM>) includes one or more Xe tanks <NUM>. At launch, all or most of the Xe may be stored in propellant storage <NUM>(<NUM>). Some of the Xe is transferred from propellant storage <NUM>(<NUM>) to propellant storage <NUM>(<NUM>) after launch. Propellants other than Xe may be used in the electric propulsion subsystem. For example, a different high atomic number, easily ionized, inert gas may be used as a propellant.

The electric thruster <NUM> may be, for example a Hall accelerator, a gridded electrostatic accelerator, a cross field (E×B) accelerator, a pulsed plasma thruster, a pulsed inductive thruster, a field-reversed configuration plasma thruster, a Wakefield accelerator, a traveling wave accelerator, and an ion cyclotron resonance heater combined with a magnetic nozzle. In some embodiments, the electric thrusters are used during orbit raising.

Note that for some launch configurations, there is a significant difference in DC power generation between the upper and lower spacecraft. For example, a direct to home (DTH) satellite may have a large DC power system, whereas a high throughput satellite (HTS) may have a smaller DC power system. However, the HTS may have a higher mass than the DTH satellite. This DC power generation difference impacts the ability to use an electric propulsion subsystem for orbit raising. In one launch configuration the lower spacecraft <NUM>(<NUM>) has a relatively large mass, but has a relatively small DC power subsystem. On the other hand, the upper spacecraft <NUM>(<NUM>) has smaller mass, but has a relatively large DC power subsystem. The relatively large DC power subsystem of the upper spacecraft <NUM>(<NUM>) may allow for efficient orbit raising of at least the upper spacecraft <NUM>(<NUM>), using an electric propulsion subsystem. In particularly, a large DC power subsystem can help to decrease the time of flight for orbit raising. However, the relatively small DC power subsystem of the lower spacecraft <NUM>(<NUM>) may restrict the orbit raising ability of the electric propulsion subsystem of the lower spacecraft <NUM>(<NUM>), which could lead to a longer time of flight.

<FIG> illustrates an example of a chemical propulsion subsystem that may be used in a spacecraft <NUM>. <FIG> depicts an example of a chemical onboard propulsion subsystem configured to include bipropellant thrusters. The chemical propulsion subsystem may include any number of low thrust chemical thrusters <NUM> and/or a main satellite thruster (MST) <NUM> manifolded by way of a control module <NUM> with fuel tank <NUM> and oxidizer tank <NUM>. The fuel tank <NUM> and the oxidizer tank <NUM> may each be loaded with a desired quantity of liquid propellant, and include an ullage volume, gaseous pressure of which may be regulated by a pressure control module <NUM>. For example the pressure control module <NUM> may include one or more pressure regulators. Helium (He) stored in pressurant tanks <NUM> at a high pressure may be reduced in pressure by the pressure control module <NUM> and delivered to the fuel tank <NUM> and the oxidizer tank <NUM>.

In an embodiment, propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) includes one or more He tanks <NUM>, one or more Fuel tanks <NUM>, and one or more Oxidizer tanks <NUM>. In some embodiments, propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) also includes one or more He tanks <NUM>, one or more Fuel tanks <NUM>, and one or more Oxidizer tanks <NUM>. Numerous examples are described below in which the propellant that is transferred from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) is propellent for an electric propulsion subsystem. However, in some embodiments, propellant that is transferred from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) is propellent for a chemical propulsion subsystem. In one embodiment, the lower spacecraft <NUM>(<NUM>) has both a chemical propulsion subsystem and an electric propulsion subsystem; however, the upper spacecraft <NUM>(<NUM>) has an electric propulsion subsystem but does not have a chemical propulsion subsystem. This configuration provides for a low center of mass in the launch configuration, and also allows the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) to perform at least part of the orbit raising of the lower spacecraft <NUM>(<NUM>) and optionally perform at least part of the orbit raising of the upper spacecraft <NUM>(<NUM>). Using the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) for at least part of the orbit raising can reduce the time of flight for the lower spacecraft <NUM>(<NUM>) and optionally the upper spacecraft <NUM>(<NUM>), without raising the center of mass of the spacecraft stack in the launch configuration.

<FIG> illustrate one embodiment of the transfer of propellent from a lower spacecraft to an upper spacecraft. <FIG> depicts an embodiment of the launch configuration in which propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) is empty and propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) contains significantly more propellant than is needed by the lower spacecraft <NUM>(<NUM>) to complete its mission. <FIG> has similar elements depicted in <FIG>; however, the fairing <NUM>, payload adapter <NUM>, and adapter <NUM>(<NUM>) are not depicted in <FIG> to simplify the drawing. <FIG> depicts a configuration after a launch phase in which some propellant from propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) has been transferred to propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>). In an embodiment, the propellant is transferred after the launch vehicle has reached a parking orbit, but prior to deploying the spacecraft <NUM> from the launch vehicle. In an embodiment, the propellant is transferred after the spacecraft <NUM> have been deployed from the launch vehicle into a parking orbit, but prior to orbit raising of the spacecraft <NUM>. Note that the terms "lower spacecraft" and "upper spacecraft" refer to the original launch configuration and not the orientation with respect to the Earth's gravitational field after deployment.

In an embodiment, the system deploys the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) from the launch vehicle into a parking orbit after launch. Each spacecraft may be raised from the parking orbit to a mission orbit. In an embodiment, the thruster <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) is operated using propellant from the propellant storage <NUM>(<NUM>) that the system transfers subsequent to launch from the propellant storage <NUM>(<NUM>) for an orbit raising maneuver that raises at least the upper spacecraft <NUM>(<NUM>) to a higher orbit. In one embodiment, the orbit raising maneuver raises at least the upper spacecraft <NUM>(<NUM>) to a higher orbit than the parking orbit.

In one embodiment, the upper spacecraft <NUM>(<NUM>) is coupled to the lower spacecraft <NUM>(<NUM>) during at least part of the orbit raising maneuver such that the thruster <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) is operated using propellant from the propellant storage <NUM>(<NUM>) that the system transfers subsequent to launch from the propellant storage <NUM>(<NUM>). Thus, the propellant transferred from propellant storage <NUM>(<NUM>) to propellant storage <NUM>(<NUM>) may be used to raise the orbit of both spacecraft <NUM>(<NUM>), <NUM>(<NUM>). For example, both spacecraft <NUM>(<NUM>), <NUM>(<NUM>) can be raised to a higher orbit than the parking orbit when they are coupled together.

In one embodiment, the system separates the upper spacecraft <NUM>(<NUM>) from the lower spacecraft <NUM>(<NUM>) prior to an orbit raising maneuver such that the propellant transferred from propellant storage <NUM>(<NUM>) to propellant storage <NUM>(<NUM>) is used to raise the orbit of the upper spacecraft <NUM>(<NUM>) but not the lower spacecraft <NUM>(<NUM>) during at least part of the orbit raising maneuvers.

<FIG> depict an embodiment in which the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) are separated from each other during orbit raising maneuvers. <FIG> depicts the thruster <NUM>(<NUM>) of the upper spacecraft using the propellent in propellent storage <NUM>(<NUM>) to raise the upper spacecraft <NUM>(<NUM>) to a higher orbit (e.g., a mission orbit) than the parking orbit. Prior to the orbit raising, the propellent was transferred from the propellent storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) to the propellent storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>). <FIG> depicts the thruster <NUM>(<NUM>) of the lower spacecraft using the propellent in propellent storage <NUM>(<NUM>) to raise the lower spacecraft <NUM>(<NUM>) to a higher orbit (e.g., a mission orbit) than the parking orbit. The propellent that is used for this orbit raising of the lower spacecraft <NUM>(<NUM>) was in propellent storage <NUM>(<NUM>) in the launch configuration. In one embodiment, the on-board propulsion subsystem of the lower spacecraft <NUM>(<NUM>) and the on-board propulsion subsystem of the upper spacecraft <NUM>(<NUM>) are both an electric propulsion subsystem. In one embodiment, the on-board propulsion subsystem of the lower spacecraft <NUM>(<NUM>) and the on-board propulsion subsystem of the upper spacecraft <NUM>(<NUM>) are both a chemical propulsion subsystem.

<FIG> is a flowchart of one embodiment of a process <NUM> of launching multiple spacecraft with a single launch vehicle, and performing an orbit raising maneuver using propellent transferred from a lower spacecraft to an upper spacecraft. Steps <NUM> - <NUM> of process <NUM> may be performed by one or more control circuits. The one or more control circuits may include circuity in a spacecraft <NUM> and/or in ground control <NUM>. The one or more control circuits may be implemented in hardware and/or software.

Step <NUM> includes deploying a payload stack into a launch vehicle. The payload stack includes a lower spacecraft <NUM>(<NUM>) and an upper spacecraft <NUM>(<NUM>) mechanically coupled together in a stack in a launch configuration. Optionally, the payload stack may include three or more spacecraft in a stack that are mechanically coupled together in a stack in a launch configuration. Each spacecraft in the stack is mechanically coupled to at least one other spacecraft in the stack. The lower spacecraft <NUM>(<NUM>) is mechanically coupled with a payload adapter <NUM> of a launch vehicle. In one embodiment, the lower spacecraft <NUM>(<NUM>) includes an inter-spacecraft coupling arrangement <NUM> that is mechanically coupled, in the launch configuration, with an adapter <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>). The payload stack may be placed into a fairing <NUM> of the launch vehicle. <FIG> depicts one embodiment of the launch configuration.

Step <NUM> includes configuring a propellant line arrangement to couple a first propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) and a second propellant storage <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>). The lower spacecraft <NUM>(<NUM>) has a first propulsion subsystem that includes the first propellant storage <NUM>(<NUM>) and a first thruster <NUM>(<NUM>). The upper spacecraft <NUM>(<NUM>) has a second propulsion subsystem that includes the second propellant storage <NUM>(<NUM>) and a second thruster <NUM>(<NUM>).

Step <NUM> includes transferring propellant by way of the propellant line arrangement from the first propellant storage <NUM>(<NUM>) to the second propellant storage <NUM>(<NUM>) after a launch phase of the launch vehicle. In an embodiment, step <NUM> is performed after the launch phase has raised the launch vehicle to a parking orbit. Process <NUM> allows the center of mass of the stack to be lower during the launch phase. In one embodiment, the center of mass is lowered by about. <NUM> meters. Lowering the center of mass reduces the structural bending moment on launch, which protects the spacecraft <NUM>. In an embodiment, one or more control circuits in the lower spacecraft <NUM>(<NUM>) and/or the upper spacecraft <NUM>(<NUM>) control the transfer of the propellant.

Step <NUM> includes deploying the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>) from the launch vehicle to a parking orbit after the launch phase. The lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>) may remain mechanically coupled together after deployment, or may be separated from each other after deployment. In one embodiment, step <NUM> is performed prior to step <NUM>. In one embodiment, step <NUM> is performed after step <NUM>. In an embodiment, one or more control circuits in the lower spacecraft <NUM>(<NUM>) and/or the upper spacecraft <NUM>(<NUM>) control the deployment.

Step <NUM> includes operating the second thruster of the upper spacecraft <NUM>(<NUM>) using the propellant from the second propellant storage <NUM>(<NUM>) that was transferred subsequent to launch from the first propellant storage <NUM>(<NUM>) for an orbit raising maneuver that raises an orbit of at least the upper spacecraft <NUM>(<NUM>). In one embodiment, the orbit raising maneuver raises the orbit of both the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>). Numerous embodiments of step <NUM> are discussed below. In an embodiment, one or more control circuits in the upper spacecraft <NUM>(<NUM>) controls the second thruster.

In one embodiment, the lower spacecraft <NUM>(<NUM>) has both an electric propulsion subsystem and a chemical propulsion subsystem. In one embodiment, the chemical propulsion subsystem is used for orbit raising to reduce the time of flight for both the lower spacecraft and the upper spacecraft. The time of flight refers to the time to raise the spacecraft from a parking orbit to a mission orbit.

<FIG> is a flowchart of one embodiment of a process of operating thrusters to raise orbits of the multiple spacecraft. <FIG> depict one embodiment of firing of thrusters to raise the orbits in the process of <FIG>. Step <NUM> includes operating a chemical thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). The spacecraft remain mechanically coupled to each other during step <NUM>. <FIG> depicts the firing of the chemical thruster <NUM> of the lower spacecraft <NUM>(<NUM>) to raise the orbit of both the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>). In an embodiment, the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) are raised to a higher orbit than a parking orbit at which the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) were deployed from the launch vehicle. In one embodiment, the chemical thruster <NUM> is an MST, which substantially reduces the time-of-flight of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). <FIG> depicts the fuel tank <NUM>, oxidizer tank <NUM>, and control module <NUM> of the chemical propulsion subsystem. Other elements of the chemical propulsion subsystem are not depicted in <FIG>.

Step <NUM> includes mechanically separating the lower spacecraft from the upper spacecraft. The transferring of the propellent from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) occurs prior to this separation. The transferring of the propellent from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) may occur prior to or after step <NUM>. The propellent that is transferred is for an electric propulsion subsystem. In one embodiment, the propellent is Xenon. The transferring of the propellant was discussed in step <NUM> of process <NUM>, but is not depicted in the process of <FIG>.

Step <NUM> includes operating an electric thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>). <FIG> depicts the firing of the electric thruster(s) <NUM> of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>). In one embodiment, the lower spacecraft <NUM>(<NUM>) is raised to a mission orbit. In an embodiment, the propellent used in step <NUM> was in the storage <NUM>(<NUM>) of the lower spacecraft at launch of the launch vehicle. <FIG> depict the storage for electric thruster <NUM>(<NUM>), PMA <NUM>, and electric thrusters <NUM> of the electric propulsion subsystem. Other elements of the electric propulsion subsystem are not depicted.

Step <NUM> includes operating an electric thruster of the upper spacecraft <NUM>(<NUM>) to raise the orbit of the upper spacecraft <NUM>(<NUM>). <FIG> depicts the firing of the electric thruster(s) <NUM> of the upper spacecraft <NUM>(<NUM>) to raise the orbit of the upper spacecraft <NUM>(<NUM>). In one embodiment, the upper spacecraft <NUM>(<NUM>) is raised to a mission orbit. Step <NUM> is performed in one embodiment of step <NUM> of process <NUM>. The propellent used in step <NUM> was in the storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) at launch of the launch vehicle. <FIG> depict the storage for electric thruster <NUM>(<NUM>), PMA <NUM>, and electric thrusters <NUM> of the electric propulsion subsystem. Other elements of the electric propulsion subsystem are not depicted.

In one embodiment, the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>) is used during orbit raising of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). Optionally, the DC power subsystem of the lower spacecraft <NUM>(<NUM>) can be used to assist in orbit raising using the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>), which can reduce time-of-flight. Additionally, a chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) may be used during an initial portion of the orbit raising of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>).

<FIG> is a flowchart of one embodiment of a process of using a chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) and an electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>) for orbit raising of both spacecraft <NUM>(<NUM>), <NUM>(<NUM>). <FIG> depict one embodiment of firing of thrusters during orbit raising, and will be discussed in connection with <FIG>. Step <NUM> in <FIG> includes operating a chemical thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). The spacecraft remain mechanically coupled to each other during step <NUM>. <FIG> depicts the firing of the chemical thruster <NUM> of the lower spacecraft <NUM>(<NUM>) to raise the orbit of both the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>). In an embodiment, the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) are raised to a higher orbit than a parking orbit at which the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) were deployed from the launch vehicle. In one embodiment, the chemical thruster <NUM> is an MST, which substantially reduces the time-of-flight of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>).

<FIG> also depicts components of an electric propulsion subsystem of the lower spacecraft <NUM>(<NUM>), as well as components of an electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>). The lower spacecraft <NUM>(<NUM>) has a DC power system <NUM>(<NUM>), which may be used to power its electric propulsion subsystem. The upper spacecraft <NUM>(<NUM>) has a DC power system <NUM>(<NUM>), which may be used to power its electric propulsion subsystem. However, note that in step <NUM> the electric propulsion subsystems are not used.

Step <NUM> includes operating an electric thruster of the upper spacecraft <NUM>(<NUM>) to raise the orbit of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). In an embodiment, the orbit raising of step <NUM> occurs after the orbit raising of step <NUM>. In one embodiment, the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>) are each raised to a mission orbit in step <NUM>. <FIG> depicts the firing of the electric thruster(s) <NUM> of the upper spacecraft <NUM>(<NUM>) to raise the orbit of both spacecraft <NUM>(<NUM>), <NUM>(<NUM>) while the spacecraft remain mechanically coupled to each other. In step <NUM>, at least the DC power system <NUM>(<NUM>) of the upper spacecraft <NUM>(<NUM>) is used to power the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>). Optionally, the DC power system <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) may be used to assist in powering the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>), which can reduce the time of flight. Step <NUM> is performed in one embodiment of step <NUM> of process <NUM>. The propellent used in step <NUM> was in the storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) at launch of the launch vehicle. After step <NUM>, the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>) are separated from each other in step <NUM>.

As noted above, the lower spacecraft <NUM>(<NUM>) may have both an electric propulsion subsystem and a chemical propulsion subsystem. In one embodiment, the chemical propulsion subsystem is used for orbit raising of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft (<NUM>). Then, after separating the spacecraft <NUM>(<NUM>), <NUM>(<NUM>), the chemical propulsion subsystem may continue to be used for orbit raising of the lower spacecraft <NUM>(<NUM>). This technique is similar to an embodiment discussed above in connection with <FIG>, with a difference being that instead of using the electric propulsion subsystem of the lower spacecraft <NUM>(<NUM>) for orbit raising of the lower spacecraft <NUM>(<NUM>) (see step <NUM> in <FIG>), the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) is used for orbit raising of the lower spacecraft (see step <NUM> below).

<FIG> is a flowchart of one embodiment of a process of operating thrusters to raise orbits of multiple spacecraft in which the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) is used for orbit raising of the lower spacecraft <NUM>(<NUM>) after the two spacecraft have been separated, which reduces time-of-flight for the lower spacecraft <NUM>(<NUM>) relative to an embodiment of <FIG>. <FIG> depict one embodiment of firing of thrusters to raise the orbits, and will be discussed in connection with <FIG>. Step <NUM> includes operating a chemical thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). Step <NUM> may be similar to step <NUM> of <FIG>, and will thus not be discussed in detail.

Step <NUM> includes separating the lower spacecraft from the upper spacecraft. The transferring of the propellent from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) occurs prior to this separation. The transferring of the propellent from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) may occur prior to or after step <NUM>. The propellent that is transferred is for an electric propulsion subsystem. In one embodiment, the propellent is Xenon. The transferring of the propellant was discussed in step <NUM> of process <NUM>, but is not depicted in the process of <FIG>.

Step <NUM> includes operating a chemical thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>). <FIG> depicts the firing of the chemical thruster <NUM> of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>). In one embodiment, the lower spacecraft <NUM>(<NUM>) is raised to a mission orbit.

Step <NUM> includes operating an electric thruster of the upper spacecraft <NUM>(<NUM>) to raise the orbit of the upper spacecraft <NUM>(<NUM>). <FIG> depicts the firing of the electric thruster(s) <NUM> of the upper spacecraft <NUM>(<NUM>) to raise the orbit of the upper spacecraft <NUM>(<NUM>). In one embodiment, the upper spacecraft <NUM>(<NUM>) is raised to a mission orbit. Step <NUM> is performed in one embodiment of step <NUM> of process <NUM>. The propellent used in step <NUM> was in the storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) at launch of the launch vehicle.

In some cases, it may be desirable to quickly raise the orbit of the lower spacecraft <NUM>(<NUM>). In one embodiment, the two spacecraft <NUM>(<NUM>), <NUM>(<NUM>) are separated prior to orbit raising. Then, the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) is used for orbit raising of the lower spacecraft <NUM>(<NUM>) and the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>) is used for orbit raising of the upper spacecraft <NUM>(<NUM>). This technique is similar to an embodiment discussed above in connection with <FIG>, with a difference being that the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) is not used for joint orbit raising of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>) (see step <NUM> in <FIG>). <FIG> provide further details.

<FIG> is a flowchart of one embodiment of a process of operating thrusters to raise orbits of multiple spacecraft in which the chemical propulsion subsystem of the lower spacecraft <NUM>(<NUM>) is used for orbit raising of the lower spacecraft <NUM>(<NUM>) and the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>) is used for orbit raising of the upper spacecraft <NUM>(<NUM>). Step <NUM> includes separating the lower spacecraft from the upper spacecraft. The transferring of the propellent from the lower spacecraft <NUM>(<NUM>) to the upper spacecraft <NUM>(<NUM>) occurs prior to this separation. The propellent that is transferred is for an electric propulsion subsystem. In one embodiment, the propellent is Xenon. The transferring of the propellant was discussed in step <NUM> of process <NUM>, but is not depicted in the process of <FIG>.

Step <NUM> includes operating a chemical thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>). <FIG> depicts the firing of the chemical thruster <NUM> of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>). In one embodiment, the lower spacecraft <NUM>(<NUM>) is raised from a parking orbit to a mission orbit.

Step <NUM> includes operating an electric thruster of the upper spacecraft <NUM>(<NUM>) to raise the orbit of the upper spacecraft <NUM>(<NUM>). <FIG> depicts the firing of the electric thruster(s) <NUM> of the upper spacecraft <NUM>(<NUM>) to raise the orbit of the upper spacecraft <NUM>(<NUM>). In one embodiment, the upper spacecraft <NUM>(<NUM>) is raised from a parking orbit to a mission orbit. Step <NUM> is performed in one embodiment of step <NUM> of process <NUM>. The propellent used in step <NUM> was in the storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) at launch of the launch vehicle.

In some cases, the thrusters of the lower spacecraft <NUM>(<NUM>) might not be compatible with orbit raising. In such cases, the electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>) may be used for all orbit raising of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). <FIG> is a flowchart of one embodiment of a process of using an electric propulsion subsystem of the upper spacecraft <NUM>(<NUM>) for orbit raising of both spacecraft <NUM>(<NUM>), <NUM>(<NUM>). Step <NUM> includes operating an electric thruster of the upper spacecraft <NUM>(<NUM>) to raise the orbit of both the lower spacecraft <NUM>(<NUM>) and the upper spacecraft <NUM>(<NUM>). The spacecraft remain mechanically coupled to each other during step <NUM>. <FIG> depicts the firing of the electric thruster(s) <NUM> of the upper spacecraft <NUM>(<NUM>) to raise the orbit of both the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>). In an embodiment, the upper spacecraft <NUM>(<NUM>) and the lower spacecraft <NUM>(<NUM>) are raised from a parking orbit to a mission orbit. Step <NUM> includes separating the upper spacecraft <NUM>(<NUM>) from the lower spacecraft <NUM>(<NUM>).

In some embodiments, there are more than two spacecraft <NUM> in the stacked launch configuration. <FIG> depicts one embodiment of a stacked launch configuration in which there are three spacecraft <NUM>(<NUM>), <NUM>(<NUM>) and <NUM>(<NUM>). The embodiment is similar to an embodiment of <FIG>, but has a second upper spacecraft <NUM>(<NUM>) above a first upper spacecraft <NUM>(<NUM>). Propellant from the lower spacecraft <NUM>(<NUM>) may be transferred to the second upper spacecraft <NUM>(<NUM>) by way of propellant lines and a propellant line coupling device. More particularly, propellant line <NUM>(<NUM>), coupling device <NUM>(<NUM>), and propellant line <NUM>(<NUM>) couple a port of propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) with a port of propellant storage <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>). Therefore, propellant from the propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) may be transferred to the propellant storage <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>) subsequent to launch and prior to orbit raising. Therefore, the center of mass of the spacecraft stack, in the launch configuration, may be lowered significantly thereby reducing structural bending moment. In one embodiment, the propellant storage <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>) and the propellant storage <NUM>(<NUM>) of the first upper spacecraft <NUM>(<NUM>) are both empty at launch, which lowers the center of mass relative to having propellent in storage <NUM>(<NUM>) and/or <NUM>(<NUM>). Lowering the center of mass reduces structural bending moment at launch.

<FIG> illustrate one embodiment of the transfer of propellent from the lower spacecraft <NUM>(<NUM>) to the first upper spacecraft <NUM>(<NUM>) and the second upper spacecraft <NUM>(<NUM>). <FIG> has similar elements depicted in <FIG>; however, the fairing <NUM>, payload adapter <NUM>, and adapter <NUM>(<NUM>) are not depicted in <FIG> to simplify the drawing. <FIG> depicts a configuration after launch in which some propellant from propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) has been transferred to propellant storage <NUM>(<NUM>) of the first upper spacecraft <NUM>(<NUM>) and some propellant from propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) has been transferred to propellant storage <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>). In an embodiment, the propellant is transferred after the launch vehicle has reached a parking orbit, but prior to deploying the spacecraft <NUM> from the launch vehicle. In an embodiment, the propellant is transferred after the spacecraft <NUM> have been deployed from the launch vehicle into a parking orbit, but prior to orbit raising of the spacecraft <NUM>.

<FIG> illustrate one embodiment of the transfer of propellent from the lower spacecraft <NUM>(<NUM>) to a first upper spacecraft <NUM>(<NUM>) and a second upper spacecraft <NUM>(<NUM>). <FIG> depicts an embodiment of a stacked launch configuration in which there are three spacecraft <NUM>(<NUM>), <NUM>(<NUM>) and <NUM>(<NUM>). In this embodiment, the lower spacecraft <NUM>(<NUM>) has a first inter-spacecraft coupling arrangement <NUM>(<NUM>) that is mechanically coupled, in the launch configuration, with an adapter <NUM>(<NUM>) of the first upper spacecraft <NUM>(<NUM>). The lower spacecraft <NUM>(<NUM>) has a second inter-spacecraft coupling arrangement <NUM>(<NUM>) that is mechanically coupled, in the launch configuration, with an adapter <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>). <FIG> depicts a configuration after launch in which some propellant from propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) has been transferred to propellant storage <NUM>(<NUM>) of the first upper spacecraft <NUM>(<NUM>) and some propellant from propellant storage <NUM>(<NUM>) of the lower spacecraft <NUM>(<NUM>) has been transferred to propellant storage <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>).

In some embodiments, the process of <FIG> is modified for the stacked launch configuration of <FIG> or <FIG>. Step <NUM> may be modified by additionally configuring the propellant line arrangement to couple the first propellant storage <NUM>(<NUM>) and the third propellant storage <NUM>(<NUM>). Step <NUM> may be modified by additionally transferring propellant by way of the propellant line arrangement from the first propellant storage <NUM>(<NUM>) to the third propellant storage <NUM>(<NUM>) after launch of the launch vehicle. Step <NUM> may be modified by additionally deploying the second upper spacecraft <NUM>(<NUM>) from the launch vehicle to the parking orbit. Step <NUM> may be performed to operate a thruster of the first upper spacecraft <NUM>(<NUM>) using the propellant from the second propellant storage <NUM>(<NUM>) that was transferred subsequent to launch from the first propellant storage <NUM>(<NUM>) for an orbit raising maneuver that raises an orbit of at least the first upper spacecraft <NUM>(<NUM>). Additionally, a thruster <NUM>(<NUM>) of the second upper spacecraft <NUM>(<NUM>) may be operated using the propellant from the third propellant storage <NUM>(<NUM>) that was transferred subsequent to launch from the first propellant storage <NUM>(<NUM>) for an orbit raising maneuver that raises an orbit of at least the second upper spacecraft <NUM>(<NUM>). A wide range of orbit raising can be performed. For example, a chemical thruster of the lower spacecraft <NUM>(<NUM>) could be used for orbit raising of the three spacecraft <NUM>(<NUM>), <NUM>(<NUM>) and <NUM>(<NUM>), followed by using an electric thruster of the lower spacecraft <NUM>(<NUM>) to raise the orbit of the lower spacecraft <NUM>(<NUM>), using electric thruster of the first upper spacecraft <NUM>(<NUM>) to raise the orbit of the first upper spacecraft <NUM>(<NUM>) and using an electric thruster of the second upper spacecraft <NUM>(<NUM>) to raise the orbit of the second upper spacecraft <NUM>(<NUM>). This example is a variation of an embodiment of <FIG>. Other orbit raising processes such as those in <FIG>, <FIG>, <FIG>, and <FIG> may also be modified to orbit raise a second upper spacecraft.

<FIG> is a block diagram of one embodiment of spacecraft <NUM>, which in one example (as discussed above) is a satellite. In one embodiment, spacecraft <NUM> includes a bus <NUM> and a payload <NUM> carried by bus <NUM>. Some embodiments of spacecraft <NUM> may include more than one payload. The payload provides the functionality of communication, sensors and/or processing systems needed for the mission of spacecraft <NUM>.

In general, bus <NUM> is the spacecraft that houses and carries the payload <NUM>, such as the components for operation as a communication satellite. The bus <NUM> includes a number of different functional subsystems or modules, some examples of which are shown. Each of the functional subsystems typically include electrical systems, as well as mechanical components (e.g., servos, actuators) controlled by the electrical systems. These include a command and data handling subsystem (C&DH) <NUM>, attitude control systems <NUM>, mission communication systems <NUM>, power subsystems <NUM>, gimbal control electronics <NUM> that be taken to include a solar array drive assembly, a propulsion subsystem <NUM> (e.g., thrusters), propellant storage <NUM> to fuel some embodiments of propulsion subsystem <NUM>, and thermal control subsystem <NUM>, all of which are connected by an internal communication network <NUM>, which can be an electrical bus (a "flight harness") or other means for electronic, optical or RF communication when spacecraft is in operation. In some embodiments the propulsion subsystem <NUM> is used for orbit raising, as disclosed herein. In some embodiments, the propellant storage <NUM> is empty at launch with the propellant being transferred from a lower spacecraft after launch, as disclosed herein. In some embodiments, the propellant storage <NUM> stores propellent at launch with the propellant being transferred to a higher spacecraft after launch, as disclosed herein.

Also represented are an antenna <NUM>, that is one of one or more antennae used by the mission communication systems <NUM> for exchanging communications for operating of the spacecraft with ground terminals, and a payload antenna <NUM>, that is one of one or more antennae used by the payload <NUM> for exchanging communications with ground terminals, such as the antennae used by a communication satellite embodiment. Other equipment can also be included.

The command and data handling module <NUM> includes any processing unit or units for handling includes command control functions for spacecraft <NUM>, such as for attitude control functionality and orbit control functionality. The attitude control systems <NUM> can include devices including torque rods, wheel drive electronics, and control momentum gyro control electronics, for example, that are used to monitor and control the attitude of the spacecraft. Mission communication systems <NUM> includes wireless communication and processing equipment for receiving telemetry data/commands, other commands from the ground control terminal <NUM> to the spacecraft and ranging to operate the spacecraft. Processing capability within the command and data handling module <NUM> is used to control and operate spacecraft <NUM>. An operator on the ground can control spacecraft <NUM> by sending commands via ground control terminal <NUM> to mission communication systems <NUM> to be executed by processors within command and data handling module <NUM>. In one embodiment, command and data handling module <NUM> and mission communication system <NUM> are in communication with payload <NUM>. In some example implementations, bus <NUM> includes one or more antennae as indicated at <NUM> connected to mission communication system <NUM> for wirelessly communicating between ground control terminal <NUM> and mission communication system <NUM>. Power subsystems <NUM> can include one or more solar panels and charge storage (e.g., one or more batteries) used to provide power to spacecraft <NUM>. Propulsion subsystem <NUM> (e.g., thrusters) is used for changing the position or orientation of spacecraft <NUM> while in space to move into orbit, to change orbit or to move to a different location in space. The gimbal control electronics <NUM> can be used to move and align the antennae, solar panels, and other external extensions of the spacecraft <NUM>.

In one embodiment, the payload <NUM> is for a communication satellite and includes an antenna system (represented by the antenna <NUM>) that provides a set of one or more beams (e.g., spot beams) comprising a beam pattern used to receive wireless signals from ground stations and/or other spacecraft, and to send wireless signals to ground stations and/or other spacecraft. In some implementations, mission communication system <NUM> acts as an interface that uses the antennae of payload <NUM> to wirelessly communicate with ground control terminal <NUM>. In other embodiments, the payload could alternately or additionally include an optical payload, such as one or more telescopes or imaging systems along with their control systems, which can also include RF communications to provide uplink/downlink capabilities.

The components connected to the bus <NUM> may by themselves, or in combination with components in ground control <NUM>, be referred to as one or more control circuits. The one or more control circuits may comprise hardware and/or software. The one or more control circuits may be implemented at least in part by executing processor executable instructions on a processer (e.g., a microprocessor). The one or more control circuits may be implemented at least in part by an Application Specific Integrated Circuit (ASIC), FPGA, etc..

For purposes of this document, it should be noted that the dimensions of the various features depicted in the figures may not necessarily be drawn to scale.

For purposes of this document, reference in the specification to "an embodiment," "one embodiment," "some embodiments," or "another embodiment" may be used to describe different embodiments or the same embodiment.

For purposes of this document, a connection may be a direct connection or an indirect connection (e.g., via one or more other parts). In some cases, when an element is referred to as being connected or coupled to another element, the element may be directly connected to the other element or indirectly connected to the other element via intervening elements. When an element is referred to as being directly connected to another element, then there are no intervening elements between the element and the other element. Two devices are "in communication" if they are directly or indirectly connected so that they can communicate electronic signals between them.

For purposes of this document, the term "based on" may be read as "based at least in part on.

For purposes of this document, without additional context, use of numerical terms such as a "first" object, a "second" object, and a "third" object may not imply an ordering of objects, but may instead be used for identification purposes to identify different objects.

For purposes of this document, the term "set" of objects may refer to a "set" of one or more of the objects.

Claim 1:
A system comprising:
a plurality of spacecraft (<NUM>) mechanically coupled together in a stack in a launch configuration, the plurality of spacecraft (<NUM>) comprising:
a first spacecraft (<NUM>(<NUM>)) comprising a first propellant storage (<NUM>(<NUM>)) and a first thruster (<NUM>(<NUM>)) coupled with the first propellant storage (<NUM>(<NUM>)), wherein the first spacecraft (<NUM>(<NUM>)) is configured to mechanically couple with a payload adapter (<NUM>) of a launch vehicle in the launch configuration; and
a second spacecraft (<NUM>(<NUM>)) comprising a second propellant storage (<NUM>(<NUM>)) and a second thruster (<NUM>(<NUM>)) coupled with the second propellant storage (<NUM>(<NUM>)), wherein in the launch configuration the second spacecraft (<NUM>(<NUM>)) is above the first spacecraft (<NUM>(<NUM>)) in the stack, wherein the second propellant storage (<NUM>(<NUM>)) is empty at launch; and
a propellant line arrangement (<NUM>, <NUM>) that couples the first propellant storage and the second propellant storage (<NUM>(<NUM>));
wherein the system is configured to:
transfer propellant by way of the propellant line arrangement (<NUM>, <NUM>), subsequent to a launch phase of the launch vehicle, from the first propellant storage (<NUM>(<NUM>)) to the second propellant storage (<NUM>(<NUM>));
deploy the first spacecraft (<NUM>(<NUM>)) and the second spacecraft (<NUM>(<NUM>)) from the launch vehicle subsequent to the launch phase; and
operate the second thruster (<NUM>(<NUM>)) with the transferred propellant in the second propellant storage (<NUM>(<NUM>)) during an orbit raising maneuver of at least the second spacecraft (<NUM>(<NUM>)) subsequent to the deployment of the first spacecraft (<NUM>(<NUM>)) and the second spacecraft (<NUM>(<NUM>)) from the launch vehicle.