Abstract: This project is related to the inventor, Cyrus Nejat, previous patent Application Number: U.S. Ser. No. 12/011,127. In this study, the main discussion emphasizes on building a spacecraft based on mathematics. The orientation of the low thrust engine spacecraft was structured in such a way that the Kinematics and kinetics equations be written for large elements, by means of the purposed Nejat Kinetics Expansions and Nejat Kinematics Expansions. These equations were used to design Nejat Space Station. Simplified CN (Cyrus Nejat) Equations of Motion used for the Special Spacecraft Rout in Space.

Abstract: In an exemplary embodiment, a pattern is recognized from digitized images. A first image metric is computed from a first digitized image and a second image metric is computed from a second digitized image. A composite image metric is computed as a function of the first image metric and the second image metric, and a pattern is identified by comparing the composite image metric against a reference image metric. The function may be a simple average or a weighted average. The image metric may include a separation distance between features, or a measured area of a feature, or a central angle between two arcs joining a feature to two other features, or an area of a polygon whose vertices are defined by features, or a second moment of a polygon whose vertices are defined by features. The images may include without limitation images of friction ridges, irises, or stars.

Abstract: The present invention provides an airframe structure of an aircraft or spacecraft, with: a hollow body section which can be subjected to an internal pressure; a membrane arrangement which has at least one single-part, multi-curved membrane component for sealing off the internal pressure from an external pressure which acts on the hollow body section and differs from the internal pressure; and a joining structure for a pressure tight joining of the membrane arrangement to a region of the hollow body section; wherein the membrane arrangement forms a receiving well which is accessible from outside the hollow body section, extends at least partially into the hollow body section and is for receiving a component of the aircraft or spacecraft.

Abstract: System and method for inducing rapid reentry of orbital debris including determining a spatial extent of the orbital debris, and deploying dust to the orbital debris to enhance the drag on the orbital debris.

Abstract: A space based manufacturing system including a control module and a manufacturing module. The manufacturing module contains the tools required for automated processing of materials into finalized components. The control module allows command and control of the manufacturing module as well as communication with earth based systems. For component manufacture, the component requiring manufacture is identified in space, designed and engineered on earth, and manufactured in space using computer integrated manufacturing to tie these processes together. The astronaut in the control module monitors the safety of the manufacturing operation and may control manufacturing in real time.

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability. Although this approach is applicable to provide attitude control for any flight vehicle including all types of missiles, kill-vehicles and space craft, it is particularly applicable for smaller highly maneuverable cost-constrained missile systems. One such system is an “Active Protection System” or APS in which a missile system is integrated with a vehicle such as a HumVee or armored personnel carrier to provide defensive counter-measures against possible attack.

Abstract: Actuator for a device for the rotary positioning of a movable element for space equipment comprising a part attached to the fixed portion of said equipment, a bearing, a sleeve designed to actuate the movable portion of said equipment and mounted on an output shaft supported by a first race of said bearing, said actuator comprising a mechanically movable input means and being capable of converting a movement of the input means into a rotary movement of the output shaft about the axis of said bearing, characterized in that said second race of said bearing is connected in rotation to the part of said equipment, in that an adjustable stop so as to angularly limit the relative rotation of the two races of the bearing, and in that the rate of rotation of the output shaft in response to a movement of the input means is different depending on whether or not the sleeve is resting on the adjustable stop.

Abstract: Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.

Abstract: A system and method of generating and distributing power includes one or more microwave power transmitters at locations on Earth adjacent natural fuel or power resources such as natural gas, oil, solid fuel, or geothermal energy. The fuel or energy source is converted into electricity on site, and the electricity is then converted into microwave power beams transmitted from the microwave power transmitter towards a redirector satellite in orbit about the Earth. The redirector satellite then sends one or more microwave beams to rectennas located in consumer nations at appropriate sites for feeding the power grid or to additional redirector satellites for directing to rectennas located on the far side of the Earth.

Abstract: An active vibration damping (AVD) control system for spacecraft provides a simple-to-implement and robust formulation that provides a novel damping control method for reducing spacecraft structural vibrations and improving antenna and instrument pointing. The AVD control system comprises an excitation signal generator configured to generate excitation input signals, and a damping model identification unit configured to receive system identification data and configured to produce control model parameters, the system identification data comprising the excitation input signals and information associated with motion of the spacecraft. The AVD control system further comprises an AVD control unit configured to receive the control model parameters, the AVD control unit configured to produce AVD control signals to control one or more actuators of the spacecraft.

Abstract: Sky/Space elevators structure comprises circle cylindrical structure provide multi floor Section levels. major center structure of center elevator provide transportations from Bottom cockpit levels to top cockpit floor levels. First section levels of multi floors provide bottom cockpit, escape cockpit with eject Rockets, control office, passenger rooms, bed rooms, food service rooms, lavatory rooms, Landing pads, winching machines with multi ropes. Second section levels of multi floors provide center elevators, circle center hangers, jet And rocket fuel tank storages and power plants, outer multi docking bays, multi robotic Arms anchor at outer walls at docking bays. Third section levels floors provide center elevators, circle cylindrical multi soft envelopes from top of middle floors to top of ceiling floors, circle cylindrical carbon fiber composite outer envelopes from top of middle floors to top floors, each envelopes of multi envelopes filled pressurized helium gas which make it float at atmosphere.

Abstract: A spacecraft pressure vessel has a tub member. A sidewall member is coupled to the tub member so that a bottom section of the sidewall member extends from an attachment intersection with the tub member and away from the tub member. The bottom section of the sidewall member receives and transfers a load through the sidewall member.

Abstract: Sky station structure comprises circle center core structure and circle outer Ring structure which comprises multi floor section levels. Major center core structure center elevator provide transportations from bottom Cockpit floor levels to top cockpit floor levels. First section levels of multi floors provide cockpit, control office, passenger Compartments, bed rooms, food service compartments, lavatory rooms, landing Pads, rope with winching machines and jet and rocket fuel tanks.

Abstract: A system and corresponding method for a launch vehicle or spacecraft for releasably connecting a first body (100) with a first interface (101) and a second body (200) with a second matching interface (201), said system comprising: a belt (300) for releasably securing said first body (100) to said second body (200); a circumferential trench (203) at said second interface (201) for receiving said belt (300) in order to provide for a fixation of said belt (300) with relation to said second body (200); mechanical fixation means (301) attaching said belt (300) to said first body (100), said mechanical fixation means (301) being provided to enable a circumferential shifting movement of said belt (300) with respect to said circumference of said first body (100) in order to initiate a separation of the first body (100) from the second body (200), wherein said circumferential shifting movement induces a relative movement of said belt (300) with respect to said circumference of said first body (100) in order to remove

Abstract: A method for racing rocket-powered vehicles directly against one another is provided in which a first rocket-powered vehicle simultaneously races against a second rocket-powered vehicle to be the first to complete a race course. The method may include the first and second rocket-powered vehicles performing a pre-determined maneuver while proximate a group of spectators, and/or the rocket-powered vehicles strategically performing the steps of gliding and boosting the flight of their rocket-powered vehicle in accordance with a pre-determined maximum fuel criteria. The method further may include permitting spectator interaction with participants of the racing competition and enabling spectators to compete with actual participants via virtual vehicles. The method may also include the rocket-powered vehicles performing a refueling operation. The method may further include providing audible or visual identifiers of the vehicles.

Abstract: An active vibration damping (AVD) control system for spacecraft provides a simple-to-implement and robust formulation that provides a novel damping control method for reducing spacecraft structural vibrations and improving antenna and instrument pointing. The AVD control system comprises an excitation signal generator configured to generate excitation input signals, and a damping model identification unit configured to receive system identification data and configured to produce control model parameters, the system identification data comprising the excitation input signals and information associated with motion of the spacecraft. The AVD control system further comprises an AVD control unit configured to receive the control model parameters, the AVD control unit configured to produce AVD control signals to control one or more actuators of the spacecraft.

Abstract: Systems and methods for aircraft guidance using a localizer capture criteria for rectilinear displacement data are disclosed. In one embodiment, the method includes determining a rectilinear deviation D between a current aircraft location and a final defined path (FDP) of an aircraft and determining a location at which the aircraft should begin a reposition maneuver based on the rectilinear deviation D. The method starts a reposition maneuver of the aircraft at a location determined based on a relationship between D and characteristics of the aircraft during the reposition maneuver. In some embodiments, the characteristics of the aircraft may include a velocity of the aircraft with respect to ground, an aircraft track angle, a heading of the FDP of the aircraft, a maximum allowed bank angle of the aircraft during a reposition maneuver, and a time allowance for aircraft rollup and rollout.

Abstract: A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

Abstract: A tubular distributor in a missile having a right-angled hollow tubular first section, the right-angled hollow tubular first section having a first leg and a second leg, a straight hollow tubular second section, an end of the first leg of the right-angled hollow tubular first section perpendicularly connected to a first end of the hollow tubular second section, a straight hollow tubular third section, a first end of the hollow tubular third section perpendicularly connected to the first end of the straight hollow tubular second section, and a close/open valve positioned within the straight hollow tubular third section, the close/open valve positioned between a gas generator and the straight hollow tubular second section.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

Abstract: A rotary positioning device of a movable element for space equipment comprising a part attached to a fixed portion of the equipment and a handle actuating the movable portion of the equipment, said handle being rigidly connected to a first race of a ball or roller antifriction bearing and said fixed part being connected to the second race of said antifriction bearing, wherein a link between said fixed part and the second race is an elastic link in rotation about the axis of said antifriction bearing and wherein a stop is rigidly attached to one of the races in order to interact with an element rigidly attached to the other race, so that the relative rotation of the two races of said antifriction bearing is limited angularly.

Abstract: The subject of the present invention is a method for improving route and 4D prediction calculations by FMS in the framework of ATC tactical flight instructions, which method enables the FMS of an aircraft to carry out its usual predictions as precisely as possible when it has left or anticipates leaving its initial flight plan following an instruction from the air traffic controller, and has no instructions telling it where and when to return to the initial flight plan, and the invention is characterized in that it consists in transmitting to the aircraft, from an air traffic control centre, information enabling the FMS system to be aware of traffic crossing points (X1) and control sector changes, and to use this information to predict the coordinates of a point (X2) at which it is supposed to rejoin its initial flight plan at the earliest opportunity after the crossing point that required an alteration of trajectory and at the latest opportunity on the last point of the current sector.

Abstract: An ultrahigh altitude sun-synchronous orbit satellite system having one or plural satellites orbiting the sun such that the satellites revolve around the earth in a substantially circular or elliptic motion at an altitude of several million kilometers from the earth, beyond the sphere of earth gravity influence. The satellites are placed on an orbital plane relative to both the sun and the earth and keep a distance and geometry between the satellites, sun and earth substantially constant. The satellite system performs any one of the services of space observation, global observation, and satellite communication. The satellites orbit the sun with both inclination and eccentricity distinct from those of the revolution of the earth and revolve around the earth with a sun synchronous property in which the local solar time is kept constant at a point on the surface of the earth directly beneath the satellite.

Abstract: A control system for adjusting the attitude of a spacecraft comprises a set of control moment gyroscopes (CMGs) configured to allow null space maneuvering. The control system further comprises a momentum actuator control processor coupled to the set of CMGs and configured to determine a mandatory null space maneuver to avoid singularities and determine an optional null space maneuver to increase available torque. The mandatory null space maneuver can be calculated based upon certain gimbal angles, and can be implemented by augmenting the inverse-Jacobian control matrix.

Abstract: Disclosed herein is an attitude correction apparatus for an Inertial Navigation System (INS) using a camera-type solar sensor. The present invention relates to a system for correcting errors occurring in an inertial navigation system, in which inertial sensors, such as gyroscopes and accelerometers are combined with each other to calculate the attitude, velocity and position of an airplane, and to an apparatus for utilizing a sun-line of sight vector, generated by a camera-type solar sensor, that uses images of the moving sun, and the output value of the inertial navigation system, thus correcting the attitude of an airplane and the errors of sensors. The attitude correction apparatus of the present invention includes a camera-type solar sensor for detecting the sun, a signal processing unit for receiving and synchronizing information, and a data collection processing unit for performing post-processing on information, thus correcting an error.

Abstract: Systems and methods for are adapted for automatic implementation of exclusion zone avoidance for target-tracking vehicles, such as spacecraft. The systems and methods are configured to monitor pointing commands (commanded attitude and angular rates) generated for target tracking, and modify these commands as necessary to avoid pointing a boresight into an exclusion zone.

Abstract: Embodiments of separation apparatuses are generally described herein. Other embodiments may be described and claimed. In an embodiment, a separation apparatus is provided that is configured to be disposed between a first component and a second component associated with an aerospace vehicle. The separation apparatus comprises a sealed cavity filled with gas, and the separation apparatus is configured to expand based on a decrease in atmospheric pressure. This expansion is configured to separate the first component from the second component.

Abstract: A method of and apparatus for determining and controlling the inertial attitude of a spinning artificial satellite without using a suite of inertial gyroscopes. The method and apparatus operate by tracking three astronomical objects near the Earth's ecliptic pole and the satellite's and/or star tracker's spin axis and processing the track information.

Abstract: According to an embodiment of the present invention there is provided a kill-vehicle to be used in an exo-atmospheric anti-missile interceptor aimed at hitting a target, the kill-vehicle having a main body and comprising: an electronic box; a sensor unit coupled to the electronic box and including at least one sensor for tracking the target at a certain field of view; an inertial measurement unit coupled to the sensor unit; and a divert system controlled by the electronic box for providing the kill-vehicle with thrust at a desired direction; said divert system and electronic box constituting said main body, wherein the kill-vehicle further comprises at least one gimbals unit coupled to the main body and to the sensor unit for controllably changing an angle between the sensor unit and the main body, and wherein said electronic box is configured to synchronically operate said divert system and gimbals unit such that the target remains in the field of view of said at least one sensor and the thrust is provided i

Abstract: A radiation shield for use with a manned spacecraft is claimed. The shield has a container that is substantially filled with a substantially radiation absorbing material. The container has attachment members that cooperate with corresponding attachment members on the inner surface of a spacecraft. The radiation absorbing material provides a measure of protection to crewmembers and equipment against particle radiation that is present in space.

Abstract: A mating and connection system for securing adjacent stages of a launch vehicle. The system includes a locking flange connected to each of a first vehicle stage and a second vehicle stage. A compression ring is positioned internal to the first and second vehicle stages. The compression ring is shaped to compress together the locking flanges of the first and second stages upon engagement with the locking flanges. A locking jack is capable of being activated from an exterior of the first and second stages and operates to selectively move the compression ring into and out of engagement with the locking flanges.

Abstract: In a method for injecting a plurality of spacecraft into different circum-earth or interplanetary orbits individually in a single launch, a plurality of spacecraft coupled to an assist module are injected into an interplanetary orbit having a periodicity synchronous with the earth's revolution period. Then, in a maneuver allowing the assist module to re-counter with and pass near to the earth (Earth swing-by), the assist module appropriately performs an orbital change maneuver and a separation maneuver for each of the spacecraft in a sequential order. Through these maneuvers, a closest-approach point to the earth is changed for each of the spacecraft so as to drastically change a subsequent orbital element for each of the spacecraft. The assist module takes a sufficient time to determine a target orbit for each of the spacecraft with a high degree of accuracy until a half month to several days before a closest-approach time in the Earth swing-by.

Abstract: The invention provides, in some aspects, improved methods, apparatus and systems for unmanned aerial vehicle (UAV) operation that utilize multiple data links between a UAV and a control station in order to transmit control and actionable intelligence data. Such methods, apparatus and systems can be used, for example, to monitor a selected environment (e.g., an oil field or other terrain/environment of interest). In a related aspect, such data links comprise satellite communication channels.

Abstract: An apparatus and method for providing an aircraft-based wireless communications service is disclosed. An exemplary system includes a plurality of aircraft each including on-board equipment for supporting wireless communications with one or more dual mode handsets and for exchanging wireless communication traffic and control information. One or more ground stations communicate with the plurality of commercial aircraft using feeder communications links exchanging the wireless communication traffic and control information and providing interfaces with a terrestrial telecommunications infrastructure. A control center manages the one or more ground stations and the on-board equipment of the commercial aircraft and dynamically assigns resources to the on-board equipment of the plurality of aircraft using an overlapped set of coverage patterns.

Abstract: A modular adapter is attachable to an avionics box of an aircraft to enable network communication between the avionics box and other avionics boxes or controllers on the aircraft, local computing devices, and/or remote computing devices or remote servers in an external network, such as an Internet. The adapter includes a microserver module having a web-based server, a computer processor and memory, a data-over-power module configured to connect to a power connector that delivers power to the avionics box and transmits data to the microserver module, a connector module configured to plug into a power port of the avionics box such that power delivered by the power connector passes through the adapter to the avionics box, and a test port connector configured to plug into a test port of the avionics box. The test port connector enables the microserver module to access data from and send data to the avionics box.

Abstract: The invention relates to a method for photographing on board of a flying rotating body and system for carrying out said method. According to said invention, pictures (V0, V90, V180, V270) are taken at predetermined angular positions of said flying body by a device which is rigidly fixed to the front thereof and are exposed to an image geometrical transformation required for the display thereof.

Abstract: A space based orbital kinetic energy weapon system and method of using same is provided. The space based orbital kinetic energy weapon system includes a satellite having a control system configured to maintain an orbit in outer space around the earth and to deorbit the satellite on a desired trajectory corresponding to an earth based target upon a command, and a projectile object operably connected to the satellite. The projectile object includes a dense mass and a heat shield operably surrounding the mass such that at least a portion of the mass survives reentry into the earth's atmosphere and strikes the earth based target delivering its kinetic energy.

Abstract: The invention relates to a method, a satellite, and a system or an arrangement with at least one satellite for detecting flying objects that are located in the vicinity of a planet, planetoid or similar celestial bodies. The invention further relates to the use thereof for carrying out said method and particularly to a constellation of LEO satellites (LEO=Low Earth Orbit) as an early warning of ballistic missiles, wherein said constellation comprises only satellites on equatorial orbits or orbits with low inclination. Satellite constellations in the low earth orbit (LEO) for missile detection are used for early warning of ballistic missiles, either by detecting the combustion phase of the flying object or by detection during the free-flight phase. The viewing direction of the sensors can be directed directly toward the earth or at an angle past the atmosphere.

Abstract: A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form.

Abstract: A device for controlling heat flow in a spacecraft which always has the same face facing towards the earth, a pair of mutually parallel opposed North and South faces perpendicular to the North-South axis of the earth and two pairs of mutually parallel opposed East/West and Earth/Anti-earth faces, heat-dissipating or -transmitting equipment being provided on the internal walls of the North and South faces, this device comprising a plurality of heat pipes connecting the North and South faces of said craft to another pair of opposed faces of said craft and forming a heat-pipe loop in thermal-conduction contact with one another.

Abstract: A device for determining a flight trajectory of a follower aircraft during a patrol flight, as well as a system for aiding a patrol flight including such a device. The device including another device to determine a flight trajectory of a follower aircraft which allows the follower aircraft to fly along one and the same flight trajectory as a lead aircraft, but with a posterior duration equal to a particular temporal offset.

Abstract: A multiple instrument distributed aperture sensor (“MIDAS”) science payload system mounted on a spacecraft, including a spacecraft interface ring affixing the MIDAS science payload system to the spacecraft, and a multiple telescope array (“MTA”) further including a mechanical subsystem further including an optical bench, an optical subsystem mounted upon the mechanical subsystem collecting light and merging the light into a passive, actively-sensed or hyperspectral image, and a laser subsystem providing laser illumination for collecting active remote sensing data. The MIDAS science payload system also includes a hexapod in physical communication with and between the spacecraft interface ring and the mechanical subsystem.

Abstract: A satellite equipment panel on which may be mounted an installation equipment of a predetermined function, connectable by an interface, constitutes an artificial satellite. The satellite equipment panel includes a panel body, at least two interfaces for an interconnection to another satellite equipment panel, a line transfer switch disposed within the panel body for line transferring of the interconnection between the interfaces, wiring disposed within the panel body and connected at one end to one of the interfaces and at the other end to the line transfer switch for interconnecting the interfaces on that panel body. The interfaces and the wiring, in cooperation with a support structure, constitute a wiring module disposed within the panel body. The interface may comprise at least one of interfaces of electric communication, optical communication, and optical sensor.

Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: Methods and systems for controlling multi-body vehicles with fuel slosh are provided. In a method for stabilizing a vehicle with fuel slosh, a controller for a multi-body assembly is formed by selecting vehicle configuration and velocity as states of a rigid body. Equations of motion are written for the multi-body assembly, and velocity states are determined that are unactuated. A decoupling transformation is defined from the unactuated velocity states. The equations of motion are transformed using the decoupling transformation such that unactuated states are decoupled from actuated states. A slosh state estimator is coupled to the controller such that it is in operative communication with an input to the controller and an output from the controller.

Abstract: A wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in an aircraft, spacecraft, or vehicle may include a honeycomb center having a cavity which is at least partially filled with particle material.

Abstract: A GPS tracker is disposed on launch hardware that separates from a spacecraft launch vehicle during ascent to orbit with the launch hardware having a suborbital trajectory from launch to impact while being tracked so as to track the launch hardware during suborbital flight, such as for tracking separated fuel stages, external tanks, external boosters, and payload fairings that return to earth.

Abstract: Disclosed is a command planning apparatus of a low-earth orbit satellite, and a low-earth orbit satellite control system including the same. The present invention automates the process of executing the command plan for converting the satellite task schedule planned on the ground into telecommands available by the satellite in the low-earth orbit satellite control system, and automatically selects a data set established by the parameters related to the execution task of the satellite according to the mapping rule.

Abstract: A modular spacecraft incorporating a launch vehicle interface design that also functions as a berthing or docking interface for the spacecraft. The vehicle interface utilizes existing launch vehicle components to minimize cost and time to flight. In addition, the spacecraft is constructed from off-the-shelf launch vehicle components that enable a low cost construction as well as a secondary payload carrying functionality.