Abstract: A first part, a second part, and a seal ring are fastened together to form a pressure structure configured for a spacecraft structure of a spacecraft, wherein the first part and the second part are each formed from a single workpiece.

Abstract: Systems and methods for performing airport surface collision-avoidance. A wingtip-mounted camera allows the pilot to positively ascertain that the wingtip will clear objects located in the video. An exemplary system implemented on an aircraft includes a wingtip module having a camera that generates a video stream and a communication device that transmits the generated video stream. A processor receives the video stream and generates a reticule for the video stream. A display device simultaneously presents the video stream and the reticule. The reticule includes a horizon line and is based on a focal length of a lens of the camera and height of the camera above ground. The reticule includes curved and/or straight distance lines and curved or straight travel lines. The travel line(s) correspond to at least one aircraft component or a zone of importance and are based on location of the camera and trajectory of the aircraft.

Abstract: A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

Abstract: A spacecraft coupling system includes an integral component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The integral component may include a central ring, a plurality of leaf elements arranged at the perimeter of the component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently tension the leaf elements against surfaces on the mating component. To reduce cost and complexity, the integral component is a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.

Abstract: A dozen or more orbiting solar generators stay in constant touch. They can be congregated rapidly in space at any desired secret location. Once congregated they all focus their energy to a death star. This death star is a newly launched ICBM with a microwave or laser collector. A laser generator uses this huge energy to project a non-nuclear death ray to a target. The target could be a city, a ship or a satellite. In the event of an asteroid approaching earth, this system could destroy an asteroid. In peacetime the orbiting solar generators supply electric power to an earth based power grid.

Abstract: A method and apparatus comprising a location reference system and a control module. The location reference system is configured to generate location information for a number of mobile platforms in an environment. The control module is configured to receive the location information for the number of mobile platforms from the location reference system. The control module is further configured to generate command signals for the number of mobile platforms using the location information. The control module is further configured to send the command signals to the number of mobile platforms to operate the number of mobile platforms in the environment such that operation of the number of mobile platforms emulates the operation of a number of spacecraft systems in a non-Earth terrestrial environment.

Abstract: A microsatellite comprising a propulsion module for moving and/or pointing the microsatellite and an imaging device (100) mounted to the propulsion module. Furthermore there is a fuel supply (210) located within the imaging device (100).

Abstract: In one embodiment, a variable surface landing platform (VARSLAP) includes a base for contacting a landing surface; at least 3 adjustable struts interconnected with the base, wherein each strut is bisected by a strut actuator-housing, and wherein the at least 3 adjustable struts are interconnected to a main body aerospace craft (MAC); a sensor array on the base; and an attitude determination and control system (ADCS).

Abstract: A multi-body aerospace apparatus includes a first aerospace body, a second aerospace body, and a flow separation member. The second aerospace body is attached adjacent to the first aerospace body with a gap disposed between the first aerospace body and the second aerospace body. The flow separation member is attached to the first aerospace body or to the second aerospace body.

Abstract: Example methods and systems for determining a distribution of balloons based on population densities is provided. A method may include receiving information indicating a region divided into a plurality of horizontal bands of latitudes and a population density for one or more areas of the region. The method may also include associating the population density for a given area with a corresponding horizontal band of latitude in which the given area resides, and based on the population density associated with each horizontal band of latitude, determining a distribution of a plurality of balloons per horizontal band of latitude. The method may also include providing instructions to control the distribution of the plurality of balloons per horizontal band of latitude to remain in a trajectory substantially within a respective horizontal band of latitude.

Abstract: According to aspects of the embodiments, there is provided an apparatus and method to synchronize trajectories from independent systems such as from a flight management system and the ground Air traffic control during the entire history of a flight. Since a number of trajectory discrepancy factors will intervene during the lifetime of a flight, such as a change in flight intent, controller intervention, or large deviations of the actual flight from the predicted trajectory due to prediction errors, there is need to dynamically monitor these deviations and control a dynamic synchronization cycle. A dynamic trajectory synchronization algorithm attempts to bring each of the systems back into balance whenever a disturbance causes an imbalance.

Abstract: The systems and methods of the invention modulate atmospheric gases to temporarily increase the amount of atmospheric particles in the path of the debris, in order to decelerate the debris and accelerate natural orbital decay to the point of atmospheric re-entry. In one aspect of the invention, clearing the space debris includes propelling a plume of atmospheric gases substantially orthogonal to the path of the debris such that the debris collides with the gaseous plume as it passes through the plume. Increased atmospheric drag from the gaseous particles of the plume in the path of the debris obstructs a forward propagation of the debris and gradually decelerates the debris, leading eventually to atmospheric recapture.

Abstract: An electronic flight planning system is provided, arranged to implement a preferred method for identifying conflicts between flight plans for aircraft. In the preferred method, the system receives, as data input from one or more users, a plurality of flight plans each defining a flight by an aircraft; the system determines, for each aircraft and its respective received flight plan, a three-dimensional region of potential conflict, representative both of the uncertainty in the position of the aircraft and of a region of air exclusion appropriate for the aircraft or for the respective received flight plan; and the system determines, on the basis of the determined regions of potential conflict, whether one of the received flight plans is in conflict with any of the other received flight plans.

Abstract: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks.

Abstract: Methods and apparatus are presented for spacecraft operation in which a control problem is formulated using a control law or steering law as a path constraint or as a dynamic constraint, and the control problem is solved to provide a guidance command trajectory for use in operating spacecraft control momentum gyroscopes to guide the spacecraft from an initial state to a desired final state.

Abstract: A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction.

Abstract: A system and method for safely flying an unmanned aerial vehicle (UAV), unmanned combat aerial vehicle (UCAV), or remotely piloted vehicle (RPV) in civilian airspace uses a remotely located pilot to control the aircraft using a synthetic vision system during at least selected phases of the flight such as during take-offs and landings.

Abstract: A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

Abstract: Systems and methods are operable to present graphical information indicating capability of an aircraft to change altitude. An exemplary embodiment determines an altitude change capability of the aircraft; determines an altitude change capability icon based on the determined altitude change capability of the aircraft, wherein the altitude change capability icon is defined by at least a leading portion, a trailing portion, a top portion, and a bottom portion, wherein a slope of the leading portion of the altitude change capability icon corresponds to the determined altitude change capability of the aircraft, and wherein the leading portion and the trailing portion are separated by at least the top portion and the bottom portion; and communicates the altitude change capability icon to a display for presentation to the crew of the aircraft.

Abstract: An attitude estimator that uses sun sensor outputs as the only attitude determination measurements to provide three-axis attitude information. This is accomplished by incorporating the Euler equation into the estimator. An unscented Kalman filter is employed to accommodate various nonlinear characteristics and uncertainties of the spacecraft dynamics and thus improve the robustness and accuracy of the attitude estimate.

Abstract: A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.

Abstract: Wing load alleviation methods and apparatus are disclosed. An example method includes collecting data related to a condition of an aircraft; and when a condition identifier implemented via a logic circuit indicates that the condition comprises a high load condition, automatically generating a plurality of control signals to coordinate a first deflection of a first control surface of a configurable winglet and a second deflection of a second control surface of a wing adjacent to the winglet.

Abstract: A method is provided for controlling a set of at least two satellites, designed to provide a service on a geostationary orbit, rendering said service on a non-geostationary orbit, in which means involved in the performance of said service, installed on board a satellite, are deactivated when the sun can damage it, and means involved in the performance of said service installed on board another satellite of the set are activated, when this is necessary to the continuity of the service.

Abstract: A dozen or more orbiting solar generators stay in constant touch. They can be congregated rapidly in space at any desired secret location. Once congregated they all focus their energy to a death star. This death star is a newly launched ICBM with a microwave or laser collector. A laser generator uses this huge energy to project a non-nuclear death ray to a target. The target could be a city, a ship or a satellite. In the event of an asteroid approaching earth, this system could destroy an asteroid. In peacetime the orbiting solar generators supply electric power to an earth based power grid.

Abstract: An orbital launch system and its method of operation use a maneuver to improve the launch condition of a booster rocket and payload. A towed launch aircraft, to which the booster rocket is mounted, is towed to a predetermined elevation and airspeed. The towed launch aircraft begins the maneuver by increasing its lift, thereby increasing the flight path angle, which increases the tension on the towline connecting the towed launch aircraft to a towing aircraft. The increased tension accelerates the towed launch aircraft and booster rocket, while decreasing the speed (and thus the kinetic energy) of the towing aircraft, while increasing kinetic energy of the towed launch aircraft and booster rocket by transferring energy from the towing aircraft. The potential energy of the towed launch aircraft and booster rocket is also increased, due to the increased lift. The booster rocket is released and ignited, completing the launch.

Abstract: Technology for predicting and correcting a trajectory is described. The technology can create a model to predict a position of the reusable launch vehicle at a time in the future; observe a wind condition during ascent of the reusable launch vehicle; store the observed wind condition in a wind map; predict during ascent a position and a terminal lateral velocity of the reusable launch vehicle at a terminal altitude; and correct a flight trajectory of the reusable launch vehicle based on the wind map.

Abstract: An artificial satellite system includes at least two panel type artificial satellites closely connected with a plurality kind of multi networks and the minimum necessary essential tools for one artificial satellite installed on a substrate of each panel type artificial satellite, wherein the multi networks are formed by a communicating network for communicating data among data processing tools installed on each of the panel type artificial satellites, a heat pipe for providing thermal energy among tools installed on each of the panel type artificial satellites and a battery supplying line for connecting battery controlling devices installed in the each panel type artificial satellite so that the artificial satellite system can maintain higher and various controlling performance with a back-up effect of the multi network in the case that any function tool is damaged in one of the panel type artificial satellite.

Abstract: A method of landing a capsule-spacecraft having a crew compartment containing crew, light cargo, and whatever other elements are associated with crew safety and comfort during emergency recovery, such as survival equipment and a service component including any propulsion components, heat shield, heavier structure, or other equipment not directly connected with the crew component. In the event of a propulsion system failure, the crew compartment component is immediately separated from the service component, either by automatic or crew action. One or more parachutes are then deployed by rapid methods, such as rocket extraction, from the crew compartment. Because the space craft is separated into two parts the weight of the parachutes is reduced in proportion as the weight of the crew compartment is to the total capsule-spacecraft.

Abstract: The present invention is a Partial Automated Alignment and Integration System (PAAIS) used to automate the alignment and integration of space vehicle components. A PAAIS includes ground support apparatuses, a track assembly with a plurality of energy-emitting components and an energy-receiving component containing a plurality of energy-receiving surfaces. Communication components and processors allow communication and feedback through PAAIS.

Abstract: Radiation shields include an outer composite wall, an inner composite wall, and an enclosed fuel chamber disposed between the inner and outer composite walls. A fuel may be contained within the enclosed fuel chamber. Spacecraft include one or more such radiation shields, and may further include a fuel cell and a conduit providing fluid communication between the fuel chamber of the radiation shield and the fuel cell. Methods of forming a radiation shield system include forming an enclosed fuel chamber between an outer composite wall and an inner composite wall of a radiation shield, and providing fuel within the enclosed fuel chamber.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.

Abstract: An exo-atmospheric intercepting method for intercepting in space multiple objects, including acquiring and tracking multiple inflated objects which fly towards a protected territory. The method further includes launching an interceptor missile accommodating a plurality of kill vehicles each hosting a plurality of punching objects and classifying the multiple objects into clusters. In respect of each cluster of objects, determining an ejection condition responsive to meeting of which a kill vehicle is ejected from the interceptor missile towards the cluster of objects and thereafter releasing from the kill vehicle a plurality of punching objects such that every inflated object in the cluster is likely, with a high degree of certainty, to be punched by one or more punching objects.

Abstract: In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display

Abstract: The present invention is a space vehicle valve system which controls the internal pressure of a space vehicle and the flow rate of purged gases at a given internal pressure and aperture site. A plurality of quasi-unique variable dimension peaked valve structures cover the purge apertures on a space vehicle. Interchangeable sheet guards configured to cover valve apertures on the peaked valve structure contain a pressure-activated surface on the inner surface. Sheet guards move outwardly from the peaked valve structure when in structural contact with a purge gas stream flowing through the apertures on the space vehicle. Changing the properties of the sheet guards changes the response of the sheet guards at a given internal pressure, providing control of the flow rate at a given aperture site.

Abstract: A vehicle for launching from a gun such as a gas gun and having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: A system, method, and apparatus are disclosed for agile dedicated spacecrafts for spinning microwave imagers and sounders. In one or more embodiments, the system, method, and apparatus involve an agile, zero net-momentum, spinning space vehicle, which includes a body and an instrument package. In one or more embodiments, the instrument package is mounted directly onto the body such that the space vehicle can point the instrument package not only along the space vehicle's orbital velocity vector, but in any direction within the space vehicle's field of regard. The space vehicle's spin axis is aligned with the instrument package's scan axis. The space vehicle experiences zero net-momentum on orbit by including a counter-rotating momentum storage device. In one or more embodiments, the instrument package is a scanning microwave imaging/sounding instrument, which is utilized as an Earth climate and weather sensor.

Abstract: A computerized method for transmitting data between a multi core vehicle management system and a vehicle system. The method can include receiving, at a vehicle management system computer, a vehicle system request message from a requesting vehicle management system component. The requesting vehicle management system component can be one of a plurality of vehicle management system components, and the vehicle system request message can have a destination vehicle system component. The method can include generating a sanitized vehicle system request message based on the requesting vehicle management system component and the destination vehicle system component. The sanitized vehicle system request message can be transmitted to said destination vehicle system component.

Abstract: Disclosed herein, in certain embodiments, is a method of altering the stability of unstable space debris. In some embodiments, the method further comprises changing the orbit of the unstable space debris.

Abstract: A first part, a second part, and a seal ring are fastened together to form a pressure structure configured for a spacecraft structure of a spacecraft, wherein the first part and the second part are each formed from a single workpiece.

Abstract: A multifunctional controller includes an onboard computer (OBC) and a power supply unit (PCDU) of a satellite. The controller includes reconfiguration functions for monitoring the correct functioning of components of an onboard computer of the satellite and for switching over between redundant components and/or turning off electrical loads of the satellite in the event of a malfunction. The controller also includes control functions for controlling and distributing energy to satellite components, which is designed for turning on and off the power supply to satellite components together with the reconfiguration unit.

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. Small objects with perigee above about 900 km where the debris lifetime can be centuries can be targeted for de-orbiting.

Abstract: Fiber-based debris interceptors are used to intercept and/or contain space debris. The debris interceptors may be made up of fibers that are formed in space from a material supply on a space vehicle. The fibers for the debris interceptors may be formed by extrusion, with a heat source, such as a mirror to focus sunlight, used to heat the material of the material supply that is carried on the space vehicle. The debris interceptor may be separated from the space vehicle, and used to remove debris from an orbit, or otherwise prevent debris entering an orbit from damaging a satellite or other spacecraft that travels in that orbit. The debris interceptor may be deployed prior to later launch of a valuable spacecraft, in order to “cleanse” the intended orbit of debris. Debris objects may pass through the debris interceptor, but in so doing may lose energy so as to de-orbit.

Abstract: The invention relates to a mixing system for inerting a gas volume. A first exhaust gas that is provided by a fuel cell, and a second exhaust gas that is provided by a hydrogen reformer, can be mixed to form an inert gas mixture. The mixture can be fed into the gas volume for inerting.

Abstract: A spacecraft magnetic shield apparatus is disclosed. One embodiment has an armature attached at one end of a spacecraft and an electromagnet attached to the other end. A computer determines the position of the armature and electromagnet in relation to the spacecraft, and a power source powers the electromagnet. In operation, the positioning of the electromagnet is generally in line with incoming charged particles or ion radiation and powering of the electromagnet creates a magnetic field that deflects a percentage of the incoming charged particles or ion radiation from directly impacting the spacecraft.

Abstract: A system for facilitating autonomous landing of aerial vehicles on a surface. A beam emitter is directed downwards. A control module is configured to govern the vehicle. A processor processes image data. The beam emitter is arranged to emit simultaneously at least four beams directed towards the surface in order to project a pattern thereon. One beam emitter of the at least four beam emitters is placed in the center. An image capturing module captures subsequent images of the pattern.

Abstract: A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for sensing flight direction of a spacecraft. According to an example embodiment of the invention, a method is provided for determining flight direction of a spacecraft. The method includes providing at least one imaging detector associated with a spacecraft; imaging at least a portion of a celestial body onto the at least one imaging detector; acquiring, by the at least one imaging detector, sequential images of at least a portion of the celestial body; and determining the spacecraft flight direction relative to the celestial body based at least in part on processing the sequential images, wherein the processing is performed by one or more computer processors.

Abstract: A protective device for an electronic unit on a space exploration vehicle. A Laplace transform calculation unit generates a Laplace transform of an electronic unit state. A system parameter identification unit identifies system parameters based on the Laplace transform of electronic unit states. A Fourier transform calculation unit generates a ratio of the ground contacting mechanism state to a highest dominant frequency of the measured electronic unit state. A critical travel speed calculation unit generates a critical travel speed based on the identified system parameters. A calculation unit for threshold of travel speed generates a threshold of a travel speed based on the critical travel speed. An autonomous motion controller generates a control signal that drives the space exploration vehicle based on the threshold of the travel speed.

Abstract: A vehicle includes a first sub-vehicle, and a second sub-vehicle which is repeatably moveable between coupled and uncoupled conditions with the first sub-vehicle. The first and second sub-vehicles each include a landing system and propulsion system. The first and second sub-vehicles are in the coupled condition during take-off. The first and second sub-vehicles are separately flyable in the uncoupled condition. Both vehicles are launched horizontally, by a ramp, or vertically, using atmospheric lift to achieve atmospheric flight, orbital, or sub-orbital launch.