Abstract: In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

Abstract: A satellite system operates at altitudes between 180 km and 350 km relying on vehicles including an engine to counteract atmospheric drag to maintain near-constant orbit dynamics. The system operates at altitudes that are substantially lower than traditional satellites, reducing size, weight and cost of the vehicles and their constituent subsystems such as optical imagers, radars, and radio links. The system can include a large number of lower cost, mass, and altitude vehicles, enabling revisit times substantially shorter than previous satellite systems. The vehicles spend their orbit at low altitude, high atmospheric density conditions that have heretofore been virtually impossible to consider for stable orbits. Short revisit times at low altitudes enable near-real time imaging at high resolution and low cost. At such altitudes, the system has no impact on space junk issues of traditional LEO orbits, and is self-cleaning in that space junk or disabled craft will de-orbit.

Abstract: A method of roll steering of a spacecraft to align an aspect of the spacecraft, such as the surface of solar arrays carried by the spacecraft, to the sun, is described. The roll steering occurs only when the sun is at an angle (?) relative to the orbital plane of the spacecraft and when the spacecraft is not eclipsed by a body it is orbiting. This dayside-only roll steering of the spacecraft increases the power efficiency of the spacecraft. A spacecraft may include a controller which causes an attitude control subsystem to steer the spacecraft about a roll axis to position the surface of the solar array such that an axis normal to the surface of the solar array is aligned with the direction to a sun when the sun is visible to the spacecraft, and maintain a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.

Abstract: Model based inertial navigation for a spinning projectile is provided.

Abstract: A goods processing apparatus can include a pivotable display, a sensor, and a controller. The sensor detects an angle of inclination of the pivotable display. The pivotable display is rotatable about a x-axis of a Cartesian coordinate system. The sensor is disposed on the pivotable display and includes respective transducers at least in a direction of a y-axis and a z-axis of the Cartesian coordinate system. The sensor generates respective digital measured values for each of the y-axis and the z-axis. The controller processes the two digital measured values to derive the angle of inclination of the pivotable display based on the two digital measured values, and stores, in a memory of the goods processing apparatus, the derived angle of inclination.

Abstract: A spacecraft has a flat antenna array having an edge and a middle portion. A reconfigurable reaction-momentum wheel is coupled to the antenna array to roll and/or pitch the antenna array in small magnitudes. The reconfigurable reaction-momentum has a reaction operating state or mode (high-torque, low momentum) and a momentum operating state or mode (low-torque, high momentum). A thruster is coupled to the antenna array to move the antenna array.

Abstract: A method and system for activating thrusters of a vehicle for trajectory-tracking control of the vehicle. A transfer orbit generator to generate a transfer orbit for the vehicle from an initial orbit to a target orbit, and a feedback stabilization controller. Compute the target orbit for the vehicle about the celestial body. Compute a free trajectory with patch points along the free trajectory using a free trajectory module, each patch point includes a position and a velocity. Determine a feedback gain at each patch point using a feedback gain module, wherein a state penalty function at each patch point is set to match a state uncertainty function at the same patch point. Apply the feedback gain at each patch point to map the position and the velocity at each patch point to delta v commands, to maintain the target orbit using a feedback stabilization controller.

Abstract: A spacecraft nutation inhibition method for low-orbit geomagnetic energy storage in-orbit delivery includes: S1, enabling a delivery connection rod to be slidably connected to two mass blocks in a length direction, and adjusting the center of mass of a spacecraft system to pass through a main connecting shaft; S2, respectively measuring, calibrating and adjusting the center of mass and the principal axis of inertia of the delivery connection rod that is to deliver the space target or de-orbit debris; S3, carrying out energy storage delivery; S4, respectively adjusting the center of mass and the moment of inertia of the delivery connection rod after delivering the space target or de-orbit debris; S5, carrying out energy dissipation and unloading; and S6, enabling the spacecraft system to prepare to grab the next space target or de-orbit debris and proceeding to the next delivery work cycle.

Abstract: The system for very early detection and suppression of fires is comprised of the network of low orbiting micro-satellites, local drones, processing and communication equipment and fire suppression capabilities with fire retardants and water delivered by drones, helicopters, planes and/or ground fire crews. Micro-satellites and drones are equipped with very sensitive, high resolution imaging spectrometers operating in multiple visible and infrared wavelengths. Processors are used to analyze spectroscopic micro-satellite images to detect fires and to verify validity of fire detection by analysis of spectroscopic drone images. The system can prevent large wild fires anywhere in the world rapidly with high detection sensitivity and reliability.

Abstract: A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The divert thruster system may have three divert thrusters evenly spaced around a circumference of the vehicle, offset 120 degrees from each other. The divert thrusters are located at a longitudinal (axial) location along the vehicle at or close to a center of gravity of the vehicle. In addition the vehicle may have an aft axial thrusters that may be used in maneuvering the vehicle.

Abstract: Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

Abstract: A method is provided for realigning or relieving mechanical stress in a spacecraft frame. The process includes providing a spacecraft which includes at least two frame subsections connected by a mechanical connector. The mechanical connector provides both a soft dock connection which mechanically connects the two frame subsections but allows relative movement between the two frame sections and a hard dock connection which mechanically connects the two frame subsections but does not allow relative movement between the two frame sections. Once in space, a controller causes the mechanical connector to transition from a hard dock connection to a soft dock connection, which is maintained for a predetermined time period to realign or relieve stress within the spacecraft frame. Thereafter, the controller causes the mechanical connector to transition from the soft dock connection back to the hard dock connection.

Abstract: A control apparatus includes a detection unit configured to detect an object from an image captured by an imaging apparatus, a control unit configured to control a drive unit in such a manner that an imaging direction of the imaging apparatus is changed following a movement of the object detected by the detection unit, and a determination unit configured to determine information about the movement of the object detected by the detection unit. The control unit controls drive frequency of the drive unit based on the information about the movement determined by the determination unit.

Abstract: The invention obtains a straddle-type vehicle information processor and a straddle-type vehicle information processing method capable of recognizing that a traveling straddle-type vehicle enters a falling phase with a high degree of accuracy at appropriate timing and thereby contributes to improvement in occupant safety. A straddle-type vehicle information processor 10 includes: a posture information acquisition section 11 that at least acquires a roll rate Rr and a yaw rate Ry generated in a traveling straddle-type vehicle 1 as posture information; and a falling phase recognition section 12 that recognizes that the straddle-type vehicle 1 enters a falling phase in the case where a change in a degree of instability over time, which is derived at least on the basis of the roll rate Rr and the yaw rate Ry, shows an increasing tendency.

Abstract: A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The attitude control system may have two pairs of attitude control thrusters, with one of the pairs diametrically opposed from the other pair, on opposite sides of an end (such as a rear end) of the vehicle. The attitude control thrusters all have radial and circumferential components to their thrust, and various combinations of the attitude control thrusters may be used to achieve desired roll, pitch, and/or yaw.

Abstract: A control method for a non-orthogonal gimbal includes obtaining an actual attitude of the gimbal, determining a target attitude of the gimbal according to the actual attitude of the gimbal and an angle between a first rotation axis of a first drive motor and a second rotation axis of a second drive motor, determining an attitude error according to the actual attitude and the target attitude, and controlling one or more of a plurality of drive motors according to the attitude error to cause the gimbal to approach the target attitude. The gimbal includes the plurality of drive motors including the first drive motor, the second drive motor, and the third drive motor. The gimbal further includes a base, a first axis arm, a second axis arm, and a third axis arm.

Abstract: A control system configured to execute a safing mode sequence for a spacecraft is disclosed. The control system includes one or more star trackers that each include a field of view to capture light from a plurality of space objects surrounding the celestial body. The control system also includes one or more actuators, one or more processors in electronic communication with the one or more actuators, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to determine a current attitude of the spacecraft, and re-orient the spacecraft from a current attitude into a momentum neutral attitude.

Abstract: Systems and methods are provided for calculating satellite access windows for a constellation of imaging satellites. In some implementations, systems and methods are provided for managing execution of native programs on high performance computing systems.

Abstract: A control system for a spacecraft for determining a resultant torque that is exerted upon a spacecraft by one or more magnetic torque rods is disclosed. The spacecraft is configured to revolve around a celestial body in an orbit. A magnetic field of the celestial body is predictable, and a direction of the magnetic field located around the orbit is fixed. The control system includes the one or more magnetic torque rods, one or more processors in electronic communication with the one or more magnetic torque rods, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the one or more magnetic torque rods to exert the resultant torque upon the spacecraft.

Abstract: Provided are an earth satellite attitude data fusion system and method, applicable to an earth satellite space environment to estimate attitude data of a satellite. When the earth satellite attitude data fusion system of the present invention is used to perform the earth satellite attitude data fusion method, the first step is to perform a body rates/quaternion attitude data processing operation. Then, the next step is to perform an attitude/rates data fusion processing operation, wherein an attitude data fusion algorithm module receives a first IAE result data from a first EKF, and a second IAE result data from a second EKF, and performs an attitude/rates data fusion algorithm in a subsystem level to evaluate an attitude estimation IAE performance based on the first IAE result data, and the second IAE result data.

Abstract: A method for the safe release of artificial satellite in Earth orbit includes the steps of providing an orbital transport spacecraft able to move at orbital height and comprising a plurality of PODs for releasing satellites transported by the orbital transport spacecraft, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft to release the orbital transport spacecraft from the space launcher, in case of failure to release the orbital transport spacecraft or in case of breakdown of the orbital transport spacecraft after releasing from the space launcher, activating a safety subsystem of the orbital transport spacecraft to generate a POD activation sequence to release the satellites.

Abstract: A method of deploying a constellation of satellites includes using a single launch vehicle to deploy a plurality of satellites at an initial altitude on a same initial orbit, controlling said satellites such that an altitude of some of the satellites is modified while their inclination relative to an equatorial plane and a type of trajectory, of the some of the satellites, remains identical so that each satellite reaches a drift altitude selected from a drift set, with orbits of various satellites shifting relative to one another, and controlling the satellites to be moved sequentially in order to reach a same final altitude, said sequential movement being performed in such a manner that the satellites describe final orbits having trajectories with a same angle of inclination relative to the equatorial plane, a same apogee and perigee, and the same final altitude but presenting distinct longitudes for ascending nodes.

Abstract: A portable flat panel antenna system and method for using the same are disclosed. In one embodiment, the portable satellite antenna apparatus comprises a flat panel antenna and a container to house the antenna, the container having at least one radio-frequency (RF) transparent material through which the antenna is operable to transmit and receive satellite communications.

Abstract: The present disclosure generally relates to user interfaces for managing peer-to-peer transfers. In some examples, a device provides user interfaces for initiating and managing transfers. In some examples, a device provides user interfaces corresponding to completed transfers. In some examples, a device provides user interfaces for providing visually distinguishable message object appearances based on message designation. In some examples, a device provides user interfaces for activating accounts for accepting and sending transfers. In some examples, a device provides user interfaces for exchanging accounts for use in a transfer. In some examples, a device provides user interfaces for splitting transfers between two or more accounts. In some examples, a device provides user interfaces for generating and displaying a transfers history list. In some examples, a device provides user interfaces for voice-activation of transfers.

Abstract: A method for the deployment of reconnaissance devices including buoy cameras and robotic devices in a target mission area of a remote location in space utilizing a maneuverable descent de-booster capsule and a buoyant vessel for the deployment is disclosed, including identifying the target area from an orbiting spacecraft; deploying the de-booster into orbit over the target area; initiating gradual descent of the de-booster in the atmosphere of the remote location in space; ejecting the buoyant vessel and its payload from the de-booster; filling the buoyant portion of the buoyant vessel with a lifting gas to cause the buoyant portion to become a large balloon; activating reconnaissance devices on the bay portion of the buoyant vessel, including video and other devices for monitoring and surveiling the target mission area; maneuvering the buoyant vessel to refine mission site selection; opening cargo bay doors at a predetermined altitude to deliver payloads including buoy cameras to the target mission area; ca

Abstract: A system for providing spacecraft-based services, preferably including one or more spacecraft and one or more ground control elements, wherein the spacecraft can include one or more payloads associated with one or more organizations. A method for providing spacecraft-based services, preferably including receiving service requests, determining request assignments, and/or controlling spacecraft.

Abstract: A system and a method for identifying and tracking unacknowledged marine vessels. The system includes a sensing system having one or more observation platforms positioned remotely above one or more marine vessels, each with a navigation system, and one or more payloads coupled to the observation platform(s). The payloads have one or more optical receivers to observe, geolocate, and receive optical emissions from the marine vessels to detect optical signatures. The payloads have one or more AIS receivers to observe, geolocate, and receive AIS emissions from the marine vessels to detect AIS signatures. The payloads have one or more RF receivers to receive RF emissions from the marine vessels to detect RF signatures. The payloads have at least one processor with an analysis software to process and analyze the optical, AIS, and RF signatures, to identify and track one or more unacknowledged marine vessels from the marine vessels.

Abstract: Methods and systems disclosed herein relate to determining a projected change in bandwidth demand in a specified area during a specified future time period, repositioning one or more balloons in a high-altitude balloon network based on the projected change in bandwidth demand, and providing, using the one or more balloons, at least a portion of the bandwidth demanded in the specified area during the specified future time period.

Abstract: An apparatus for simultaneously receiving and transmitting data in space may include a receiver configured to receive an incoming beam transmitted from a source along a receive vector between the source and the receiver. The apparatus may also include a transmitter to generate a transmitted beam along a transmit vector. The apparatus may further include a single-axis gimbal configured to rotate the transmit vector about an axis substantially perpendicular to the receive vector, and an attitude-control system configured to rotate the apparatus about an axis parallel to the receive vector or the transmit vector.

Abstract: A method measures a frequency characteristic at a feed axis control unit configured to drive a motor in accordance with a velocity command value to control a velocity or a position of a movable portion of a driven body. The velocity command value includes a velocity reference value from a host device or a velocity command calculator and a sweep signal swept in order to measure the frequency characteristic. The method includes moving the feed axis in one direction by commanding the velocity reference value where a moving velocity of the feed axis is constant, exciting by providing a sine wave having an amplitude less than a magnitude of the velocity reference value to the sweep signal, and measuring the frequency characteristic of a feed axis drive system including the motor.

Abstract: An orbiting satellite can be maintained in a virtual orbit, having an orbital period equal to the natural orbit of a satellite at a different altitude, by equipping the satellite with at least one radial thruster. Radial thrusters on the anti-nadir-facing side of the satellite allow for virtual orbits higher than the natural altitude, while radial thrusters on the nadir-facing side of the satellite allow for virtual orbits lower than the natural altitude. This allows a satellite to evade threats, such as orbital debris and/or hostile spacecraft, without losing its relative position within a satellite constellation or experiencing the diminished services often attendant such maneuvers. Similar techniques can also be used for surveillance of orbiting satellites.

Abstract: Techniques for orienting an earth-orbiting spacecraft include determining, using a star tracker on board the spacecraft, a first vector aligned between an ecliptic pole of the earth and the spacecraft, adjusting attitude of the spacecraft so as to align a first axis of the spacecraft with the first vector, and rotating the spacecraft about the first axis until presence of the sun is registered. Rotation rates may be subsequently reduced, such that the sun remains within a field of view of the sun sensor or of a solar array of the spacecraft.

Abstract: Included herein is an electronic pen (100) with pen position detection, comprising at least a writing lead (113), at least an electric voltage source (103), at least one digital control unit (120) and at least one data transfer module (111), characterized in that the electronic pen (100) comprises at least three position determination sensors (105, 112, 104), wherein said determination sensors are configured such that from their measurement data an over-determination of the position and/or movement of the electronic pen (100) can be determined.

Abstract: A spacecraft includes at least a first thruster support mechanism (TSM) and a second TSM, each TSM including a pointing arrangement, an elongated structural member and thruster for performing orbit raising north-south stationkeeping, east-west stationkeeping, and momentum management. A first pointing arrangement is articulable only by way of first and second revolute joints, the first revolute joint being rotatable about a first axis fixed with respect to the spacecraft. The second pointing arrangement is articulable only by way of third and fourth revolute joints, the third revolute joint being rotatable about a third axis fixed with respect to the spacecraft. The first axis and the third axis are asymmetrically arranged with respect to a spacecraft coordinate system origin such that the first and third axis are at acute angles to a spacecraft pitch axis and the acute angle of the first axis is less than that of the third axis.

Abstract: Drone-based wireless communications systems are provided, as are methods carried-out by such wireless communications systems. In one embodiment, the wireless communications system includes a Satellite Signal Transformation (SST) unit and a plurality of aerial network drones, which can be deployed over a designated geographical area to form a multi-drone network thereover. During operation, the SST unit transmits a network source signal, which contains content extracted from a satellite signal. The multi-drone network receives the network source signal, disseminates drone relay signals containing the content through the multi-drone network, and broadcastings user device signals containing the content over the designated geographical area.

Abstract: Methods and systems disclosed herein relate to determining a projected change in bandwidth demand in a specified area during a specified future time period, repositioning one or more balloons in a high-altitude balloon network based on the projected change in bandwidth demand, and providing, using the one or more balloons, at least a portion of the bandwidth demanded in the specified area during the specified future time period.

Abstract: A navigation satellite signal reception apparatus includes a satellite antenna; a satellite orbital information collection unit that collects orbital information of a navigation satellite; a peripheral environment spatial information collection unit that collects spatial information for a peripheral environment of an installation position of the satellite antenna; a positional information collection unit that collects positional information for the installation position of the satellite antenna; and a signal correction unit that performs a determination process to determine whether a navigation satellite associated with the received satellite signal is in a directly viewable state or in a non-directly-viewable state from the installation position of the satellite antenna, and that performs a correction process on a satellite signal from a navigation satellite in an NLOS state, on the assumption that the satellite signal is a reflected wave.

Abstract: Disclosed herein are embodiments of a balloon-based positioning system and method. In one example embodiment, a system includes a group of at least three balloons deployed in the stratosphere and a control system configured for: determining a first set of spatial relationships relating to the group; determining a second set of spatial relationships relating to at least a portion of the group and to a reference point; determining a position of the reference point relative to the earth; using the determined first set, the determined second set, and the determined position of the reference point relative to the earth as a basis for determining a position of a target balloon in the group relative to the earth; and transmitting the determined position of the target balloon relative to the earth.

Abstract: A CubeSat side panel with an additional storage compartment includes a satellite endcap, a hinge assembly, and at least one CubeSat component. A plurality of lateral lips and a top extremity of the satellite endcap delineate a storage compartment within the satellite endcap. The storage compartment allows the Cubesat component to be mounted upon an inner surface of the satellite endcap. The hinge assembly connects the satellite endcap to a frame of the CubeSat thus allowing the CubeSat side panel to open upward and away from the CubeSat. Resultantly, the hinge assembly provides easy access to the Cubesat component of the satellite endcap and other existing components that are positioned within the frame of the CubeSat.

Abstract: A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

Abstract: A signal processing device includes a Kalman filter that extracts a DC component of an input signal by performing Kalman filter processing on the basis of observation noise and system noise which are estimated from the input signal.

Abstract: The invention relates to the determination of the rotational position of a sensor by means of a laser beam emitted by a satellite. For this purpose, the sensor includes a rotational position determination device which has a laser beam detection device for detecting the laser beam emitted by the satellite. Moreover, the rotational position determination device includes a control device which is designed for determining the rotational position of the rotational position determination device based on the detected laser beam.

Abstract: An apparatus on a satellite includes a standard fixed-path Michelson interferometer. The Michelson interferometer includes an input, at least one first output detector, and at least one second output detector. The Michelson interferometer includes a plurality of respective fields of view and a corresponding plurality of scanning azimuthal angles relative to a satellite velocity vector. The plurality of respective fields of view corresponds to a plurality of tangent points with constant tangent point height arranged around an Earth horizon circle. The apparatus includes an attitude determination and control system on the satellite, or an actuator on the satellite. The apparatus includes an input mirror and/or input optics in optical communication with the input of the Michelson interferometer.

Abstract: Provided is an apparatus for controlling an orbiting satellite by sensing a change in a yaw angle of the orbiting satellite and calculating a ground sample distance (GSD) based on the yaw angle. The apparatus may include a sensor configured to sense a yaw angle corresponding to yaw steering of the orbiting satellite, and a processor configured to calculate, based on the yaw angle, a GSD corresponding to a length of a pixel projected onto a planetary surface scanned by the orbiting satellite.

Abstract: A method includes receiving, at a flight management system of an aircraft, a required time of arrival (RTA) of the aircraft at a first location. The method includes receiving, at the flight management system, an input indicating an RTA index value. The method further includes modifying a speed of the aircraft based on the RTA and the RTA index value. The speed is determined by the flight management system as part of a flight plan of the aircraft.

Abstract: Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a propulsion subsystem with electric thrusters that are installed with two-axis gimbal assemblies. The spacecraft also includes a controller that identifies a target spin axis for the spacecraft, determines an actual spin axis for the spacecraft during the transfer orbit, determines gimbal angles for the electric thruster(s) that adjust the actual spin axis toward the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles.

Abstract: A tactile vibration control system and method for a smart terminal. The system includes: a command generator, a tactile driver, a linear resonant actuator, a sensing module, a feedback unit and a comparator; by arranging a plurality of sensors that monitor or sense the vibrating status of the linear resonant actuator, channels of the sensor signals are generated when the actuator vibrates; the feedback unit sends the sensing signals characterizing the physical quantities related to the vibration modes output by the plurality of sensors to the comparator as the feedback signal; and the comparator generates an error signal according to the feedback signal and a desired signal in the input signal and sends the error signal to the command generator so that the command generator adjusts the generated initial commanding signal according to the error signal and achieves the close-loop control of the linear resonant actuator.

Abstract: A system and methods for calculating an attitude and a position of an object in space are disclosed. Measurements in relation to an object, stars, and a signal timing are received at a combined orbit and attitude determination system to provide received measurements. An estimated separation angle error, an estimated position error, and an estimated attitude error are estimated based upon the received measurements to provide estimated errors.

Abstract: Systems and methods are described herein for mounting a thruster onto a vehicle. A thruster mounting structure may comprise a first, second, and third rotational joint, a boom, and thruster pallet, and a thruster attached to the thruster pallet. The first rotational joint may be attached to the vehicle and configured to rotate in a first axis. The first rotational joint may be connected to the boom and configured to pivot the boom about the first axis. The boom may be connected to the second rotational joint, which is connected to the third rotational joint and configured to rotate the third rotational joint in the first axis. The third rotational joint may be connected to the thruster pallet and configured to pivot the thruster pallet in a second axis that is perpendicular to the first axis.

Abstract: The present disclosure provides a computer implemented method of providing an indicator useful for piloting an aircraft. The aircraft comprises an antenna configured to communicate with a transceiver. The method comprises: obtaining an antenna envelope characterizing directions relative to the aircraft for which a directive gain of the antenna exceeds a predetermined threshold; determining a direction of the transceiver relative to the aircraft; calculating a maneuvering range of the aircraft by comparing the antenna envelope and the transceiver direction, wherein the maneuvering range is indicative of eligible orientations of the aircraft for maintaining the transceiver within the antenna envelope; and outputting data indicative of the maneuvering range.