Abstract: A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

Abstract: An air-to-air coupling 13 (e.g. for receiving a probe in probe-and-drogue refuelling) comprises retaining members 19, 27 for interacting with a further member (e.g. a refuelling probe) to hold the further member in place. An active drive system 39, 21 may drive the holding members and may thereby also actively drive the further member into place. Alternatively the active drive 39, 21 may drive another member such as a locking member 31 to hold the retaining members 19, 27 in position once the further member is in place. The active drive releases the retaining members 19, 27 or moves them out of position to allow the further member to be removed. This allows the further member to be inserted and removed with a lower force than is used to hold it in place. The coupling may also be used for in-air recovery of an unmanned aircraft.

Abstract: A landing gear system uplock arrangement (300, 500) including: a hook (310) defining a gap (314), wherein the hook is movable between a first position, at which the hook is for retaining a movable element (299, 499) of a landing gear system in the gap, and a second position, at which the hook is for permitting movement of the element into and out from the gap; a lock (320) that is changeable between a locked state, in which the lock prevents movement of the hook from the first position to the second position, and an unlocked state, in which the lock permits movement of the hook from the first position to the second position; and a sensor arrangement (330) for sensing whether the element is present in the gap.

Abstract: In order to improve linear drives on aircraft with regards to backlash, gear reduction, self-lock capability, load transfer and wear, a linear drive device is provided that has a first member with engaging teeth, such as a tooth rack and a second member which functions as a drive unit. The second member includes a plurality of movable teeth that are actuated by a cam shaft. The cam shaft has a control cam portion that is shaped such that the movable teeth perform a wave-like motion that forces the first member along its longitudinal direction relative to the second member.

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall.

Abstract: A recovery parachute assembly may comprise a container comprising an open base end, a parachute packed within the container, a plurality of riser lines and suspension lines packed within the container and proximate the open base end, a tray including a lip configured to receive the open base end of the parachute container, and a first standoff block coupled to the tray, wherein the first standoff block compresses at least one of the riser lines or suspension lines into the base end of the container and away from the tray, wherein the first standoff block defines a channel between the lip of the tray and the first standoff block, wherein the channel includes a plurality of drain holes formed along a distal edge of the tray.

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

Abstract: Methods and apparatus to recover rotorcraft are disclosed. A disclosed example apparatus includes a rotor of a vehicle, a rotatable hub to support the rotor, and a rotor hook disposed on the rotor. The rotor hook has a groove to receive a recovery line. The rotor is to contact the recovery line when the vehicle is flown toward the recovery line.

Abstract: An aeronautical car includes a ground-travel system including a drivetrain; an air-travel system including a detachable portion configured to house a propulsion device configured to provide thrust and to be driven by the drivetrain when the detachable portion is connected to the aeronautical car, and at least one flight mechanism configured to provide lift once the aeronautical car is in motion; and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.

Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: The present disclosure describes various systems, devices, and methods configured to retrieve a fixed-wing aircraft from free flight using a flexible capture member and a monopole assembly.

Abstract: A system for positioning at least one satellite in working orbit, characterized in that the system for positioning satellites in working orbit comprises: a first attachment device configured to attach a first satellite to the system for positioning satellites in working orbit; a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges; a secondary propulsion device which is re-ignitable; at least one position sensor configured to measure the position of said system; a monitoring unit connected to said at least one position sensor and which is configured to control a firing of the cartridges of the main propulsion device to move said system from a transfer orbit to a working orbit of the first satellite, said monitoring unit being further configured to control an opening of the first attachment device to separate said system from the first satellite.

Abstract: A pitch change link may include a shaft having a first end region and a second end region, and a bearing cartridge on at least one of the first end region and the second end region. The bearing cartridge may include a bearing and a bearing ring at least partially surrounding the bearing. The bearing ring may have a geometric symmetry and a cross section that is wider at a first end than at a second end, the first end may oppose the second end.

Abstract: The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.

Abstract: A structural member for an aircraft or spacecraft has at least one fiber plastic composite, the fiber plastic composite having at least one or a plurality of plies. The structural member also has at least one pre-stressing means providing internal stresses to the fiber plastic composite. The fiber plastic composite and the pre-stressing means are configured and arranged to form a balanced system the internal stresses of which are essentially balanced to zero in a cured state of the said system. The balanced system of the structural member is able to counteract loading stresses exerted to the airframe in service such, that a damage caused by the loading stress is easily detectable visually.

Abstract: A system for controlling an aircraft in response to deployment of an ejection seat may comprise a seat controller located on the ejection seat and configured to output a signal in response to initiation of an ejection sequence. An aircraft controller may be configured to receive the signal from the seat controller. A tangible, non-transitory memory may be configured to communicate with the aircraft controller. The tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the aircraft controller, cause the aircraft controller to perform operations, which may comprise receiving the signal from the seat controller, receiving data signals from an operational data source, and sending command signals configured to control a component of the aircraft.

Abstract: A multicopter system according to one aspect of the present invention includes a multicopter configured to fly in a state of holding a package and a mooring device that is installed at a target position of a flight of the multicopter and includes a linear member that extends in a predetermined direction from the target position, the multicopter including a reception portion that has the shape of a recess including an opening open toward one direction and is configured to receive the linear member via the opening.

Abstract: An article of manufacture, a force reduction release mechanism and system for selectively maintaining and releasing components under tensile tension, the release mechanism offering mechanical gain such that the force required to activate a release between the components is a mere fraction of the heavy tensile tension force. Other aspects of the invention include novel cargo parachute system utilizing the release mechanism and a parachute stabilization arrangement utilizing at least one releasable stabilization anchor.

Abstract: In an aspect, in general, a spooling apparatus includes a filament feeding mechanism for deploying and retracting filament from the spooling apparatus to an aerial vehicle, an exit geometry sensor for sensing an exit geometry of the filament from the spooling apparatus, and a controller for controlling the feeding mechanism to feed and retract the filament based on the exit geometry.