Richmond Hill, Canada

MacDonald, Dettwiler and Associates

www.mdacorporation.com
Richmond Hill, Canada

MacDonald, Dettwiler and Associates Ltd. is a Richmond, British Columbia global communications and information company. MDA has locations throughout Canada, and the United States operating under the MDA brand name.MDA's most visible products may be the Canadarm, Canadarm2 and Dextre remote manipulator systems used on NASA's Space Shuttle and International Space Station programs.MDA provides operational solutions to commercial and government organizations worldwide, including: Airborne Surveillance Solutions Satellite Ground station Maritime Information Systems Aviation Information Systems Geospatial information services, including Satellite Data Distribution, Value-Added Information Services and Intelligence Information Services Communications satellites Communications satellite payloads Communications satellite subsystems and related ground systems Commercial satellite hosted payload services Robotic surgery research via its NeuroArm development program Space robotics, satellite information and payload systems Radar and optical satellite imagery, and, remote sensingMDA is a member of the British Columbia Technology Industry Association. Wikipedia.

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Patent
MacDonald, Dettwiler and Associates | Date: 2017-03-29

There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset centre of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to centre of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non- parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset centre-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.


Patent
MacDonald, Dettwiler and Associates | Date: 2017-01-27

A TEM-line network architecture for RF components used in antenna system, includes an electrically conductive main body forming an outer conductor defining a signal channel, and an electrically conductive center conductor electrically grounded to the main body at predetermined locations. The center conductor is electromagnetically isolated from the outer conductor at RF frequencies while being connected and supported within the signal channel only at at least one of the predetermined locations. The outer conductor is preferably formed of three layers with the center conductor being integral with one of the layers.


Patent
MacDonald, Dettwiler and Associates | Date: 2017-08-23

A TEM-line network architecture (10) for RF components used in antenna system, includes an electrically conductive main body (12) forming an outer conductor (14) defining a signal channel, and an electrically conductive center conductor (16) electrically grounded to the main body (12) at predetermined locations (34). The center conductor (16) is electromagnetically isolated from the outer conductor (14) at RF frequencies while being connected and supported within the signal channel only at at least one of the predetermined locations (34). The outer conductor (14) is preferably formed of three layers (20,22,24) with the center conductor (16) being integral with one of the layers (24).


Patent
MacDonald, Dettwiler and Associates | Date: 2017-03-08

The present invention provides a capture mechanism for capturing and locking onto the Marman flange located on the exterior surfaces of spacecraft/satellites. The capture mechanism achieves its goal of quickly capturing a client spacecraft by splitting the two basic actions involved into two separate mechanisms. One mechanism performs the quick grasp of the target while the other mechanism rigidises that grasp to ensure that the target is held as firmly as desired.


Patent
MacDonald, Dettwiler and Associates | Date: 2017-10-11

A reflector deployment and pointing mechanism (10), for deploying and pointing a reflector (12) of an antenna movably mounted on a structure (14), has a first actuator (20) mounted on the structure (14), a second actuator (30) mounted on the first actuator (20), and a third actuator (40) mounted on the second actuator (30) and connected to the reflector (12). The first (20) or second actuator (30) is the deployment actuator, and, respectively, the second (30) or first (20), and the third (40) actuators are the pointing actuators and have their axis of rotation (36 or 26, 46) generally intersecting a feed oriented point (13) of a signal reflecting surface (16) of the reflector (12).


Patent
MacDonald, Dettwiler and Associates | Date: 2015-05-19

There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset centre of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to centre of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset centre-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.


Patent
MacDonald, Dettwiler and Associates | Date: 2016-07-25

The present invention provides a capture mechanism for capturing and locking onto the Marman flange located on the exterior surfaces of spacecraft/satellites. The capture mechanism achieves its goal of quickly capturing a target spacecraft by splitting the two basic actions involved into two separate mechanisms. One mechanism performs the quick grasp of the target while the other mechanism rigidises that grasp to ensure that the target is held as firmly as desired. To achieve a speedy grasp, the grasping action is powered by springs and an over-centre mechanism triggered either mechanically by a plunger or electronically by sensors and a solenoid. This forces two sets of jaws, one on either side of the object to be grasped, to close quickly over the target object. The jaws can be set up to grasp gently, firmly, or even not close completely on the target. The key is that they must close tightly enough so that the protrusions on the target cannot escape from the jaws due to any possible motions of the target. Once the jaws have sprung shut, a second mechanism draws the jaws (and their closing mechanism) back into the body of the tool pulling the captured target onto two rigidisation surfaces. The mechanism keeps pulling backwards until a pre-established preload is reached at which point the target is considered suitably rigidised to the capture mechanism.


Patent
MacDonald, Dettwiler and Associates | Date: 2015-08-14

Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.


Patent
MacDonald, Dettwiler and Associates | Date: 2015-08-14

Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.


Patent
MacDonald, Dettwiler and Associates | Date: 2016-03-16

A steerable antenna configuration (10) having all actuators (28, 30) and the feed source (16) mounted on a stationary side of the antenna thereby eliminating the need of having to supply power and/or communication signal through a rotation mechanism. A first actuator (28) rotates a reflector assembly (22) about a first axis (24), and a second actuator (30) rotates at least a main reflector (32) of the reflector assembly (22) about a second axis (26) perpendicular to the first axis (24). The second axis (26) is rotatable about the first axis (24) via the first actuator (28).

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