Class / Patent application number | Description | Number of patent applications / Date published |
244173100 | With payload accommodation | 42 |
20080258013 | High altitude payload structures and related methods - A system and method is described generally for providing a high altitude structure including an elongated structure coupled to the ground and extending skyward. The elongated structure at least partially supported by buoyancy effects, the elongated structure including at least one lumen, the at least one lumen configured to transport at least one material and to vent the at least one material to the atmosphere. The system and method also include a gas having a density that is less dense than that of the atmosphere outside of the elongated structure; the gas is disposed in one or more voids of the elongated structure. The system and method includes the use of an introducer configured to provide the gas into the one or more voids. The system and method further include a payload coupled to the elongated structure and being held aloft by the elongated structure. | 10-23-2008 |
20090250556 | LIVING INTERPLANETARY FLIGHT EXPERIMENT CAPSULE - A light-weight capsule having internal components comprised of sample containers with living organisms in solid and liquid form, inner carrier, multiple seals is disclosed to protect the samples contained within and to withstand an impact of up to 4000 G in outer space or Earth applications being subject to extreme conditions of varying radiation, temperature, pressure, and shock. The present capsule provides a compact and durable design with features for reducing size, mass and weight while increasing strength, structural integrity, and sealing strength to protect the samples contained interiorly and to withstand extreme conditions for travel in deep space or inhospitable places on Earth. | 10-08-2009 |
20100327119 | Satellite communication system, infrastructure and method of providing same - A satellite communication system, infrastructure, and method of providing same, involves inventorying certain types of pre-selected communication satellite payload modules and communication satellite bus modules based on analysis of anticipated communication satellite needs and providing each payload and bus module with a pre-configured standard interface coupling. When communication satellite parameters for a customer are received, a selection is made of one or more of the inventoried payload modules and also of the inventoried communication satellite bus module that is sized and configured to accommodate the selected payload module or modules. The selected payload module or modules are coupled to the selected bus module via the standard interface coupling, and the selected bus module is, in turn, coupled to a launch vehicle. | 12-30-2010 |
20120112010 | PAYLOAD LAUNCH LOCK MECHANISM - A payload launch lock mechanism includes a base, a preload clamp, a fastener, and a shape memory alloy (SMA) actuator. The preload clamp is configured to releasibly restrain a payload. The fastener extends, along an axis, through the preload clamp and into the base, and supplies a force to the preload clamp sufficient to restrain the payload. The SMA actuator is disposed between the base and the clamp. The SMA actuator is adapted to receive electrical current and is configured, upon receipt of the electrical current, to supply a force that causes the fastener to elongate without fracturing. The preload clamp, in response to the fastener elongation, either rotates or pivots to thereby release the payload. | 05-10-2012 |
20130221162 | PAYLOAD ADAPTERS INCLUDING ANTENNA ASSEMBLIES, SATELLITE ASSEMBLIES AND RELATED SYSTEMS AND METHODS - Payload adapters for launch vehicles include a ring structure having an opening formed therein and at least a portion of an antenna assembly coupled to a circular sidewall of the ring structure at least partially within the opening of the ring structure. Satellite assemblies may include a payload adapter comprising a ring structure having a circular opening formed therein and an antenna assembly including a parabolic reflective dish formed within the circular opening. Launch stack systems may include a primary payload and a secondary payload adapter including an antenna dish integrally formed with a ring structure of the secondary payload adapter. Methods of forming a satellite assembly include positioning at least a portion of the antenna assembly within an opening formed in a ring-shaped payload adapter for a launch vehicle and coupling the at least a portion of the antenna assembly to the ring-shaped payload adapter. | 08-29-2013 |
20130221163 | LAUNCH LOCK ASSEMBLIES INCLUDING AXIAL GAP AMPLIFICATION DEVICES AND SPACECRAFT ISOLATION SYSTEMS INCLUDING THE SAME - Embodiments of a launch lock assembly are provided, as are embodiments of a spacecraft isolation system including one or more launch lock assemblies. In one embodiment, the launch lock assembly includes first and second mount pieces, a releasable clamp device, and an axial gap amplification device. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement; and, when actuated, releases the first and second mount pieces from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device normally residing in a blocking position wherein the gap amplification device obstructs relative axial motion between the first and second mount pieces. The axial gap amplification device moves into a non-blocking position when the first and second mount pieces are released from clamped engagement to increase the range of axial motion between the first and second mount pieces. | 08-29-2013 |
20150097085 | PRINTED SPACECRAFT SEPARATION SYSTEM - 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. | 04-09-2015 |
20150136914 | LOAD BEARING INTERFACE RING FOR SPACECRAFT - The invention relates to a load bearing interface ring ( | 05-21-2015 |
20150367965 | SPACE VEHICLE WITH CUSTOMIZABLE PAYLOAD AND DOCKING STATION - A “black box” space vehicle solution may allow a payload developer to define the mission space and provide mission hardware within a predetermined volume and with predetermined connectivity. Components such as the power module, radios and boards, attitude determination and control system (ADCS), command and data handling (C&DH), etc. may all be provided as part of a “stock” (i.e., core) space vehicle. The payload provided by the payload developer may be plugged into the space vehicle payload section, tested, and launched without custom development of core space vehicle components by the payload developer. A docking station may facilitate convenient development and testing of the space vehicle while reducing handling thereof. | 12-24-2015 |
20160102689 | Marman Clamp With A Shape Memory Alloy Actuator - A Marman clamp is disclosed. The Marman clamp includes a release mechanism with either pins or tubes formed with a shape memory alloy. The release mechanism opens and closes the clamp depending on the temperature of the pins or tubes. The temperature of the pins or tubes may be based on whether a space vehicle including the clamp is in a direct line of sight of radiation from the sun. Alternatively, a heat source may control the temperature of the pins or tubes. The Marman clamp may also open and close as a result of an independent force applied to the release mechanism. | 04-14-2016 |
20160251093 | TRUSS STRUCTURE | 09-01-2016 |
244173200 | Including vibration control | 7 |
20090008504 | Elastomer-Based Modular Multi-Axis Vibration/Shock Isolation Device - The device comprises at least three isolating modules each having two rigid pieces, one of which is fastened to the carrier structure and the other of which is fastened to the support for the vibrating equipment, these pieces being linked by at least one isolating stud made of an elastomer, which attenuates the transmission of low-amplitude vibrations from the equipment to the structure, the deformation of at least one stud in tension-compression and in shear being limited by three flexible stops each mounted on only one of the pieces and the free end of which is facing the other of said pieces and not in contact with it, at rest. Each stop comprises an elastomer element coming into contact with the facing other piece during deformations of sufficient amplitude of the isolating stud, the stiffness of the elastomer of the stop being greater than that of the stud. Application to the isolation of vibrating equipment on a satellite carrier structure. | 01-08-2009 |
20120061520 | LOW SHOCK FRANGIBLE JOINT - A frangible joint structure includes shock attenuation features formed as an integral part of the joint structure. Shock attenuation is achieved through use of, for example, slots or grooves that are machined directly, or otherwise formed integrally, into the frangible joint structure. Adequate shock attenuation is achieved solely by the features machined or otherwise formed in the frangible joint together with the typical assembly of the frangible joint into various structures (e.g., as a payload separator for rockets, missiles, satellites, etc.), without the need for additional hardware components and thus without the need for assembly of the frangible joint shock attenuation device. | 03-15-2012 |
20130284857 | ADAPTOR AND PAYLOAD LAUNCH VEHICLE - An object is to provide an adaptor that can attenuate a vibration acting on a payload using a simple structure, and a payload launch vehicle. The adaptor ( | 10-31-2013 |
20140084113 | LAUNCH LOCK ASSEMBLIES WITH REDUCED PRELOAD AND SPACECRAFT ISOLATION SYSTEMS INCLUDING THE SAME - Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece. | 03-27-2014 |
20140291452 | ISOLATORS HAVING DAMPER-EXTERNAL THERMAL COMPENSATORS AND SPACECRAFT ISOLATION SYSTEMS EMPLOYING THE SAME - Embodiments of an isolator are provided, as are embodiments of a spacecraft isolation system employing a number of three parameter isolators. In one embodiment, the isolator includes an externally-pressurized damper assembly and a thermal compensator, which is located external to the externally-pressurized damper assembly. The damper assembly includes, in turn, a damper assembly housing and a first hydraulic chamber configured to be filled with a damping fluid. The first hydraulic chamber is located within the damper assembly housing and is fluidly coupled to the thermal compensator. A first bellows is disposed within the damper assembly housing and bounds an inner circumference of the first hydraulic chamber such that the first bellows is externally pressurized when the first hydraulic chamber is filled with the damping fluid. | 10-02-2014 |
20140332632 | ISOLATION OF PAYLOAD FROM LAUNCH VEHICLE DYNAMIC LOADS - An adapter arrangement includes a first adapter ring for interfacing with a launch vehicle payload interface ring, a second adapter ring for interfacing with a payload launch vehicle interface ring, and a plurality of vibration isolation devices disposed between and attached to each of the first adapter ring and the second adapter ring. The first adapter ring has a first standard interface with the launch vehicle payload interface ring and the second adapter ring has a second standard interface with the payload launch vehicle interface ring. | 11-13-2014 |
20160047433 | MAGNETICALLY DAMPED ISOLATOR AND POINTING MOUNT - A magnetically damped mounting and isolation system with pointing capability. A payload is mounted to an isolator plate, a base plate is mounted to a satellite or other space vehicle, and the isolation system provides damping of all six degrees of freedom of isolator plate motion relative to the base plate. Three bidirectional magnetic dampers are connected between the isolator plate and the base plate and arranged to provide the required amount of temperature-independent damping. The bidirectional magnetic dampers can be connected to the base plate and the isolator plate in different configurations based on desired mass and natural frequency characteristics. Flexures which statically position the isolator plate are also designed to optimize normal modes of vibration. The isolation system may include a motion amplification feature to increase magnetic damping effectiveness, and the isolation system may also include active positioning of the payload relative to the satellite. | 02-18-2016 |
244173300 | And payload deployment | 24 |
20080290222 | SPACECRAFT LOW TUMBLE LINEAR RELEASE SYSTEM - Systems and methods for releasing a spacecraft payload at a substantially constant velocity are disclosed. A linear actuator is used that includes a spring loaded and fluid filled chamber. The spring drives against a piston within the chamber that includes a control orifice that restricts the fluid flowing from one side of the piston to the other and results in a substantially constant damped motion of the piston. The piston drives a rod from the chamber that is attached to a capture device that holds a flange of the spacecraft payload. The capture device moves along a linear guide toward an open end. Spring loaded latches are held in a closed position by the side walls of the guide as the capture device moves. The latches release the flange as exit the open end of the guide. | 11-27-2008 |
20090108138 | Space object deployment system and method - Provided is a space object deployment system. Specifically, the system in at least one embodiment, includes at least one deployable object. A deployment chamber is paired with each deployable object, each chamber including: a base opposite from the deployable object; and a spring loaded countermass coupled to the base and slidably disposed within the chamber, the deployment chamber at least partially disposed within a rotatable body transverse to the axis of rotation. At least one coupler is paired to each deployable object and adapted to detachably couple the deployable object to the body and constrain the countermass within the chamber. An associated method of use is provided as well. | 04-30-2009 |
20090108139 | Catalyzed decomposing structural payload foam - A high energy, e.g., ultraviolet (UV), catalyzed decomposing foam encapsulating a payload to be boosted in space provides an ultra-light weight, adaptable means to facilitate survival of much lighter, smaller satellites and space hardware under boost environment. The decomposable foam is to contain multiple satellites within a booster payload in lieu of the traditionally heavy and complex structural framework. The catalyzed decomposing foam significantly lowers the weight and structure of all space hardware. This packaging system is especially beneficial where several or even hundreds of satellites are required for a constellation system, thereby significantly benefiting all technologies applied in space, ranging from the telecommunication industry to DOD applications. In addition to weight and cost savings, advantages of this foam are many in that it is adaptable to any payload shape as it may be injected, sprayed, formed, molded, easily cut or manufactured to support any geometry required. | 04-30-2009 |
20110089293 | SPACE OBJECT DEPLOYMENT SYSTEM AND METHOD - Provided is a space object deployment system. Specifically, the system in at least one embodiment, includes at least one deployable object. A deployment chamber is paired with each deployable object, each chamber including: a base opposite from the deployable object; and a spring loaded countermass coupled to the base and slidably disposed within the chamber, the deployment chamber at least partially disposed within a rotatable body transverse to the axis of rotation. At least one coupler is paired to each deployable object and adapted to detachably couple the deployable object to the body and constrain the countermass within the chamber. An associated method of use is provided as well. | 04-21-2011 |
20110198447 | Actuation system for mobile elements with dynamically compensated and opposite relative motions - An actuation system for at least two mobile elements with dynamically compensated and opposite relative motions, without disturbance of the elements fixed in the same rigid structure as it, and resistant to exterior loadings, in the case of a translational motion of the mobile elements, includes, in a rigid structure, at least one linear actuator linked to a motion transmission device with four rigid arms, articulated at their ends and forming a lozenge, of which each of two first opposite vertices is linked to a corresponding mobile element, and whose other two opposite vertices have a single translational degree of freedom. | 08-18-2011 |
20110240802 | DEVICE FOR TRANSPORTING AND EJECTING SMALL SPACE PAYLOADS - A device for transporting and ejecting small space payloads, in particular picosatellites, including a tubular body provided with a device for attachment onto a launch vehicle, the body including at least two longitudinal guide rails which can receive a satellite fixedly arranged inside the body in a storage position during transport and which can be moved along the guide rails towards a front end of the body during ejection, an ejection mechanism including a device for translatably moving a satellite in a longitudinal fashion, a drive device connected to the movement device and suitable for engaging with a satellite, and a device for controlling the ejection mechanism. According to the invention, the movement device includes a transport device including at least one cable extending in a closed loop inside the body, the closed loop passing around said guide rails and including passage areas extending in parallel on either side of the guide rails so that when the cable is moved by the control unit, the drive device can move a satellite on the rails towards the front end of the body. | 10-06-2011 |
20120104177 | SHOCKLESS SEPARATION DEVICE FOR SPACE APPLICATION - Provided is a shockless separation device for a space application configured to fix a deployment part to a satellite while launching the satellite, and shocklessly separate the deployment part from the satellite when the satellite enters its orbit in space. The shockless separation device includes a fastening projection, a fastening recess part and a heating part. The fastening projection part is provided in the deployment part. The fastening recess part is provided in the satellite, and formed of a shape-memory alloy such that the fastening projection part is inserted into the fastening recess part to be fixed before heating, and when the fastening recess part is heated to a transformation temperature or more, the inside of the fastening recess part is recovered to be expanded to separate the fastening projection. The heating part is controlled to heat the fastening recess part when the satellite enters its orbit in space. | 05-03-2012 |
20120228436 | SPACECRAFT PAYLOAD POSITIONING WITH RESPECT TO A VIRTUAL PIVOT POINT - A spacecraft payload element is rotated by a mechanism about virtual pivot point (VPP) substantially distant from the mechanism. The mechanism couples the payload element to a spacecraft main body structure, and has a four-bar linkage configured to rotate the payload element about a virtual pivot point (VPP). The VPP may be proximate to the focus or center of gravity (cg) of the payload element. Rotation of the payload element about the VPP may be controlled by linear or rotary actuators which drive the four-bar linkage. The four-bar linkage may be configured to provide a mechanical advantage to the actuator. | 09-13-2012 |
20120261515 | Platform and launch initiation system for secondary spacecraft for launch vehicle - A platform and launch initiation control system for secondary spacecraft for a launch vehicle includes an aluminum honeycomb core sandwiched between top and bottom structural aluminum skins and strengthened by a spider-like stiffener. Spool inserts for engaging the secondary spacecraft are arranged on the platform. A computer processor based auxiliary payload support unit (APSU) is provided on the platform and receives power and enable signals through a single cable from the LV to permit the APSU to control the release of the secondary spacecraft transparently to the LV without impacting LV operations. | 10-18-2012 |
20130009012 | COUPLING AND SEPARATING DEVICE, COUPLING AND SEPARATING SYSTEM, AND COUPLING AND SEPARATING METHOD - A coupling and separating device is provided which can reduce a separation impact when separating a launch vehicle and a structure. The coupling and separating device is provided with a clamp band | 01-10-2013 |
20130240675 | Technique for De-Orbiting Small Debris from the Near-Earth Space Environment - 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. | 09-19-2013 |
20130327895 | SYSTEMS FOR INTERCONNECTING DUAL MANIFESTED SPACECRAFT - Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft. | 12-12-2013 |
20140027578 | METHOD AND DEVICE FOR THE SUCCESSIVE LAUNCHING OF TWO SATELLITES - According to the invention, a link is established between the fixed part ( | 01-30-2014 |
20140131521 | Adaptor System for Deploying Small Satellites - An adaptor system includes a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly, a bend/shear restrain assembly that is non-coaxial with the actuator-release connector, and a biasing element. The actuator-release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The actuator-release actuator-release mechanism assembly may pass through the launch vehicle adaptor plate to engage the space vehicle separation plate to hold the space vehicle separation plate substantially parallel to the launch vehicle adaptor plate prior to release of the space vehicle separation plate. | 05-15-2014 |
20140131522 | PLATFORM AND LAUNCH INITIATION SYSTEM FOR SECONDARY SPACECRAFT FOR LAUNCH VEHICLE - A platform and launch initiation control system for secondary spacecraft for a launch vehicle includes an aluminum honeycomb core sandwiched between top and bottom structural aluminum skins and strengthened by a spider-like stiffener. Spool inserts for engaging the secondary spacecraft are arranged on the platform. A computer processor based auxiliary payload support unit (APSU) is provided on the platform and receives power and enable signals through a single cable from the LV to permit the APSU to control the release of the secondary spacecraft transparently to the LV without impacting LV operations. | 05-15-2014 |
20140319283 | CANISTERIZED SATELLITE DISPENSER - A canisterized satellite dispenser includes one or more of: a pair of guide rails that eliminate the requirement of a rectangular profile for the satellite; a preload system that secures the canisterized satellite during transport and launch, and releases to deploy the canisterized satellite; a constant-force spring to provide a uniform and predictable dispensing force; an external rectangular profile in each dimension; and internal support surfaces that simplify the design of canisterized satellites, particularly those with deployable components. Each canisterized satellite includes a pair of opposing flanges on a lower portion of the satellite that ride in a channel formed by the dispenser's guide rails and restraining flanges; no other support constraints are imposed. During travel and launch, the satellite flanges are held against the restraining flanges, rigidly fixing the satellite to the dispenser until the satellite is deployed. | 10-30-2014 |
20140319284 | SYSTEMS FOR INTERCONNECTING DUAL MANIFESTED SPACECRAFT - Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft. | 10-30-2014 |
20150102174 | SIDE-BY-SIDE MULTIPLE LAUNCH CONFIGURATION - A launch vehicle payload that includes at least two spacecraft is disclosed. The launch vehicle includes a single payload adapter. Each spacecraft has a launch vehicle adapter structure providing a respectively coplanar structural interface directly with the single launch vehicle payload adapter. The spacecraft share a launch vehicle payload fairing volume substantially side-by-side and are detachably coupled together such that a positive clearance is provided between adjacent, non-abutting structural body surfaces of each spacecraft. | 04-16-2015 |
20150329224 | PAYLOAD EJECTION SYSTEM - 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. | 11-19-2015 |
20150353211 | PNEUMATIC CUBESAT PAYLOAD DEPLOYMENT SYSTEM UTILIZING LAUNCH VEHICLE TANK PRESSURE - A rail-captive sled for deploying payloads into outer space from a space launch vehicle. The sled is driven by a piston, powered by residual tank pressure from a tank native to the space launch vehicle. The rails are arranged parallel and adapted to a cross-sectional shape of a payload, such as small satellites or cubesats. The sled is a box frame sled with an adaptation to receive the piston. The rails may be attached to the residual pressure tank, with the piston in the residual pressure tank and aligned to the rails, or the pressure may be drawn from tank plumbing to a cylinder specific to the piston. The rails have a releasable closure to avoid unplanned egress of the payload, and the closure locks in the open position once released. The piston may be constrained by a direct constraint or by the closure via the payload. | 12-10-2015 |
20160031572 | DOOR MECHANISM FOR SATELLITE DEPLOYER SYSTEM - Disclosed herein is an improved door system for a satellite deployer for storing, transporting, and deploying space payloads, as well as the method of its use. The satellite deployer's door system as described herein allows for increased efficiency due to the configuration of the mechanical structures used in the satellite deployment process. | 02-04-2016 |
20160046397 | MULTIPLE SPACE VEHICLE LAUNCH SYSTEM - A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle. | 02-18-2016 |
20160075452 | Space Structure Deployment System - A method and apparatus for deploying a space structure. The space structure is secured to a base with release mechanisms that engage features of the space structure when the base is in a first position. The base is moved from the first position to a second position to deploy the space structure. The release mechanisms are moved at substantially a same time to disengage from the features and release the space structure from the base without imparting a transverse load to the space structure when the base moves from the first position towards the second position to deploy the space structure. | 03-17-2016 |
20160107771 | NANOSAT Electrothermal Deployment System - An electrothermal deployment system may be configured for controlled release of various apparatus from their prelaunch stowage positions in small satellites. The deployment system includes a fusible line secured to a structural component of the satellite, as well as to various deployable apparatus secured to, within, or on the satellite. The deployable apparatus may include items such as solar panels and antennas. The deployment system includes an electrically resistive element such as a burn bar formed of a cylinder or tube, including a resistor pad overlying and/or incorporated within an exterior surface of the burn bar. The burn bar may be coupled to an electrical circuit configured to heat the resistor for the purpose of melting the fusible line secured in direct contact therewith, thus causing the fusible line to break to cause deployment. The fusible line is configured to remain in secure contact with the resistor until apparatus deployment. | 04-21-2016 |