公开(公告)号：WO2023027892A1

公开(公告)日：2023-03-02

申请号：PCT/US2022/039924

申请日：2022-08-10

申请人： MAXAR SPACE LLC

发明人： BAGHDASARIAN, Varouj

IPC分类号： B64G1/64

摘要： Technology is disclosed herein for a spacecraft launch restraint and dispensing structure (100). The dispensing structure (100) has a number of trusses (110) and a central structure (104). When the trusses (110) are in a support position, each spacecraft may be supported at one point by the central structure (104) and at two points by one or more of the trusses. Therefore, each spacecraft may be supported at three points, thereby providing a stable support for each spacecraft. The spacecrafts do not touch each other and do not bear the weight of other spacecrafts. In a deployment position, the trusses (110) extend away from the satellites and do not support the satellites; however, the satellites initially remain connected to the central structure (104). In the deployment position, the trusses (110) are out of an ejection path such that the satellites can be ejected in a desired sequence from the central structure (104).

公开(公告)号：WO2023080955A1

公开(公告)日：2023-05-11

申请号：PCT/US2022/043298

申请日：2022-09-13

申请人： MAXAR SPACE LLC

发明人： BAIN, Harold Mark ,  RENAULT, Yann ,  LAZBIN, Jennifer Lynn ,  GOLDSMITH, Jonathan Edward

IPC分类号： G06F11/20

摘要： A distributed computer system for a spacecraft is disclosed. The system has multiple computer nodes, each controlling a different aspect of a mission of the spacecraft. Each node includes a control circuit(s) that controls a set of components, a router processor, and a programmable processor. The programmable processor of each respective computer node issue commands to the control circuit(s) of the respective computer node to carry out an aspect of the mission associated with the respective computer node. Upon failure of the programmable processor in a particular computer node, a healthy programmable processor sends commands to the router processor in the particular computer node. The router processor of the particular computer node routes the commands received from the remote programmable processor to the control circuit(s) in the particular computer node to control the set of components to carry out the aspect of the mission associated with particular computer node.

公开(公告)号：WO2023027893A1

公开(公告)日：2023-03-02

申请号：PCT/US2022/039928

申请日：2022-08-10

申请人： MAXAR SPACE LLC

发明人： BAGHDASARIAN, Varouj

IPC分类号： B64G1/64

摘要： Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts (102) may be arranged around a central post (104). The dispensing structure has primary tie-down mechanisms (120) that axially clamp the stacks of spacecrafts (102) when in a stowed position. Each primary tie-down mechanism (120) may have a rod (110a, 110b) located between two adjacent stacks, such that the rod (110a, 110b) tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms (122) that radially connect the spacecrafts to the central post (104). After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts (102). The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

公开(公告)号：WO2021230986A1

公开(公告)日：2021-11-18

申请号：PCT/US2021/024729

申请日：2021-03-29

申请人： MAXAR SPACE LLC

发明人： TURNER, Andrew E.

IPC分类号： B64G1/24 ,  B64G1/44 ,  B64G1/28 ,  B64G1/36 ,  B64G1/242 ,  B64G1/244 ,  B64G1/283 ,  B64G1/361 ,  B64G1/40 ,  B64G1/443

摘要： 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. 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.

公开(公告)号：WO2022133029A1

公开(公告)日：2022-06-23

申请号：PCT/US2021/063706

申请日：2021-12-16

申请人： MAXAR SPACE LLC

发明人： FREESTONE, Michael ,  CAYTON, Brian M. ,  RAPPOLT, John ,  SEIWERTS, Shane Abraham ,  FLUITT, Daniel ,  ZIEMANN, Kevin

IPC分类号： F16F1/373 ,  F16B7/04

摘要： A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting (110) of a strut (106) used to connect a structural element (102) to a payload (104). The end fitting (110) may include outer and inner cylindrical hubs (120, 122), with a space between the outer and inner cylindrical hub (120, 122) at least partially filled with a viscoelastic material (136). In a further example, the passively damped mechanical system includes legs (204) used to connect a structural element (102) to a bracket (200) configured to support a payload. Each leg (204) may include a hollow interior having a lattice (208) structure to add strength and a viscoelastic material (210) to provide passive damping.