PROPULSION SUBSYSTEM Clause Samples
The Propulsion Subsystem clause defines the requirements, specifications, and responsibilities related to the design, manufacture, integration, and performance of the propulsion system within a larger project or contract, such as a spacecraft or satellite. This clause typically outlines the technical standards the propulsion subsystem must meet, the testing and acceptance procedures, and the division of tasks between the contracting parties. By clearly delineating these aspects, the clause ensures that the propulsion subsystem will function as intended and that accountability for its performance is established, thereby reducing the risk of disputes or failures related to this critical component.
PROPULSION SUBSYSTEM. [***] [The remaining 3 pages (pages 8-1 through 8-3) of this section have been omitted and filed separately with the Commission.]
PROPULSION SUBSYSTEM. 6.1 FUNCTIONAL REQUIREMENTS 6.2 PROPELLANT BUDGETS
PROPULSION SUBSYSTEM. 4-10 4.6.1 Qualification..........................................4-10 4.6.2 Acceptance Testing.....................................4-10 4.7 SOLAR ARRAY.....................................................4-10 4.7.1 Solar Panel Coupon Qualification.......................4-10 4.7.1 Solar Panel Coupon Qualification.......................4-11 4.7.2 Acceptance Testing.....................................4-11 4.7.2 Acceptance Testing.....................................4-12 4.8 ELECTRICAL POWER SUBSYSTEM......................................4-13 4.8.1 Qualification..........................................4-13 4.8.2 Protoflight and Acceptance.............................4-13 4.9 SPACECRAFT CONTROL ELECTRONICS SUBSYSTEM........................4-14 4.10 THERMAL CONTROL SUBSYSTEM.......................................4-14 4.11 STRUCTURE SUBSYSTEM.............................................4-14 4.11.1 Qualification..........................................4-14 4.11.2 Protoflight and Acceptance Tests.......................4-14 4.12
PROPULSION SUBSYSTEM. The satellite propulsion subsystem shall include all components and assemblies associated with storing, conditioning, routing, controlling, and expelling propellant, as required to change the satellite’s attitude and angular or linear velocity. The propulsion subsystem includes all propulsion hardware and propellants required to achieve placement into geosynchronous orbit from the geo-transfer orbit existing at separation from the launch vehicle. Liquid bi-propellant thrusters shall be utilized during the various operational phases following separation from the launch vehicle until the end of mission life including all major velocity maneuvers, apogee injection, and final de-orbit maneuver. It shall be possible to restart and operate any thruster at any time required for the mission with no thermal constraints. [*] [*] CONFIDENTIAL TREATMENT REQUESTED BY ICO GLOBAL COMMUNICATIONS (HOLDINGS) LIMITED. Propellant and gas leaks shall be minimized consistent with the satellite orbit lifetime. It shall be possible to predict depletion of the propellant at 15 years after beginning of life to an accuracy of [*] [*]