The Hubble Space Telescope is unquestionably one of the most important scientific instruments ever developed. Designed for launch and subsequent on-orbit maintenance by astronauts and the space shuttle, the Hubble Space Telescope presented a unique and challenging set of flight operations issues. The complexity of the operations required a sophisticated level of mission planning and execution, particularly in robotics and extravehicular activity. Detailed planning by the flight operations team and the crew before the launch of the Hubble Space Telescope onboard the space shuttle Discovery was critical to the successful achievement of the objectives. The on-orbit execution of the mission plan, the anomalies encountered, and the resulting lessons learned from the deployment mission were important not only for preparations for the later servicing missions but also for a variety of missions, including those dedicated to the International Space Station assembly.

How Launching Hubble Space Telescope Influenced Space Shuttle Mission Operations

This work aims to facilitate deployment of novel distributed space systems architectures such as Federated Satellite Systems (FSS). In particular, the purpose of the work is to identify retrofitting possibilities to incorporate existing satellites into a network. For the satellite case, the paper presents a systematic review of possible retrofitting options such as direct modifications, which include replacement and addition of interfaces, and indirect modifications with adding an intermediary (FSS Negotiator). While the paper concludes that direct modifications of existing satellites are non-feasible from the technical point of view, it also identifies a possible scenario of retrofitting by adding as an intermediary a Negotiator satellite. The link budget for the inter-satellite link between an existing satellite mission such as SPOT-6 and FSS Negotiator was estimated. The work concludes that from the link budget point of view with the existing communication technologies such configuration can provide a slant range limited from several hundred to thousands kilometers. Through analysis of open data of satellite characteristics, including ITU information concerning planned or existing space stations, the work comes up with several models for the further trade-off analysis, identifying how parameters of FSS Negotiator such as an operated bandwidth and frequency, types of supported modulations and cumulative throughput correlate with the covered number of satellites. These results might be used for the tradeoff analysis for the FSS Negotiator mission design. Eventually paper proposes several possible FSS Negotiator architectures and its high-level technical requirements based on analysis of characteristics of existed and planned satellites.

https://hal.archives-ouvertes.fr/hal-01685291/document

Identifying retrofitting opportunities for Federated Satellite Systems

*† ‡ The amenability of satellites to on-orbit servicing (OOS) is assessed through the development of an agent-based model. With the context of a multi-year servicing campaign in the GEO (geosynchronous orbit) belt, OOS is treated as a multi-variable optimization problem with the principal trade of minimizing both ∆V (change in velocity) expenditures and transfer time. Assuming current launch vehicle, propulsion, and robotic technology for servicing vehicles, the focus in the model is on the serviceability of target satellites. Servicing vehicle operations are simulated over time, completing maneuvers as a function of pathdependent servicing operations. Primary outputs of the agent model are the cost of servicing (mean ∆V expenditure by servicing vehicle for satisfying tickets) and the performance of target satellites (availability for mission operations). Many interesting lessons emerged from the agent-based model of OOS with implications for both serviceability assessments of target satellites and servicing provider architecture. Most fundamentally, the high availability of GEO satellites in the model suggests that satellites work too well to stress a simple OOS system. Servicing vehicles were idle more than 90% of the time leading to a probability of two or more servicing vehicles conducting missions simultaneously of less than 1%. OOS business models need to balance the attraction of GEO due to the high concentration of valuable spacecraft and friendly orbital dynamics with the high-reliability of GEO satellites launched over the past two decades. Nomenclature a phase = Semi major axis of the phasing orbit for the servicer target a = Semi major axis of the target satellite orbit k servicer = Number of phasing revolutions of the servicer k t arg et = Number of phasing revolutions of the target satellite

Agent Model of On-Orbit Servicing Based on Orbital Transfers

The STS-38 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-seventh flight of the Space Shuttle and the seventh flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-40/LWT-33), three Space Shuttle main engines (SSME's) (serial numbers 2019, 2022, 2027), and two Solid Rocket Boosters (SRB's), designated as BI-039. The STS-38 mission was a classified Department of Defense mission, and as much, the classified portions of the mission are not presented in this report. The sequence of events for this mission is shown. The significant problems that occurred in the Space Shuttle Orbiter subsystem during the mission are summarized and the official problem tracking list is presented. In addition, each Space Shuttle Orbiter problem is cited in the subsystem discussion.

/pdf/sts-38-space-shuttle-mission-report-1jotpmyk2s.pdf

STS-38 Space Shuttle mission report

The STS-31 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-fifth flight of the Space Shuttle and the tenth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-34/LWT-27), three Space Shuttle main engines (SSME's) (serial numbers 2011, 2031, and 2107), and two Solid Rocket Booster (SRB) (designated as BI-037). The primary objective of the mission was to place the Hubble Space Telescope (HST) into a 330 nmi. circular orbit having an inclination of 28.45 degrees. The secondary objectives were to perform all operations necessary to support the requirements of the Protein Crystal Growth (PCG), Investigations into Polymer Membrane Processing (IPMP), Radiation Monitoring Equipment (RME), Ascent Particle Monitor (APM), IMAX Cargo Bay Camera (ICBC), Air Force Maui Optical Site Calibration Test (AMOS), IMAX Crew Compartment Camera, and Ion Arc payloads. In addition, 12 development test objectives (DTO's) and 10 detailed supplementary objectives (DSO's) were assigned to the flight. The sequence of events for this mission is shown. The significant problems that occurred in the Space Shuttle Orbiter subsystems during the mission are summarized, and the official problem tracking list is presented. In addition, each of the Space Shuttle Orbiter problems is cited in the subsystem discussion.

https://ntrs.nasa.gov/api/citations/19920008146/downloads/19920008146.pdf

STS-31 Space Shuttle mission report

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STS-38 Space Shuttle mission report

STS-31 Space Shuttle mission report