On-orbit servicing commercial opportunities with security implications

The On-Orbit Servicing (OOS) working group discussed legal and political implications of developing a commercial OOS industry. The group considered the benefits that OOS and Active Debris Removal (ADR) can offer the satellite industry, as well as potential disadvantages for international relations between space faring nations. To gain an accurate perspective of stakeholders involved in such a process, the OOS working group held a mock hearing for OOS licensing, with members of the working group assigned to represent stakeholders. Working group members presented their cases at a simulated domestic regulatory panel, constructed of members representing various government ministers, to fully explore stakeholder views. The mock hearings explored the challenges faced by OOS and ADR entrepreneurs as well as the benefit of regulation. The groups highlighted recommendations to ensure the practicality of OOS and determine how best to encourage licensing and regulation of such activities, as summarised below. 1. The United Nations (UN) should provide regulatory guidelines for OOS and ADR. 2. Government agencies should license OOS. The Federal Aviation Administration (FAA) has taken responsibility for licensing commercial space transportation in the United States and this should be extended to OOS/ADR missions to enable short-term advancement prior to further UN regulation. 3. Government should support OOS and ADR development to ensure continued demand. This includes leading by example on government satellites and potential launch levies to enable on-going ADR funding. 4. All stakeholders should prevent weaponisation of space through transparency of operations. 5. Nations should initiate international cooperation on ADR. OOS and ADR will ensure sustainable use of satellites, particularly in LEO and GEO, for the coming decades. It is through transparency, economic stimulation and close monitoring that such endeavours will be successful

An approach to ground based space surveillance of geostationary on-orbit servicing operations

AbstractOn Orbit Servicing (OOS) is a class of dual-use robotic space missions that could potentially extend the life of orbiting satellites by fuel replenishment, repair, inspection, orbital maintenance or satellite repurposing, and possibly reduce the rate of space debris generation. OOS performed in geostationary orbit poses a unique challenge for the optical space surveillance community. Both satellites would be performing proximity operations in tight formation flight with separations less than 500m making atmospheric seeing (turbulence) a challenge to resolving a geostationary satellite pair when viewed from the ground. The two objects would appear merged in an image as the resolving power of the telescope and detector, coupled with atmospheric seeing, limits the ability to resolve the two objects. This poses an issue for obtaining orbital data for conjunction flight safety or, in matters pertaining to space security, inferring the intent and trajectory of an unexpected object perched very close to one׳s satellite asset on orbit. In order to overcome this problem speckle interferometry using a cross spectrum approach is examined as a means to optically resolve the client and servicer׳s relative positions to enable a means to perform relative orbit determination of the two spacecraft. This paper explores cases where client and servicing satellites are in unforced relative motion flight and examines the observability of the objects. Tools are described that exploit cross-spectrum speckle interferometry to (1) determine the presence of a secondary in the vicinity of the client satellite and (2) estimate the servicing satellite׳s motion relative to the client. Experimental observations performed with the Mont Mégantic 1.6m telescope on co-located geostationary satellites (acting as OOS proxy objects) are described. Apparent angular separations between Anik G1 and Anik F1R from 5 to 1 arcsec were observed as the two satellites appeared to graze one another. Data reduction using differential angular measurements derived from speckle images collected by the 1.6m telescope produced relative orbit estimates with better than 90m accuracy in the cross-track and in-track directions but exhibited highly variable behavior in the radial component from 50 to 1800m. Simulations of synthetic tracking data indicated that the radial component requires approximately six hours of tracking data for an Extended Kalman Filter to converge on an relative orbit estimate with less than 100m overall uncertainty. The cross-spectrum approach takes advantage of the Fast Fourier Transform (FFT) permitting near real-time estimation of the relative orbit of the two satellites. This also enables the use of relatively larger detector arrays (>106 pixels) helping to ease acquisition process to acquire optical angular data

Ground verification of the feasibility of telepresent on-orbit servicing

In an ideal case telepresence achieves a state in which a human operator can no longer differentiate between an interaction with a real environment and a technical mediated one. This state is called transparent telepresence. The applicability of telepresence to on-orbit servicing (OOS), i.e., an unmanned servicing operation in space, teleoperated from ground in real time, is verified in this paper. For this purpose, a communication test environment was set up on the ground, which involved the Institute of Astronautics (LRT) ground station in Garching, Germany, and the European Space Agency (ESA) ground station in Redu, Belgium. Both were connected via the geostationary ESA data relay satellite ARTEMIS. Utilizing the data relay satellite, a teleoperation was accomplished in which the human operator as well as the (space) teleoperator was located on the ground. The feasibility of telepresent OOS was evaluated, using an OOS test bed at the Institute of Mechatronics and Robotics at the German Aerospace Center (DLR). The manipulation task was representative for OOS and supported real-time feedback from the haptic-visual workspace. The tests showed that complex manipulation tasks can be fulfilled by utilizing geostationary data relay satellites. For verifying the feasibility of telepresent OOS, different evaluation methods were used. The properties of the space link were measured and related to subjective perceptions of participants, who had to fulfill manipulation tasks. An evaluation of the transparency of the system, including the data relay satellite, was accomplished as well

Project Summaries, 1989 - 1990

Student designs summarized here include two undergraduate space designs and five graduate space designs from fall 1989, plus four undergraduate space designs and four undergraduate aircraft designs from spring 1990. Progress in a number of programs is described. The Geostationary Satellite Servicing Facility, the Lunar Farside Observatory and Science Base, the Texas Educational Satellite, an asteroid rendezvous vehicle, a Titan probe, a subsystems commonality assessment for lunar/Mars landers, a nuclear-thermal rocket propelled Earth-Mars vehicle, and a comprehensive orbital debris management program are among the topics discussed

Active space debris removal system

Tato diplomová práce se zabývá návrhem systému aktivního řešení kosmické tříště. Kosmická tříšť, nebo také kosmický odpad, je pojem používaný v kosmonautice k popisu všech antropogenních, neaktivních vesmírných objektů, fragmentů a zbytků všeho, co vzniklo rozpadem kosmické technologie, která byla vypuštěna na oběžnou dráhu člověkem. Kosmická tříšť se vyznačuje nekontrolovaným pohybem celistvých objektů nebo jejich fragmentů s vysokými rychlostmi pohybu a vysokou kinetickou energií. S rozvojem kosmonautiky a její postupnou integrací do běžného lidského života, představuje rostoucí množství kosmického odpadu vážný problém ohrožující budoucnost veškerých kosmických misí. Lidstvo tak v současnosti čelí potenciální hrozbě v podobě zamezení kosmických letů a využívání kosmických technologií po mnoho dalších generací.This diploma thesis focuses on the design of an active space debris removal system. Space debris is a term used in cosmonautics to describe all anthropogenic inactive space objects, fragments, and remnants of everything created by the decay of space technology, which has been launched into orbit by humans. Space debris is characterized by the uncontrolled movement of whole bodies or fragments with high velocities and high kinetic energy. With the development of cosmonautics and its gradual integration into ordinary human life, the increasing amount of space debris poses a serious problem threatening the future of space missions. Thus, humanity is currently facing a potential threat, in the form of the prevention of space flights and the use of space technology for many generations

Concept for a Distributed, Modular, In-space Robotically Assembled, RF Communication Payload in GEO

In this paper, we discuss a concept for a Radio Frequency (RF) Ka band communications payload that is robotically assembled and serviced in space using a servicing vehicle such as the Robotic Servicing of Geosynchronous Satellites (RSGS) vehicle being developed by the Defense Advance Research Projects Agency (DARPA). Our work focuses on how to modularize a representative Ka band communications payload into discrete modules that are hosted on a persistent platform. In our concept, each module consists of a primary aperture and the associated RF and electronics required to serve a particular coverage area or type. These modules are notionally packaged in a form factor capable of launching as a secondary payload via an EELV Secondary Payload Adapter (ESPA) ring or a Payload Orbital Delivery System (PODS) module. The overall payload consists of an earth coverage module, regional coverage modules, high gain regional coverage modules, and a host interface unit (HIU). We discuss the notional capabilities and requirements of each module. We present two different architecture concepts corresponding to two different persistent platform concepts. In one concept, the persistent platform is made up of small, independent spacecraft that are connected together with structural members with communication channels. The payload modules are hosted on the individual spacecraft. In the second approach, the platform consists of a large central spacecraft with a structural truss that has power, communication and thermal loops. The payload modules are hosted on the truss through standard interfaces. We present aspects of the mission concept on how the payload may be modularized, launched (as secondary launch elements), acquired by the RSGS vehicle in space and assembled on to the persistent platform. We discuss the robotics aspects of assembly and servicing of the payload modules. A key aspect of this concept is the serviceability of the payload. Central to the modular and discrete payload design is an intent to refurbish the payload incrementally as technology evolves or the components fail. Existing geosynchronous communication satellites are designed and built as monolithic spacecraft which makes any servicing beyond refueling fairly complicated. This makes it hard to take advantage of the post launch evolution in technology, particularly in the electronics elements. Our concept is aimed at modularizing the payload such that the modules, particularly the electronics elements, can be easily serviced using the RSGS vehicle. Our concept attempts to take advantage of the long service life of high reliability system components in the core satellite bus while allowing rapid expansion and upgrading of the communications payload through the addition and replacement of individual payload modules

Concept for a Distributed, Modular, In-space Robotically Assembled, RF Communication Payload in GEO

In this paper, we discuss a concept for a Radio Frequency (RF) Ka band communications payload that is robotically assembled and serviced in space using a servicing vehicle such as the Robotic Servicing of Geosynchronous Satellites (RSGS) vehicle being developed by the Defense Advance Research Projects Agency (DARPA). Our work focuses on how to modularize a representative Ka band communications payload into discrete modules that are hosted on a persistent platform. In our concept, each module consists of a primary aperture and the associated RF and electronics required to serve a particular coverage area or type. These modules are notionally packaged in a form factor capable of launching as a secondary payload via an EELV Secondary Payload Adapter (ESPA) ring or a Payload Orbital Delivery System (PODS) module. The overall payload consists of an earth coverage module, regional coverage modules, high gain regional coverage modules, and a host interface unit (HIU). We discuss the notional capabilities and requirements of each module. We present two different architecture concepts corresponding to two different persistent platform concepts. In one concept, the persistent platform is made up of small, independent spacecraft that are connected together with structural members with communication channels. The payload modules are hosted on the individual spacecraft. In the second approach, the platform consists of a large central spacecraft with a structural truss that has power, communication and thermal loops. The payload modules are hosted on the truss through standard interfaces. We present aspects of the mission concept on how the payload may be modularized, launched (as secondary launch elements), acquired by the RSGS vehicle in space and assembled on to the persistent platform. We discuss the robotics aspects of assembly and servicing of the payload modules. A key aspect of this concept is the serviceability of the payload. Central to the modular and discrete payload design is an intent to refurbish the payload incrementally as technology evolves or the components fail. Existing geosynchronous communication satellites are designed and built as monolithic spacecraft which makes any servicing beyond refueling fairly complicated. This makes it hard to take advantage of the post launch evolution in technology, particularly in the electronics elements. Our concept is aimed at modularizing the payload such that the modules, particularly the electronics elements, can be easily serviced using the RSGS vehicle. Our concept attempts to take advantage of the long service life of high reliability system components in the core satellite bus while allowing rapid expansion and upgrading of the communications payload through the addition and replacement of individual payload modules

Method and associated apparatus for capturing, servicing, and de-orbiting earth satellites using robotics

This invention is a method and supporting apparatus for autonomously capturing, servicing and de-orbiting a free-flying spacecraft, such as a satellite, using robotics. The capture of the spacecraft includes the steps of optically seeking and ranging the satellite using LIDAR; and matching tumble rates, rendezvousing and berthing with the satellite. Servicing of the spacecraft may be done using supervised autonomy, which is allowing a robot to execute a sequence of instructions without intervention from a remote human-occupied location. These instructions may be packaged at the remote station in a script and uplinked to the robot for execution upon remote command giving authority to proceed. Alternately, the instructions may be generated by Artificial Intelligence (AI) logic onboard the robot. In either case, the remote operator maintains the ability to abort an instruction or script at any time, as well as the ability to intervene using manual override to teleoperate the robot.In one embodiment, a vehicle used for carrying out the method of this invention comprises an ejection module, which includes the robot, and a de-orbit module. Once servicing is completed by the robot, the ejection module separates from the de-orbit module, leaving the de-orbit module attached to the satellite for de-orbiting the same at a future time. Upon separation, the ejection module can either de-orbit itself or rendezvous with another satellite for servicing. The ability to de-orbit a spacecraft further allows the opportunity to direct the landing of the spent satellite in a safe location away from population centers, such as the ocean