Autonomous Relative Navigation for Small Spacecraft

The thesis deals with the relative navigation between two small formation flying spacecraft. The inter-satellite distance is measured using locally generated radiofrequency ranging signals. Design considerations for the spacecraft and the relative navigation system are discussed as well as the estimation of the relative state. The influence of...

Potentials and Limitations of CDMA Networks for Combined Inter-Satellite Communication and Relative Navigation

Precision formation flying missions require formation acquisition and maintenance through the interactions among spacecraft by the inter-satellite communication and relative navigation. This paper analyses the dedicated system constraints of the network architecture for precision formation flying missions. The critical time issue and the...

Relative state estimation and observability analysis for formation flying satellites

Relative state estimation and observability for formation flying satellites in the presence of sensor noise

This paper presents an investigation into the relative state estimation and observability for two formation flying satellites using two different relative navigation sensor sets. The first set consists out of a transmitter antenna on one satellite and a single receiver antenna on the other satellite to measure the inter-satellite range using a...

Applications of a Networked Array of Small Satellites for Planetary Observation

The goal of this study is to explore those applications which can best utilize a network of orbiting satellites working as a distributed computing array. The satellites are presumed to be low-cost mini- or micro-satellites orbiting Earth or some other celestial body (i.e., an asteroid, moon, etc.), and should have a (near) constant communication...

Relative Orbital Element Estimation and Observability Analysis for Formation Flying Satellites using Inter-Satellite Range Measurements Only

This paper investigates to what extent the relative orbital elements of two satellites flying in formation can be estimated making use of inter-satellite range measurements only. Since the determination of relative orbital elements does not require the orientation of the relative orbit with respect to absolute inertial space to be resolved, as...

Fractionated spacecraft: The new sprout in distributed space systems

This paper provides a survey of current state-of-the-art technologies of fractionated spacecraft, a new architecture for distributed space systems. The survey covers six aspects: architecture, networking, wireless communication, wireless power transfer, distributed computing, and planned missions implementing this architecture. As a result of...

Status of the fast mission: Micro-satellite formation flying for technology, science and education

FAST (Formation for Atmospheric Science and Technology demonstration) is a cooperative Dutch Chinese formation flying mission led by Delft University of Technology (TU Delft) in the Netherlands and Tsinghua University in China. It is expected to be the first international micro-satellite formation flying mission to achieve objectives in three...

Towards a miniaturized photon counting laser altimeter and stereoscopic camera instrument suite for microsatellites

In the following we review the optimization for microsatellite deployment of a highly integrated payload suite comprising a high resolution camera, an additional camera for stereoscopic imaging, and a single photon counting laser altimeter. This payload suite, the `Stereo Imaging Laser Altimeter' SILAT has been designated for deployment aboard...

Conceptual Design of the FAST-D Formation Flying Spacecraft

The paper presents the latest results in the design of FAST-D, the Dutch micro-satellite for the Dutch–Chinese FAST (Formation for Atmospheric Science and Technology demonstration) formation flying mission. Over the course of the 2.5 year mission, the two satellites, FAST-D and FAST-T, will demonstrate various new technologies and perform...

Mission Design of the Dutch-Chinese FAST Micro-Satellite Mission

The paper treats the mission design for the Dutch-Chinese FAST (Formation for Atmospheric Science and Technology demonstration) mission. The space segment of the 2.5 year mission consists out of two formation flying micro-satellites. During the mission, new technologies will be demonstrated and, using spectropolarimeter and altimeter payloads on...

Increasing system performance and flexibility: Distributed computing and routing of data within the fast formation flying mission

In 2007, the Tsinghua University, China, and the Delft University of Technology, The Netherlands, have agreed to jointly define, develop and operate the Formation for Atmospheric Science and Technology demonstration (FAST) mission. FAST will allow for a synoptic evaluation of global aerosol data and altitude profiles of the cryosphere with two...

Development of a generic inflatable de-orbit device for CubeSats

New space debris mitigation guidelines require satellites in low Earth orbit to de-orbit within 25 years after end of life. This effectively limits the orbital altitude of conventional CubeSat satellites to 400-700 km. For CubeSats employing the generic inflatable de-orbit device discussed here, this range is extended to 910 km by increasing the...