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The T5 Ion Propulsion Assembly for Drag Compensation on GOCE

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The T5 Ion Propulsion Assembly for Drag Compensation on GOCE The T5 Ion Propulsion Assembly for Drag Compensation on GOCE Dr C H Edwards and Mr N C Wallace QinetiQ Ltd, Cody Technology Park, Ively Road, Farnborough, GU14 0LX, UK C Tato Astrium CRISA, C/Torres Quevedo, 9 Tres Cantos, 28760 Madrid, Spain P van Put Bradford Engineering B.V., De Wijper 26 4726 TG Heerle, The Netherlands ABSTRACT Due to the nature of the gravity field measurements to be made by GOCE, the satellite must fly in a near-circular, sun-synchronous, dawn-dusk orbit at an altitude of around 250 km. At this altitude the residual air drag is significant, and must be actively compensated by onboard thrusters. In addition, the gradiometer instrument is sensitive to linear acceleration, which must also be precisely compensated for by the thrusters. The dominant component of the drag force is in the primary flight axis, requiring a propulsion system capable of continuous throttling between 1 and 20 mN, with a thrust resolution of 12 µN, a response rate up to 2.5 mN/s, and a thrust vector stability of better than ± 0.2 degrees. In addition to the drag compensation role, the propulsion system will also be operated at a fixed high thrust during orbit-raising for the long eclipse season. These stringent requirements can only realistically be met using a highly controllable ion propulsion system, which on GOCE is known as the ion propulsion assembly (IPA). The QinetiQ T5 Kaufman-type ion thruster assembly (ITA) is the heart of this system, and is ideally suited for this mission, having been designed for a nominal thrust of between 15 - 25 mN, and including solenoid magnets which allow the operating parameters to be efficiently and accurately controlled over the required thrust range. As such the QinetiQ T5 ion thruster represents an enabling technology for the mission. This paper presents an overview of the IPA system and its components, and is intended to provide the GOCE scientific users with an understanding of the technology, its performance, and the challenges, which have been overcome to provide it. • INTRODUCTION The Gravity Field and Steady State Ocean Circulation Earth Explorer (GOCE) Mission is the first of a series of “Earth Explorer Core Missions” that the European Space Agency is to undertake in the frame of its “Living Planet Programme - Earth Observation Envelope Programme”. The mission objective of GOCE is to provide unique models of the Earth’s gravity field and of its equipotential reference surface, as represented by the geoid, on a global scale with high-spatial resolution and very high accuracy. This will not only help to advance knowledge of the Earth’s interior structure but will also help to develop a much deeper understanding in areas such as ocean circulation, ice sheet balance and thus climatology. The Agency has selected a Core Team consisting of Alenia Spazio as the GOCE Prime Contractor, with Astrium GmbH as the Platform responsible Contractor, Alcatel Space Industries as the Gradiometer Instrument responsible Contractor and ONERA as the supplier of the Gradiometer accelerometers and of the related support at Gradiometer Instrument and System Level. Astrium GmbH as the Platform Contractor is responsible for provision of the Ion Propulsion Assembly, including the overall system design, specification and procurement of the individual products of the IPA. The following products make up the IPA and are to be supplied by the indicated sub-contractors: ____________________________________________ Proc. Second International GOCE User Workshop “GOCE, The Geoid and Oceanography”, ESA-ESRIN, Frascati, Italy, 8-10 March 2004 (ESA SP-569, June 2004) • Ion Thruster Assembly (ITA) QinetiQ Ltd. including control algorithms QinetiQ Ltd. • Ion Propulsion Control Unit (IPCU) Astrium-CRISA including HV transformer and Ion Beam converter. Astrium GmbH and flight software QinetiQ Ltd. • Proportional Xenon Feed Assembly (PXFA) Bradford Engineering B.V. (including flow control algorithms) The main function of the IPA is to compensate in real-time for the drag force experienced by the satellite operated in the proposed GOCE orbit. The orbit is a near-circular, sun-synchronous, dawn-dusk orbit at an altitude of around 250 km, and leads to a drag profile on the spacecraft consisting of relatively large variations at a frequency equivalent to the orbital period, superimposed by smaller magnitude variations at higher frequencies up to 10 Hz. • THE ION PROPULSION ASSEMBLY A schematic of the IPA architecture is shown in Figure 1. The system is a cold redundant architecture, comprising two Ion Thruster Assemblies (ITA), which are powered and controlled by two Ion Propulsion Control Units (IPCU), and fed propellant directly from the tank by two Proportional Xenon Feed Assemblies (PXFA). The Xenon Storage Tank and associated pipework complete the assembly, but these items are not discussed in this paper. The IPCU provides overall control of the system, receiving power, timing and enable commands directly from the spacecraft and thrust control commands from the Drag Free Attitude Control System (DFACS) via the MIL-1553 Bus. These control commands are interpreted by the IPCU, and converted into the appropriate demand signals for the ITA and PXFA using software and control algorithms defined and supplied by QinetiQ Ltd. 2 x Primary Power 2 x 1 PPS Nominal 1 x Status 2 x reg. / 5 x fixed current, IPCU 4 x fixed voltage to ITA 2 x HPC 1 x MIL-Bus nom. Nominal 1 x MIL-Bus red. ITA 6 x Signal 8 x Sec. Power Neutraliser PXFA 1 53B 5 1 x reg./ 2 x fixed Xenon Flow Xenon Tank Bus 1 L- 1 x reg./ 2 x fixed Xenon Flow I PXFA 2 M Neutraliser 8 x Sec. Power 6 x Signal Redundant 1 x MIL-Bus red. ITA 2 x HPC 1 x MIL-Bus nom. Redundant 1 x Status IPCU 2 x 1 PPS 2 x reg. / 5 x fixed current, 4 x fixed voltage to ITA 2 x Primary Power Figure 1 IPA Architecture The IPA products are mounted on the propulsion module panel, in the layout shown in Figure 2. The IPCUs are mounted on the inside surface of the panel, while the PXFAs and ITAs are mounted on the external surface. The ITAs are mounted together on a separate structure close to the centreline of the spacecraft. Each ITA is canted to a nominal angle of 2.4 degrees, and includes an adjustable mounting bracket, to ensure that the nominal thrust vector can be aligned with the spacecraft centre of gravity prior to launch. Figure 2 Ion Propulsion Module Layout • ION THRUSTER ASSEMBLY (ITA) The GOCE ITA is based on the existing T5mkV thruster design, as shown in Figure 3. It is of conventional Kaufman configuration, with a direct current (DC) discharge between a hollow cathode and a cylindrical anode used to ionise the propellant gas. The efficiency of this plasma production process is enhanced by the application of a magnetic field within the discharge chamber, which can also be used to provide accurate throttling. A 10 cm diameter grid system, forming the exit to the discharge chamber, extracts and accelerates the ions, to provide the required thrust. The thrust produced depends on the number and velocity of the ejected ions. The number of ions extracted is dependent on the ion density in the discharge chamber and the transparency of the grid system, and the velocity depends only on the accelerating potential applied to the ions. An external hollow cathode, referred to as the neutraliser, emits the electrons necessary to neutralise the space charge of the emerging ion beam. SOLENOID ISOLATOR ANODE OUTER POLE PROPELLANT HOLLOW CATHODE SCREEN ACCELERATOR KEEPER BAFFLE GRID GRID CATHODE ISOLATOR SUPPORT INNER POLE MAIN FLOW DISTRIBUTOR DISCHARGE CHAMBER INSULATORS FERROMAGNETIC CIRCUIT MAGNETIC PROPELLANT FIELD LINE EARTHED INSULATOR CATHODE SCREEN NEUTRALISER ASSEMBLY Figure 3 QinetiQ T5 mkV Thruster Table 1 ITA Key Parameters Mass 2.95 kg (including adjustable mounting bracket) Dimensions ∅ 190 mm x 242 mm long (including adjustable mounting bracket) Grid ∅ 100 mm Thrust range 1 to 20 mN Thrust Noise 1.2 mN/√Hz @ 1 mHz to 0.012 mN/√Hz @ 100 Hz Power 55 W to 585 W (across thrust range) Specific Impulse 500 s to 3500 s (across thrust range) Total impulse capability > 1.5 x 106 Ns (under GOCE continuous throttling conditions) Cycle life GOCE requirement: > 1000 On/Off cycles T5 capability: > 8500 On/Off cycles Thrust vector stability < ± 0.1 degrees (across thrust range) Beam divergence < 25 degrees (2σ half-cone angle @ 1 mN) < 12 degrees (2σ half-cone angle @ 20 mN) The GOCE requirements have lead to challenges in terms of the grid design. In particular, the wide thrust range, coupled with the long lifetime requirement have necessitated a detailed optimisation of the grid design to be performed. The grid optimisation entailed detailed modelling of the ion extraction and erosion processes using an ion- optics modelling tool called SAPPHIRE. The grid modelling led to the adoption of a twin grid configuration, with the ion optics system optimised to the mission profile and lifetime requirements. The accelerator grid material was also changed to graphite, in order to provide additional operational margin whilst reducing mass • ITA CONTROL ALGORITHMS The ITA is controlled using a set of algorithms, specifically designed to meet the challenging GOCE requirements. The control algorithm architecture is shown in Figure 4. The ITA uses three of its input parameters to control the output thrust. The flow rate and anode current are adjusted relatively slowly, in an open-loop mode, to provide a coarse control of the thrust, while the solenoid magnet current is adjusted quickly, in a closed-loop mode, to provide fine control for high accuracy and quick response.
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