AspireSpace
				The British Amateur Space / Rocket Programme

ASPIRESPACE - PAYLOADS

ASPIRE II will yield between 3-6 minutes of good (low drag) micro-gravity, which is sufficient to allow a number of payloads to take advantage of this period.

The avionics will be housed in a modular system of boxes, housing two circuit boards each. There will be 6 boxes The boxes slot into a two-storey frame which takes the structural loads. This is situated just underneath the nosecone. The top of the avionics frame supports the payload bay, and is level with the bottom of the nosecone, ie the payload/s occupy the space inside the hollow ogive nosecone. The payload/s will be mounted (via a frame) onto a circular plate (around 340mm dia) on top of the avionics frame.

The boxes are 240mm tall, 45mm thick and the depth (length) is 150mm.

A number of payloads have been proposed for launch on ASPIRE II rockets. Any interested party may propose a payload for flight on one of the AspireSpace rockets. These are evaluated and accepted for flights, as and when, launches become available. AspireSpace is always keen to accept payload proposals, and advice on payloads. To this end, a list of proposed payloads is listed below. These proposals are offered as possible projects for student (or other) teams, who wish to take advantage of payload opportunities.

1. Spectro-Gamma

A gamma ray spectrometer for investigation of gamma rays. The detector uses a Thallium doped Caesium Iodide, CsI(Tl) scintillation system, with scintillations within a small CsI crystal being detected by photodiodes. This allows the payload to be implemented at very low cost. The Scintillator is bonded to a photodiode using an optically transparent adhesive. A small surface mount amplifier is connected to the photodiode. The output signal from this payload is then fed through the avionics and telemetry system, where it is relayed back to the ground. The signal arriving at the ground can then be analysed on a multichannel analyser to determine the nature of the observations detected.

2. Spectro-X

An X-ray spectrometer for investigation of Astronomical X-ray sources. The X-ray spectrometer payload will utilise a similar low cost solid state subsystem to the gamma ray spectrometer payload,

3. SubOT

This is a proposed suborbital astronomical telescope payload, using a CCD array mounted to a small optical telescope. The telescope will be a 6" Schmidt-Cassegrain Reflector. This type of telescope is chosen because of its lightness and compactness. The CCD array will be spectrally sensitive to optical and near Infra-Red wavelengths. Small cold gas jets will allow rudimentary pointing of the instrument via the rocket.

4. AIRCam and AVisCam

These are the Astronomical IR Camera and Astronomical Visible Camera. Both use 35 mm cameras, and are mounted in one payload rack. AIRCam is loaded with IR sensitive film, and AVisCam is loaded with visible light sensitive film. A simple electronic timer circuit is connected to the electronic shutter release mechanisms, triggering a number of astronomical exposures over the duration of the payload operation phase.

5. The Waverider test programme

The Waverider test programme requires dedicated launches of ASPIRE rockets carrying waverider test vehicles for hypersonic test flights.

6. Nephelometer

This payload is a reflight of the nephelometer payload originally designed to fly on ASPIRE I. The design has been updated since then, to take advantage of advances in both electronics technology and reductions in electronics costs. The Nephelometer is used for meteorological observations.

7. ASPIRESpy

A Remote Sensing payload carrying an Earth observation payload consisting of a CCD video camera transmitting data back to Earth, rather than recording it onboard, and 2 wide angle lens 35 mm cameras, one carrying film sensitive to visible wavelengths, and the other carrying film sensitive to IR wavelengths.

8. MuGELOI

Micro Gravity Effects on Lac Operon Induction. - This is a payload experiment which investigates enzyme evolution per unit density of cell. Two chambers in a syringe hold IPTG, the chemical which induces the Lac Operon, and Toluene to lyse the cells and ONPG which is catabolised by the lac operon product enzyme beta- galactosidase to a yellow product. The contents are injected into a container which holds the bacteria and a growth medium at 37*C.

PAYLOAD BAY ELECTRICAL INTERFACES

The control of the payload operations and sequencing will be handled as follows: The payload will have a basic set of 8 Analogue to Digital channels for analogue data, using a high density 15 way canon-D plug connector (8 Analogue lines, 2 power lines, 1 ground line). There will also be 8 digital (TTL 74HC compatible) input channels and 8 digital output channels connected to the opto-isolated avionics module, which will utilise a 25 way canon-D plug connector (8 digital input lines, 8 digital output lines, 4 power lines, 2 ground lines). These will not connect to the Telemetry Proccessor, but to the Sequence Command and Control Proccessor which controls and sequences the onboard functions of all the payloads, and many other subsystems in the rocket.

PAYLOAD BAY ACCESS

Access to the payload bay will be possible until the final phases of launch. At this point, the payload bay and all other internal fixytures will be closed off by the aeroshell, which will fit over the payload bay. An umbilical will be connected to the rocket until launch, so that external power can be maintained to all onboard systems, thus conserving onboard power.