This document contains the draft budget for the University of Leicester Space Research Centre CubeSat project. All subsystems are listed, their individual components costed and an overall estimated hardware cost is given in the executive summary at the end of the document.
The cost for the payload subsystem is going to be a nanometeoroid detector, possibly in combination with an optical camera and has not been considered in this document. A reasonable estimate for this subsystem will only be possible once more work has been done in this area.
1. Mechanical Bus and Thermal Control
It is possible to obtain a cubesat kit from Pumpkin Incorporated .
Assembly (in ½U, 1U, 1½U, 2U or 3U size), a Base Plate Assembly and a Cover Plate
Assembly. Each kit contains either solid-wall or skeletonized versions of these
● A CubeSat Kit Development Board for in-lab development, debugging and testing.
● A CubeSat Kit FM430 Flight Module for use in the CubeSat Kit Flight Model.
● An external universal +5Vdc switching power supply 3.
● An MSP430 Flash Emulation Tool and FM430 programming adapter.
● A USB cable.
● CubeSat Kit and Salvo RTOS software on CD-ROM 5.
● A Remove-Before-Flight Pin and lanyard.
● Miscellaneous fasteners / mounting hardware.
● A printed User Manual and other documentation.
Price based on cubesat kit- skeletonised, 1U will be $ 5000 (current conversion £2498)
According to  it is possible to use passive cooling to keep satellite within -40˚C to +85˚C range. Cubesat kit  specifies instrument rage is -40˚C to +85˚C except SD/MMC mass storage cards which are typically specified over -20˚C to + 65˚C.It is assumed that all required thermal control can be achieved through passive methods at negligible extra cost.
According to  radiation hardened electronics parts are difficult to find so code correction and outer protection were used as radiation protection.
2. Attitude Determination and Control System (ADCS)
The attitude determination system is going to use magnetoresistors in order to determine satellite attitude from earths magnetic field. The two viable solutions are a pre made board or to build our own. The pre build option is Honeywells HMR2300r , this is a 3 axis strap down magnetometer with a RS232 output. It has a operating temperature range -40 to 80°C and a field range of ±2 guass. The cost of the board alone is $997.60, approximately £520.
If the board is produced in-house, a set of suitable magnetoresistors have to be purchased. These would be Honeywells HMC1001 and HMC1002. These are 1 and 2 axis magnetoresistors working together to provide 3 axis determination. These achieve this by providing 3 output voltages which give the 3 components of the magnetic vector, which can then be used to derive the attitude. These 2 sensors have the same field range and operational temperature as the HMR2300r , but are significantly cheaper costing £10 and £15 respectfully. On top of this a board would need to be built, at a cost of £20 for the board plus staff time for it to be qualified. The other option would be to buy a pre made space qualified PCB at a cost of £200 - £300
Additional costs assumed for the periphery electronics, including items such as amplifiers and the analogue digital converters have been estimated to be around £50.
According to Tim Stevenson Attitude Control Magentorquers can be produced in house at negligible cost.
The high efficiency GaAs arrays produced by EMCore and provided by Clyde Space are beyond our financial reach at ~£10k per 100mm x 100mm array.
An alternative could be off-the-shelf commercial solar cells, which would then need to be space qualified. Panasonic sunceram cells provide sufficient power at efficiencies of 12%-16% and are cost effective at ~$100 per cube face.
Specs according to  for 2 cells in series:
1.2 A/hour each
10 W hour
Includes: temperature sensor, current monitor, voltage monitor, under voltage/over voltage protection.
Mass- no more than 60g (Clyde Space still currently working on batteries)
2 Batteries can fit into a 1U Cubesat
Cost £400 (per battery) 
4. Communication system (Comms)
The communications subsystem will have the task of communicating house keeping data and payload data with the groundstation.
On the satellite side it will consist of a modem, transceiver (TX) and antenna.
The CubeSat kit described in section 1. is compatible with a modem/transmitter system provided by Microhard Systems (www.microhardcorp.com) . A quote has been obtained from Microhard for a 2.4GHz Transceiver development platform  containing:
Sea-launch converted Zenit launcher or a Soyuz freget vehicle.
SpaceX. Falcon 1 developed launch vehicle.
The following table contains a summary of all the subsystem costs + 25% contingency. The biggest uncertainty at this moment seems to be in the cost of suitable solar cells if the Panasonic Sunceram do not qualify.
£20,000 (not included in contingency)
We suggest an extra £1000 contingency due to the solar cell issues.