The 1st flight of our technological demonstrator MIURA 1 SN1 will allow us to gather as much data as possible for the validation and design of the technology that will be later transferred to and integrated in MIURA 5.
Additionally, this 1st suborbital flight will permit ZARM to study microgravity conditions through the gathering of valuable data needed for scientific experiments to be carried out in future suborbital flights.
The flight will last 12 minutes, during which microgravity conditions will be experienced from an altitude of 80km, and will reach its peak at an altitude of around 150km. A team from PLD Space will recover the rocket from the Atlantic Ocean once landing has occurred.
Experimental test flight in collaboration with the Centre of Applied Space Technology and Microgravity (ZARM) carrying a payload containing sensors for the collection of data in microgravity conditions.
Key Figures
Designed for microgravity research and technology development.
Mass budget 25 Kg / 55 lb
Volume 590 mm (diametrer) / 260 mm (height)
Power supply 28 V / 10 A / battery 0.5 Ah
Data storage 16 Gb / Mbyte/s
Telemetry data-rate of 0,8 Mbit/s
GNC Technology and Avionics development by GMV
Telemetry system
Power Storage and Distribution
Dedicated Payload Computer
Sensor Conditioning and Acquisition
Main engines TVC y RCS commanding
Composite overwrapped Helium Pressure Vessel
Cryogenic Liquid Oxygen (LOX):
1000 l (litres of LOX) / -182 ºC (Oxygen Temperature)
Mass at take off > 2550 Kg / 5622 lb
Propulsion system
Liquid Rocket Engine developed by PLD Space
The TEPREL-1B, a Liquid Bi-propellant engine running on Kerosene and Oxygen
122 second burn time
30 kN of thrust at seal level
< 5 Gs of acceleration during ascent
Height > 12,5 m / 41 ft
Mass budget 25 Kg / 55 lb
Volume 590 mm (diameter) / 260 mm (height)
Power supply 28 V / 10 A / battery 0.5 Ah
Data storage 16 Gb / Mbyte/s
Telemetry data-rate of 0,8 Mbit/s
Composite Overwrapped Helium Pressure Vessel
Cryogenic Liquid Oxygen (LOX) Tank:
1.000 l / -182 ºC
Kerosene Tank (KER): 600 l
Mass at takeoff > 2.550 kg / 5.622 lb
Liquid Rocket Engine developed by PLD Space
TEPREL-B, a Liquid Bi-propellant engine running on Kerosene and Oxygen (KeroLOX). In 2021, it became the first fully-private, liquid propulsion based LOX-Kerosene engine developed in the history of Europe
122 second burn time
30 kN of thrust at sea level
< 5 Gs of acceleration during ascent
Diameter 0,7 m/2,3ft
153 km
100 km
80 km
58 km
51 km
0,4 km
0 km
80 km
5 km
3 km
0 km
APOGEE
SPACE CONDITIONS
BEGINNING OF MICROGRAVITY
BEGINNING OF
ALIGNMENT
PICH MANEUVER
MECO
BEGINNING OF
DOWNRANGE
PICH MANEUVER
LIFT-OFF
END OF MICROGRAVITY
DROGUE PARACHUTES
MAIN PARACHUTES
SPLASHDOWN
For 85% of the year, our launch site boasts sunny skies and temperate weather. Thus, launch scrubs and delays due to inclement weather are reduced.
The historic El Arenosillo test range is located near Huelva, in south-west Spain (37°05’59.96” N,06°44’10.63” W). From this base, over 550 sounding rockets have been launched to date. El Arenosillo is owned and managed by INTA (National Space Authority), an institution that belongs to the Spanish Ministry of Defense. It has all the necessary equipment and facilities to support PLD Space commercial launch operations.
Launching services schedule
& pre-reservation
For a nominal flight, the time between the flight ticket procurement and flight is ONE YEAR, as shown in the mission timeline. If a different lead time is required by the user, it is possible to adapt this timeline. If this is the case, please contact PLD Space for further details.
Payload booking request
Flight ticket procurement & mission definition
Payload development
Payload integration & testing
Launch campaign
Flight
