1U-3U+ Cubesat Deployer by JSC SRC "Progress"

1st Latin American IAA CubeSat WorkShop. Brasília, Brasil. December 8th - 11th, 2014

JSC Space Rocket Center Progress

Universal 1U-3U+ CubeSat DeployerDmitriy Zaretskiy , Eugeni Kosmodemyanskii, Aleksandr Romanov, Maxim Sivov , Maxim Trusov, Vadim Yudintsev

http://www.samspace.ru


Outline

Historical Background

Mechanical design

Separation dynamics

Installation

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About Space Rocket Center Progress


1st Latin American IAA CubeSat WorkShop. Brasília, Brasil. December 8th - 11th, 2014 4


1957

1941-19451910 2010

20132013

1896 2010


Launch service

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Pleyades (ESA) Gaia (ESA)Resurs-P (Russia)Mars-Express (ESA)

Over 1800 manned and unmanned launches of the Soyuz rocket since 1967

More than 90launches of spacecraft were performed since 1999 under the agreement with foreign customers.Obzor-R (Russia) 2015


Bion-M with piggyback satellites

Bion-M is a large spacecraft for research in the field of space biology and medicine.

Launch of Bion-M № 1 was performed in 2013.

Aist spacecraft and five foreign small satellites of CubeSat type were used as a piggyback payload.

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Image source: http://samspace.ru/multimedia/images/selected_images/142/

Mechanical design

CubeSat Deployer


Multi-interface (satellites or orbital stages)

Reliable and proven components

Experimental validation

No debris

Design Principles

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Modular design

Door module

Hinges, latches, hold down and release mechanism

Base module

Guide rails

Separation spring module

Separation spring, platform with guide rails

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Multi-format

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1U 2U 3U, 3U+

Modular design allows to build deployers for various CubeSat form-factors

Set of separation springs is developed to separate satellites at a speed from 0.5 to 0.8 m/s


Sensors

The separation sensor detects the separation of the CubeSat from the platform

The temperature sensor measures the temperature inside the base module. All the surfaces of the deployer are wrapped by a multi-layer Insulation

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CubeSat Requirements

Form factors:

1U, 1.5U

2U

3U, 3U+

Standard CubeSat requirements*

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*Munakata, Riki. "Cubesat design specification rev. 13." The CubeSat Program, California Polytechnic State University 1 (2009).

Separation dynamics


Separation dynamics

Separation speed

0.5 … 0.8 m/s

Angular velocity

1U CubeSats: < 15 °/s

3U CubeSats: < 5 °/s

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Angular velocity of 1U CubeSat

Angular velocity of 1U CubeSatfor different COG offset and δ =0.5 mm

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Angular velocity of 3U CubeSat

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Angular velocity of 3U CubeSatfor different COG offset and δ =0.5 mm


3-Unit Deployer Simulation

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Installation


Transfer compartment

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Image source: R.N. Akhmetov et al. Low-cost launch services for micro satellites by means of utilization of Soyuz orbital stage Small Satell. Earth Obs. Dig. 7-th Int. Symp. Int. Acad. Astronaut. Berlin, 2009.


Transfer compartment

H≈250-300 km

The orbital stage is rotated by gas engine after the separation of the main payload

The attitude motion of the orbital stage will affect to the motion of the separated CubeSats

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Satellites

Bion-M / Foton-M satellites

Circular orbit H = 500 – 600 km

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Platform for external equipment


H=1000 km, i = 62.8°

H=1500 km, i = 82.4°

H=835 km, i = 98.7° (SSO)

“Volga” upper stage

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Image source: http://samspace.ru/multimedia/images/selected_images/103/


Main payloads

Aist-2, Lomonosov

Additional payload

3U CubeSat SamSat-218/D

Planned start date

December 2015

Space-launch complex

Vostochny

The First Launch

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Modular multiformat design: 1U, 1.5U, 2U, 3U, 3U+

Low angular velocities of separated satellites

High reliability p>0,999

Temperature sensor

Separation sensor

Passive thermal control system

Adaptation to the SRC space vehicles

Key features of the Deployer

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Vadim Yudintsev, Dmitriy Zaretskiy, Eugeni Kosmodemyanskii , Oksana Vagner, Aleksandr Romanov, Maxim Sivov, Maxim Trusov

The CubeSat deployer developer team


Contacts

JSC SRC «Progress», 18, Zemetsa str., Samara, Russia

Phone: +7 (846) 955-13-61 Fax: +7 (846) 992-65-18

e-mail: [email protected]

http://www.samspace.ru

1U-3U+ Cubesat Deployer by JSC SRC "Progress"

Engineering

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