VEGA Launch Vehicle: Trajectory & Attitude Control System

Alma Mater Studiorum Università di Bologna. School of Engineering and Architecture - Forlì

VEGA Launch Vehicle: Trajectory & Attitude Control System

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Seminar Contents


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Contents 

Brief GMV group overview



VEGA Launcher Programme



Ascent Trajectory Description



VEGA: Its origin from early 60ths



VEGA VV01 Launch



Launcher Attitude Control System



Conclusion


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WHO

WE ARE


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GENERAL 

Multinational conglomerate founded in 1984



Private capital



Offices in Spain, Portugal, Poland, USA, Germany, Romania, India and Malaysia



Over 1,100 employees all over the world



Roots tied to the Space and Defense industries



Currently operating in Aeronautics, Space, Defense, Security, Transportation, Healthcare and ICT industries.


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GMV IN THE WORLD

SPAIN MADRID – HEADQUARTERS VALLADOLID



Offices in Spain, Portugal, Poland, USA, Germany, Romania, India and Malaysia

SEVILLE BARCELONA

VALENCIA CANARY ISLANDS

 

LEON

Technology deployed in 5 continents

ZARAGOZA PORTUGAL

Permanent staff in 10 countries

USA GERMANY POLAND ROMANIA MALAYSIA INDIA

€

115M€

(total turnover)

Over 1.100 employees VEGA Launch Vehicle: Trajectory & Attitude Control System

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INDUSTRIES       



Aeronautics Space Defense Security Healthcare Transportation Telecommunications Public Sector and Corporate ICT


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GMV IN NUMBERS: SUSTAINED GROWTH 

Solid economical growth financed by the resources generated by the company: 50% in the last 4 years



Growth in all sectors, particularly in Transport and Space



Reasonable overall expectative for 2012 and 2013


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STRONG EMPLOYMENT GENERATION 8%

4%

3% 12%



GMV employees today over 1.100 people from which around 85 in Portugal

73% Tit. Universitario Grado Superior (inc. Doctor) Tit. Universitario Grado Medio Ciclo Grado Superior Técnico Administrativo



Over 85% with university degrees with engineering, physics and maths profiles



In the last 4 years GMV generated over 70 new employments in Space sector


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[Analysis by Sector]

Talk

VEGA Launcher


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VEGA LAUNCHER PRESENTATION VEGA is the smallest launcher of the European fleet operated by Kourou Space center in the French Guiana.

Main Data

Height

30 m

Diameter

3m

Liftoff mass

137 tonnes

Payload mass*

1500 kg


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VEGA LAUNCHER ELEMENTS VEGA is a four stage launcher 

First three stages uses a solid propellant (HTPB) – P80 – Z23 (Zefiro 23) – Z9 (Zefiro 9)



Forth stage is equippend with re-startable liquid propelent – AVUM (Attitude Vernier Upper Module)


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VEGA LAUNCHER ELEMENTS AVUM

P80 Height

10.5 m

Diameter

3m

Propellant mass

88 t

Burn time

107 s

Max. engine thrust

3040 kN

Height

1,7m

Diameter

1.9 m

Propellant mass

550 kg

Burn time

317 s

Max. engine thrust

2450 N

Z23

Z9

Height

7.5 m

Height

3.85 m

Diameter

1.9 m

Diameter

1.9 m

Propellant mass

23.9 t

Propellant mass

10.1 t

Burn time

71.6 s

Burn time

117 s

Max. engine thrust

1200 kN

Max. engine thrust

313 kN


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LAUNCH SEQUENCE Time

Event

Altitude km

Speed km/s

T0

P80 ignition

n/a

n/a

0.3 s

Liftoff

n/a

n/a

1 min 55.6 s

Zefiro-23 ignition

61

1.7

3 min 38.5 s

Zefiro-9 ignition

135

3.8

3 min 43.5 s

Fairing separation

138

3.9

5 min 47.1 s

Zefiro-9 shut down

182

7.7

5 min 54.1 s

AVUM 1st boost

185

7.7

8 min 45 s

AVUM shut down,

260

7.8

48 min 7.3 s

AVUM 2nd boost

1447

6.6

52 min 10.5 s

AVUM shut down

1450

6.9


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LAUNCH PROFILE


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Launcher Main Facts


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VEGA -PROGRAMM VEGA stands in Italian  

VEGA-Vettore Europeo di Generazione Avanzata VERTA-Vega Research and Technology Accompaniment


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VEGA ORGANIZATION


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Talk

VEGA history: back to 60ths


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VEGA HISTORY 

Vega officially became an ESA programme in June 1998



The Vega programme has its origins back in the 1990s



The ASI Italian space agency and Italian industry developed concepts and began pre-development work based on their established knowhow in solid propulsion.



Italian Space activities started in 1964 with the San Marco project and the San Marco-1 Launch


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SCOUT and SAN-MARCO PROJECT 





Italy was the 3rd Country in the World to launch a satellite in 1964 with the San-Marco-1 Satellite

In 1967 San-Marco2 was launched by the San Marco platform from Kenya Coast

The programme S.Marco performed almost 10 launches in twenty years


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SAN MARCO SCOUT LAUNCH RECORD Launch Date

Payload

26-04-1967

San Marco 2

12-12-1970

SAS-A

24-04-1971

San Marco-3

15-11-1971

S-Cubed A

15-11-1972

SAS-B

18-02-1974

San Marco-4

15-10-1974

Ariel 5

07-05-1975

SAS-C

25-03-1988

San MarcoD/L

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Comments San Marco 1 had previously been launched from Wallops i n the USA

Satellite operations were directed from a control center at the Appleton Lab, U.K.

SAN-MARCO Project 

SAN-MARCO project was fully developed under the leadership of Prof. Luigi Broglio who instituted the school of Aerospace Engineering in Rome in 1952 on the previous school of aeronautical engineering


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SAN-MARCO Photos Gallery


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Last Scout Launcher in Rome !!!


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Talk

VEGA Qualification Launch: VV01


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VV01- VEGA Qualification Flight 

Vega's first launch, dubbed VV01, is planned for 13 February 2012.



The vehicle will lift off from the new Vega launch site at Europe’s Spaceport in Kourou, French Guiana, carrying nine satellites into orbit: – LARES laser relativity satellite – ALMASat-1 from University of Bologna – Seven CubeSats from European Universities.



The mission qualified the overall Vega system


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VV01 ALMASAT


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VV01 Launch from Jupiter Control Room


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VEGA-MAIDEN FLIGHT

GMV Partecipation VEGA programme


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VEGA-GNC

FPSA



Two years project aiming at developing the launcher Flight Program Software Alternative (FPSA)



GMV personnel embedded in the GNC System Design Team at ELV

– Launcher Reaction and Attitude Control System – Launcher Guidance Algorithms Improvements – Fault Detection Identification and Recovery (FDIR)


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GMV Contribution 

GMV is partecipating to the VEGA Programme with an important involvement in the FPSA project



FPSA: Stands for Flight Program Software Alternitive



This represents a new version of the FPS available since the second flight

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GMV contribution in many critical areas – GNC-Algorithms • •

Navigation and Guidance Roll and Attitude Control System

– Quality Assurance – RAMS Courtesy of ELV VEGA Launch Vehicle: Trajectory & Attitude Control System

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How does GNC work ? INERTIAL NAVIGATION UNIT (NAVIGATION )

ONBOARD COMPUTER (GUIDANCE )

TVC

(CONTROL )


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What is the origin of Guidance Navigation and Control (GNC) NAVIGATION WHAT

WHERE

GUIDANCE IS THE NEW COURSE TO THE DESTINATION

?

CONTROL HOW TO CONTROL THE BOAT TO KEEP THE NEW COURSE


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AM

I?

Satellite Navigator in our car is not different !!! NAVIGATION AND GUIDANCE

CONTROL


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Navigation 

Both Vega and Ariane5 make use of the same inertial navigation platform,



Thales Avionics Quasar 3000, a strapdown platform based on linear accelerometers and ring-laser-gyros



Performances are quoted as 1σ – Attitude drift: 0.03 deg/h – Position drift: 1.5 Km/h.



It provides the pitch and yaw control during propulsive phase of the flight with input data from Vega control system.

Gyro

Attitude rate

INS

AHRS

Attitude

∆v in inertial att in inertial

Accelerometer


Local acceleration

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Guidance 2nd step in the Navigation › Guidance › Control chain Function •

Compute the attitude angles to command the control system to follow optimal trajectory

•

Process and transform Navigation Data to compute error in position and velocity with respect to required

Open Loop Guidance • During P80 and Z29 – Atmospheric Flight – Pitch / Yaw programmes Orbital manoeuvres, Coasting - Pointing to programmed attitude • Second Payload Injection – Pointing, ∆velocity to programmed Closed Loop Guidance • During Exo-Atmospheric boosts – Z9, AVUM1, AVUM2 • Closed loop optimum pitch and yaw computation based on analytical formulae


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Open Loop Guidance: Conservative Scheme   

Main objective is to reduce the aerodynamic loads during the atmospheric flight The launcher constantly try to keep to zero the Angle of Attack The resulting trajectory is known as: “Gravity Turn”

Relative Velocity Vector


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Closed Loop Guidance. Adaptive Scheme 

Guidance commands are computed based on actual position and velocity in order to get the final prescribed orbit

Final Orbit Propelled Arc

Thrust Direction VEGA Launch Vehicle: Trajectory & Attitude Control System

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Null Miss Condition: Manoeuvre from ICBMs X-Axis

Vˆn Vˆ0



  V

  R     a tan  V0   V0  

 R      0  Y-Axis


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ICBM: Minuteman Venting Port ?


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Open Loop / Closed Loop


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Attitude control: Thrust Vector Control (TVC)

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The Thrust Vector Control (TVC) system comprises two electroactuators that operate the gambled engines.



It provides the pitch and yaw control during propulsive phase of the flight with input data from Vega control system.


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Attitude control: Roll and attitude control system (RACS) 

The attitude control is provided by two clusters of three cold gas (GN2) thrusters during: – Ballistic flight (3-axis or spin-up)

– Roll control during the propelled phases



Each thruster provides a thrust of 50 N, fed from one single vessel

X

6 4

5

X

15°

Y

5 6

1

2 3


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Z

Y.

2

3

15° 15°

Z

Attitude control phases TVC • (pitch and yaw) RACS • (roll rate and angle)

RACS control: • 3 axes stabilization • Attitude maneuvers • Payload pointing


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Conclusions and Remarks


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Conclusion and Remarks 

On 6th of May 2013 VV02 was successfully performed with FPSA.



Vega Reached two different orbits releasing several satellites.



This was the first VERTA flight



Several Flights have been already scheduled for the launcher including the interesting VEGA+IXV


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Questions


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Thank you

Emanuele Di Sotto Head of EDL & Launchers Space Systems-GNC Aerospace www.gmv.com


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