Ракета-носитель LYRA

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http://www.asi.it/en/flash_en/accessing/lyra

LYRA
VEGA evolution

The LYRA project responds to the need for broadening the flexibility and capability of the European family of small- to medium-size launchers. The objective is to make the most of the opportunity of a market which indicates a growth trend and diversification in launch service demand for LEO/MEO orbits.

In addition, the project has been directed to rule out the need for acquiring launches outside of Europe, in particular, for intermediate class satellites. Future ASI missions could be included among these.

The primary objective of the LYRA project is to increase VEGA's performance by about 30%, without significant impacts on the price of the launch service.

In 2005 Phase A of the project was concluded which outlined the reference configuration of the launcher and the main subsystems In April 2007 the contract for Phase B for the "Launch system and liquid propulsion" contract was signed .The programme activities are to take place within a four-year time frame according to the contract's provisions, during which system level activities will take place, including an innovative approach at the GNC and the development of a new flight prototype software and activities in propulsion with regard to the definition of the launcher's third stage (to substitute the current 3° stage ZEFIRO 9 solid, and 4° stage AVUM stockable liquid) made up of the new oxygen-methane MIRA thrusters.

Propulsion activity which makes up 75% of the contract will therefore concentrate on the definition, realization and full-scale test firing of a technological demonstrator realized with the Russian industry, KBKhA.

Статья Афанасьева и Воронцова "Европейские носители : контуры будущего" в НК №7 за 2010 год:

Планы модернизации лёгкого европейского носителя направлены на увеличение энергетики при снижении числа ступеней. По программе Vega-E1 предполагается довести грузоподъёмность ракеты до 2т на полярной орбите. Для этого исходную первую ступень Р80 заменят на Р120, а вторую Z23 - на Z40. Вариант модернизации Vega-E2 более радикален: в рамках программы LYRA на ракете планируется заменить третью и четвёртую ступени одной, с кислородно-метановым ЖРД. Уже ведутся работы по созданию демонстрационного двигателярасширительного цикла Mira с тягой 10 тс (первое огневое испытание должно состояться в 2012 г.). Комбинация "Р120+Z40+ метановая ступень позволит выводить на полярную орбиту  до 3 т. Кроме того для модификации "Веги" ЕКА по-прежнему изучает ступени Р100 и Aestus-2.

ГОДОВОЙ ОТЧЕТ ОАО КБХА за 2007 год

Двигателестроительная тематика востребована в контрактах по внешнеэкономической деятельности, особенно перспективным является контракт с итальянской компанией «Авио» на разработку кислородно-углеводородного ЖРД.

Кислородно-углеводородный с итальянцами это имеется ввиду скоре всего метан кислородный безгенераторный ЖРД на базе РД-0146

http://www.avanturist.org/forum/index.php?topic=101.msg472134#msg472134

РД-0146 на СПГ работает, сколько там УИ получилсь не помню. А вот 11Д55 перевести наСПГ не получилось. В конце 90х было два пуска (инициативных)-оба раза сгорели. Преимущества СПГ следующие: больше удельная, чем на керосине, очень дешево, значительно проще реализуются требования по многоразовости (не нужно уродоваться с термовакуумной сушкой двигателя после ОИ, можно сделать несложный плазменный запальник). Недостатки, Вы справедливо, отметили-низкая плотность, криогеника. Считается, что будущее на первых ступенях за СПГ, да и "вверху" он тоже весьма прилично смотрится. Пока сейчас ведутся в основном НИРовские работы, по схеме "газ-газ" в том числе, но до реального железа пока далеко. РД-0146 на СПГ работает, но пока он никому не нужен.

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http://www.propulsion2010.com/assets/pdf/SP2010_Programme.pdf

L. ARIONE, AVIO S.p.A Development Status of the LM10-MIRA Engine for the  LYRA  Launch  Vehicle  

D. SCARPINO, AVIO S.p.A  LYRA Program: LOX-CH4 Firing Test Activities at FAST2 Stand

A. MOGAVERO, Avio S.p.A Numerical Simulation of Mixing and Combustion in Supercritical O2/CH4 Liquid Rocket Combustion Chamber

К сожалению только названия докладов.  

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http://www.accademiadellescienze.it/media/293?_view=raw
 

Попытка перевода с итальянского:

Национальная программа LYRA / MYRA

Общее между РД-0146 и MYRA:

• турбонасос LOX
• Камера сгорания
• Система управления
• оборудование (краны,
регуляторы, датчики)

Новые компоненты MYRA
• турбонасос СН4
• Форсуночная головка
• Система воспламенения

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Попытка перевода с итальянского:

Национальная программа LYRA / MYRA

Тестирование по программе испытаний прототипа

• Тест маломасштабного инжектора LOX-LCH4 тягой 30 кН на стенде FAST2 (AVIO)
• Тестирование новой системы воспламенения на FAST 2 (AVIO)
• Тестирование компонентов насоса СН4 на стенде FAST2 с доработками (AVIO): • Подшипники в СН4 • индуктор

• Огневые испытания полноразмерной камеры сгорания (с форсуночной головкой AVIO в России (на оборудовании КБХА));
• Огневые испытания полно масштабного прототипа : 900 с Макс +
15 циклов зажигания (запуска) в России (на оборудовании КБХА);
• Огневые испытания прототипа на стенде HYBROB в Италии
(CIRA)

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http://www.enginsoft.it/applications/discipline/meccanica.html

Modellizzazione e Simulazione del Transitori di Accensione del Motore LM-10 MIRA     AVIO/CIRA CFX     2008     ita

Английский вариант:
http://www.enginsoft.com/proceedings/
Требуется регистрация на сайте.

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И здесь тоже.
http://www.sciencedirect.com/science?_ob=ArticleURL&_udi=B6V1N-4WCK05S-3&_user=10&_coverDate=12%2F31%2F2009&_rdoc=1&_fmt=high&_orig=search&_origin=search&_sort=d&_docanchor=&view=c&_searchStrId=1458096936&_rerunOrigin=google&_acct=C000050221&_version=1&_urlVersion=0&_userid=10&md5=febc787e6ebc905a241739d31ed8c15e&searchtype=a

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http://www.aviogroup.com/en/media_room/press_release/2007/engine_for_the_future_lyra_launch_vehicle_is_ignited

Engine for the future Lyra launch vehicle is ignited
   2007/11/07

The first cryogenic engine ever tested in Italy
The first ignition test of the new engine fuelled with liquid oxygen and methane (LOX-CH4) was conducted at the FAST 2 test stand in Colleferro (Rome).
The test performed in Colleferro (Rome) is a major step forward in the development of the MIRA engine that Avio will produce in collaboration with Russian company KBKhA within the framework of the LYRA program funded by the Italian Space Engine. An upgraded version of the new European launcher VEGA, LYRA is expected to achieve an increase in payload, from the current 1,600 kg to 2,000 kg, to be placed in a 700 km polar orbit, without this entailing a significant increase in launch service costs.
The ignition test lasted 2 seconds as planned. It was preceded by an initial flow of liquid oxygen to cool down the feed lines. After this initial test, the testing campaign will go on and will culminate in a firing time of 20 seconds.
The improved performance capabilities of the LYRA launch vehicle compared to the Vega will be based on the introduction of a third stage fuelled with liquid oxygen and methane, developed starting from the MIRA demonstrator, which will replace the current solid propellant third stage (Zefiro 9) and the liquid propellant fourth stage (AVUM) of the Vega.

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Как интересно!

индуктор

Это наверное зажигание.

Интересно, но ведь есть "Урал" совместно с Снекмой, где делается полностью новый двигатель. А про работу КБХА с Фиатом я, лично, никогда не слышал, хотя там выше отцитированно

Интересно, насколько реалистична эта ЛИРА и действительно ли она будет использовать фактически дериватив РД-0146. И да, нигде в слайдах нет распределения работы сторон? AVIO сможет сделать ТНА?

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2007 год:
http://www.oosa.unvienna.org/pdf/publications/st_space_37E.pdf

Italy initiated Phase 1 of the Lyra programme on 20 June. The $47-million contract to study evolutions of the Vega launch vehicle went to a joint venture of Avio and the Italian space agency. Lyra's goal is to enable Vega to boost a 2-tonne payload into a 700-km orbit by replacing the current Vega's Zefiro-9 solid-propellant third stage (see below) and Avum liquid-propellant fourth stage with a new Mira liquid oxygen-methane propulsion unit and developing a new navigation guidance control system. The full-scale Mira demonstrator engine is planned, but would require an additional $93
million to $106 million to complete its development.

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Успешное огневое испытание российско-итальянского жидкостного ракетного двигателя
http://www.kbkha.ru/?p=17&news_id=128

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http://www.esa.int/Our_Activities/Space_Transportation/Vega_Evolution_preparation_and_Space_Rider_development

Vega Evolution preparation and Space Rider development

30 November 2017

ESA signed two contracts today with Italy's ELV and Thales Alenia Space to extend Europe's Vega space system capabilities and competitiveness, and develop Space Rider for payload return capability.

ELV will develop and extensively test a new European cryogenic upper stage engine development model for Vega evolutions beyond 2025, based on low-cost liquid oxygen–methane propulsion.

The engine replaces the current Zefiro-9 solid-propellant motor and the AVUM upper stage engine for Vega-E, matching Vega-C performance at significantly reduced costs and improved flexibility.

In addition, complementing the Small Spacecraft Mission Services (SSMS) programme already under development, ELV will investigate how existing motors such as the P120, P80, Z40, Z23, Z9, could be used to create a family of Vega-E configurations able to place payloads of 200–2500 kg into orbit.

This will incorporate promising technologies in the areas of 3D layer-by-layer additive manufacturing, hydrogen peroxide as low-toxicity propulsion, and advanced avionics, offering competitive production and operational costs.

The contract concerning the Vega evolution activities worth €53 million was signed by ESA Director of Space Transportation Daniel Neuenschwander and ELV Managing Director Andrea Preve at ESA headquarters in Paris.

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http://www.avio.com/en/press-release/successfully-tested-the-m10-methane-engine-prototype/

13 Nov 2018                   
Successfully tested the M10-methane engine prototype
                      

Colleferro 13 November 2018 – Today in Colleferro Avio successfully tested the prototype of the new M10 liquid oxygen-methane engine, developed by Avio in partnership with the European Space Agency within the Vega E (Vega Evolution) program. The prototype is a scaled model of the third stage propulsion engine which will equip the Vega launcher starting from 2024.
The technology adopted represents a true innovation for both propulsion efficiency and environmental sustainability, given its reduced emissions and combustion waste. The prototype has been structured through additive manufacturing following Avio's SMSP (Single Material Single Part) patent, exploiting advanced 3D-laser printing technologies.
Giulio Ranzo, CEO of Avio, commented: "Avio is very satisfied with the M10 test result, the first European prototype of a LOx-Methane engine, a truly cutting-edge technology with extremely low environmental impact, available to very few players worldwide.  In the medium term, this engine will allow to replace the last two propulsion stages (Z9 and Avum) with a new cryogenic propulsion stage far more efficient and flexible. Our objective is to keep on increasing Vega's cost competitiveness and maneuverability to orbit small satellites in low earth orbit, while the possibility to launch bigger satellites in geostationary and medium orbits will be ensured by Ariane 6".