Orion

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Испытания основного парашюта 1-й ступени РН Арес-1 8 окт 2009

Угу... таки спасать ступень будут
Тока почему один кумпол? У евонного прародителя три купола, если верить камере на ускорителе

Ares I First Stage. Powering NASA's newest rocket

Because of the heavier weight and higher speed of the Ares I booster as well as its drop from a higher altitude, the launch vehicle's parachutes are much larger and stronger than those used for the space shuttle boosters. The first parachute to be deployed in the three-stage recovery system is the pilot parachute, measuring approximately 11.5 feet in diameter. As the pilot parachute deploys, it automatically releases the 68-foot-diameter drogue parachute, which is used to maneuver the booster into a vertical position and further slow its descent. Once the booster is slowed, a cluster of three main parachutes, each 150 feet in diameter, is deployed. The main parachutes continue to slow the booster prior to splashdown in the ocean.

Всё верно - будет 3 :!: основных парашюта.
Масса отработавшей ступени 586344 - 504516 = 81828 кг.
В  октябре испытали один, наверняка в 2010 проведут испытание "связки" из 3х.  :idea:

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Архив новостей НК Выпуск № 812, текущий.

11.10.2009 / 00:05   Проведено успешное испытание парашюта для "Ареса"

      Как сообщила пресс-служба NASA, 8 октября нынешнего года на полигоне Армии США "Юма" U.S. Army's Yuma Proving Ground) в штате Аризона было проведено успешное испытание парашюта, предназначенного для возвращения на Землю первой ступени перспективной ракеты-носителя Ares-1.
      Макет ступени был сброшен с борта самолета С-17 с высоты 7,5 км. Раскрывшийся вслед за этим парашют обеспечил успешное приземление груза.
      Состоявшееся 8 октября испытание было девятым в ряду испытаний парашюта для Ares-1.

Чудеса перевода  (Lost in translation):
- Сбрасывался не макет ступени в натруральную величину (конечная масса ступени 81828 кг) а груз массой 32658 (~40% от массы ступени);
- По поводу высоты - если первести футы в метры то будет 7620 м
Уважаемый К.И., исправьте пожалуйста.

[Agent]

[Agent]

http://www.nasa.gov/mission_pages/constellation/ares/ullage_motor.html
NASA's Marshall Center Completes Successful Ullage Motor Development Test for Ares I Rocket

[Agent]

A-3 Test Stand Construction Moves Forward With Tank Installations

Oct. 2, 2009 -- Nine water, isopropyl alcohol (IPA) and liquid oxygen (LOX) tanks have been delivered and installed, with five more water tanks scheduled to arrive in upcoming weeks. The two IPA tanks shown on the left and the three LOX tanks shown on the right are 35,000 gallons each. The four water tanks in the center are 39,000 gallons each. All 14 of the tanks will be used by the chemical steam generators units that will be installed on the A-3 stand for creating simulated altitudes of up to 100,000 feet. The IPA and LOX tanks will fuel the generators; the other tanks will provide the water needed to generate the steam necessary for creating the simulated altitudes. The tanks are 65 to 85 feet tall and weigh 270,000 to 320,000 pounds each. The A-3 Test Stand remains on schedule for completion and activation in 2011.

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PDFs from NASA Technical Report Server:

Developing the Parachute System for NASA's Orion: An Overview at Inception
Machin, Ricardo; Taylor, Anthony P.; Royall, Paul
Johnson Space Center 2007 - 16 Pages

As the Crew Exploration Vehicle (CEV) program developed, NASA decided to provide the parachute portion of the landing system as Government Furnished Equipment (GFE) and designated NASA Johnson Space Center (JSC) as the responsible NASA center based on JSC s past experience with the X-38 program. JSC subsequently chose to have the Engineering Support contractor Jacobs Sverdrup to manage the overall program development. After a detailed source selection process Jacobs chose Irvin Aerospace Inc (Irvin) to provide the parachutes and mortars for the CEV Parachute Assembly System (CPAS). Thus the CPAS development team, including JSC, Jacobs and Irvin has been formed. While development flight testing will have just begun at the time this paper is submitted, a number of significant design decisions relative to the architecture for the manned spacecraft will have been completed. This paper will present an overview of the approach CPAS is taking to providing the parachute system for CEV, including: system requirements, the preliminary design solution, and the planned/completed flight testing.

2008 Accomplishments for CEV Parachute Assembly System (CPAS)
Martin, Ricardo
Johnson Space Center 2009 - 4 pages

The Crew Exploration Vehicle (CEV) Parachute Assembly System (CPAS) project is responsible for the design, development, fabrication, qualification and delivery of the CEV parachute system to support the Orion pad/ascent flight tests and the first three orbital flight tests (including the first human mission). This article will discuss the technical and research achievements accomplished in calendar year 2008, broken into three key categories: prototype testing and analysis (also referred to as the Generation 1 design), system requirements definition and design of the flight engineering development unit, and support for the Orion vehicle flight testing (primarily Pad-Abort 1).

Development and Testing of the Orion CEV Parachute Assembly System (CPAS)
Johnson Space Center 2009 - 12 pages

The Crew Exploration Vehicle (CEV) is an element of the Constellation Program that includes launch vehicles, spacecraft, and ground systems needed to embark on a robust space exploration program. As an anchoring capability of the Constellation Program, the CEV shall be human-rated and will carry human crews and cargo from Earth into space and back again. Coupled with transfer stages, landing vehicles, and surface exploration systems, the CEV will serve as an essential component of the architecture that supports human voyages to the Moon and beyond. In addition, the CEV will be modified, as required, to support International Space Station (ISS) mission requirements for crewed and pressurized cargo configurations. Headed by Johnson Space Center (JSC), NASA selected Jacobs Engineering as the support contractor to manage the overall CEV Parachute Assembly System (CPAS) program development. Airborne Systems was chosen to develop the parachute system components. General Dynamics Ordnance and Tactical Systems (GD-OTS) was subcontracted to Airborne Systems to provide the mortar systems. Thus the CPAS development team of JSC, Jacobs, Airborne Systems and GD-OTS was formed. The CPAS team has completed the first phase, or Generation I, of the design, fabrication, and test plan. This paper presents an overview of the CPAS program including system requirements and the development of the second phase, known as the Engineering Development Unit (EDU) architecture. We also present top level results of the tests completed to date. A significant number of ground and flight tests have been completed since the last CPAS presentation at the 2007 AIAA ADS Conference.

Design of Launch Abort System Thrust Profile and Concept of Operations
Langley Research Center 2008 - 11 pages

This paper describes how the Abort Motor thrust profile has been tailored and how optimizing the Concept of Operations on the Launch Abort System (LAS) of the Orion Crew Exploration Vehicle (CEV) aides in getting the crew safely away from a failed Crew Launch Vehicle (CLV). Unlike the passive nature of the Apollo system, the Orion Launch Abort Vehicle will be actively controlled, giving the program a more robust abort system with a higher probability of crew survival for an abort at all points throughout the CLV trajectory. By optimizing the concept of operations and thrust profile the Orion program will be able to take full advantage of the active Orion LAS. Discussion will involve an overview of the development of the abort motor thrust profile and the current abort concept of operations as well as their effects on the performance of LAS aborts. Pad Abort (for performance) and Maximum Drag (for separation from the Launch Vehicle) are the two points that dictate the required thrust and shape of the thrust profile. The results in this paper show that 95% success of all performance requirements is not currently met for Pad Abort. Future improvements to the current parachute sequence and other potential changes will mitigate the current problems, and meet abort performance requirements.

Ares I-X Flight Test Philosophy
Davis, S. R.; Tuma, M. L.; Heitzman, K.
Marshall Space Flight Center 2007 - 27 Pages.

In response to the Vision for Space Exploration, the National Aeronautics and Space Administration (NASA) has defined a new space exploration architecture to return humans to the Moon and prepare for human exploration of Mars. One of the first new developments will be the Ares I Crew Launch Vehicle (CLV), which will carry the Orion Crew Exploration Vehicle (CEV), into Low Earth Orbit (LEO) to support International Space Station (ISS) missions and, later, support lunar missions. As part of Ares I development, NASA will perform a series of Ares I flight tests. The tests will provide data that will inform the engineering and design process and verify the flight hardware and software. The data gained from the flight tests will be used to certify the new Ares/Orion vehicle for human space flight. The primary objectives of this first flight test (Ares I-X) are the following: Demonstrate control of a dynamically similar integrated Ares CLV/Orion CEV using Ares CLV ascent control algorithms; Perform an in-flight separation/staging event between an Ares I-similar First Stage and a representative Upper Stage; Demonstrate assembly and recovery of a new Ares CLV-like First Stage element at Kennedy Space Center (KSC); Demonstrate First Stage separation sequencing, and quantify First Stage atmospheric entry dynamics and parachute performance; and Characterize the magnitude of the integrated vehicle roll torque throughout the First Stage (powered) flight. This paper will provide an overview of the Ares I-X flight test process and details of the individual flight tests.

[Старый]

А на чём улаживательный мотор работает? Топливо какое?

[integrall]

Пишут только:

The ullage settling motor is a small, solid rocket motor

only 9 inches in diameter and 47 inches in length,

the motor will fire for four seconds

[Bell]

Пишут только:

The ullage settling motor is a small, solid rocket motor

only 9 inches in diameter and 47 inches in length,

the motor will fire for four seconds

Ну да, только вот выхлоп у него какой-то не сОлидный

[Брабонт]

Ну да, только вот выхлоп у него какой-то не сОлидный

Необычный факел для РДТТ. Скорее подумал бы про гибрид.

[Дмитрий В.]

Ну да, только вот выхлоп у него какой-то не сОлидный

Необычный факел для РДТТ. Скорее подумал бы про гибрид.

Ах, ты, черт! Сколько пищи для изысканий опровергастов: "Амеры разучились делать РДТТ!" :lol:

[Agent]

Это слегка отмодифицированный двигатель отделения шаттловых бустеров
Тут хорошо видно

ЗЫ: The propellant is an ammonium perchlorate-hydroxyl-terminated polybutadiene (AP-HTPB) formulation with 2% aluminum.

[Старый]

Да уж, не сОлидный, и тем более не смесевой. На гомогенный ещё можно было бы подумать.

[Dude]

По мне так нормальный "nearly smokeless exhaust" свойственный новым твердотопливным смесям и двигателям с большим давлением в КС. Если это что-то типа AP/HTPB/Al 80/18/2( или даже 88/10/2), то такой вид выхлопа вполне объясним.

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[Salo]

http://www.comspacewatch.com/news/viewpr.html?pid=29396

ATK Delivers A High-Tech First to NASA - A Crew Module Structure Made of Composite Materials

ATK's Innovative Engineering and Manufacturing Expertise Produces Lightweight Composite Structure for Evaluation

ATK's Composite Crew Module to Undergo Structural Testing by NASA

Alliant Techsystems (NYSE: AT) has delivered a technological first to NASA: a full-scale, crew module structure made of composite materials. The Composite Crew Module (CCM) is a unique capsule design that has the potential to reduce the overall weight of future manned launch vehicles.

Composite structures reduce launch costs through weight savings and are presently used on a variety of space launch vehicles and aerospace structures. However, the CCM is unique in that it was specifically designed and built to resemble a space capsule. Full-scale structural testing will be performed at NASA's Langley Research Center to determine the strength and viability of the composite structure. During the destructive testing, the CCM will be placed under load conditions similar to those observed during launch, on-orbit, landing, and abort scenarios.

Led by the NASA Engineering and Safety Center (NESC), ATK was part of a team of NASA and industry experts who designed and fabricated the CCM to demonstrate how composite materials could be used to develop a pressurized space capsule. ATK is a major composite manufacturer and supplier for modern military and commercial aircraft, and space launch vehicles. ATK provided composites design, analysis, manufacturing and assembly expertise for the CCM program.

"ATK has decades of experience in building composite structures for launch vehicles, military aircraft, and most recently commercial aircraft such as the Airbus A350," Jack Cronin, President, ATK Mission Systems. "We have applied our innovative engineering and manufacturing capabilities to help the CCM team build a cutting-edge, composite space structure. We demonstrated our ability to perform, partner and deliver an advanced composite structure that's never been built for NASA."

Fabricated and assembled at ATK's Iuka, Miss. facility, the CCM combines some of the most advanced composite manufacturing technologies in use today. Constructed in two primary sections, the upper and lower shells are joined together with a splice joint and cured using out-of-autoclave technology. The bonding of the composite assemblies and integration of metal hardware were achieved by combining existing technology and ATK's innovative manufacturing processes.

ATK is a premier aerospace and defense company with more than 18,000 employees in 22 states, Puerto Rico and internationally, and revenues of approximately $4.8 billion. News and information can be found on the Internet at www.atk.com.

[Чебурашка]

Изделие для макетирования баков, трубопроводов, кабелей и прочей начинки в командном модуле "Ориона" в центре им. Кеннеди

[bsdv]

Изделие для макетирования баков, трубопроводов, кабелей и прочей начинки в командном модуле "Ориона" в центре им. Кеннеди

Интересно, когда же CAD/CAM окончательно добьет "дедовские методы" , и добьет ли?

[Местный]

Никогда . Результат макетирования обязательно надо щупать руками , а то гладко было на бумаге . . . .

[Лютич]

ага. и только на готовом издели внезапно обнаруживается, что хрен ты просунешь руку в оставленый для обслуживания проем, если толко они у тебя не совсем тоненькие