우주선용 열 차폐 및 열 보호 시스템(TSP) 기술 동향 및 시장 전망 2025-2035

우주선 대기권 재진입을 위한 타일 기반, 삭마형, 확장형 공기역학적 감속기 열 보호 시스템(TSP) 및 열 차폐에 대한 기술평가와 향후 10년간 시장 전망을 포괄하는 보고서

모두 보기 설명 목차, 표 및 그림 목록 자주 묻는 질문 가격 Related Content
우주선의 열 보호 시스템(TSP) 기술환경을 분석하고 있는 이번 보고서에서는 과거 및 미래의 TSP 재료 및 설계를 분석하고, 우주 물류의 새로운 기회를 평가하여 2035년까지의 시장 예측 및 전망을 제공합니다.
이 보고서에서 아래와 같은 주요 정보를 제공합니다.
 
우주 산업 개요
  • 다양한 목적(발사 사업자, 상업용 저궤도(LEO) 화물 운송)의 상업적 우주 사업자의 증가
  • 열 보호 시스템용(TSP) 소재 설계에 대한 상업화의 영향
  • 화물 및 유인 우주선 개발 타임라인
 
대기권 재진입
  • 재진입 물리학 및 대기 가열 개요 (대류열 및 복사열로 구분)
  • 둥근 형상(Blunt Body) 개념과 열 보호 시스템의 필요성
  • TPS 소재 선택 및 설계, 다양한 범주의 성능 한계
 
타일 기반 TPS
  • 타일 기반 TPS의 밀도, 방사율, 열전도율 및 온도 한계
  • 셔틀 시대부터 스타십까지 타일 기반 시스템의 역사적 개요
  • 단열 타일, 코팅, 세라믹 블랭킷 및 고온 구조물 등 부품별 개발 경로
  • 실리카 기반 타일, 강화 탄소-탄소, TUFROC, 스타쉽 타일
  • 소재 밀도 및 온도 한계 벤치마킹
 
확장 가능한 공기역학 감속기
  • 발사 페어링(Launch Fairing) 직경 증가가 탄소 계수(Ballistic Coefficient) 및 최대 가열에 미치는 영향
  • NASA의 HIAD 및 LOFTID. 시험 프로그램 개요, 제작 기술 및 사용된 소재
  • 확장 가능한 공기역학 감속기가 상업용 부스터의 재사용성을 실현하는 원리
  • 기계적으로 전개되는 공기역학 감속기
  • 시험 비행을 계획중인 주요 상용 업체들
 
삭마형 TPS
  • 가장 까다로운 재진입 환경에서 삭마형 TSP의 필요성 개요
  • 삭마형 및 열분해 열전달 메커니즘 요약
  • 삭마형 제품군 및 개발 일정 요약
  • 벌집 구조 삭마형 TSP(예: AVCOAT)
  • PICA 열 차폐 및 잠재적 재사용 가능성
  • 카본 페놀 열 차폐
  • NASA 의 HEEET 와 같은 신흥 3D 직조 열 보호 시스템
 
시장 전망
  • 카테고리 및 운영주체 (정부 vs. 민간)별 향후 10년간 세부 TSP 시장 전망
 
이 보고서에서 다루는 주요 내용은 아래와 같습니다.
 
1. 핵심 요약
2.우주 산업 개요
  • 상업적 우주 사업자의 증가
  • 미세중력(Microgravit Manufacturing) 제조의 등장
  • 소재 설계에 대한 상업화의 영향
  • 화물 및 유인 우주선 개발 타임라인
3. 대기권 진입
  • 열 보호 시스템(TSP) 필요성 및 둥근 형상(Blunt Body) 개념
  • 대류 및 복사열
  • TPS 압력 및 가열 성능 범위
4. 타일 기반 열 보호 시스템(TPS)
  • 소재 요구 사항
  • 부품별 개발 경로
  • 실리카 기반 타일, 강화 탄소-탄소, TUFROC, 스타쉽 타일
  • 소재 밀도 및 온도 한계 비교
5. 확장형 공기역학적 감속기
  • 탄도 계수 및 가열 영향
  • HIAD, LOFTID 테스트 프로그램
  • 상업용 부스터 재사용성
  • 기계적으로 전개되는 공기역학적 감속기
6. 삭마형 열 보호 시스템(TSP)
  • 삭마형 및 열분해 열전달 메커니즘
  • 삭마형 제품군 및 개발 일정 요약
  • 벌집구조 삭마형 TSP(예: AVCOAT)
  • PICA 열 차폐
  • 카본 페놀(Carbon Phenolic) 열 차폐
  • 3D 직조 열 보호 시스템, HEEET
7. 시장 전망
 
Thermal protection systems (TPS) are designed to protect spacecraft from the enormous aerodynamic heating generated during the entry into an atmosphere. The hottest parts of the Space Shuttle during re-entry reached 1,650°C, while the Galileo probe that entered Jupiter's atmosphere reached 16,000°C. Protecting the spacecraft during this intense thermal heating is the sole purpose of a TPS - and since the earliest days of space travel, innovations and advancements in TPS have been crucial to enabling space missions. The space industry is rapidly evolving, with commercial operators beginning to take on roles in the emerging 'Space Economy' and seeking to reduce launch costs. Governmental agencies remain at the forefront of material science and development as mission goals become more ambitious, from landing greater payloads on Mars to exploring the outer planets. This report contextualizes the TPS requirements of different re-entry profiles and breaks down the core categories of TPS.
 
 
Performance envelopes for a range of thermal protection systems. Commercial interest is focused on insulation tiles through to PICA. Pressures and temperatures beyond this are only encountered in the exploration of outer planets or exceptionally large payloads - currently the mission domain of governmental agencies.
A new geometry for Starship seeks to solve the problems of the Shuttle-era TPS
For the 'lower' heating rates (1,650°C is still beyond the melting point of stainless steel) encountered on returning from a low-Earth-orbit (LEO) - high-temperature insulative silicon tiles are an often-used approach. Because the overall heat flux is lower, utilizing reusable TPS is possible and desirable as it lowers the cost to orbit and enables a higher launch cadence. The NASA Space Shuttle program was intended to provide a low-cost, rapidly reusable spacecraft that could ferry crew and cargo from the surface to a LEO. However, the Shuttle's TPS was plagued by high construction costs, lengthy maintenance requirements, and damaged tiles were the cause of the Columbia disaster.
 
The promise of rapidly reusable silicon-tile based insulation remains appealing, and SpaceX has opted for this TPS for its Starship upper-stage. However, several key design differences of Starship could potentially negate some of the cost and performance problems of the Starship. The report breaks down how tile shape, spacecraft geometry, and choice of substructure material could all contribute to greater TPS performance. The report also outlines the developments of the key subcategories of reusable TPS, from advanced carbon-carbon and other hot structures to developments in high emissivity coatings and TUFROC, offering performance data and material composition throughout.
 
Inflatable TPS - an emerging option at the forefront of development
One of the fundamental constraints of any launched spacecraft is the 'rocket-fairing', that is, the width of the rocket nose at launch. However, the physics of atmospheric entry favors the largest heat shield diameter possible. A novel and emerging technique is to use an inflatable or mechanically expandable TPS that is stowed on launch but expands before re-entry. This is seen as a viable way to enable greater payload missions, with some commercial operators also pursuing this avenue for LEO cargo return. This approach comes with a host of technical challenges, but great advancements are being made, and in 2022, NASA completed the first successful LEO re-entry with its LOFTID (Low Earth Orbit Flight Test of an Inflatable Decelerator). The report unpacks the key material opportunities in these TPS, such as aerogel insulators, high-temperature ceramic fabrics, and the need for solid-gas generators. Potential applications for this development are also examined, including high-value booster engine return, high-altitude landings, and higher payload delivery.
 
Ablators - from Apollo to Orion
 
Generic ablator structure beginning with a substrate material (often carbon or silica fibers) which are impregnated with a resin (phenolic resin is common) and additives (such as silica micro balloons). An additional structure (such as a honeycomb matrix) may be added for support. Pyrolysis converts the 'virgin' material into 'char, ' transferring heat away from the structure. Source: IDTechEx.
 
An ablative TPS is the ultimate form of protection, used when a spacecraft's reentry speed means all other options would simply not stand up to the heat. Ablation can aptly be described asenergy management through material consumption, and the ablator itself disintegrates in a controlled manner during re-entry, transferring away heat and protecting the substructure beneath. Ablators have been used from lunar returns (AVCOAT honeycomb on Apollo) to entry into Jupiter (Carbon Phenolic). This report breaks down the material families of ablators, highlighting their material construction, installation, and performance envelopes. Historical context is provided, such as the atrophy of Carbon Phenolic capabilities due to the cessation of aerospace-grade Rayon production, and where 3D-woven fabrics may fit in as a replacement. Commercially developed variants, such as SpaceX's PICA-X (Phenolic impregnated carbon ablator-X) are covered, as well as assessing the potential semi-reusability of ablators well within their performance envelope.
Industry overview and market analysis
As part of its research, IDTechEx has examined several existing and upcoming space cargo/crew vehicles with a variety of TPS selections. Factors such as launch cadence, dimensions, and material selection provide a detailed assessment of the state of the industry. This extensive market analysis also forms the foundation of IDTechEx's market forecasts for TPS systems up to 2035, split by material demand (in m2) and USD.
 
IDTechEx's research includes coverage of several key players and projects in space crew and cargo transfer vehicles, a key application of TPS. Source: IDTechEx.
 
Key Aspects
A review and context of the space industry
  • The emerging presence of commercial space operators for a variety of purposes (launch operators, commercial LEO cargo transfer)
  • Implications of commercialization on material design for thermal protection systems
  • Development timeline of cargo and crewed spacecraft
 
Atmospheric Entry
  • Overview of reentry physics and atmospheric heating (split by convective and radiative heat.
  • Blunt body concept and the need for thermal protection systems.
  • Material selection and design for TPS, and performance envelopes for a variety of categories.
 
Tile-based TPS
  • Density, emissivity, conductivity and temperature limits for tile-based TPS.
  • Historical overview of tile-based systems, from the Shuttle-era to Starship.
  • Development pathway of component categories, from high-insulation tiles, coatings, ceramic blankets, and hot structures
  • Silica based tiles, Reinforced-carbon-carbon, TUFROC, Starship tiles
  • Material density and temperature limit benchmarking
 
Expandable Aerodynamic Decelerators
  • How increasing the diameter beyond the launch fairing affects ballistic coefficient and peak heating.
  • Overview of NASA's HIAD and LOFTID test programs, including construction techniques and materials used.
  • How expandable aerodynamic decelerators could unlock commercial booster reusability.
  • Mechanically deployable aerodynamic decelerators
  • Key commercial players with test-flights planned.
 
Ablative TPS
  • Overview of the need of ablators in the most challenging reentry environments.
  • Summary of ablative and pyrolysis heat transfer mechanisms
  • Summary of ablator families and development timeline
  • Honeycomb ablators (e.g. AVCOAT)
  • PICA heat shields, and its potential reusability.
  • Carbon Phenolic heat shields
  • Emerging 3D Woven thermal protection systems, such as NASA's HEEET
 
Forecasts
  • Granular 10-year market forecasts for TPS, split by category and operators (governmental vs commercial).
Report MetricsDetails
Historic Data1991 - 2024
CAGRThe global market for Thermal Protection Systems for Spacecraft will reach US$90 million in 2035, a CAGR of 3.3% compared with 2024.
Forecast Period2025 - 2035
Forecast UnitsUSD, Area (m2)
Regions CoveredWorldwide
Segments CoveredThermal protection systems; ablative systems, tile-based systems
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1.EXECUTIVE SUMMARY
1.1.Thermal Protection Systems - Introduction
1.2.The Space Industry is Changing
1.3.Commercial Orbital Launches Growing Rapidly
1.4.Reusable Entry/Transfer Vehicles - Cargo and Crewed
1.5.LEO Partially Reusable Return Vehicle Testing Timeline
1.6.Thermal Protection Systems & 'Aerobraking'
1.7.Options for Decelerating
1.8.Peak Heat, Total Heat, and Stagnation Pressure
1.9.Categories of Thermal Protection System
1.10.TPS Performance Envelope (1)
1.11.TPS Performance Envelope
1.12.Role of Industry in Material and Manufacturing of Heat Shields
1.13.Forecasting Overview
1.14.Annual Installation Area of Thermal Protection Systems
1.15.Market Value of TPS, 1991-2035
1.16.TPS Market Value Forecast (1)
1.17.TPS Market Value Forecast (2)
2.SPACE INDUSTRY
2.1.Thermal Protection Systems - Introduction
2.2.The Space Industry is Changing
2.3.Commercial Interest in Space
2.4.Commercial Orbital Launches Growing Rapidly
2.5.Orbital Launches by Country of Operator, 1957-2024
2.6.BEO Launches Remain Low
2.7.SpaceX a Dominant Player Among Launch Providers
2.8.Space Mission Domain
2.9.Microgravity manufacturing
2.10.Commercialization of Space - Implications for Material Design
2.11.Cargo and Crew Capsules - TPS Enables Reusability
2.12.Cargo and Crew Transportation
2.13.Reusable Entry/Transfer Vehicles - Cargo and Crewed
2.14.Reusable Entry/Transfer Vehicles - Cargo and Crewed
2.15.LEO Partially Reusable Return Vehicle Testing Timeline
2.16.Partial Reusability
2.17.Partial Reusability - TPS Options
2.18.Crew/Cargo Return Vehicles
3.ATMOSPHERIC RE-ENTRY
3.1.Tsiolkovsky's Rocket Equation
3.2.Thermal Protection Systems & 'Aerobraking'
3.3.Atmospheric Entry - Overview
3.4.Energy of Orbital Vehicles
3.5.Options for Decelerating
3.6.Blunt Body Concept
3.7.Convective vs Radiative Heat
3.8.Peak Heat, Total Heat, and Stagnation Pressure
3.9.Categories of TPS
3.10.Categories of Thermal Protection System
3.11.Thermal Protection Systems
3.12.Cost and Performance
3.13.TPS Peak Heating and Pressure Limits
3.14.TPS Performance Envelope (1)
3.15.TPS Performance Envelope (2)
3.16.Role of Industry in Material and Manufacturing of Heat Shields
4.TILE-BASED TPS
4.1.Reusable TPS Overview
4.2.Material Requirements for Reusable TPS
4.3.Importance of Surface Emissivity
4.4.Thermal Conductivity
4.5.Temperature and Density
4.6.Reusable TPS Material Development Pathway
4.7.Spacecraft Geometry Affects Heating
4.8.Silica Based Tiles
4.9.Reinforced Carbon-Carbon (RCC) - (1)
4.10.Reinforced Carbon-Carbon (RCC) - (2)
4.11.RCC/ACC Manufacturing Overview
4.12.TUFROC
4.13.Advanced TUFROC
4.14.NASA Space Shuttle Orbiter vs SpaceX Starship
4.15.SpaceX Starship TPS
4.16.Thermal Conductivity and Density of Reusable TPS
4.17.Temperature Limits and Material Densities
4.18.Emissivity of TPS
4.19.TPS Component Manufacturers
5.EXPANDABLE AERODYNAMIC DECELERATORS
5.1.Overview
5.1.1.Expandable Aerodynamic Decelerators
5.1.2.Opportunities Enabled by EADs
5.1.3.Challenges for EADs
5.1.4.The Ballistic Coefficient
5.1.5.Ballistic Coefficient - Impact on Heat Flux
5.1.6.Venus Missions - Ballistic Coefficient and Peak Heating
5.1.7.Diameter on Heating
5.1.8.Options for Increasing the Ballistic Coefficient
5.2.HIAD
5.2.1.HIAD Deployment
5.2.2.NASA HIAD Construction
5.2.3.Material Selection for F-TPS
5.2.4.F-TPS
5.2.5.F-TPS Temperature
5.2.6.Aerogels for F-TPS
5.2.7.Gas-Generators
5.2.8.ATMOS PHOENIX - Commercial IAD
5.2.9.Booster Reusability
5.2.10.ULA Vulcan BE-4 Reusability
5.3.MDAD
5.3.1.NASA ADEPT
5.3.2.ADEPT Construction - Spiderweave
5.3.3.Commercial MDADs
6.ABLATIVE TPS
6.1.Overview
6.1.1.Ablative TPS
6.1.2.Ablation Introduction
6.1.3.High Energy Heatshield Environment
6.1.4.Surface Ablation Mechanisms
6.1.5.Pyrolysis
6.1.6.Material Requirements for Ablative Systems
6.1.7.Summary of Ablator Families(1)
6.1.8.Summary of Ablator Families (2)
6.1.9.Ablative TPS Timeline
6.1.10.Ablative Materials - Categorization by Form
6.1.11.Families of Ablators
6.1.12.NASA TPS Portfolio Development
6.2.Honeycomb Ablators
6.2.1.Material Composition of an Ablator (1)
6.2.2.Material Composition of an Ablator (2)
6.2.3.Honeycomb Ablators
6.2.4.Avcoat - Apollo to Orion
6.2.5.Orion Switch to Tiled Avcoat
6.2.6.Compositions of Silicone Ablators
6.3.PICA
6.3.1.PICA
6.3.2.PICA Production
6.3.3.PICA-X for SpaceX Dragon
6.3.4.Reusability of Ablators
6.4.Carbon Phenolic
6.4.1.Carbon Phenolic
6.5.3D Woven TPS
6.5.1.Woven Thermal Protection Systems
6.5.2.HEEET
6.5.3.Woven TPS Range of Densities
6.5.4.Woven TPS Performance Envelope
6.5.5.Woven TPS for Compression Pads on Orion
7.FORECASTS
7.1.Forecasting Overview
7.2.Cost per kg to Orbit
7.3.TPS Cost Progression (1)
7.4.TPS Cost Progression (2) - Ablative
7.5.TPS Cost Progression (3) - Tile-Based
7.6.TPS Cost Progression (3) - Tile-Based
7.7.Number of Flights, 1991-2024
7.8.SpaceX a Dominant Player Among Launch Providers
7.9.Annual Installation Area of Thermal Protection Systems
7.10.Market Value of TPS, 1991-2035
7.11.TPS Market Value Forecast (1)
7.12.TPS Market Value Forecast (2)
 

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In most locations reports can be purchased by credit card, or else by direct bank payment.

How and when do I receive access to IDTechEx reports?

When paying successfully by credit card, reports can be accessed immediately. For new customers, when paying by bank transfer, reports will usually be released when the payment is received. Report access will be notified by email.

How do I assign additional users to the report?

Users can be assigned in the report ordering process, or at a later time by email.

Can I speak to someone about purchasing a report?

Please email research@idtechex.com stating your location and we will quickly respond.
 

Ordering Information

우주선용 열 차폐 및 열 보호 시스템(TSP) 기술 동향 및 시장 전망 2025-2035

£$¥
전자 (사용자 1-5명)
£5,650.00
전자 (사용자 6-10명)
£8,050.00
전자 및 1 하드 카피 (사용자 1-5명)
£6,450.00
전자 및 1 하드 카피 (사용자 6-10명)
£8,850.00
전자 (사용자 1-5명)
€6,400.00
전자 (사용자 6-10명)
€9,100.00
전자 및 1 하드 카피 (사용자 1-5명)
€7,310.00
전자 및 1 하드 카피 (사용자 6-10명)
€10,010.00
전자 (사용자 1-5명)
$7,000.00
전자 (사용자 6-10명)
$10,000.00
전자 및 1 하드 카피 (사용자 1-5명)
$7,975.00
전자 및 1 하드 카피 (사용자 6-10명)
$10,975.00
전자 (사용자 1-5명)
元50,000.00
전자 (사용자 6-10명)
元72,000.00
전자 및 1 하드 카피 (사용자 1-5명)
元58,000.00
전자 및 1 하드 카피 (사용자 6-10명)
元80,000.00
전자 (사용자 1-5명)
¥990,000
전자 (사용자 6-10명)
¥1,406,000
전자 및 1 하드 카피 (사용자 1-5명)
¥1,140,000
전자 및 1 하드 카피 (사용자 6-10명)
¥1,556,000
전자 (사용자 1-5명)
₩9,800,000
전자 (사용자 6-10명)
₩14,000,000
전자 및 1 하드 카피 (사용자 1-5명)
₩11,200,000
전자 및 1 하드 카피 (사용자 6-10명)
₩15,400,000
Click here to enquire about additional licenses.
If you are a reseller/distributor please contact us before ordering.
お問合せ、見積および請求書が必要な方はm.murakoshi@idtechex.com までご連絡ください。
우주선 열 보호 시스템(TSP) 시장규모는 2035년까지 9천만 달러 규모로 성장할 것으로 전망

보고서 통계

슬라이드 152
전망 2035
게시 Mar 2025
 

콘텐츠 미리보기

pdf Document Webinar Slides
pdf Document Sample pages
 

Customer Testimonial

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"The resources provided by IDTechEx, such as their insightful reports and analysis, engaging webinars, and knowledgeable analysts, serve as valuable tools and information sources... Their expertise allows us to make data-driven, strategic decisions and ensures we remain aligned with the latest trends and opportunities in the market."
Global Head of Product Management and Marketing
Marquardt GmbH
 
 
 
ISBN: 9781835701102

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