Rocket Engine Patents: Who Leads, Where the Gaps Are 2026
- Filing has cooled since 2021. The 93-family peak in 2021 has not been matched since; 2022's 59 families mark the midpoint of a declining run down to a partial 12 in 2026.
- China and Russia now out-file Europe combined. 317 Chinese and 158 Russian receiving-office filings sit alongside 435 from the United States, changing where defensive searches need to start.
- The most-cited prior art is decades old. The top-cited record, a combustion chamber patent, carries 121 citations — a sign of foundational influence, not of where current claim activity sits.
Filing growth compares 2021 (93 records) with 2024 (60) — a three-year span. 2024 is the most recent year we treat as complete: publication lags filing by roughly 18 months, so 2025 onwards are still filling in and any growth rate that ends there would understate the field. Top-5 share is the combined record count of the five largest assignees divided by all 1,286 records in scope (CR5), not by the ranked leaders only.
What this landscape covers
This dataset tracks 1,286 patent families filed against rocket engine technology terms — staged combustion cycle, regenerative cooling, turbopump, injector design and thrust chamber — restricted to the F02K jet and reaction propulsion classification. Coverage runs from 2015 through a partial 2026, giving a decade-plus view of how claim activity has moved across engine subsystems rather than the vehicle or mission layer above them.
Because publication lags filing by roughly 18 months, the last one to two years in any trend understate real filing activity; treat the most recent bars as a floor, not a ceiling.
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Filing trend and technology composition
Two views of the same 1,286-family dataset: how filing volume has moved year over year, and how those families distribute across the IPC subclasses that sit around core rocket propulsion.
A decade of rise and pullback
Filings rose from 42 in 2017 to a peak of 93 in 2021, then eased through a 59-family midpoint in 2022 down to a partial 12 in 2026. The shape is a filing wave that has already crested rather than a technology still accelerating.
Concentrated in jet propulsion, thin everywhere else
F02K covers all but one of the 1,286 records, confirming the search is on-target. Everything below it is a long way behind — spacecraft (B64G, 94), pumps (F04D, 52), metal working (B23P, 35), turbines (F01D, 25), welding (B23K, 22), additive manufacturing (B33Y, 22) and combustion chambers (F23R, 22) — each a candidate adjacent claim space rather than a core one.
Shares are the percentage of the 1,286 records in scope. A patent can carry several IPC classes, so the shares add up to more than 100%.
Go deeper on Rocket Engine Technology Landscape with Eureka
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Try EurekaThe prior art shaping this space
US11846256B2 — Liquid rocket engine assemblies and related methods
A liquid rocket engine assembly comprising a thrust chamber, a nozzle, and a joint structure. The joint structure attaches the thrust chamber and the nozzle and comprises at least one seal element and an attachment ring interposed between the thrust chamber and the nozzle. Fasteners extend between the nozzle and the thrust chamber through the at least one seal element and the attachment ring. Materials of the thrust chamber and of the nozzle comprise different coefficients of thermal expansion.Filed by Northrop Grumman Systems Corporation, granted 2023-12-19 — the joint structure claim targets the thermal-expansion mismatch problem at the thrust chamber-to-nozzle interface directly.
| # | Publication no. | Patent title | Citations |
|---|---|---|---|
| 1 | US6151887A | Combustion chamber | 121 |
| 2 | US5052176A | Combination turbojet-ramjet-rocket propulsion system | 80 |
| 3 | US5918460A | Liquid oxygen gasifying system for rocket engines | 79 |
| 4 | US6619031B1 | Multi-mode multi-propellant liquid rocket engine | 74 |
| 5 | US4771600A | Tripropellant rocket engine | 74 |
| 6 | US4073138A | Mixed mode rocket engine | 74 |
| 7 | US6135393A | Spacecraft attitude and velocity control thruster system | 73 |
| 8 | US20030175453A1 | Actively-cooled fiber-reinforced ceramic matrix composite rocket propulsion thrust chamber and method of prod… | 71 |
| 9 | US4707982A | Thermal regenerative injector | 70 |
| 10 | US6226980B1 | Liquid-propellant rocket engine with turbine gas afterburning | 69 |
Citation counts reflect influence within this searched corpus and skew toward older filings; they are not a proxy for current claim strength.
Each row carries its publication number; clicking a row searches Eureka by that number.
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Four patterns stand out once the filings are aggregated by year, geography and citation weight.
The filing wave has crested
2021's peak of 93 families has not been approached since; the run down through 2022's 59-family midpoint to a partial 12 in 2026 describes a technology area past its filing peak, not one still ramping.
Three receiving offices carry the field
United States, China and Russia together account for the large majority of filings, ahead of Europe's 131 and WIPO's 62. Freedom-to-operate work that only checks USPTO and EPO will miss a large share of the active claim base.
Foundational art is old, not current
The most-cited record in the corpus is a combustion chamber patent with 121 citations, well ahead of the next tier around 74-80. High citation counts here mark historical influence on later filers, not where today's claim activity concentrates.
Collaboration is limited and personal
Only ten co-assignee pairs appear in the dataset, and the strongest link is an individual inventor pairing rather than a corporate joint venture, alongside one clear corporate-group pair. Cross-entity R&D collaboration is the exception in this field, not the norm.
Eureka can read the same corpus for gaps instead of for coverage: under-claimed branches adjacent to rocket engine technology landscape, with the prior art for and against each one.
Who is filing, and where the field is open
Recent-year momentum is negative or flat across every assignee tracked here, consistent with the broader post-2021 pullback in filing volume.
Established filers are pulling back
Assignees with long filing histories in this dataset show single-digit latest-year counts and negative year-over-year movement rather than fresh acceleration, matching the corpus-wide decline from the 2021 peak.
A long tail behind the leaders
The assignee ranking spans the full 1,286-family set, and activity concentrates at the top with a long tail of entities holding only one or two families each — typical of a field with both state research institutes and newer commercial entrants.
Corporate groups file jointly, most others do not
One Chinese corporate-group pair co-files 17 families together, the clearest sign of an internal group filing structure in the dataset; outside that pair, most co-assignee links are individual inventors rather than company-to-company alliances.
| Assignee | Recent year | YoY |
|---|---|---|
| Beijing Aerospace Propulsion Institute | 1 | -67% |
| VENUS AEROSPACE CORP | 1 | -50% |
| United Technologies Corporation | 0 | — |
| Korea Aerospace Research Institute (KARI) | 0 | — |
| Xi'an Aerospace Propulsion Institute | 0 | -100% |
| Bolotin Nikolay Borisovich | 0 | — |
| BOLOTIN NIKOLAJ BORISOVICH | 0 | — |
| Snecma | 0 | — |
Where to take this analysis
The trends above point to specific next steps depending on whether the goal is freedom-to-operate, R&D targeting or competitive tracking.
Check freedom-to-operate beyond the US and EPO
With China and Russia together outweighing Europe in filing volume, a freedom-to-operate review limited to US and EPO records will miss a substantial share of active claims in this space.
Explore assignee filings in EurekaTarget the under-claimed adjacent subclasses
B33Y, B23K and F23R each carry a fraction of F02K's volume; a claim built around additive-manufactured thrust chambers or dissimilar-metal nozzle joints has more room to move than one filed directly against core combustion chamber art.
Map white space in EurekaWatch for renewed filing activity, not just past peaks
Filing volume has declined since 2021, but publication lag means the last one to two years understate real activity; monitoring fresh filings as they publish will catch any renewed push earlier than annual counts alone.
Set up monitoring in EurekaCommon questions about rocket engine patents
This dataset of 1,286 patent families shows filing concentrated among a small group of state research institutes and established aerospace manufacturers, with a long tail of single-family filers behind them. Rather than one dominant holder, the field splits between long-running national propulsion institutes and newer commercial entrants that have filed only in the last few years. Checking the assignee ranking directly, rather than relying on brand recognition, is the reliable way to identify the actual leaders for a given subsystem.
Filing peaked at 93 families in 2021 and has fallen in every year since, down to a partial 12 in 2026. This pattern is consistent with a filing wave that followed a period of intense commercial launch-vehicle development, followed by consolidation as programmes matured past their initial claim-staking phase. It does not necessarily mean underlying R&D has slowed by the same degree, because publication lags filing by roughly 18 months, so the last one to two years in the trend understate real activity.
Staged combustion cycle claims cover how propellant is burned in stages to drive turbopumps before final combustion, while regenerative cooling claims cover how fuel or oxidizer is routed through the engine structure, typically the thrust chamber wall, to manage heat before combustion. Both terms sit inside the same F02K classification in this dataset and often appear in the same filing family, since a single engine design frequently addresses both problems together. Searching them as separate terms, as this landscape does, helps isolate which specific subsystem a given patent actually protects.
The clearest gaps sit in subclasses adjacent to core F02K propulsion claims but carrying far fewer filings: additive manufacturing (B33Y, 22 records), welding and brazing (B23K, 22), and combustion chamber design (F23R, 22), all a fraction of F02K's 1,285. Within those, additive-manufactured thrust chamber structures, turbopump bearing and seal integration, and dissimilar-metal nozzle joints are under-claimed relative to the density of core thrust chamber and injector art. These are reasonable areas to search before drafting a new claim, since less prior art means more room to secure a defensible position.
By receiving office, the United States leads with 435 filings against China's 317 in this dataset, with Russia a distant third at 158 and Europe at 131. The United States retains the largest single share, but China and Russia combined represent a filing volume that a US- or Europe-only freedom-to-operate search would completely miss. Given the dataset's coverage window through a partial 2026, any comparison of national leadership should also account for publication lag understating the most recent one to two years.
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Disclaimer. This page is generated from Patsnap Eureka data drawn from a limited snapshot of global patent and scientific-literature records, and is provided for general information and reference only.
Patent data carries inherent limitations: recent filings (typically the most recent 18–24 months) are under-counted due to standard publication lag; counts may be reported at either a patent-family or a patent-record basis and are not always directly comparable; classification, applicant-name, and citation data may contain errors, duplicates, or omissions; and the underlying search query defines and constrains the scope shown. As a result, the analysis may be incomplete or inaccurate and may not reflect the full technology landscape.
Nothing on this page constitutes an exhaustive prior-art, novelty, freedom-to-operate, or validity search, nor does it constitute legal, financial, investment, or professional advice, and it should not be relied upon as such. Any patent, commercial, or strategic decision should be verified independently and reviewed with qualified patent, legal, and domain professionals. Patsnap makes no warranties, express or implied, as to the accuracy, completeness, or fitness for any particular purpose of the information presented.
Machine translation. Assignee and organisation names originally recorded in Chinese, Japanese or Korean have been rendered into English by an AI translation step so that the tables stay readable. These renderings are best-effort and may not match a company’s registered English name; the original name is what the underlying patent record carries, and it is what any Eureka query launched from this page uses.