- International families
- 1,8302015 to 2024
- Leading country
- United States3.2× the next
- All families
- 10khome filings included
- Over five years
- Falling2020 to 2024 against the five before
Year by year
Patent families by country of origin and the year of the earliest filing, 2000 to 2025; 2025 is a part year, still filling in. International families are those for which protection was sought beyond one country.
Volume
International patent families in the capability, by the year of the earliest filing.
Source: Global Institute for National Capability (GINC), 2026. Underlying patents from 107 patent offices, IFI CLAIMS and Google
Share by country
Each country's share of the year's international families, in per cent: the capability's five largest countries of origin, 2015 to 2024, and the rest of the world.
Source: Global Institute for National Capability (GINC), 2026. Underlying patents from 107 patent offices, IFI CLAIMS and Google
Country leaderboard
International patent families, 2015 to 2024, by country of origin. Growth compares the latest five full years with the five before.
Ten largest
United States
France
Germany
Japan
China
United Kingdom
South Korea
Canada
Italy
India
732
229
172
130
104
73
55
40
32
28
| 2000 to 2025 | ||||||
|---|---|---|---|---|---|---|
| 1 | United States | 732 | 40.0% | 0.8× | 1,480 | |
| 2 | France | 229 | 12.5% | 0.6× | 302 | |
| 3 | Germany | 172 | 9.4% | 0.8× | 257 | |
| 4 | Japan | 130 | 7.1% | 0.9× | 303 | |
| 5 | China | 104 | 5.7% | 2.5× | 6,285 | |
| 6 | United Kingdom | 73 | 4.0% | 1.1× | 119 | |
| 7 | South Korea | 55 | 3.0% | 1.9× | 491 | |
| 8 | Canada | 40 | 2.2% | 1.4× | 51 | |
| 9 | Italy | 32 | 1.7% | 1.5× | 48 | |
| 10 | India | 28 | 1.5% | 1.8× | 28 | |
| 11 | Israel | 27 | 1.5% | 0.9× | 31 | |
| 12 | Russia | 18 | 1.0% | 0.6× | 658 | |
| 13 | Spain | 17 | 0.9% | 1.1× | 23 | |
| 14 | Austria | 16 | 0.9% | 3.0× | 17 | |
| 15 | Switzerland | 13 | 0.7% | 1.6× | 17 | |
| 16 | Sweden | 13 | 0.7% | 0.6× | 17 | |
| 17 | Taiwan | 12 | 0.7% | 0.7× | 29 | |
| 18 | Australia | 11 | 0.6% | 0.6× | 28 | |
| 19 | Poland | 11 | 0.6% | 2.7× | 49 | |
| 20 | Türkiye | 10 | 0.5% | 4.0× | 24 | |
| 21 | Netherlands | 6 | 0.3% | 1.0× | 9 | |
| 22 | Finland | 6 | 0.3% | 2.0× | 8 | |
| 23 | Brazil | 5 | 0.3% | 4.0× | 13 | |
| 24 | New Zealand | 5 | 0.3% | 1.5× | 5 | |
| 25 | Mexico | 5 | 0.3% | 1.5× | 7 | |
| 26 | Belgium | 4 | 0.2% | 0.3× | 6 | |
| 27 | South Africa | 4 | 0.2% | 3.0× | 4 | |
| 28 | Singapore | 3 | 0.2% | 2.0× | 4 | |
| 29 | Liechtenstein | 2 | 0.1% | 1.0× | 2 | |
| 30 | Portugal | 2 | 0.1% | – | 2 | |
| 31 | Norway | 1 | 0.1% | – | 1 | |
| 32 | Luxembourg | 1 | 0.1% | 0.0× | 1 | |
| 33 | Saudi Arabia | 1 | 0.1% | 0.0× | 6 | |
| 34 | Malaysia | 1 | 0.1% | 0.0× | 1 | |
| 35 | Ireland | 0 | 0.0% | – | 1 | |
| 36 | Czechia | 0 | 0.0% | – | 5 | |
| 37 | Hungary | 0 | 0.0% | – | 2 |
Applicants
The largest applicants by international patent families, 2015 to 2024: across the world, then within each of the five countries with the most families in Advanced Propulsion & Hypersonic Systems. Names are as held in the source and are not consolidated across subsidiaries.
Global
1,830 international families
ARIANEGROUP SAS · France
GEN ELECTRIC · United States
BOEING CO · United States
RAYTHEON CO · United States
AEROJET ROCKETDYNE INC · United States
ARIANEGROUP GMBH · Germany
102
70
66
60
49
49
United States
732 international families
GEN ELECTRIC
BOEING CO
RAYTHEON CO
AEROJET ROCKETDYNE INC
HAMILTON SUNDSTRAND CORP
ZE BOING KOMPANI
70
66
60
49
25
18
France
229 international families
ARIANEGROUP SAS
AIRBUS SAFRAN LAUNCHERS SAS
AIRBUS DEFENCE & SPACE SAS
CENTRE NAT ETD SPATIALES
CENTRE NAT RECH SCIENT
SNECMA
102
29
21
20
19
18
Germany
172 international families
ARIANEGROUP GMBH
DEUTSCH ZENTR LUFT & RAUMFAHRT
AIRBUS DS GMBH
AIRBUS DEFENCE & SPACE GMBH
BAYERN CHEMIE GES FUER FLUGCHEMISCHE ANTRIEBE MBH
ROLLS ROYCE DEUTSCHLAND LTD & CO KG
49
24
19
15
8
6
Japan
130 international families
MITSUBISHI HEAVY IND LTD
JAPAN AEROSPACE EXPLORATION
MITSUBISHI ELECTRIC CORP
NAT RES & DEVELOPMENT AGENCY JAPAN AEROSPACE EXPLORATION AGENCY
IHI CORP
IHI AEROSPACE CO LTD
28
23
16
16
13
5
China
104 international families
XIAN AEROSPACE PROPULSION INSTITUTE
SHANGHAI INST SPACE PROPULSION
UNIV NANJING AERONAUTICS & ASTRONAUTICS
XIAN SPACE ENGINE COMPANY LTD
BEIJING INSTITUTE TECH
HANGZHOU INSTITUTE FOR ADVANCED STUDY UNIV OF CHINESE ACADEMY OF SCIENCES
9
7
6
6
4
4
Similar capabilities
The nine capabilities that share the most international patent families with Advanced Propulsion & Hypersonic Systems, 2015 to 2024: the families counted in both as a share of those counted in either. Each card shows its five largest countries.
National Security
Assured Space Access
44.7% shared · 893 families in both
United States
France
Germany
Japan
China
348
166
106
80
69
Critical Technology
Space Launch & Reusable Systems
44.1% shared · 917 families in both
United States
France
Germany
Japan
China
369
176
121
104
78
Strategic Infrastructure
Satellites & Orbital Systems
8.2% shared · 872 families in both
United States
China
Japan
France
South Korea
3,071
2,252
925
693
509
National Security
Control of the Air
6.8% shared · 149 families in both
United States
United Kingdom
Germany
Türkiye
France
176
57
50
43
41
Critical Technology
Satellite & Constellation Technologies
4.5% shared · 487 families in both
United States
China
Japan
France
South Korea
2,984
2,248
933
651
508
Strategic Infrastructure
Launch, Maintenance & Support
4.1% shared · 111 families in both
United States
France
Germany
United Kingdom
Japan
428
135
90
56
54
National Security
Space Domain Awareness & Control
2.4% shared · 53 families in both
Japan
United States
France
Germany
China
145
123
41
26
21
Critical Technology
Energetic Materials
2.3% shared · 56 families in both
United States
France
China
Germany
Japan
166
62
59
59
41
National Security
Long-Range Strike
2.2% shared · 58 families in both
United States
Germany
United Kingdom
France
Israel
278
159
88
77
44
Crosswalk
How Advanced Propulsion & Hypersonic Systems is matched to the patent classifications. The entries below were chosen for it; each stands for itself and everything beneath it in the scheme, 111 Cooperative entries in all. A patent family counts when any of its codes, in either scheme and at any office, falls under one of them. Codes since retired are placed under the entries that replaced them.
| Entry | Title in the scheme | Why it is chosen | CPC codes | IPC codes | Documents |
|---|---|---|---|---|---|
| F02K9/00 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof | Rocket engines | 61 | 48 | 55,721 |
| F02K7/00 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof | Ramjets, scramjets and pulse jets | 15 | 13 | 10,989 |
| F23R7/00 | Intermittent or explosive combustion chambers | Detonation and pulsed combustion chambers | 1 | 1 | 1,709 |
| F03H1/00 | Using plasma to produce a reactive propulsive thrust | Plasma and ion thrusters | 16 | 1 | 9,327 |
| B64G1/40 | Arrangements or adaptations of propulsion systems | Spacecraft propulsion systems | 17 | 1 | 19,104 |
| B64C30/00 | Supersonic type aircraft | Supersonic and hypersonic aircraft | 1 | 1 | 2,465 |
CPC and IPC codes are the codes in use on patent documents, at any office, that fall under the entry. Documents is the larger of the two schemes' counts of documents carrying one of them. An entry with no IPC codes can be told apart only in the Cooperative scheme.
The Cooperative codes in use that count towards Advanced Propulsion & Hypersonic Systems: 111 codes on 97,015 documents. The full crosswalk is in the cpc-to-capability.csv download.
| Code | Title | Under entry | How placed | Documents |
|---|---|---|---|---|
| B64G1/402 | Propellant tanks; Feeding propellants | B64G1/40 | In the scheme | 3,731 |
| F02K9/95 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements | F02K9/00 | In the scheme | 2,768 |
| F02K9/64 | Combustion or thrust chambers having cooling arrangements | F02K9/00 | In the scheme | 2,712 |
| F02K9/52 | Injectors | F02K9/00 | In the scheme | 2,646 |
| B64G1/40 | Arrangements or adaptations of propulsion systems | B64G1/40 | In the scheme | 2,615 |
| F02K9/97 | Rocket nozzles | F02K9/00 | In the scheme | 2,540 |
| B64C30/00 | Supersonic type aircraft | B64C30/00 | In the scheme | 2,465 |
| B64G1/401 | Liquid propellant rocket engines | B64G1/40 | In the scheme | 2,442 |
| F02K9/96 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring | F02K9/00 | In the scheme | 2,210 |
| B64G1/413 | Ion or plasma engines | B64G1/40 | In the scheme | 2,106 |
| F02K7/10 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines | F02K7/00 | In the scheme | 2,085 |
| F02K9/60 | Constructional parts; Details not otherwise provided for | F02K9/00 | In the scheme | 1,869 |
| F02K9/62 | Combustion or thrust chambers | F02K9/00 | In the scheme | 1,802 |
| F23R7/00 | Intermittent or explosive combustion chambers | F23R7/00 | In the scheme | 1,709 |
| F02K9/34 | Casings; Combustion chambers; Liners thereof | F02K9/00 | In the scheme | 1,547 |
| F02K9/44 | Feeding propellants | F02K9/00 | In the scheme | 1,490 |
| F02K9/42 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants | F02K9/00 | In the scheme | 1,420 |
| F02K9/58 | Propellant feed valves | F02K9/00 | In the scheme | 1,419 |
| B64G1/4021 | Tank construction; Details thereof | B64G1/40 | In the scheme | 1,414 |
| F02K9/972 | Fluid cooling arrangements for nozzles | F02K9/00 | In the scheme | 1,352 |
| F02K9/50 | Feeding propellants using pressurised fluid to pressurise the propellants | F02K9/00 | In the scheme | 1,337 |
| F02K9/605 | Reservoirs | F02K9/00 | In the scheme | 1,238 |
| F02K7/18 | Composite ram-jet/rocket engines | F02K7/00 | In the scheme | 1,229 |
| F02K9/48 | Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases | F02K9/00 | In the scheme | 1,224 |
| F02K9/974 | Nozzle- linings; Ablative coatings | F02K9/00 | In the scheme | 1,166 |
| F03H1/0012 | Means for supplying the propellant | F03H1/00 | In the scheme | 1,149 |
| F02K7/02 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet | F02K7/00 | In the scheme | 1,143 |
| F02K9/72 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants | F02K9/00 | In the scheme | 1,123 |
| F02K9/46 | Feeding propellants using pumps | F02K9/00 | In the scheme | 1,104 |
| B64G1/409 | Unconventional spacecraft propulsion systems | B64G1/40 | In the scheme | 1,042 |
| F02K7/16 | Composite ram-jet/turbo-jet engines | F02K7/00 | In the scheme | 1,033 |
| F03H1/00 | Using plasma to produce a reactive propulsive thrust | F03H1/00 | In the scheme | 1,010 |
| F03H1/0075 | Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift | F03H1/00 | In the scheme | 1,006 |
| F02K9/346 | Liners, e.g. inhibitors | F02K9/00 | In the scheme | 1,001 |
| F02K9/08 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants | F02K9/00 | In the scheme | 992 |
| F03H1/0081 | Electromagnetic plasma thrusters | F03H1/00 | In the scheme | 992 |
| F02K9/56 | Control | F02K9/00 | In the scheme | 976 |
| F02K9/10 | Shape or structure of solid propellant charges | F02K9/00 | In the scheme | 964 |
| F02K9/24 | Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges | F02K9/00 | In the scheme | 951 |
| F02K9/80 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control | F02K9/00 | In the scheme | 935 |
| F02K9/32 | Constructional parts; Details not otherwise provided for | F02K9/00 | In the scheme | 929 |
| B64G1/411 | Electric propulsion | B64G1/40 | In the scheme | 916 |
| F02K9/84 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles | F02K9/00 | In the scheme | 891 |
| F02K9/68 | Decomposition chambers | F02K9/00 | In the scheme | 886 |
| F02K9/00 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof | F02K9/00 | In the scheme | 880 |
| B64G1/407 | Solar sailing | B64G1/40 | In the scheme | 790 |
| F03H1/0037 | Electrostatic ion thrusters | F03H1/00 | In the scheme | 784 |
| F02K9/38 | Safety devices, e.g. to prevent accidental ignition | F02K9/00 | In the scheme | 762 |
| B64G1/403 | Solid propellant rocket engines | B64G1/40 | In the scheme | 755 |
| B64G1/415 | Arcjets or resistojets | B64G1/40 | In the scheme | 750 |
| F02K9/425 | Propellants | F02K9/00 | In the scheme | 744 |
| F03H1/0087 | Electro-dynamic thrusters, e.g. pulsed plasma thrusters | F03H1/00 | In the scheme | 731 |
| F02K7/06 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves | F02K7/00 | In the scheme | 727 |
| F02K9/94 | Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants | F02K9/00 | In the scheme | 703 |
| F03H1/0006 | Details applicable to different types of plasma thrusters | F03H1/00 | In the scheme | 699 |
| F02K9/86 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section | F02K9/00 | In the scheme | 686 |
| F02K7/00 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof | F02K7/00 | In the scheme | 685 |
| F02K9/26 | Burning control | F02K9/00 | In the scheme | 684 |
| F02K9/805 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control servo-mechanisms or control devices therefor | F02K9/00 | In the scheme | 674 |
| F02K9/36 | Propellant charge supports | F02K9/00 | In the scheme | 643 |
| F02K9/78 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant | F02K9/00 | In the scheme | 637 |
| F03H1/0018 | Arrangements or adaptations of power supply systems | F03H1/00 | In the scheme | 631 |
| B64G1/4024 | Propellant tanks; Feeding propellants refuelling in space | B64G1/40 | In the scheme | 627 |
| F02K9/978 | Closures for nozzles; Nozzles comprising ejectable or discardable elements | F02K9/00 | In the scheme | 595 |
| F02K7/005 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the engine comprising a rotor rotating under the actions of jets issuing from this rotor | F02K7/00 | In the scheme | 592 |
| F02K9/343 | Joints, connections, seals therefor | F02K9/00 | In the scheme | 586 |
| F02K9/12 | Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics | F02K9/00 | In the scheme | 576 |
| F02K7/14 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines | F02K7/00 | In the scheme | 563 |
| F02K9/28 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle | F02K9/00 | In the scheme | 547 |
| F02K9/82 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases | F02K9/00 | In the scheme | 523 |
| F02K9/88 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles | F02K9/00 | In the scheme | 522 |
| F02K9/90 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors | F02K9/00 | In the scheme | 514 |
| F02K7/08 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being continuous | F02K7/00 | In the scheme | 507 |
| F02K9/18 | Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity | F02K9/00 | In the scheme | 497 |
| B64G1/408 | Nuclear spacecraft propulsion | B64G1/40 | In the scheme | 470 |
| B64G1/417 | Electromagnetic fields or flux without mass expulsion | B64G1/40 | In the scheme | 443 |
| F02K7/04 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with resonant combustion chambers | F02K7/00 | In the scheme | 417 |
| F02K9/976 | Deployable nozzles | F02K9/00 | In the scheme | 414 |
| B64G1/4022 | Arrangements of tanks in or on spacecraft | B64G1/40 | In the scheme | 396 |
| F02K9/14 | Shape or structure of solid propellant charges made from sheet-like materials, e.g. of carpet-roll type, of layered structure | F02K9/00 | In the scheme | 392 |
| F03H1/0031 | Thermal management, heating or cooling parts of the thruster | F03H1/00 | In the scheme | 390 |
| F02K9/563 | Control of propellant feed pumps | F02K9/00 | In the scheme | 380 |
| F02K9/566 | Control elements and safety devices, e.g. pressure relief valves | F02K9/00 | In the scheme | 367 |
| F03H1/0043 | Electrostatic ion thrusters characterised by the acceleration grid | F03H1/00 | In the scheme | 366 |
| F03H1/0093 | Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma | F03H1/00 | In the scheme | 336 |
| F02K7/12 | Injection-induction jet engines | F02K7/00 | In the scheme | 335 |
| F02K9/40 | Cooling arrangements | F02K9/00 | In the scheme | 310 |
| F03H1/0025 | Neutralisers, i.e. means for keeping electrical neutrality | F03H1/00 | In the scheme | 309 |
| F03H1/0062 | Electrostatic ion thrusters grid-less with an applied magnetic field | F03H1/00 | In the scheme | 299 |
| F02K9/70 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using semi- solid or pulverulent propellants | F02K9/00 | In the scheme | 297 |
| F02K9/30 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles | F02K9/00 | In the scheme | 283 |
| B64G1/404 | Hybrid rocket engines | B64G1/40 | In the scheme | 278 |
| F02K7/105 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines using a solid fuel | F02K7/00 | In the scheme | 273 |
| F03H1/0068 | Electrostatic ion thrusters grid-less with an applied magnetic field with a central channel, e.g. end-Hall type | F03H1/00 | In the scheme | 273 |
| F02K7/075 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with multiple pulse-jet engines | F02K7/00 | In the scheme | 268 |
| F02K9/763 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with solid propellant | F02K9/00 | In the scheme | 230 |
| B64G1/4005 | Air-breathing propulsion | B64G1/40 | In the scheme | 223 |
| F02K9/76 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants | F02K9/00 | In the scheme | 217 |
| F03H1/005 | Electrostatic ion thrusters using field emission, e.g. Field Emission Electric Propulsion [FEEP] | F03H1/00 | In the scheme | 212 |
| F02K9/92 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control incorporating means for reversing or terminating thrust | F02K9/00 | In the scheme | 189 |
| F02K7/20 | Composite ram-jet/pulse-jet engines | F02K7/00 | In the scheme | 187 |
| F02K9/66 | Combustion or thrust chambers of the rotary type | F02K9/00 | In the scheme | 181 |
| F02K7/067 | Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves having aerodynamic valves | F02K7/00 | In the scheme | 180 |
| F02K9/54 | Leakage detectors; Purging systems; Filtration systems | F02K9/00 | In the scheme | 153 |
| F03H1/0056 | Electrostatic ion thrusters with an acceleration grid and an applied magnetic field | F03H1/00 | In the scheme | 140 |
| F02K9/766 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with liquid propellant | F02K9/00 | In the scheme | 139 |
| F02K9/22 | Shape or structure of solid propellant charges of the front-burning type | F02K9/00 | In the scheme | 116 |
| F02K9/74 | Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant | F02K9/00 | In the scheme | 107 |
| B64G1/4026 | Propellant tanks; Feeding propellants providing propellant to propulsion systems of differing type | B64G1/40 | In the scheme | 106 |
| F02K9/20 | Shape or structure of solid propellant charges of the external-burning type | F02K9/00 | In the scheme | 86 |
| F02K9/16 | Shape or structure of solid propellant charges of honeycomb structure | F02K9/00 | In the scheme | 60 |