PL439030A1 - Aircraft propulsion system - Google Patents

Aircraft propulsion system

Info

Publication number
PL439030A1
PL439030A1 PL439030A PL43903021A PL439030A1 PL 439030 A1 PL439030 A1 PL 439030A1 PL 439030 A PL439030 A PL 439030A PL 43903021 A PL43903021 A PL 43903021A PL 439030 A1 PL439030 A1 PL 439030A1
Authority
PL
Poland
Prior art keywords
electromagnetic radiation
aircraft
receiver
duct
source
Prior art date
Application number
PL439030A
Other languages
Polish (pl)
Inventor
Paweł Wawrzyński
Original Assignee
Paweł Wawrzyński
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Paweł Wawrzyński filed Critical Paweł Wawrzyński
Priority to PL439030A priority Critical patent/PL439030A1/en
Publication of PL439030A1 publication Critical patent/PL439030A1/en

Links

Landscapes

  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

Wynalazek dotyczy układu do napędzania statku powietrznego, w szczególności do wynoszenia ładunków na orbitę okołoziemską, w którym statek powietrzny zawiera zamocowaną do swojego kadłuba jednostkę napędową (1) zawierającą obudowę (2) ze ścianką boczną i wewnętrznym przelotowym kanałem (3), w którym usytuowany jest odbiornik (8) promieniowania elektromagnetycznego (7) do ogrzewania powietrza przepływającego przez kanał (3), oraz zawierającą zespół (10) do sprężania powietrza wlotowego. Na długości przelotowego kanału (3), na której usytuowany jest odbiornik (8) promieniowania elektromagnetycznego (7) kanał (3) ma zmienną powierzchnię przekroju poprzecznego zwiększającą się w kierunku od wlotu (4) do wylotu (5) powietrza. Układ zawiera ponadto źródło (6) promieniowania elektromagnetycznego (7) skonfigurowane do kierowania wiązek promieniowania elektromagnetycznego (7) do odbiornika (8), które to źródło (6) usytuowane jest poza statkiem powietrznym.The invention relates to a system for propelling an aircraft, in particular for launching cargo into earth orbit, in which the aircraft comprises a propulsion unit (1) attached to its fuselage, comprising a housing (2) with a side wall and an internal through channel (3) in which there is a receiver (8) for electromagnetic radiation (7) for heating the air flowing through the duct (3), and comprising an assembly (10) for compressing the intake air. Along the length of the passage duct (3), on which the receiver (8) of electromagnetic radiation (7) is located, the duct (3) has a variable cross-sectional area increasing in the direction from the air inlet (4) to the air outlet (5). The system further comprises a source (6) of electromagnetic radiation (7) configured to direct the beams of electromagnetic radiation (7) to a receiver (8), which source (6) is located outside the aircraft.

PL439030A 2021-09-24 2021-09-24 Aircraft propulsion system PL439030A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL439030A PL439030A1 (en) 2021-09-24 2021-09-24 Aircraft propulsion system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL439030A PL439030A1 (en) 2021-09-24 2021-09-24 Aircraft propulsion system

Publications (1)

Publication Number Publication Date
PL439030A1 true PL439030A1 (en) 2023-03-27

Family

ID=85785169

Family Applications (1)

Application Number Title Priority Date Filing Date
PL439030A PL439030A1 (en) 2021-09-24 2021-09-24 Aircraft propulsion system

Country Status (1)

Country Link
PL (1) PL439030A1 (en)

Similar Documents

Publication Publication Date Title
RU2168445C2 (en) Device for suction of boundary layer and for monitoring of shock boundary layer for aircraft
US20160017751A1 (en) Cooling device for a turbojet engine of an aircraft nacelle
US10486821B2 (en) Jet engine anti-icing and noise-attenuating air inlets
CN101365870B (en) Infrared suppression system
CN101952171B (en) Aircraft propulsion assembly comprising hot air bleed systems
US11220343B2 (en) Frost protection system for an aircraft engine nacelle
US8099973B2 (en) Environmental control system
US10260371B2 (en) Method and assembly for providing an anti-icing airflow
CN111071460A (en) Nacelle for an aircraft engine
US2632295A (en) Inlet ram for power plants
US7753311B2 (en) Propulsion system, aircraft comprising the propulsion system and an outlet device for a jet engine
RU2672197C2 (en) Aircraft propulsion assembly with fire extinguishing system
US4989807A (en) S-shaped jet engine inlet diffuser
RU2116935C1 (en) Aircraft suction generator system for maintenance of boundary-layer laminarity
BR0318553B1 (en) fluid cooling system of an aircraft and its aircraft
RU2008107594A (en) ENGINE INSTALLATION FOR AIRCRAFT AND AIRCRAFT CONTAINING AT LEAST ONE SUCH ENGINE INSTALLATION
US20110005188A1 (en) Air intake lip for turbojet nacelle
US10436148B2 (en) Convergent-divergent nozzle
BR112012032281A2 (en) propelled aircraft, especially aircraft formed as a flying wing and / or reduced radar signature
US4182119A (en) Air pump for turbofan fuel control system
US20160257413A1 (en) Anti-icing system for an aircraft
US20080236939A1 (en) Exhaust silencer assembly
PL439030A1 (en) Aircraft propulsion system
US11643216B2 (en) Aircraft engine nacelle comprising a system of ice protection
US2370062A (en) Exhaust conduit