CN106321283B - The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power - Google Patents

The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power Download PDF

Info

Publication number
CN106321283B
CN106321283B CN201610885546.9A CN201610885546A CN106321283B CN 106321283 B CN106321283 B CN 106321283B CN 201610885546 A CN201610885546 A CN 201610885546A CN 106321283 B CN106321283 B CN 106321283B
Authority
CN
China
Prior art keywords
passage
dual
aircraft
mode
turbogenerator
Prior art date
Legal status (The legal status 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 status listed.)
Active
Application number
CN201610885546.9A
Other languages
Chinese (zh)
Other versions
CN106321283A (en
Inventor
王成鹏
薛龙生
焦运
徐相荣
徐培
有连兴
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nanjing University of Aeronautics and Astronautics
Original Assignee
Nanjing University of Aeronautics and Astronautics
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 Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Priority to CN201610885546.9A priority Critical patent/CN106321283B/en
Publication of CN106321283A publication Critical patent/CN106321283A/en
Application granted granted Critical
Publication of CN106321283B publication Critical patent/CN106321283B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • 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
    • F02K7/10—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
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles

Abstract

The invention discloses a kind of pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power, the hypersonic inlet of dual-mode scramjet passage, jet pipe respectively with aircraft precursor, body integrated design afterwards, based on dual-mode scramjet passage, turbogenerator passage, rocket injection punching engine passage is arranged in parallel with dual-mode scramjet passage, make under different flight Mach numbers triple channel according to the mutually coordinated work of respective condition of work, dual-mode scramjet passage is in parallel up and down with rocket injection punching engine passage, turbogenerator passage is in parallel with the two left and right, and devise double hair patterns of left and right side-by-side configuration.Present invention preserves the service behaviour advantage of turbogenerator low-to-medium altitude, rocket injection punching engine can ensure that aircraft provides larger thrust-drag margin during acceleration is climbed across supersonic speed, realize to climb in the aircraft short time and accelerate to cruising altitude.

Description

The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power
Technical field
The present invention relates to pneumatic/propelling integrated layout designs technical field of hypersonic aircraft, one kind is referred to Circulation propulsion system is combined using TRBCC（Turbine and Rocket Based Combined Cycle, turborocket base Combination circulation propulsion system）Hypersonic aircraft aerodynamic arrangement method.
Background technology
Hypersonic aircraft is one of important research direction of future aircraft.Such aircraft can dense atmosphere, Near space and realized across atmosphere hypersonic（Ma>5）Maneuvering flight, fight and beat in information acquisition, monitoring, scouting, transport Hit etc. has broad application prospects, and military and civilian for future is all of great importance.
To realize that such aircraft is usual from low speed to hypersonic and be capable of the wide Mach number of landing aircraft Using turbine base or rocket based combined cycle engine, i.e. TBCC engines and RBCC engines.Both combination circulations are started Machine has larger difference, in cruising phase based on different thermodynamic cycle modes in overall structural arrangement（Hypersonic cruise When）Based on scramjet engine, but both combined cycle engines all come with some shortcomings.Though TBCC engines So possess preferably in, low-altitude performance, but its installation on board the aircraft when transonic speed, supersonic speed climb acceleration and Mach number it is big Thrust-drag margin is smaller after 2.5, and turbine mode is transitioned into sub- combustion mode and sub- combustion mode is transitioned into ultra-combustion ramjet mode When thrust discontinuity be present.RBCC engines comparatively than relatively low, complete to compare TBCC engines during same task by specific impulse Oil consumption rate is high and aircraft takeoff weight is big, and economy is poor when repeatedly using, and equally in Asia, combustion mode is transitioned into super burn There is also thrust discontinuity during punching press mode；But it has in work range of Mach numbers, and Rule adjusting is simple, thrust-weight ratio compared with Greatly, the advantages of being adapted to the short time to accelerate flight.Therefore, during superior combined cycle engine is not only required in, low latitude across sound Fast stage, the boost phase that climbs possess preferable acceleration and relatively low fuel consumption, and it is installed on board the aircraft Should also have larger thrust-drag margin, should also have continuity in mode conversion phase thrust.
The content of the invention
For above-mentioned the deficiencies in the prior art, it is an object of the invention to provide a kind of based on the hypersonic of assembly power The propelling integrated layout method of flight vehicle aerodynamic, turbine base or rocket based combined cycle engine are used in the prior art to improve Applied to insufficient present on aircraft；The present invention is by turbogenerator passage, rocket injection punching engine passage and double Mode punching engine passage is fused together, in both possessing, the superior function of low-latitude flying section, installation on board the aircraft across The velocity of sound and the supersonic speed accelerating sections that climbs possess abundant thrust-drag margin, ensure continuity during engine mode transition again；Simultaneously Rocket injection punching press passage can be embodied to capture incoming as the flow-regulating passage of hypersonic bimodal punching press runner Make full use of, slackened the adverse effect that spillage drag is brought.
To reach above-mentioned purpose, the invention discloses a kind of hypersonic aircraft based on assembly power pneumatically to promote one Body layout method, wherein, the hypersonic inlet of dual-mode scramjet passage, jet pipe respectively with before aircraft Body, rear body integrated design, based on dual-mode scramjet passage, turbogenerator passage, rocket injection punching press hair Motivation passage is arranged in parallel with dual-mode scramjet passage, makes under different flight Mach numbers triple channel according to respective condition of work Mutually coordinated work, including step are as follows：
（1）According to hypersonic aircraft general design requirement, the dual-mode scramjet under cruising condition is designed Passage；Wherein the hypersonic inlet of dual-mode scramjet passage is using streamlined impeller method and aircraft precursor lower surface Integrated design, while air intake duct compressing surface/precursor following table surface construction based on integration entirely bores precursor rider face closely；Tail Jet pipe and body lower surface integrated design after aircraft；
（2）According to the dimensional parameters of rocket injection punching engine design point, and it is based on above-mentioned dual-mode scramjet Passage, sent out in dual-mode scramjet passage back structure rocket injection punching engine passage, and with bimodal punching press Motivation passage shares inlet mouth and exported with jet pipe, using upper and lower paralleling model；
（3）By above-mentioned binary channels distribution structure in parallel into the double hair patterns in left and right, and the position based on the two and inner side are empty Between, turbogenerator passage is constructed, it is in parallel with the two left and right；Turbogenerator passage shares inlet mouth in side, simultaneously Jet pipe outlet is shared in side, possesses independent passage adjustable plate；Be laid out according to above three engine passageways outlet port, The regulatory demand of size and operation mode, using two dimension and the Model Design jet pipe of three-dimensional arrangement expansion；Rocket injection rushes Hydraulic motor passage section in parallel with dual-mode scramjet channel outlet is designed using two-dimensional expansion, continuously linear regulation；Whirlpool Turbine channel outlet is designed with the section in parallel of the two using three-dimensional expansion, separately adjustable.
Preferably, above-mentioned dual-mode scramjet passage includes：Hypersonic inlet, distance piece, combustion chamber and Jet pipe.
Beneficial effects of the present invention：
The present invention is laid out using hypersonic aircraft body and TRBCC Propulsion Integrateds, passes through propulsion system three Passage co-ordination, solve the problems, such as be used alone TBCC propulsion systems across supersonic speed climb accelerating sections thrust-drag margin deficiency and Thrust discontinuous problem during mode conversion, when also solving less economical when RBCC propulsion systems are used alone and mode conversion The discontinuous problem of thrust, while fully high efficiency make use of the incoming that air intake duct captures, and reduces spillage drag and brings not Profit influences, in addition the integrated design of air intake duct precommpression face and body precursor lower surface, when improving hypersonic flight Lift-drag ratio.
Brief description of the drawings
Fig. 1 is the integrated configuration figure of TRBCC propulsion systems and body；
Fig. 2 is turbogenerator passage, rocket injection punching engine passage, dual-mode scramjet passage are opened Aircraft front view under state；
Fig. 3 is closed for turbogenerator passage, and rocket injection punching engine passage is opened, and dual-mode scramjet leads to Aircraft front view under road open mode；
Fig. 4 is closed for turbogenerator passage, and rocket injection punching engine passage is closed, and dual-mode scramjet leads to Aircraft front view under road open mode；
Fig. 5 is turbogenerator passage, rocket injection punching engine passage, dual-mode scramjet passage are opened Aircraft rearview under state；
Fig. 6 is closed for turbogenerator passage, and rocket injection punching engine passage is opened, and dual-mode scramjet leads to Aircraft rearview under road open mode；
Fig. 7 is closed for turbogenerator passage, and rocket injection punching engine passage is closed, and dual-mode scramjet leads to Aircraft rearview under road open mode；
Fig. 8 is that single TRBCC propulsion systems operation mode switches schematic diagram.
Embodiment
For the ease of the understanding of those skilled in the art, the present invention is made further with reference to embodiment and accompanying drawing Bright, the content that embodiment refers to not is limitation of the invention.
A kind of pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power of the present invention, will be superb Velocity of sound aircraft body and TRBCC Propulsion Integrateds design, wherein, dual-mode scramjet passage it is hypersonic enter Air flue, jet pipe respectively with aircraft precursor, rear body integrated design；Turbogenerator passage, rocket injection punching engine Passage is arranged in parallel with dual-mode scramjet passage, mutually coordinated work, be ensure that aircraft is slided and is run, takes off, across ultrasound Speed, which is climbed, accelerates to the continuity of thrust when cruising phase whole process has larger thrust-drag margin and mode conversion, disappears simultaneously Weak spillage drag, aerodynamic arrangement's profile have higher lift-drag ratio, and referring to figs. 1 to shown in Fig. 8, including step is as follows：
（1）According to hypersonic aircraft general design requirement, the dual-mode scramjet under cruising condition is designed Passage 18, including the part such as hypersonic inlet, distance piece, combustion chamber, jet pipe；Wherein dual-mode scramjet passage Hypersonic inlet using streamlined impeller method and the integrated design of aircraft precursor lower surface 17, while based on integration Air intake duct compressing surface/precursor following table surface construction entirely bores precursor rider face 1 closely；Jet pipe and body lower surface one after aircraft Change design, body lower surface 3 uses horizontal plane layout type；（2）Size according to rocket injection punching engine design point is joined Number, and above-mentioned dual-mode scramjet passage 18 is based on, rushed in dual-mode scramjet passage back structure rocket injection Hydraulic motor passage 20, and share inlet mouth 2 and jet pipe outlet 4 with dual-mode scramjet passage, in use Lower paralleling model；
（3）By above-mentioned binary channels distribution structure in parallel into the double hair patterns in left and right, and the position based on the two and inner side are empty Between, construction turbogenerator passage 19 is in parallel with the two left and right；Turbogenerator passage shares inlet mouth in side, together When jet pipe outlet is shared in side, possess independent passage adjustable plate, i.e., turbogenerator passage is sent out with the punching press of rocket injection Motivation feeder connection adjustable plate 15 and turbogenerator passage and rocket injection punching engine channel outlet adjustable plate 16；Foundation The regulatory demand of above three engine passageways outlet port layout, size and operation mode, using two dimension and three-dimensional arrangement The Model Design jet pipe 21 of expansion；Rocket injection punching engine channel outlet 10 and dual-mode scramjet channel outlet 11 sections in parallel are designed using two-dimensional expansion, continuously linear regulation；Turbogenerator channel outlet uses three with the section in parallel of the two Dimensional expansion design, it is separately adjustable；
（4）Low latitude is taken off boost phase and low mach stage, and turbogenerator passage is opened completely, and thrust is mainly by whirlpool Turbine provides, and as 5 be the turbogenerator feeder connection that opens in Fig. 2,12 be the turbogenerator opened in Fig. 5 Channel outlet；
（5）Low mach is climbed boost phase, and rocket injection punching engine passage is opened completely, as augmented thrust, Accelerate aircraft and fly in a short time to climb boost phase across supersonic speed, as 6 be the rocket injection punching press hair that opens in Fig. 2 Motivation feeder connection, 10 be the rocket injection punching engine channel outlet opened in Fig. 5；
（6）Mode conversion is climbed boost phase, and turbogenerator does not produce substantially with the increase of flying height and speed Thrust, now its passage is closed, as 8 be the turbogenerator feeder connection that closes in Fig. 3,13 close in Fig. 6 Turbogenerator channel outlet, rocket injection punching engine passage and the then continuous uniform transition of dual-mode scramjet passage Regulation；
（7）The complete start-up period of dual-mode scramjet passage, rocket injection punching engine passage 20 is closed, is such as schemed 9 be the rocket injection punching engine feeder connection closed in 4, and 14 be the rocket injection punching engine closed in Fig. 7 Channel outlet, now thrust produced completely by dual-mode scramjet；7 be the dual-mode scramjet opened in Fig. 2 Feeder connection；
（8）Turbogenerator passage 19 need to completely close in the prestart of dual-mode scramjet passage 18, therefore, turbine Engine passageways and rocket injection punching engine feeder connection adjustable plate 15 and turbogenerator passage and rocket injection punching press Engine passageways outlet regulating plate 16 is directly closed；Rocket injection punching engine passage 20 and dual-mode scramjet passage 18 need it is gradually excessive, therefore, rocket injection punching engine passage and dual-mode scramjet feeder connection adjustable plate 22 and Rocket injection punching engine passage and the even regulation slowly closing of dual-mode scramjet channel outlet adjustable plate 23.Fig. 8 Air-flow moves towards change before and after middle arrow expression passage switching.
Concrete application approach of the present invention is a lot, and described above is only the preferred embodiment of the present invention, it is noted that for For those skilled in the art, under the premise without departing from the principles of the invention, some improvement can also be made, this A little improve also should be regarded as protection scope of the present invention.

Claims (2)

  1. A kind of 1. pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power, it is characterised in that bimodulus The hypersonic inlet of state punching engine passage, jet pipe respectively with aircraft precursor, rear body integrated design, with bimodulus Based on state punching engine passage, turbogenerator passage, rocket injection punching engine passage and bimodal punching press are started Machine passage is arranged in parallel, and makes under different flight Mach numbers triple channel according to the mutually coordinated work of respective condition of work, including step is such as Under：
    （1）According to hypersonic aircraft general design requirement, the dual-mode scramjet passage under cruising condition is designed； Wherein the hypersonic inlet of dual-mode scramjet passage is using streamlined impeller method and aircraft precursor lower surface one Change design, while air intake duct compressing surface/precursor following table surface construction based on integration entirely bores precursor rider face closely；Jet pipe With body lower surface integrated design after aircraft；
    （2）According to the dimensional parameters of rocket injection punching engine design point, and above-mentioned dual-mode scramjet passage is based on, In dual-mode scramjet passage back structure rocket injection punching engine passage, and lead to dual-mode scramjet Road shares inlet mouth and exported with jet pipe, using upper and lower paralleling model；
    （3）By above-mentioned binary channels distribution structure in parallel into the double hair patterns in left and right, and the position based on the two and inner space, structure Turbogenerator passage is made, it is in parallel with the two left and right；Turbogenerator passage shares inlet mouth in side, while in side Shared jet pipe outlet, possesses independent passage adjustable plate；According to above three engine passageways outlet ports layout, size with And the regulatory demand of operation mode, using two dimension and the Model Design jet pipe of three-dimensional arrangement expansion；Rocket injection punching press is started Machine passage section in parallel with dual-mode scramjet channel outlet is designed using two-dimensional expansion, continuously linear regulation；Propeller for turboprop Machine channel outlet is designed with the section in parallel of the two using three-dimensional expansion, separately adjustable.
  2. 2. the pneumatic propelling integrated layout method of the hypersonic aircraft according to claim 1 based on assembly power, Characterized in that, above-mentioned dual-mode scramjet passage includes：Hypersonic inlet, distance piece, combustion chamber and tail spray Pipe.
CN201610885546.9A 2016-10-10 2016-10-10 The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power Active CN106321283B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610885546.9A CN106321283B (en) 2016-10-10 2016-10-10 The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610885546.9A CN106321283B (en) 2016-10-10 2016-10-10 The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power

Publications (2)

Publication Number Publication Date
CN106321283A CN106321283A (en) 2017-01-11
CN106321283B true CN106321283B (en) 2018-02-06

Family

ID=57820120

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201610885546.9A Active CN106321283B (en) 2016-10-10 2016-10-10 The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power

Country Status (1)

Country Link
CN (1) CN106321283B (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106989891B (en) * 2017-03-30 2020-01-10 南京航空航天大学 Acceleration self-starting experimental method for hypersonic air inlet
CN107336842B (en) * 2017-06-07 2020-05-26 北京航空航天大学 Hypersonic wave-rider canard aerodynamic layout method
CN107630767B (en) * 2017-08-07 2019-07-09 南京航空航天大学 Based on pre- cold mould assembly power hypersonic aircraft aerodynamic arrangement and working method
CN107985626B (en) * 2017-10-27 2021-02-19 南京航空航天大学 Aerodynamic layout design method based on variable configuration aerospace vehicle
CN108561244B (en) * 2017-12-29 2019-10-18 厦门大学 The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist
CN109733634B (en) * 2019-01-08 2020-11-24 厦门大学 Design method of three-dimensional inward-turning four-channel hypersonic combined air inlet channel
CN112340014B (en) * 2020-11-06 2022-05-13 南京航空航天大学 Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof
CN112678206B (en) * 2020-12-29 2022-10-18 中国航天空气动力技术研究院 Pneumatic layout structure and design method of reusable carrier
CN115081117B (en) * 2022-07-04 2023-08-01 南京航空航天大学 Precooling turbine rocket engine performance evaluation method
CN117208194B (en) * 2023-11-09 2024-01-09 清华大学 Wing-hair reconfiguration type variant aircraft

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7216474B2 (en) * 2004-02-19 2007-05-15 Aerojet-General Corporation Integrated air inlet system for multi-propulsion aircraft engines
US7797943B2 (en) * 2006-10-18 2010-09-21 Aerojet-General Corporation Core burning for scramjet engines
US7886516B2 (en) * 2006-12-18 2011-02-15 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system
CN101143623A (en) * 2007-09-28 2008-03-19 大连海事大学 Suction type rocket combination circulation engine
CN103879556B (en) * 2014-03-31 2016-03-02 冯加伟 Wide flight envelope morphing aircraft
CN105156228A (en) * 2015-09-29 2015-12-16 清华大学 Ejector-assistant turbine-based combined cycle engine

Also Published As

Publication number Publication date
CN106321283A (en) 2017-01-11

Similar Documents

Publication Publication Date Title
CN106321283B (en) The pneumatic propelling integrated layout method of hypersonic aircraft based on assembly power
CN104632411B (en) Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways
CN106285946B (en) The channel of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle
CN107630767B (en) Based on pre- cold mould assembly power hypersonic aircraft aerodynamic arrangement and working method
CN109670269B (en) Design method of multi-channel parallel three-power combined engine
US8292217B2 (en) Hypersonic inlet systems and methods
CN105156228A (en) Ejector-assistant turbine-based combined cycle engine
CN108561244B (en) The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist
CN106837550A (en) The method for designing of hypersonic triple channel air intake duct
CN103879556A (en) Wide flight envelop morphing aircraft
CN205047319U (en) Draw and penetrate auxiliary type turbine punching press combination cycle dynamo
CN110541773A (en) Wide-speed-range ramjet engine combustion chamber and working method thereof
CN203740127U (en) Variant unmanned combat aerial vehicle (UCAV)
CN109236496B (en) Design method of three-power combined engine with switchable sub-combustion and super-combustion channels
CN203740126U (en) Morphing aircraft with wide flight envelope
CN109408993B (en) Design method of turbofan and ramjet combined engine with rocket inside
JP2003090233A (en) Variable cycle propulsion system having compressed air branching means for supersonic aircraft
CN109733634B (en) Design method of three-dimensional inward-turning four-channel hypersonic combined air inlet channel
GB1483813A (en) Aircraft multi-engine configuration
CN106014683B (en) A kind of TBCC SERN structures of band supercharging flow control apparatus
CN105571810B (en) Translational inner-parallel combined power air intake channel mode conversion device and translational inner-parallel combined power air intake channel mode conversion method
CN109538377B (en) Design method of three-power combined engine sharing sub-combustion chamber
CN107061010B (en) A kind of rocket based combined cycle engine structure changes air intake duct
CN105539863A (en) Integrated aerodynamic layout method for hypersonic aircraft forebody, air inlet duct and supporting plate
CN209083430U (en) The turbofan punching press combined engine of rocket built in a kind of outer culvert

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant