CN103728140A - Flight test pod for small-sized turbojet engine - Google Patents

Flight test pod for small-sized turbojet engine Download PDF

Info

Publication number
CN103728140A
CN103728140A CN201310652093.1A CN201310652093A CN103728140A CN 103728140 A CN103728140 A CN 103728140A CN 201310652093 A CN201310652093 A CN 201310652093A CN 103728140 A CN103728140 A CN 103728140A
Authority
CN
China
Prior art keywords
gondola
engine
frames
frame
small
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.)
Granted
Application number
CN201310652093.1A
Other languages
Chinese (zh)
Other versions
CN103728140B (en
Inventor
李全祥
王红州
刘学杰
陈华
田玉艳
张海英
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.)
Chinese Flight Test Establishment
Original Assignee
Chinese Flight Test Establishment
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 Chinese Flight Test Establishment filed Critical Chinese Flight Test Establishment
Priority to CN201310652093.1A priority Critical patent/CN103728140B/en
Publication of CN103728140A publication Critical patent/CN103728140A/en
Application granted granted Critical
Publication of CN103728140B publication Critical patent/CN103728140B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Testing Of Engines (AREA)

Abstract

The invention belongs to the technical field of aviation power test flights and relates to a flight test pod for a small-sized turbojet engine. The flight test pod for the small-sized turbojet engine is characterized by comprising a front pod section, a middle pod section and a tail pod section, wherein an air inlet channel is installed in the front pod section, the middle pod section which is used for installation of an engine body and a control unit of the engine body is in butt joint with the front pod section and the tail pod section, and an engine exhaust port which is of a semi-open structure is formed in the tail pod section. According to the flight test pod for the small-sized turbojet engine, the test engine is installed in the flight test pod which is independent of an aerial carrier platform, power of the aerial carrier platform is not provided by the test engine, and therefore relative independence between the test engine and the aerial carrier platform is guaranteed. A user just needs to change the local structure of the flight test pod, and then different types of engine verification test flights can be conducted, and the refitting cost is greatly reduced.

Description

A kind of small-sized turbojet engine flight test gondola
Technical field
The invention belongs to aviation power Flight Test Technique field, relate to a kind of gondola for small-sized turbojet engine flight test.
Background technology
According to product development sizing requirement, domestic new R&D motives is wanted complete design sizing, all will be through certain flight test checking.Current, no matter at home or abroad, the flight test checking means of engine generally take new R&D motives to be arranged on the aircraft platform that technology maturity is high and to carry out.
At present, for small-sized turbojet engine (≤1000Kgf), carry out flight test and there is no Special test platform.Large and medium-sized thrust test platform cannot directly apply to the test of small-sized turbojet engine.In addition, due to blockade on new techniques, abroad about the technical information of engine test platform is difficult to obtain.Therefore, for meeting small-sized turbojet engine, carry out the demand of flight test, be necessary to develop and a kind ofly can be used for the gondola that small-sized turbojet engine makes a flight test.
Summary of the invention
Goal of the invention: develop and a kind ofly can meet small-sized turbojet engine and carry out the gondola of the demand of flight test.
Technical scheme: a kind of small-sized turbojet engine flight test gondola, it comprises gondola leading portion, gondola stage casing and gondola rear, wherein, before gondola, intersegmental part is provided with air intake duct, for install the gondola stage casing of engine body and control module thereof with before gondola, rear docks, and gondola rear is provided with the engine exhaust port of semi-open-type structure.
Gondola leading portion is between 1 to 3 frame, and inner air intake duct is S type, wherein, is S type section between 1 to 2 frame, and 2 frames are between 3 frames being straight-line segment.
Gondola stage casing is between 3-8 frame, and 4-8 frame wherein connects by the long purlin of 7 T-shapes, and between frame, long purlin and covering, employing riveted joint is wet is connected, and forms a semi-monocoque structure.
The Main Load of engine and weight are delivered on general hanger by 6 frames, 7 frames, and wherein, 7 frames are interface frame, mating frame behind stage casing, bear the aerodynamic loading of gondola back segment and the construction weight of self.
Gondola rear comprises 8 to 11 frames, longeron and covering, and wherein, 8,9 frames are overall frames, by 8 long purlins and a box section, be bolted, then with covering riveting; Box section and longeron, at 9 frame places, are bolted; 10 frames are comprised of two panel beating frames, are symmetrically arranged, by being riveted into one with exhausr port and longeron.
On exhausr port, lay two floor height temperature alloys, between high temperature alloy, filling heat insulator silica sand forms high temperature fair water fin.
Engine arrangement is in gondola stage casing, by main thrust pin, base, girt and vertical pull bar, realized the connection of engine and nacelle, wherein, main thrust pin is arranged between gondola aft hook 6-7 frame, and its expansion gap is by the threaded adjusting of the other one end of primary load bearing pin; Vertical pull bar is positioned on 8 frames, and one end is connected on engine body, and the other end is fixed on 8 circle edge by monaural base; Girt is between nacelle 6-7 frame, and one end is fixed on base, and the other end is connected to engine body.
Beneficial effect of the present invention: mentality of designing of the present invention is creative, test engine is arranged in a test gondola being independent of outside carrier aircraft platform, carrier aircraft platform does not rely on test engine that power is provided, keep the relative independentability of test engine and carrier aircraft platform, met small-sized turbojet engine and carry out the demand of flight test.If desired carry out dissimilar engine proving flight, as long as change the outfit after engine, test gondola is carried out to partial structurtes change, therefore greatly reduce repacking cost.In addition, the semi-open-type exhausr port of gondola rear, plays guide effect to engines tail gaseous blast, prevents the heat radiation of high temperature gas flow to carrier aircraft fuselage and abdomeinal fin.Mounting design for the engine nacelle intrinsic motivation that is equipped with small-sized turbojet engine aircraft has important reference.
Accompanying drawing explanation
Fig. 1 is gondola monnolithic case frame bitmap;
Fig. 2 is engine pod leading portion;
Fig. 3 engine pod stage casing;
Fig. 4 engine pod rear;
Fig. 5 engine installation structure;
The connection layout of Fig. 6 main thrust pin and engine;
Wherein, 1-general hanger, the vertical pull bar of 2-, 3-girt, 4-air intake duct, 5-engine body, 6-exhausr port, 7-inlet lip, 8-clip, 9-hanger, the long purlin of 10-, 11-covering, 12-maintenance lid, 13-angle section, 14-monaural base, 15-longeron, 17-box section, 18-high temperature fair water fin, 19-primary load bearing pin, 20-base.
Embodiment
The invention provides a kind of gondola for small-sized turbojet engine flight test.
As shown in Figure 1, the small-sized turbojet engine flight test of the present invention gondola is provided with 10 frames altogether, and wherein stage casing 4 frames, 5 frames, 6 frames, 7 frames are cabin body main bulkhead, and 1 frame, 2 frames are structural rigidity frame, and 3 frames, 9 frames, 10 frames are ordinary construction frame.
Whole gondola is hung aboard by general hanger 1.With 3 frames, 8 frame position interphases, by gondola, divide leading portion, stage casing and rear, in both sides, stage casing, have 6 place's maintenance lids 12 as watch window and maintenance channel.
As shown in Figure 2, gondola leading portion, between 1-3 frame, is inside provided with serpentine air intake duct 4.Air intake duct 4 is divided into forward and backward two sections, take overall frame as interphase.Leading portion, 1 frame to 2 frame is serpentine section, back segment 2 frame to 3 frames are straight-line segment.In order to increase its rigidity, what prevent that air-flow from causing agitates, and between frame and frame, air intake duct outer wall is arranged clip 8.For the ease of moulding and assembling, inlet lip adopts integrated machine to add part.2 frames are that integrated machine adds frame, in order to adjust air intake duct leading portion, dock the rigging error forming with stage casing, eliminate docking jump, and 3 frames are combo box (frame and web combination).The transition of air intake duct inner wall smooth, to meet the pneumatic smooth requirement of engine.According to the theoretical profile of air intake duct, in conjunction with the structure situation of former auxiliary fuel tank radome fairing, the newly-increased inlet lip 7 at 1 frame place.
As shown in Figure 3, dock with gondola front and rear sections in gondola stage casing, between 3-8 frame, for the finished products such as engine body 5 and control module thereof are installed.Two hangers 9 that gondola stage casing is connected with general hanger 1, are positioned at 4-5 frame, between 6-7 frame.4 frames, 5 frames adopt the mount structure form of former auxiliary fuel tank; 6 frames, 7 two frames are positioned at and start owner's hitch point both sides, and the Main Load of engine and weight are delivered on general hanger 1 by 6 frames, 7 frames; 7 frames are interface frame, mating frame behind stage casing, bear the aerodynamic loading of gondola back segment and the construction weight of self.5 overall frames in gondola stage casing connect by the long purlin 10 of 7 T-shapes; Between frame, long purlin and covering 11, adopting riveted joint to wet is connected, forms a semi-monocoque structure.6 frames, 7 frames and 8 frames in gondola stage casing, for main load-carrying construction part, for integrated machine adds frame, 2024 pretensioning plates are selected in long purlin, and covering 11 is former auxiliary fuel tank covering.
The air intake duct 4 in gondola stage casing, is divided into 2 sections, in the docking of 5 frame places, then is connected with 5 frames by 4 angle sections 13.
As shown in Figure 4, after gondola rear is positioned at 9 frames, this section is furnished with the exhausr port 6 of engine.Exhausr port 6 is semi-open-type structure, and engines tail gaseous blast is played to guide effect, prevents the heat radiation of high temperature gas flow to carrier aircraft fuselage and abdomeinal fin.
Engine pod rear, mainly by 8 frames, 9 frames, 10 frames, four structural frames of 11 frame, the composition such as longeron 15 and covering 11.8,9 frames are overall frames, be bolted, then rivet with covering 11 by 8 long purlins 16 and a box section 17; Box section 17, is bolted at 9 frame places with longeron 15; 10 frames are comprised of two panel beating frames, are symmetrically arranged, by being riveted into one with exhausr port 6 and longeron 15.Because engines tail gaseous blast temperature is very high, need on exhausr port, lay two floor height temperature alloys, spacing 20mm, filling heat insulator silica sand forms high temperature fair water fin 18 between the two.
8 frames, 9 frames, 11 frames and the longeron 15 of gondola rear, be main load-carrying construction part, adopts integrated machine to add frame, and 2024 pretensioning plates are selected in long purlin 10.
As shown in Figure 5, engine arrangement, in gondola stage casing, is realized the connection of engine and nacelle by main thrust pin 19, base 20, girt 3 and vertical pull bar 2.
Main thrust pin 19 is arranged between gondola aft hook 6-7 frame upper, is symmetrically arranged, and the thrust load of engine and inertial load pass to gondola by the base 20 being attached thereto.
Vertical pull bar 2 is positioned on 8 frames, and one end is connected on engine body 5, and the other end is fixed on 8 circle edge by monaural base 14, regulates the luffing angle of engine body 5 and gondola, the pitching moment producing in order to center of gravity and the engine of balanced engine.
As shown in Figure 6, engine must leave enough gaps with primary load bearing pin 19, to meet expansion gap requirement in engine operation after installing.The adjusting in gap is by the threaded adjusting of primary load bearing pin 19 other one end.
The installation of engine, except main thrust pin, is also connected with nacelle with vertical pull bar 2 by girt 3, in order to the additional load and the moment of torsion that produce in balanced engine work.
The girt 3 of test engine is between nacelle 6-7 frame, and one end is fixed on base 20, and the other end is connected on engine body 5, in order to regulate the gap (1-1.5mm) of engine body 5 and main thrust pin 19.

Claims (7)

1. a small-sized turbojet engine flight test gondola, it is characterized in that, comprise gondola leading portion, gondola stage casing and gondola rear, wherein, before gondola, intersegmental part is provided with air intake duct, for install the gondola stage casing of engine body and control module thereof with before gondola, rear docks, and gondola rear is provided with the engine exhaust port of semi-open-type structure.
2. small-sized turbojet engine flight test gondola according to claim 1, is characterized in that, gondola leading portion is between 1 to 3 frame, and inner air intake duct is S type, wherein, is S type section between 1 to 2 frame, and 2 frames are between 3 frames being straight-line segment.
3. small-sized turbojet engine flight test gondola according to claim 1, it is characterized in that, gondola stage casing is between 3-8 frame, and 4-8 frame wherein connects by the long purlin of 7 T-shapes, between frame, long purlin and covering, adopting riveted joint to wet is connected, forms a semi-monocoque structure.
4. small-sized turbojet engine flight test gondola according to claim 1, it is characterized in that, the Main Load of engine and weight are delivered on general hanger, wherein by 6 frames, 7 frames, 7 frames are interface frame, mating frame behind stage casing, bear the aerodynamic loading of gondola back segment and the construction weight of self.
5. small-sized turbojet engine flight test gondola according to claim 1, is characterized in that, gondola rear comprises 8 to 11 frames, longeron and covering, wherein, 8,9 frames are overall frames, by 8 long purlins and a box section, be bolted, then with covering riveting; Box section and longeron, at 9 frame places, are bolted; 10 frames are comprised of two panel beating frames, are symmetrically arranged, by being riveted into one with exhausr port and longeron.
6. small-sized turbojet engine flight test gondola according to claim 1, is characterized in that, lays two floor height temperature alloys on exhausr port, and between high temperature alloy, filling heat insulator silica sand forms high temperature fair water fin.
7. small-sized turbojet engine flight test gondola according to claim 1, it is characterized in that, engine arrangement is in gondola stage casing, by main thrust pin, base, girt and vertical pull bar, realized the connection of engine and nacelle, wherein, main thrust pin is arranged between gondola aft hook 6-7 frame, and its expansion gap is by the threaded adjusting of the other one end of primary load bearing pin; Vertical pull bar is positioned on 8 frames, and one end is connected on engine body, and the other end is fixed on 8 circle edge by monaural base; Girt is between nacelle 6-7 frame, and one end is fixed on base, and the other end is connected to engine body.
CN201310652093.1A 2013-12-04 2013-12-04 A kind of small-size turbojet engine flight test pod Active CN103728140B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201310652093.1A CN103728140B (en) 2013-12-04 2013-12-04 A kind of small-size turbojet engine flight test pod

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201310652093.1A CN103728140B (en) 2013-12-04 2013-12-04 A kind of small-size turbojet engine flight test pod

Publications (2)

Publication Number Publication Date
CN103728140A true CN103728140A (en) 2014-04-16
CN103728140B CN103728140B (en) 2017-01-04

Family

ID=50452310

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201310652093.1A Active CN103728140B (en) 2013-12-04 2013-12-04 A kind of small-size turbojet engine flight test pod

Country Status (1)

Country Link
CN (1) CN103728140B (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105447249A (en) * 2015-11-25 2016-03-30 中国航空工业集团公司沈阳飞机设计研究所 Static test load calculation method for engine nacelle structure
CN105691626A (en) * 2014-11-28 2016-06-22 中国飞行试验研究院 Aircraft fuselage bottom pod
CN107672810A (en) * 2016-08-01 2018-02-09 北京遥感设备研究所 A kind of general hang flies nacelle device
CN108820246A (en) * 2018-07-25 2018-11-16 中国科学院工程热物理研究所 A kind of small-size turbojet engine quickly upper machine mounting structure and method
CN110441064A (en) * 2019-08-13 2019-11-12 中国航发贵阳发动机设计研究所 A kind of auxiliary hanging pull rod assembly method optimizing aeroplane engine machine vibration
CN111746820A (en) * 2019-03-28 2020-10-09 中国航发商用航空发动机有限责任公司 Aircraft engine flight test system and test method
CN113200149A (en) * 2021-05-18 2021-08-03 中国空气动力研究与发展中心空天技术研究所 Fixed wing unmanned aerial vehicle load structure based on intake duct

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1619489A1 (en) * 2004-07-19 2006-01-25 Techspace Aero Test equipment for the development of an aircraft gas turbine engine
RU2336514C1 (en) * 2007-03-22 2008-10-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Method of altitude test of double-circuit turbojet engines (tjedc) and test bench for its implementation
CN102023096A (en) * 2010-11-15 2011-04-20 北京航空航天大学 Internal-flow high-altitude simulation test device and test method of aviation piston engine
CN102261996A (en) * 2011-04-27 2011-11-30 北京航空航天大学 Micro jet engine test bench

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1619489A1 (en) * 2004-07-19 2006-01-25 Techspace Aero Test equipment for the development of an aircraft gas turbine engine
RU2336514C1 (en) * 2007-03-22 2008-10-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Method of altitude test of double-circuit turbojet engines (tjedc) and test bench for its implementation
CN102023096A (en) * 2010-11-15 2011-04-20 北京航空航天大学 Internal-flow high-altitude simulation test device and test method of aviation piston engine
CN102261996A (en) * 2011-04-27 2011-11-30 北京航空航天大学 Micro jet engine test bench

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
王玲玲等: "某通用吊舱起动机环境特性预测方法试验研究", 《科学技术与工程》 *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105691626A (en) * 2014-11-28 2016-06-22 中国飞行试验研究院 Aircraft fuselage bottom pod
CN105691626B (en) * 2014-11-28 2018-07-20 中国飞行试验研究院 A kind of airframe bottom gondola
CN105447249A (en) * 2015-11-25 2016-03-30 中国航空工业集团公司沈阳飞机设计研究所 Static test load calculation method for engine nacelle structure
CN105447249B (en) * 2015-11-25 2018-12-11 中国航空工业集团公司沈阳飞机设计研究所 A kind of slow test load calculation method of power structure for pod
CN107672810A (en) * 2016-08-01 2018-02-09 北京遥感设备研究所 A kind of general hang flies nacelle device
CN108820246A (en) * 2018-07-25 2018-11-16 中国科学院工程热物理研究所 A kind of small-size turbojet engine quickly upper machine mounting structure and method
CN111746820A (en) * 2019-03-28 2020-10-09 中国航发商用航空发动机有限责任公司 Aircraft engine flight test system and test method
CN110441064A (en) * 2019-08-13 2019-11-12 中国航发贵阳发动机设计研究所 A kind of auxiliary hanging pull rod assembly method optimizing aeroplane engine machine vibration
CN110441064B (en) * 2019-08-13 2021-06-22 中国航发贵阳发动机设计研究所 Auxiliary hanging pull rod assembling method for optimizing vibration of aircraft engine
CN113200149A (en) * 2021-05-18 2021-08-03 中国空气动力研究与发展中心空天技术研究所 Fixed wing unmanned aerial vehicle load structure based on intake duct

Also Published As

Publication number Publication date
CN103728140B (en) 2017-01-04

Similar Documents

Publication Publication Date Title
CN103728140A (en) Flight test pod for small-sized turbojet engine
US8220739B2 (en) Beam mounted rear propulsion system for an aircraft and aircraft with such system
US8162254B2 (en) Aircraft engine assembly comprising a junction aerodynamic fairing mounted on two separate elements
JP5479892B2 (en) Aircraft engine assembly with a cradle supporting a fan cowl, attached to two separate components
CN102673791B (en) Aircraft engine attachment pylon
US7797947B2 (en) Mounting assembly for securing an engine to an aircraft wing
CN102414083B (en) Airplane with tailcoat tail assembly and rear engine
US9211955B1 (en) Methods and apparatus for supporting engines and nacelles relative to aircraft wings
US8196861B2 (en) Rear propulsion system with lateral air inlets for an aircraft with such system
CN106061841A (en) Engine pylon structure
CN102026870A (en) Engine mounting pylon including means for attaching spars and panels arranged outside the inner space of the box
US8864066B2 (en) Rigid aircraft pylon fitted with a rib extension for taking up the moment in the lengthways direction
US20150307199A1 (en) Assembly for an aircraft comprising an attachment pylon primary structure formed with three independent elements
US20180305032A1 (en) Engine assembly for an aircraft, comprising a front engine mount incorporated with the box of the mounting pylon
GB2547020A (en) Design relating to improving aircraft
CN103144763B (en) The fixing aerodynamic structures assembly of aircraft and the shield assemblies of aircraft
CN103507961A (en) Aircraft air inlet diverter assemblies with improved aerodynamic characteristics
US20180222595A1 (en) Aircraft engine pylon with inbuilt multifunctional framework
US9932106B1 (en) Securing hydraulic lines in an aircraft
CN103748011B (en) Including turbogenerator with for being connected to the assembly of the system of airframe
US9868539B2 (en) Aircraft engine pylon to wing mounting assembly
CN102849218A (en) Mounting beam for auxiliary power unit of aircraft
US11511873B2 (en) Propulsion assembly for an aircraft, comprising a nacelle load support fastened to a pylon
CN113911361B (en) Double-hanging-point parallel large-span store hanging and throwing device
EP4391222A1 (en) Aircraft antenna

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant