CN103728140B - A kind of small-size turbojet engine flight test pod - Google Patents
A kind of small-size turbojet engine flight test pod Download PDFInfo
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- CN103728140B CN103728140B CN201310652093.1A CN201310652093A CN103728140B CN 103728140 B CN103728140 B CN 103728140B CN 201310652093 A CN201310652093 A CN 201310652093A CN 103728140 B CN103728140 B CN 103728140B
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Abstract
The invention belongs to aviation power Flight Test Technique field, relate to a kind of gondola for small-size turbojet engine flight test.It is characterized in that, including gondola leading portion, gondola stage casing and gondola rear, wherein, gondola leading portion is internally installed air intake duct, for the gondola stage casing of installing engine body and control unit thereof with before gondola, rear dock, and gondola rear is provided with the engine exhaust port of semi-open-type structure.The present invention design test engine is arranged on one independent of in the test gondola outside carrier aircraft platform, carrier aircraft platform provides power not against test engine, maintains the relative independentability of test engine and carrier aircraft platform.Only need that test gondola is carried out partial structurtes change and can carry out different types of electromotor proving flight, greatly reduce repacking cost.
Description
Technical field
The invention belongs to aviation power Flight Test Technique field, relate to a kind of for small-size turbojet engine flight test
Gondola.
Background technology
According to product development type approval requirements, domestic new R&D motives wants complete design to shape, will be through certain
Flight test checking.Currently, the most at home or abroad, the flight test checking means of electromotor are general
Take to be arranged on new R&D motives on one high aircraft platform of technology maturity and carry out.
Carry out flight test currently for small-size turbojet engine (≤1000Kgf) and there is no Special test platform.
Large and medium-sized thrust test platform then cannot directly apply to the test of small-size turbojet engine.It addition, by
In blockade on new techniques, abroad the technical data about engine test platform is difficult to obtain.Therefore, little for meeting
Type turbojet engine carries out the demand of flight test, it is necessary to develops one and can be used for small-size turbojet engine
The gondola made a flight test.
Summary of the invention
Goal of the invention: develop and a kind of can meet small-size turbojet engine and carry out the hanging of demand of flight test
Cabin.
Technical scheme: a kind of small-size turbojet engine flight test pod, it includes in gondola leading portion, gondola
Section and gondola rear, wherein, gondola leading portion is internally installed air intake duct, be used for installing engine body and
The gondola stage casing of control unit with before gondola, rear dock, and gondola rear is provided with semi-open-type structure
Engine exhaust port.
Gondola leading portion is between 1 to 3 frames, and internal air intake duct is S type, wherein, is S between 1 to 2 frames
Type section, is straightway between 2 frames to 3 frames.
Gondola stage casing is between 3-8 frame, and 4-8 frame therein is connected by 7 T-shape stringer, frame,
Use riveting wet connection between stringer and eyelid covering, form a semi-monocoque structure.
Main Load and the weight of electromotor are delivered on general hanger by 6 frames, 7 frames, and wherein, 7 frames are
Interface frame, mating frame behind stage casing, bears aerodynamic loading and the construction weight of self of gondola back segment.
Gondola rear includes 8 to 11 frames, a longeron and eyelid covering, and wherein, 8,9 frames are overall frames, by 8
Individual stringer and a box section are bolted, then with covering riveting；Box section and longeron, at 9 frames, pass through
Bolt connects；10 frames are made up of two panel beating frames, are symmetrically arranged, are riveted into longeron by air vent
Integrally.
Laying two floor height temperature alloys on air vent, between high temperature alloy, filling heat insulator quartz sand forms high temperature
Deflector.
Engine arrangement, in gondola stage casing, is realized by primary load bearing pin, base, girt and vertical ties
Electromotor and the connection of nacelle, wherein, primary load bearing pin is arranged between gondola aft hook 6-7 frame, its heat
The other end of threaded adjusting of primary load bearing pin is passed through in expansion clearance；Vertical ties is positioned on 8 frames, and one end connects
On engine body, the other end is fixed on 8 circle edge by monaural base；Girt is positioned at nacelle
Between 6-7 frame, one end is fixed on base, and the other end is connected to engine body.
Beneficial effects of the present invention: mentality of designing of the present invention is adopted an original approach, and test engine is arranged on one
Independent of in the test gondola outside carrier aircraft platform, carrier aircraft platform provides power not against test engine, protects
Hold the relative independentability of test engine and carrier aircraft platform, met small-size turbojet engine and carry out flight test
Demand.If desired different types of electromotor proving flight is carried out, as long as after the electromotor that changes the outfit, to test
Gondola carries out partial structurtes to be changed, and therefore greatly reduces repacking cost.It addition, gondola rear
Semi-open-type air vent, plays guide effect to engines tail gaseous blast, prevents high temperature gas flow to carrier aircraft fuselage
Heat radiation with abdomeinal fin.Installation for the engine nacelle intrinsic motivation of equipped small-size turbojet engine aircraft
It is designed with 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；
Fig. 6 primary load bearing pin and the connection figure of electromotor；
Wherein, 1-general hanger, 2-vertical ties, 3-girt, 4-air intake duct, 5-engine body, 6-
Air vent, 7-inlet lip, 8-clip, 9-hanger, 10-stringer, 11-eyelid covering, 12-maintenance lid,
13-angle section, 14-monaural base, 15-longeron, 17-box section, 18-high temperature deflector, 19-primary load bearing pin,
20-base.
Detailed description of the invention
The present invention provides a kind of gondola for small-size turbojet engine flight test.
As it is shown in figure 1, small-size turbojet engine flight test pod of the present invention is provided with 10 frames altogether, wherein
Stage casing 4 frame, 5 frames, 6 frames, 7 frames are nacelle main bulkhead, and 1 frame, 2 frames are structural rigidity frame, 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 separating surfaces, by gondola
Divide leading portion, stage casing and rear, have maintenance lid 12 at 6 in both sides, stage casing logical as watch window and maintenance
Road.
As in figure 2 it is shown, gondola leading portion is between 1-3 frame, serpentine air intake duct 4 is inside installed.Air inlet
Road 4 is divided into forward and backward two-stage nitration, with overall frame as separating surface.Leading portion, 1 frame to 2 frames is serpentine section, after
Section 2 frames to 3 frames are straightway.In order to increase its rigidity, prevent what air-flow from causing to agitate, frame and frame it
Between, air intake duct outer wall arranges clip 8.For the ease of molding and assembling, inlet lip uses integrated machine to add
Part.2 frames are that integrated machine adds frame, the rigging error formed to adjust air intake duct leading portion to dock with stage casing, disappear
Except docking jump, 3 frames are combo box (frame combines with web).Air intake duct inner wall smooth transition, sends out to meet
The pneumatic smooth requirement of motivation.According to the theoretical profile of air intake duct, in conjunction with the structure situation of former auxiliary fuel tank trousers,
Inlet lip 7 is increased newly at 1 frame.
As it is shown on figure 3, gondola stage casing is docked with gondola front and rear sections, between 3-8 frame, it is used for installing
The finished products such as engine body 5 and control unit thereof.Two hangers 9 that gondola stage casing is connected with general hanger 1,
It is positioned at 4-5 frame, between 6-7 frame.4 frames, 5 frames use the mount structure form of former auxiliary fuel tank；6 frames, 7 liang
Individual frame is positioned at and starts owner's hitch point both sides, the Main Load of electromotor and weight to be transmitted by 6 frames, 7 frames
On general hanger 1；7 frames are interface frame, mating frame behind stage casing, bear aerodynamic loading and the knot of self of gondola back segment
Structure weight.5 overall frames in gondola stage casing are connected by 7 T-shape stringer 10；Frame, stringer and illiteracy
Use riveting wet connection between skin 11, form a semi-monocoque structure.6 frames in gondola stage casing, 7 frames and
8 frames, for main load-carrying construction part, add frame for integrated machine, and stringer selects 2024 pretensioning plates, eyelid covering 11
For former auxiliary fuel tank eyelid covering.
The air intake duct 4 in gondola stage casing, is divided into 2 sections, docks at 5 frames, then by 4 angle sections 13 and 5
Frame is connected.
As shown in Figure 4, after gondola rear is positioned at 9 frames, this section is disposed with the air vent 6 of electromotor.Row
QI KOU 6 is semi-open-type structure, and engines tail gaseous blast is played guide effect, prevents high temperature gas flow to load
Machine fuselage and the heat radiation of abdomeinal fin.
Engine pod rear, mainly by 8 frames, 9 frames, 10 frames, four structural frames of 11 frame, a longeron
15 and the composition such as eyelid covering 11.8,9 frames are overall frames, 8 stringer 16 and a box section 17 pass through spiral shell
Tether and connect, then rivet with eyelid covering 11；Box section 17 and longeron 15, at 9 frames, are bolted；10
Frame is made up of two panel beating frames, is symmetrically arranged, and is riveted into one by air vent 6 and longeron 15.By
The highest in engines tail gaseous blast temperature, need to lay two floor height temperature alloys on air vent, spacing 20mm, two
Between person, filling heat insulator quartz sand forms high temperature deflector 18.
8 frames of gondola rear, 9 frames, 11 frames and longeron 15, for main load-carrying construction part, use integrated machine
Adding frame, stringer 10 selects 2024 pretensioning plates.
As it is shown in figure 5, engine arrangement is in gondola stage casing, by primary load bearing pin 19, base 20, girt
3 and vertical ties 2 realize the connection of electromotor and nacelle.
Primary load bearing pin 19 is symmetrically arranged on being arranged between gondola aft hook 6-7 frame, electromotor
Thrust load and inertial load pass to gondola by the base 20 being attached thereto.
Vertical ties 2 is positioned on 8 frames, and one end is connected on engine body 5, and the other end is by the bottom of monaural
Seat 14 is fixed on 8 circle edge, regulation engine body 5 and the luffing angle of gondola, starts in order to balance
Pitching moment produced by the center of gravity of machine and electromotor.
As shown in Figure 6, after electromotor is installed, it is necessary to leave enough gaps with primary load bearing pin 19, to meet
Expansion gap requirement in electromotor work.The regulation in gap is adjusted by the other end of screw thread of primary load bearing pin 19
Joint.
The installation of electromotor, in addition to primary load bearing pin, also by girt 3 and vertical ties 2 and nacelle
It is connected, produced additional load and moment of torsion in working in order to balanced engine.
The girt 3 of test engine is between nacelle 6-7 frame, and one end is fixed on base 20, separately
One end is connected on engine body 5, in order to regulate the gap of engine body 5 and primary load bearing pin 19
(1-1.5mm)。
Claims (5)
1. a small-size turbojet engine flight test pod, it is characterised in that include gondola leading portion, gondola
Stage casing and gondola rear, wherein, gondola leading portion is internally installed air intake duct, be used for installing engine body and
The gondola stage casing of its control unit with before gondola, rear dock, and gondola rear is provided with semi-open-type structure
Engine exhaust port, gondola leading portion is between 1 to 3 frames, and internal air intake duct is S type, wherein, 1 to 2
Being S type section between frame, be straightway between 2 frames to 3 frames, gondola stage casing is between 3-8 frame, wherein
4-8 frame connected by 7 T-shape stringer, use riveting wet connection, shape between frame, stringer and eyelid covering
Become a semi-monocoque structure.
Small-size turbojet engine flight test pod the most according to claim 1, it is characterised in that send out
Main Load and the weight of motivation are delivered on general hanger by 6 frames, 7 frames, wherein, after 7 frames are stage casing
Interface frame, mating frame, bears aerodynamic loading and the construction weight of self of gondola back segment.
Small-size turbojet engine flight test pod the most according to claim 1, it is characterised in that hang
Cabin rear includes 8 to 11 frames, a longeron and eyelid covering, and wherein, 8,9 frames are overall frames, long by 8
Purlin and a box section are bolted, then with covering riveting；Box section and longeron, at 9 frames, pass through bolt
Connect；10 frames are made up of two panel beating frames, are symmetrically arranged, and are riveted into one by air vent and longeron.
Small-size turbojet engine flight test pod the most according to claim 1, it is characterised in that row
Laying two floor height temperature alloys in QI KOU, between high temperature alloy, filling heat insulator quartz sand forms high temperature deflector.
Small-size turbojet engine flight test pod the most according to claim 1, it is characterised in that send out
Motivation is arranged in gondola stage casing, primary load bearing pin, base, girt and vertical ties realize electromotor
With the connection of nacelle, wherein, primary load bearing pin is arranged between gondola aft hook 6-7 frame, between its thermal expansion
Gap passes through the other end of threaded adjusting of primary load bearing pin；Vertical ties is positioned on 8 frames, and one end is connected to start
On machine body, the other end is fixed on 8 circle edge by monaural base；Girt is positioned at nacelle 6-7 frame
Between, one end is fixed on base, and the other end is connected to engine body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310652093.1A CN103728140B (en) | 2013-12-04 | 2013-12-04 | A kind of small-size turbojet engine flight test pod |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310652093.1A CN103728140B (en) | 2013-12-04 | 2013-12-04 | A kind of small-size turbojet engine flight test pod |
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| CN103728140A CN103728140A (en) | 2014-04-16 |
| CN103728140B true CN103728140B (en) | 2017-01-04 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| RU2785261C1 (en) * | 2022-06-14 | 2022-12-05 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации | Flying laboratory |
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| CN105691626B (en) * | 2014-11-28 | 2018-07-20 | 中国飞行试验研究院 | A kind of airframe bottom gondola |
| 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 |
| CN108820246B (en) * | 2018-07-25 | 2023-08-04 | 中国科学院工程热物理研究所 | Quick loading installation structure and method for small turbojet engine |
| CN111746820B (en) * | 2019-03-28 | 2022-07-12 | 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 |
| 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 |
| CN113200149B (en) * | 2021-05-18 | 2023-04-11 | 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 |
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| RU2785261C1 (en) * | 2022-06-14 | 2022-12-05 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации | Flying laboratory |
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| CN103728140A (en) | 2014-04-16 |
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