CN104139867A - System and method for loading airframe payload - Google Patents
System and method for loading airframe payload Download PDFInfo
- Publication number
- CN104139867A CN104139867A CN201310169979.0A CN201310169979A CN104139867A CN 104139867 A CN104139867 A CN 104139867A CN 201310169979 A CN201310169979 A CN 201310169979A CN 104139867 A CN104139867 A CN 104139867A
- Authority
- CN
- China
- Prior art keywords
- loading
- lever
- fuselage
- airframe
- load
- 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.)
- Pending
Links
- 238000011068 loading method Methods 0.000 title claims abstract description 110
- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000012360 testing method Methods 0.000 claims abstract description 13
- 238000007789 sealing Methods 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 3
- 238000010079 rubber tapping Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 abstract 3
- 238000013461 design Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000009661 fatigue test Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to a system and a method for loading airframe payload. The system for loading the airframe payload comprises a fixed device for loading and a loading lever system, wherein the fixed device for loading is fixed inside the airframe; a test loading interface is provided for assembling the loading lever system; an airframe penetrating loading connecting piece which is connected with an outer actuating cylinder of the air frame is connected to the final-stage lever of the lever system, and the penetrating position in the skin of the airframe is sealed. For loading, the load applied by a loading actuating cylinder is transferred to the lever system through the airframe penetrating loading connecting piece and distributed by a lever ration by use of the lever system; the distributed load is transferred to an air frame seat sliding rail or a floor beam through the fixed device for loading. Meanwhile, in the loading process, the airframe is sealed with pressure so that stable charged pressure can be ensured; as a result, the harmony between the pressure charging loading and the loading of the actuating cylinder is improved, and the reliability and authenticity of the loading system is guaranteed.
Description
Technical field
The present invention relates to a kind of test loading method, particularly a kind of airframe commercial transport loading system and loading method.
Background technology
In full machine structural static, fatigue test, fuselage load mainly comprises: the miscellaneous part being connected with fuselage passes to the load of fuselage; The force of inertia that fuselage is subject to; Be distributed in the aerodynamic force on fuselage surface; Pressure reduction in fuselage sealed module, inlet channel, dedicated bay, the specific load that forced landing, emergency landing produce.
In order to simulate truly the stressed of fuselage as far as possible, need in theory various load to apply separately, but in actual test, the restriction of place and equipment is put to the test, consider fuselage load feature and the size of each load to structure influence, the force of inertia that fuselage is subject to and the aerodynamic force being distributed on fuselage surface generally adopt adhesive bandage-lever system to load on fuselage skin, and the pressure reduction of fuselage applies by inflation.Traditional adhesive bandage-lever system loading method can meet the requirement of the whole examination of test, but to carrying that can not real simulation floor in details.Along with the raising day by day of testing technique, test requirements document increasingly stringent.The commercial transport of now civil aircraft requires distributed load on fuselage interior floor panel structure or rail structure, how on airtight construction, to apply distributed load, is the difficult problem that aircraft static(al), fatigue test must solve.
Summary of the invention
The object of the invention is: propose a kind of enforcement fuselage commercial transport loading method, can simulate comparatively exactly the transmission of commercial transport, carry out applying of commercial transport and airtight load simultaneously, and alleviated loading facilities weight, reduce the heavy difficulty of test button.
Technical scheme of the present invention is: a kind of airframe commercial transport loading system, it comprises loading fixed equipment, loads lever system, wherein, load fixed equipment and be fixed on fuselage interior, test loading interface is provided, by this interface assembling, load lever system, on lever system final stage lever, connect the fuselage of wearing being connected with pressurized strut outside fuselage and load attaching parts, and perforation place of closed fuselage covering.
Described loading is fixedly installed on fuselage interior floor, and equipment comprises that slide rail loads fixed equipment and ground sheet frame loads fixed equipment.
Slide rail loads fixed equipment and comprises loading joint and bolt, and bolt holding, in sliding-rail groove, is spirally connected with loading joint, and loading joint is fixed on slide rail face.
Ground sheet frame loads fixed equipment and comprises special joint and holding bolt, and special joint is placed on the architrave bar of floor, adopts the holding of holding bolt on ground sheet frame web.
Described loading lever system comprises first order lever, second stage lever and third stage lever, and described one-level lever is hinged on and loads on fixed equipment joint, and fuselage loading attaching parts is worn in connection; Described second stage lever, third stage lever are connected to first order lever bottom by lever attaching parts, and it is hinged that third stage lever loads fixed equipment special joint by loading facilities and ground sheet frame.
Fuselage skin perforation place is sealed by seal bellows.
Fuselage skin loading facilities and structure button heavily adopt to hang counterbalancing weight or initiatively put button and weigh; Fuselage cargo loading facilities adopts independent counterbalancing weight button weight.
An airframe commercial transport loading method, its process is as follows:
First load fixed equipment and install, and loading fixed equipment interface installation lever system, on lever system final stage lever, connect and wear fuselage loading attaching parts, at the loading attaching parts of wearing place's fuselage, connect loading pressurized strut;
During loading, the load that loading pressurized strut applies transfers loads to lever system by wearing fuselage loading attaching parts, by lever system, load is distributed by lever ratio, load after distribution is delivered on fuselage seat slide or floor bearer by loading fixed equipment, simultaneously in loading procedure, fuselage interior is carried out pressurising, is carried out the sealing of fuselage tapping by seal bellows.
Technique effect of the present invention is: the invention solves fuselage cargo or the objective problem that cannot apply from outside of carrying in the past, its good effect the has been true and accurate simulation actual stand under load of fuselage, for static(al), the fatigue test of structure of the same type have been opened an approach that fuselage test loads.
Accompanying drawing explanation
Fig. 1 is the structural representation of airframe commercial transport loading system of the present invention;
Fig. 2 is that slide rail loads connection diagram;
Fig. 3 is that ground sheet frame loads connection diagram;
Fig. 4 loads lever system structural representation;
Fig. 5 loads lever system height to reduce schematic diagram;
Fig. 6 is seal bellows structural representation;
Fig. 7 is seal bellows sealing schematic diagram,
Wherein, 1-loading fixed equipment, 2-loading water-tight equipment, 3-loading lever system, 4-loading joint, 5-bolt, 6-special joint, 7-holding bolt, 8-one-level lever, 9-second lever, 10-tri-grades of levers, 11-wear fuselage and load attaching parts, 12-first order lever, 13-second stage lever, 14-third stage lever.
The specific embodiment
Below in conjunction with accompanying drawing, many present invention are described further:
Refer to Fig. 1, it is that airframe commercial transport loading system of the present invention comprises loading fixed equipment 1, loads water-tight equipment 2, loads lever system 3.
Wherein, what load fixed equipment is divided into two kinds, a kind of for slide rail loads fixed equipment, and a kind of is that ground sheet frame loads fixed equipment.
As shown in Figure 2, slide rail loads fixed equipment and comprises and load joint 4 and bolt 5, and bolt 5 holdings, in sliding-rail groove, and are spirally connected with loading joint 4, and loading joint is fixed on slide rail face.During loading, load is delivered on slide rail by loading joint 4, and it both can apply upwards load, also can apply down load, meets simultaneously and loads positioning requirements.
As shown in Figure 3, ground sheet frame loading fixed equipment comprises special joint 6 and holding bolt 7.Wherein, special joint 6 is class ears structures, and its two sides are placed on the architrave bar of floor, adopt 7 holdings of holding bolt on ground sheet frame web.During loading, load is delivered on ground sheet frame by special joint 6, and this equipment only can apply down load, meets and load positioning requirements during test.
Described loading lever system comprises one-level lever 8, second lever 9 and three grades of levers 10 and wears fuselage loading attaching parts 11.As shown in Figure 4, adopting slide rail to load in the load(ing) point of fixed equipment, described one-level lever 8 is hinged on and loads on fixed equipment joint, the reserved joint of itself, hinged with second lever 9, three grades of levers 10, and connect and wear fuselage and load attaching parts 11, hinge hole is installed tie bolt.As shown in Figure 5, adopting second stage lever 13, the third stage lever 14 in lever system described in the load(ing) point of ground sheet frame loading fixed equipment to be connected to first order lever 12 bottoms by lever attaching parts, it is hinged that third stage lever 14 loads fixed equipment special joint by loading facilities and ground sheet frame, thereby effectively reduce height.
As shown in Figure 6, load water-tight equipment employing and be arranged on the seal bellows on fuselage skin.During due to pressurising, internal pressure is greater than external pressure, the inner seal rings of seal bellows relies on fuselage interior air pressure to be pressed on fuselage interior covering, outside seal circle is by sealing draw-in groove holding externally on covering, rely on good elasticity and the inflation pressure of rubber, solve the problem sealing after fuselage skin distortion.
In addition, commercial transport of the present invention loads lever system and adopts loss of weight design, and concrete loss of weight design is as follows:
1) use I-beam section to replace traditional channel-section steel lever system;
2) when lever design, introduce equal strength design concept, according to carrying, carry out variable section design;
3) process lightening hole taking into full account under the prerequisite of strength and stiffness.
Middle machine body button of the present invention is heavily divided into two parts: fuselage skin loading facilities and structure button heavily adopt and hang counterbalancing weight or initiatively put the method that button is heavy; Fuselage cargo loading facilities adopts the method that independent counterbalancing weight button is heavy.
Airframe commercial transport loading system fitting process of the present invention is as follows:
First loading fixed equipment installs, and loading fixed equipment interface installation lever system, on lever system final stage lever, connect and wear fuselage loading attaching parts, and with seal bellows, carry out the sealing in covering hole, at the loading attaching parts of wearing place's fuselage, connect and load pressurized strut simultaneously, to implement loading.
When airframe commercial transport loading system of the present invention is carried out load test, its detailed process is as follows:
The load that loading pressurized strut applies transfers loads to lever system by wearing fuselage loading attaching parts, by lever system, load is distributed by lever ratio, and the load after distribution is delivered on fuselage seat slide or floor bearer by loading fixed equipment.Simultaneously, in loading procedure, fuselage interior is carried out pressurising, is carried out the sealing of fuselage tapping by seal bellows, stable to guarantee pressurising, improve pressurising loading and pressurized strut loading harmony, guaranteed reliability and the authenticity of loading system.
Claims (9)
1. an airframe commercial transport loading system, it is characterized in that: comprise and load fixed equipment, loading lever system, wherein, load fixed equipment and be fixed on fuselage interior, test loading interface is provided, by this interface assembling, load lever system, on lever system final stage lever, connect the fuselage of wearing being connected with pressurized strut outside fuselage and load attaching parts, and perforation place of closed fuselage covering.
2. airframe commercial transport loading system according to claim 1, is characterized in that: described loading is fixedly installed on fuselage interior floor, and equipment comprises that slide rail loads fixed equipment and ground sheet frame loads fixed equipment.
3. airframe commercial transport loading system according to claim 2, is characterized in that: slide rail loads fixed equipment and comprises loading joint and bolt, and bolt holding, in sliding-rail groove, is spirally connected with loading joint, and loading joint is fixed on slide rail face.
4. airframe commercial transport loading system according to claim 3, it is characterized in that: described loading lever system comprises one-level lever, second lever and three grades of levers, described one-level lever is hinged on and loads on fixed equipment joint, and fuselage loading attaching parts is worn in connection.
5. airframe commercial transport loading system according to claim 2, is characterized in that: ground sheet frame loads fixed equipment and comprises special joint and holding bolt, and special joint is placed on the architrave bar of floor, adopts the holding of holding bolt on ground sheet frame web.
6. airframe commercial transport loading system according to claim 5, it is characterized in that: described loading lever system comprises first order lever, second stage lever and third stage lever, described second stage lever, third stage lever are connected to first order lever bottom by lever attaching parts, and it is hinged that third stage lever loads fixed equipment special joint by loading facilities and ground sheet frame.
7. airframe commercial transport loading system according to claim 1, is characterized in that: fuselage skin perforation place is sealed by seal bellows.
8. airframe commercial transport loading system according to claim 1, is characterized in that: fuselage skin loading facilities and structure button heavily adopt to hang counterbalancing weight or initiatively put button and weigh; Fuselage cargo loading facilities adopts independent counterbalancing weight button weight.
9. an airframe commercial transport loading method, is characterized in that, process is as follows:
First load fixed equipment and install, and loading fixed equipment interface installation lever system, on lever system final stage lever, connect and wear fuselage loading attaching parts, at the loading attaching parts of wearing place's fuselage, connect loading pressurized strut;
During loading, the load that loading pressurized strut applies transfers loads to lever system by wearing fuselage loading attaching parts, by lever system, load is distributed by lever ratio, load after distribution is delivered on fuselage seat slide or floor bearer by loading fixed equipment, simultaneously in loading procedure, fuselage interior is carried out pressurising, is carried out the sealing of fuselage tapping by seal bellows.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310169979.0A CN104139867A (en) | 2013-05-10 | 2013-05-10 | System and method for loading airframe payload |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310169979.0A CN104139867A (en) | 2013-05-10 | 2013-05-10 | System and method for loading airframe payload |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104139867A true CN104139867A (en) | 2014-11-12 |
Family
ID=51849231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310169979.0A Pending CN104139867A (en) | 2013-05-10 | 2013-05-10 | System and method for loading airframe payload |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104139867A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477407A (en) * | 2014-11-27 | 2015-04-01 | 中国飞机强度研究所 | Two-way loading and fixing device for floor beam |
| CN105836155A (en) * | 2016-03-18 | 2016-08-10 | 中国飞机强度研究所 | Double-layer floor beam loading device for aircraft structural strength test |
| CN106006502A (en) * | 2016-06-02 | 2016-10-12 | 江西洪都航空工业集团有限责任公司 | Universal lever convenient to use |
| CN109625319A (en) * | 2018-12-19 | 2019-04-16 | 中国飞机强度研究所 | Water route amphibian water load bringing device |
| CN110823719A (en) * | 2019-11-19 | 2020-02-21 | 中国飞机强度研究所 | Device is applyed to fuselage load |
| CN111409855A (en) * | 2020-04-13 | 2020-07-14 | 中国飞机强度研究所 | Fuselage lateral and heading load combined applying device and load applying method |
| CN112109919A (en) * | 2020-04-30 | 2020-12-22 | 中国飞机强度研究所 | Strength test loading point layout method |
| CN114030641A (en) * | 2021-11-08 | 2022-02-11 | 陕西飞机工业有限责任公司 | Counter weight method and device for airplane flight quality test |
| CN115290430A (en) * | 2022-07-28 | 2022-11-04 | 上海航天精密机械研究所 | Multi-directional load loading test device for curved grid wings |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060101921A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | E-fixture |
| EP2202505A1 (en) * | 2008-12-24 | 2010-06-30 | Alenia Aeronautica S.P.A. | Apparatus for testing fuselage panels |
| CN201575950U (en) * | 2009-12-14 | 2010-09-08 | 中国飞机强度研究所 | Tension and compression pad-lever loading device |
| CN201836369U (en) * | 2010-06-24 | 2011-05-18 | 中国飞机强度研究所 | Sealing bellows |
| CN202147846U (en) * | 2011-07-08 | 2012-02-22 | 中国飞机强度研究所 | Vacuum suction plate test loading system |
| CN103048124A (en) * | 2012-12-10 | 2013-04-17 | 中国飞机强度研究所 | Pulley guide loading device |
-
2013
- 2013-05-10 CN CN201310169979.0A patent/CN104139867A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060101921A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | E-fixture |
| EP2202505A1 (en) * | 2008-12-24 | 2010-06-30 | Alenia Aeronautica S.P.A. | Apparatus for testing fuselage panels |
| CN201575950U (en) * | 2009-12-14 | 2010-09-08 | 中国飞机强度研究所 | Tension and compression pad-lever loading device |
| CN201836369U (en) * | 2010-06-24 | 2011-05-18 | 中国飞机强度研究所 | Sealing bellows |
| CN202147846U (en) * | 2011-07-08 | 2012-02-22 | 中国飞机强度研究所 | Vacuum suction plate test loading system |
| CN103048124A (en) * | 2012-12-10 | 2013-04-17 | 中国飞机强度研究所 | Pulley guide loading device |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477407A (en) * | 2014-11-27 | 2015-04-01 | 中国飞机强度研究所 | Two-way loading and fixing device for floor beam |
| CN105836155A (en) * | 2016-03-18 | 2016-08-10 | 中国飞机强度研究所 | Double-layer floor beam loading device for aircraft structural strength test |
| CN106006502A (en) * | 2016-06-02 | 2016-10-12 | 江西洪都航空工业集团有限责任公司 | Universal lever convenient to use |
| CN106006502B (en) * | 2016-06-02 | 2018-09-14 | 江西洪都航空工业集团有限责任公司 | A kind of portable universal lever |
| CN109625319A (en) * | 2018-12-19 | 2019-04-16 | 中国飞机强度研究所 | Water route amphibian water load bringing device |
| CN110823719B (en) * | 2019-11-19 | 2022-06-07 | 中国飞机强度研究所 | Device is applyed to fuselage load |
| CN110823719A (en) * | 2019-11-19 | 2020-02-21 | 中国飞机强度研究所 | Device is applyed to fuselage load |
| CN111409855A (en) * | 2020-04-13 | 2020-07-14 | 中国飞机强度研究所 | Fuselage lateral and heading load combined applying device and load applying method |
| CN112109919A (en) * | 2020-04-30 | 2020-12-22 | 中国飞机强度研究所 | Strength test loading point layout method |
| CN112109919B (en) * | 2020-04-30 | 2024-04-19 | 中国飞机强度研究所 | Loading point layout method for strength test |
| CN114030641A (en) * | 2021-11-08 | 2022-02-11 | 陕西飞机工业有限责任公司 | Counter weight method and device for airplane flight quality test |
| CN114030641B (en) * | 2021-11-08 | 2024-02-13 | 陕西飞机工业有限责任公司 | Counterweight method and device for aircraft flight quality test |
| CN115290430A (en) * | 2022-07-28 | 2022-11-04 | 上海航天精密机械研究所 | Multi-directional load loading test device for curved grid wings |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104139867A (en) | System and method for loading airframe payload | |
| JP6450108B2 (en) | AIRCRAFT AND METHOD FOR MOUNTING EQUIPMENT INSTALLED OUT OF AIRCRAFT | |
| CN108238282B (en) | Central wing box test equipment | |
| CN104773306A (en) | Main landing gear three-way loading test device | |
| US9272776B2 (en) | Device for intermediate fastening between an aircraft fuselage and an aircraft landing gear | |
| CN106197981B (en) | A kind of engine auxiliary installation section structure slow test loading device and method | |
| CN102991727B (en) | A kind of constrained system of aircraft structure test | |
| CN103723285A (en) | Empennage load applying device used for plane structure strength tests | |
| CN107264836B (en) | Large-scale follow-up loading test device and test method for hatch door | |
| CN202693185U (en) | Equipment for measuring braking torque of aircraft wheel | |
| CN107757947A (en) | A kind of adjustable hydraulic pressure of rigidity does device debugging stand and adjustment method | |
| Forrest et al. | Landing gear structural health monitoring (SHM) | |
| CN106840620A (en) | A kind of device suitable for composite wing slow test loading | |
| US9315254B2 (en) | Joint assembly and method of assembling same | |
| DE102011122059A1 (en) | System and method for repairing a structural component | |
| CN103407579A (en) | Major-diameter airframe test loading clamp | |
| CN104477407A (en) | Two-way loading and fixing device for floor beam | |
| CN114199691A (en) | Airplane fuselage wallboard strength test device | |
| CN213516588U (en) | Loading device for airplane stabilizer control load test | |
| CN202481325U (en) | Reliability test device for aircraft cabin door lock | |
| CN105836155B (en) | A kind of aircraft structure strength tests double floor beam loading device | |
| CN204536020U (en) | A kind of aircraft slow test torpedo hanger loading simulation part | |
| US8024981B2 (en) | Device for test loading | |
| CN109178340A (en) | A kind of wing body docking siding and its test method for fatigue test | |
| CN114486138B (en) | Device and method for testing vibration comfort of aircraft in full-aircraft state |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141112 |