CN108860657A - Aircraft blocks experimental rig and aircraft blocks load transmission analog machine - Google Patents
Aircraft blocks experimental rig and aircraft blocks load transmission analog machine Download PDFInfo
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- CN108860657A CN108860657A CN201810482820.7A CN201810482820A CN108860657A CN 108860657 A CN108860657 A CN 108860657A CN 201810482820 A CN201810482820 A CN 201810482820A CN 108860657 A CN108860657 A CN 108860657A
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- aircraft
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- connecting rod
- experimental rig
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- 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
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
This disclosure relates to aviation field, provide that a kind of aircraft blocks experimental rig and aircraft blocks load transmission analog machine, aircraft blocks experimental rig and includes：Connecting rod is loaded, the load connecting rod is connect with the aircraft, for pushing or blocking the aircraft movement；Pressurized strut, the first end of the pressurized strut are connect with the first loading end, and second end is connect by a tensile members with the first end of the load connecting rod, are moved along a first direction for drawing the load connecting rod；Elastic parts, the first end of the elastic parts are connect with the second end of the load connecting rod, and second end is connect with the second loading end, and second loading end is oppositely arranged with first loading end；For driving the load connecting rod to move after load reaches predetermined load along direction opposite to the first direction, to block the aircraft.The disclosure can apply inertial load to aircraft, avoid the adverse effect of static loading；The also dynamic test blocked of analog, improves the accuracy rate of result of study.
Description
Technical field
This disclosure relates to aviation field, in particular to a kind of aircraft blocks experimental rig and aircraft blocks load transmission
Analog machine.
Background technique
With the development of science and technology of aviation, the technologies such as carrier-borne aircraft and land airplane have huge progress.Due to the environment that lands
Particularity, carrier-borne aircraft and land airplane require to land in relatively short distance, and the landing of carrier landing, land airplane has
The features such as speed is big, engine is worked with maximum power, therefore carrier-borne aircraft and land airplane need under the assistance of arresting gear
It blocks and stops；This can have an immense impact on to airframe structure.Therefore, usually the influence to aircraft lands is blocked in research in engineering.
Slow test is generallyd use in the prior art and studies the influence blocked to aircraft lands, and slow test includes pre- reality
Test stage and formal test stage, pre-experiment stage be by certain procedures step by step slowly plus a little load, to displacement and
Strain measurement point is observed and monitors, finds out the basic trend of structure-bearing and deformation, and examine experimental piece, support system,
The reliability of loading device and measuring device；The formal test stage often first takes the 5~10% of estimated load for initial load, measurement
Then primary stress, strain and displacement step by step, uniformly, are slowly loaded by certain procedures, and gradually measure and record each strain
The data of measurement point, displacement measurement point and load measurement point.Meanwhile examine testpieces, until reach scheduled load or
Scheduled experimental state.But it is a dynamic process that carrier-borne aircraft, which blocks, blocking power is variation in blocking engineering, will be blocked
Power, which is reduced to static loading, on board the aircraft can impact the authenticity of test result.
It is used to study the influence blocked to aircraft lands in consideration of it, this field needs the new analog machine that blocks of one kind.
It should be noted that information is only used for reinforcing the reason to the background of the disclosure disclosed in above-mentioned background technology part
Solution, therefore may include the information not constituted to the prior art known to persons of ordinary skill in the art.
Summary of the invention
The disclosure is designed to provide that a kind of aircraft blocks experimental rig and aircraft blocks load transmission simulation and sets
It is standby, and then the dynamic process of carrier landing is simulated, improve the accuracy rate of test result.
Other characteristics and advantages of the disclosure will be apparent from by the following detailed description, or partially by the disclosure
Practice and acquistion.
According to the disclosure in a first aspect, providing a kind of aircraft blocks experimental rig, which is characterized in that including：
Connecting rod is loaded, the load connecting rod is connect with the aircraft, for pushing or blocking the aircraft movement；
Pressurized strut, the first end of the pressurized strut are connect with the first loading end, second end by a tensile members with it is described
The first end connection for loading connecting rod, moves along a first direction for drawing the load connecting rod；
Elastic parts, the first end of the elastic parts are connect with the second end of the load connecting rod, second end and second
Loading end connection, second loading end are oppositely arranged with first loading end；For the band after load reaches predetermined load
It moves the load connecting rod to move along direction opposite to the first direction, to block the aircraft.
In an exemplary embodiment of the disclosure, the arresting gear further includes arrester hook.
In an exemplary embodiment of the disclosure, the load connecting rod includes load bridge and is located in the load bridge
Load brace and load cross bar, wherein the load brace is used to push the arrester hook so that the aircraft is along described the
The movement of one direction, the load cross bar block the aircraft by the arrester hook.
According to the second aspect of the disclosure, provides a kind of aircraft and blocks load transmission analog machine, which is characterized in that
Including：
Aircraft blocks experimental rig, and it is that above-mentioned aircraft blocks experimental rig that the aircraft, which blocks experimental rig,；
Support device is blocked above experimental rig positioned at the aircraft, is used to support the aircraft；
Damping unit is located above the elastic parts, for applying damping force so that the flight to the aircraft
Device stop motion.
In an exemplary embodiment of the disclosure, the support device includes guide rail and cushion block, the lower surface of the guide rail
It is fixedly connected with the upper surface of the cushion block, and ground is fixed in the lower surface of the cushion block.
In an exemplary embodiment of the disclosure, the guide rail is I-steel.
In an exemplary embodiment of the disclosure, the damping unit is a damper, and the first end of the damper is solid
Due to second loading end.
In an exemplary embodiment of the disclosure, when the load of the pressurized strut is less than the predetermined load, the work
Dynamic cylinder draws the load connecting rod and the elastic parts by the tensile members and moves along the first direction；When described
When the load of pressurized strut is greater than or equal to the predetermined load, the tensile members fracture, the elastic parts drives described add
Connecting rod is carried to move along direction opposite to the first direction.
In an exemplary embodiment of the disclosure, it is provided with foil gauge on the aircraft, for monitoring the aircraft
Ess-strain of the fuselage each section in boost phase.
In an exemplary embodiment of the disclosure, acceleration biography is provided on the aircraft and/or the load connecting rod
Sensor, to monitor the variation of the acceleration of the aircraft.
As shown from the above technical solution, the aircraft in disclosure exemplary embodiment blocks experimental rig and aircraft blocks
Resistance load transmission analog machine at least has following advantages and good effect：
It includes pressurized strut, load connecting rod and elastic parts etc. that aircraft in the disclosure, which blocks experimental rig, and pressurized strut is logical
Overtension component is connect with the first end of load connecting rod, and elastic parts is connect with the second end of load connecting rod, while loading connecting rod
It is connect with aircraft, when the load of pressurized strut is less than predetermined load, pressurized strut draws load connecting rod and bullet by tensile members
Property component is moved along the first direction；When the load of pressurized strut is greater than or equal to predetermined load, tensile members fracture, bullet
Property component drive load connecting rod along being moved in the opposite direction with first party, force aircraft stop motion.One side of the disclosure
Face forms a complete braking system by pressurized strut, load connecting rod, tensile members, elastic parts and aircraft, can
Dynamic analog blocks power and is blocking the variation in engineering, and it is accurate when the influence to aircraft lands is blocked in research to improve
Rate；On the other hand test can be blocked to aircraft and applies inertial load, avoid the adverse effect of static loading.
The disclosure it should be understood that more than general description and following detailed description be only exemplary and explanatory
, it does not limit the disclosure.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows the implementation for meeting the disclosure
Example, and together with specification for explaining the principles of this disclosure.It should be evident that the accompanying drawings in the following description is only the disclosure
Some embodiments for those of ordinary skill in the art without creative efforts, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 shows the structural schematic diagram that static(al) in the prior art blocks experimental rig；
Fig. 2 shows the structural schematic diagrams that aircraft in disclosure exemplary embodiment blocks experimental rig；
Fig. 3 shows the structural schematic diagram that aircraft in disclosure exemplary embodiment blocks experimental rig；
Fig. 4 shows the structural schematic diagram that connecting rod is loaded in disclosure exemplary embodiment；
Fig. 5 shows the structural schematic diagram that aircraft in disclosure exemplary embodiment blocks load transmission analog machine；
Fig. 6 shows the structural schematic diagram of support device in disclosure exemplary embodiment；
Fig. 7 shows acceleration-time graph of carrier-borne aircraft in disclosure exemplary embodiment；
Fig. 8 shows the schematic diagram that aircraft in disclosure exemplary embodiment blocks load transmission analog machine；
Fig. 9 A shows aircraft acceleration in disclosure exemplary embodiment-displacement changing curve figure；
Fig. 9 B shows aircraft acceleration in disclosure exemplary embodiment-time changing curve figure.
Specific embodiment
Example embodiment is described more fully with reference to the drawings.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to example set forth herein；On the contrary, thesing embodiments are provided so that the disclosure will more
Fully and completely, and by the design of example embodiment comprehensively it is communicated to those skilled in the art.Described feature, knot
Structure or characteristic can be incorporated in any suitable manner in one or more embodiments.In the following description, it provides perhaps
More details fully understand embodiment of the present disclosure to provide.It will be appreciated, however, by one skilled in the art that can
It is omitted with technical solution of the disclosure one or more in the specific detail, or others side can be used
Method, constituent element, device, step etc..In other cases, be not shown in detail or describe known solution to avoid a presumptuous guest usurps the role of the host and
So that all aspects of this disclosure thicken.
In this specification using term "one", " one ", "the" and " described " to indicate there are one or more elements/
Component part/etc.；Term " comprising " and " having " is to indicate the open meaning being included and refer in addition to listing
Element/component part/also may be present except waiting other element/component part/etc.；Term " first " and " second " etc. are only made
It is used for label, is not the quantity limitation to its object.
In addition, attached drawing is only the schematic illustrations of the disclosure, it is not necessarily drawn to scale.Identical attached drawing mark in figure
Note indicates same or similar part, thus will omit repetition thereof.Some block diagrams shown in the drawings are function
Energy entity, not necessarily must be corresponding with physically or logically independent entity.
This field in the related technology, generally use slow test research and block influence to aircraft lands, Fig. 1 shows
The structural schematic diagram that static(al) blocks experimental rig is gone out, as shown in Figure 1, one end of aircraft 101 (or testpieces) is fixed on and holds
On section A, the other end is connect by arrester hook 102 with tensile members 103；One end of pressurized strut 104 is fixed on loading end B,
The other end is fixed on reaction frame 105；Tensile members 103 are also secured on reaction frame 105 simultaneously.When simulation test, pressurized strut
104 tensioning reaction frames 105, when load reaches certain value, tensile members 103 are broken, and power is applied to realization on arrester hook 102 and blocks
Hinder effect.
Slow test is will to block power to be reduced on static loading to aircraft, and the shadow to aircraft lands is blocked in research
It rings.But it is a dynamic process that aircraft, which blocks, blocking power is variation in blocking engineering, will block power and is reduced to static(al)
Load can impact the authenticity of test result.
In view of problem present in the relevant technologies, the disclosure provides firstly a kind of aircraft and blocks experimental rig, and Fig. 2 shows
The structural schematic diagram that aircraft blocks experimental rig is gone out, as shown in Fig. 2, it includes that load connects that aircraft, which blocks experimental rig 200,
Bar 201, pressurized strut 202, elastic parts 203 and tensile members 204, wherein load connecting rod 201 is connect with aircraft, for pushing away
Move or block aircraft movement；The first end of pressurized strut 202 is connect with the first loading end, second end by tensile members 204 with
The first end connection for loading connecting rod 201 moves along a first direction for drawing load connecting rod 201；The first of elastic parts 203
It holds and is connect with the second end of load connecting rod 201, second end is connect with the second loading end, and the second loading end is opposite with the first loading end
Setting；For driving load connecting rod 201 to move in the opposite direction after load reaches predetermined load along with first party, to block
Hinder aircraft.
Aircraft in the disclosure blocks experimental rig by pressurized strut, load connecting rod, tensile members, elastic parts and flies
Row device forms a complete braking system, and when the load of pressurized strut is less than predetermined load, pressurized strut passes through tensile members
Traction load connecting rod and elastic parts move along a first direction；When the load of pressurized strut is greater than or equal to predetermined load,
The fracture of power component, elastic parts drive load connecting rod to move in the opposite direction along with first party, aircraft are forced to stop fortune
It is dynamic.Aircraft in the disclosure block experimental rig can dynamic analog block power and blocking the variation in engineering, improve simulation
The accuracy rate with the influence of aircraft lands is blocked in research in test；In addition test can be blocked to aircraft applies inertia load
Lotus avoids the adverse effect of static loading.
In an exemplary embodiment of the disclosure, Fig. 3 shows the structural schematic diagram that a kind of aircraft blocks experimental rig,
As shown in figure 3, it further includes arrester hook 205 that the aircraft in the disclosure, which blocks experimental rig, arrester hook 205 be can be set in flight
The tail portion of device, for capturing and hooking the check cable of the arresting gear on ground, guarantees aircraft short after aircraft lands
Apart from interior braking.
In an exemplary embodiment of the disclosure, Fig. 4 shows the structural schematic diagram of load connecting rod, as shown in figure 4, load
Connecting rod 201 includes load bridge 401, load brace 402 and load cross bar 403, wherein load brace 402 and load cross bar 403
In load bridge 401.When 202 tensioning of pressurized strut loads connecting rod 201 and elastic parts 203, the load promotion of brace 402 is blocked
Resistance hook 205 pushes aircraft (or testpieces) to move synchronously with pressurized strut 202；When the load in pressurized strut 202 reaches certain value
When, tensile members 204 are broken, and the elastic parts 203 of tensioning is released, and elastic parts 203 drives load connecting rod 201 reversely to transport
Dynamic, load cross bar 403 hangs up arrester hook 205 and blocks aircraft at this time, and realization blocks power and blocks effect.
In an exemplary embodiment of the disclosure, load connecting rod 201 can be fixedly connected with elastic parts 203；Load is oblique
Bar 402 can be fixedly connected with load bridge 401, and keep certain angle in vertical direction；The mode being fixedly connected can be
The modes such as weld, be bolted, naturally it is also possible to use other attachments commonly used in the art, the disclosure is not done this specifically
It limits.
In an exemplary embodiment of the disclosure, aircraft can be carrier-borne aircraft or land airplane, be also possible to other
The aircraft for needing short distance to brake；Elastic parts 203 can be the spring with stiffness coefficient, and the stiffness coefficient of spring is by flying
The peak acceleration and fuselage of row device, which are self-possessed, to be determined；Tensile members 204 can use tension pin simultaneously, by 201 He of pressurized strut
Connecting rod 202 is loaded to connect.
The disclosure also provides a kind of aircraft and blocks load transmission analog machine, and Fig. 5 shows aircraft and blocks load biography
The structural schematic diagram of analog machine is passed, is blocked as shown in figure 5, aircraft blocks load transmission analog machine 500 including aircraft
Experimental rig 501, support device 502 and damping unit 503, it is what the disclosure was recorded that wherein aircraft, which blocks experimental rig 501,
Aircraft blocks experimental rig 200；Support device 502 is located at aircraft and blocks 501 top of experimental rig, is used to support flight
Device；Damping unit 503 is located above the elastic parts 203 that aircraft blocks in experimental rig 501, hinders for applying to aircraft
Buddhist nun's power is so that aircraft stop motion.
In an exemplary embodiment of the disclosure, Fig. 6 shows the structural schematic diagram of support device, as shown in fig. 6, support
Device 502 includes guide rail 601 and cushion block 602, and in order to guarantee stability, the lower surface of cushion block 602 can pass through welding or bolt
The modes such as connection fix on the ground；The upper surface of cushion block 602 is also fixedly connected with the lower surface of guide rail 601 simultaneously, fixed to connect
The mode connect specifically can be welded connecting, be also possible to other connection types commonly used in the art, and the disclosure does not do this
It is specific to limit.In order to carry aircraft (or testpieces) and guarantee its can free movement, guide rail preferably uses I-steel so that
Aircraft (or testpieces) is free to slide on guide rail.
In an exemplary embodiment of the disclosure, for blocking carrier-borne aircraft, carrier-borne aircraft blocks load and is hung up by arrester hook
Check cable starts to gradually increase, and blocks load in 0.6s or so and reaches maximum, then gradually decreases.Fig. 7 shows carrier-borne aircraft
Acceleration-time graph, as shown in fig. 7, the acceleration of carrier-borne aircraft is gradually increased as 0≤t≤0.6s；As t=0.6s,
The acceleration of carrier-borne aircraft is maximum；As 0.6 < t≤3.5s, the acceleration of carrier-borne aircraft is gradually reduced.From the foregoing, it will be observed that in carrier-borne aircraft
When blocking load maximum, the acceleration of carrier-borne aircraft also reaches maximum value.
In an exemplary embodiment of the disclosure, Fig. 8, which shows aircraft and blocks the structure of load transmission analog machine, shows
It is intended to, as shown in figure 8, aircraft is located on 601 (not shown) of guide rail of support device 502, aircraft blocks experimental rig 501
Positioned at the lower section of aircraft and support device 502, damping unit 503 is located at aircraft and blocks elastic group in experimental rig 501
203 top of part.When pressurized strut 202 is moved along first direction, connecting rod 201 and elastic device 203 are loaded simultaneously by tensioning, also edge
First direction movement, at this time load connecting rod 201 in load brace 402 push arrester hook 205 make aircraft along first party
To movement；When the load in pressurized strut 202 reaches predetermined load, the breaking load phase of the predetermined load and tensile members 204
Deng, tensile members 204 disconnect at this time, and the elastic parts 203 of tensioning is released, elastic parts 203 drive load connecting rod 201 along
Second direction movement, the second direction are opposite with first direction；Loading cross bar 403 hangs up arrester hook 205 simultaneously, with predetermined load
It pulls aircraft to accelerate, realizes the test simulation that dynamic is blocked.
Further, after 203 tensioning of elastic parts, aircraft has biggish speed, can at this time pass through
Damping unit 503 applies damping force to aircraft, and the speed of aircraft is decreased to zero, guarantees the safety of aircraft.In this public affairs
In opening, damping unit 503 can be damper, be located at 203 top of elastic parts, and one end is fixed on the second loading end, separately
It is directed toward aircraft in one end.
In an exemplary embodiment of the disclosure, when simulation test, the peak acceleration that can choose aircraft is 5g (g
For acceleration of gravity, g=9.8m/s2), the self weight of fuselage is 3000kg, and correspondingly elastic parts 203 is for stiffness coefficient
The spring of 150kN/m, therefore the maximum load of aircraft is 150kN.Before the load of pressurized strut 202 reaches 150kN, spring
203, connecting rod 201 and aircraft is loaded to move all along first direction；When the load of pressurized strut 202 reaches 150kN, tension group
Part 204 is broken, and spring 203 drives load connecting rod 201 to move along the second direction opposite with first direction, and load cross bar 403 is hung
Upper arrester hook 205 pulls aircraft to accelerate with the load of initial 150kN, realizes the test simulation that dynamic is blocked.In spring
203 when being stretched to the initial load with 150kN, according to Hooke's law it is found that the displacement of spring 203 is：
After tensile members 204 are broken, the acceleration of aircraft can change with displacement, the variation of time, and Fig. 9 A shows
Aircraft acceleration-displacement change curve is gone out, Fig. 9 B shows aircraft acceleration-time change curve, such as
Shown in Fig. 9 A, after tensile members 204 are broken, acceleration linearly reduces with the increase of displacement；As shown in Figure 9 B, work as tension
After component 204 is broken, acceleration is gradually reduced with the increase of time, until being 0.
In an exemplary embodiment of the disclosure, one or more strains can be pasted on aircraft (or testpieces)
Piece, according to actual needs can by strain gauge adhesion aircraft (or testpieces) different parts, with monitor aircraft (or examination
Test part) ess-strain at each position in boost phase；It can also be pasted on aircraft (or testpieces) and/or load connecting rod
The quantity of acceleration transducer, acceleration transducer can be set according to actual needs, monitored and flown by acceleration transducer
The variation of the acceleration of device.
Aircraft in the disclosure, which blocks load transmission analog machine, to apply inertia to aircraft in simulation test
Load avoids the adverse effect of static loading；In addition the aircraft of the disclosure blocks load transmission analog machine and can simulate
The dynamic test blocked improves the accuracy rate for blocking the result of study of the influence to aircraft lands.
Those skilled in the art after considering the specification and implementing the invention disclosed here, will readily occur to its of the disclosure
Its embodiment.This application is intended to cover any variations, uses, or adaptations of the disclosure, these modifications, purposes or
Person's adaptive change follows the general principles of this disclosure and including the undocumented common knowledge in the art of the disclosure
Or conventional techniques.The description and examples are only to be considered as illustrative, and the true scope and spirit of the disclosure are by appended
Claim is pointed out.
It should be understood that the present disclosure is not limited to the precise structures that have been described above and shown in the drawings, and
And various modifications and changes may be made without departing from the scope thereof.The scope of the present disclosure is only limited by the attached claims.
Claims (10)
1. a kind of aircraft blocks experimental rig, which is characterized in that including：
Connecting rod is loaded, the load connecting rod is connect with the aircraft, for pushing or blocking the aircraft movement；
Pressurized strut, the first end of the pressurized strut are connect with the first loading end, and second end passes through a tensile members and the load
The first end of connecting rod connects, and moves along a first direction for drawing the load connecting rod；
Elastic parts, the first end of the elastic parts are connect with the second end of the load connecting rod, second end and the second carrying
Face connection, second loading end are oppositely arranged with first loading end；For driving institute after load reaches predetermined load
It states load connecting rod to move along direction opposite to the first direction, to block the aircraft.
2. aircraft according to claim 1 blocks experimental rig, which is characterized in that the arresting gear further includes blocking
Hook.
3. aircraft according to claim 2 blocks experimental rig, which is characterized in that the load connecting rod includes load bar
Frame and load brace and load cross bar in the load bridge, wherein the load brace is for pushing the arrester hook
So that the aircraft is moved along the first direction, the load cross bar blocks the aircraft by the arrester hook.
4. a kind of aircraft blocks load transmission analog machine, which is characterized in that including：
Aircraft blocks experimental rig, and it is the described in any item aircraft of claim 1-3 that the aircraft, which blocks experimental rig,
Block experimental rig；
Support device is blocked above experimental rig positioned at the aircraft, is used to support the aircraft；
Damping unit is located above the elastic parts, for applying damping force so that the aircraft stops to the aircraft
Only move.
5. aircraft according to claim 4 blocks load transmission analog machine, which is characterized in that the support device packet
Guide rail and cushion block are included, the lower surface of the guide rail is fixedly connected with the upper surface of the cushion block, and the lower surface of the cushion block is solid
Due to ground.
6. aircraft according to claim 5 blocks load transmission analog machine, which is characterized in that the guide rail is I-shaped
Steel.
7. aircraft according to claim 4 blocks load transmission analog machine, which is characterized in that the damping unit is
One damper, the first end of the damper are fixed on second loading end.
8. aircraft according to claim 4 blocks load transmission analog machine, which is characterized in that
When the load of the pressurized strut is less than the predetermined load, the pressurized strut adds by the way that tensile members traction is described
It carries connecting rod and the elastic parts is moved along the first direction；
When the load of the pressurized strut is greater than or equal to the predetermined load, the tensile members fracture, the elastic parts
The load connecting rod is driven to move along direction opposite to the first direction.
9. aircraft according to claim 4 blocks load transmission analog machine, which is characterized in that set on the aircraft
It is equipped with foil gauge, for monitoring described aircraft fuselage each section in the ess-strain of boost phase.
10. aircraft according to claim 4 blocks load transmission analog machine, which is characterized in that the aircraft and/
Or it is provided with acceleration transducer on the load connecting rod, to monitor the variation of the acceleration of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810482820.7A CN108860657B (en) | 2018-05-18 | 2018-05-18 | Aircraft arresting test device and aircraft arresting load transfer simulation equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810482820.7A CN108860657B (en) | 2018-05-18 | 2018-05-18 | Aircraft arresting test device and aircraft arresting load transfer simulation equipment |
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| CN108860657A true CN108860657A (en) | 2018-11-23 |
| CN108860657B CN108860657B (en) | 2021-10-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810482820.7A Active CN108860657B (en) | 2018-05-18 | 2018-05-18 | Aircraft arresting test device and aircraft arresting load transfer simulation equipment |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020206829A1 (en) * | 2019-04-08 | 2020-10-15 | 中国矿业大学 | Fretting fatigue test apparatus and method for steel wire under radial impact condition |
| CN114148545A (en) * | 2021-12-07 | 2022-03-08 | 温州理工学院 | Detection device for industrial design aircraft and use method thereof |
| CN117087872A (en) * | 2023-10-19 | 2023-11-21 | 中国飞机强度研究所 | Buffer method and buffer system for dynamic response test of impact of blocking hook of carrier-based aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060278758A1 (en) * | 2005-03-18 | 2006-12-14 | Aai Corporation | Secondary arresting line release mechanism |
| CN102530210A (en) * | 2011-12-09 | 2012-07-04 | 朱惠芬 | Aircraft carrier landing interceptor |
| CN203386409U (en) * | 2013-08-16 | 2014-01-08 | 温州中信科教设备有限公司 | Demonstration device for aircraft carrier arresting cable |
| CN103879563A (en) * | 2012-12-23 | 2014-06-25 | 吴汉民 | Speed-reducing and stopping device for aircraft landing |
| CN104002988A (en) * | 2014-04-17 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for implementing aircraft arresting static test |
| US20170021943A1 (en) * | 2013-03-14 | 2017-01-26 | Aurora Flight Sciences Corporation | Capturing Hook for Aerial System |
-
2018
- 2018-05-18 CN CN201810482820.7A patent/CN108860657B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060278758A1 (en) * | 2005-03-18 | 2006-12-14 | Aai Corporation | Secondary arresting line release mechanism |
| CN102530210A (en) * | 2011-12-09 | 2012-07-04 | 朱惠芬 | Aircraft carrier landing interceptor |
| CN103879563A (en) * | 2012-12-23 | 2014-06-25 | 吴汉民 | Speed-reducing and stopping device for aircraft landing |
| US20170021943A1 (en) * | 2013-03-14 | 2017-01-26 | Aurora Flight Sciences Corporation | Capturing Hook for Aerial System |
| CN203386409U (en) * | 2013-08-16 | 2014-01-08 | 温州中信科教设备有限公司 | Demonstration device for aircraft carrier arresting cable |
| CN104002988A (en) * | 2014-04-17 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for implementing aircraft arresting static test |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020206829A1 (en) * | 2019-04-08 | 2020-10-15 | 中国矿业大学 | Fretting fatigue test apparatus and method for steel wire under radial impact condition |
| CN114148545A (en) * | 2021-12-07 | 2022-03-08 | 温州理工学院 | Detection device for industrial design aircraft and use method thereof |
| CN114148545B (en) * | 2021-12-07 | 2023-10-31 | 温州理工学院 | Detection device for industrial design aircraft and application method thereof |
| CN117087872A (en) * | 2023-10-19 | 2023-11-21 | 中国飞机强度研究所 | Buffer method and buffer system for dynamic response test of impact of blocking hook of carrier-based aircraft |
| CN117087872B (en) * | 2023-10-19 | 2024-01-05 | 中国飞机强度研究所 | Buffer method and buffer system for dynamic response test of impact of blocking hook of carrier-based aircraft |
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|---|---|
| CN108860657B (en) | 2021-10-29 |
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