CN107651216A - Engine loading device and method applied to single-shot fixed wing aircraft slow test - Google Patents
Engine loading device and method applied to single-shot fixed wing aircraft slow test Download PDFInfo
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- CN107651216A CN107651216A CN201710993386.4A CN201710993386A CN107651216A CN 107651216 A CN107651216 A CN 107651216A CN 201710993386 A CN201710993386 A CN 201710993386A CN 107651216 A CN107651216 A CN 107651216A
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a kind of engine loading device and method applied to single-shot fixed wing aircraft slow test, including loading support, simulation of engine part, simulation load includes propeller pulling force F, the total force G of engine and propeller and propeller moment of torsion M, loading support includes pedestal, left socle, right support, after-poppet, and the upper end of after-poppet is provided with bearing one；Simulation of engine part includes quarter bend, quarter bend both ends are threaded with screw rod respectively, the lower end of upper screw rod is sequentially connected the first force snesor, lower screw rod, lower screw clearance is matched with left socle, right support, screw thread is combined with loading nut on lower screw rod, wherein, the loading nut of quarter bend left end is located above left socle, the loading nut of quarter bend right-hand member is located at below right support, engine link, balancing weight, bearing two are set on quarter bend, pull bar has been respectively articulated with bearing one, bearing two, length adjustment mechanism, the second force snesor are connected between two pull bars.
Description
Technical field
The present invention relates to aircraft slow test technical field, more particularly to applied to single-shot fixed wing aircraft slow test
Engine loading device and method.
Background technology
The problem of prior art is present be：Any aircraft must carry out full machine slow test before first-fly, to verify aircraft
Structural strength.Full machine slow test must simulate various load working conditions of the aircraft in flight course, wherein propeller and hair
Load caused by motivation is the important component of test load.The problem of presently, there are is 1) carried out using actual engine
The full machine slow test of aircraft, experimentation cost are high, and risk is big, 2) existing experimental rig loading Position is relatively fixed, and regulation is constant,
With certain limitation；3) existing experimental rig designs research and development, specific aim both for the engine of a certain certain fixing model
By force, the scope of application is small；4) due to technology blockage, do not inquire in existing file and patent and sent out for light-duty single-shot fixed wing aircraft
Motivation slow test is with the related data and document of engine loading device (before being arranged on fuselage present invention is generally directed to engine
The aircraft in portion, the patent for the engine loading device being arranged on for engine on wing can inquire two：A kind of aircraft is quiet
Power test engine loading simulation part --- utility model 201220087091.3, aircraft wing slow test are substituted with engine
Equipment --- patent of invention 201310607947.4, the two patents relate only to simulation of engine part, are not directed to load add
Carry and put).To sum up, there is following defect in prior art：
1) it is big using the full machine slow test cost height of actual engine, risk, loaded load size and loading position tool
There is limitation；
2) existing experimental rig is developed for a certain concrete model engine, is only applicable to simulate this certain fixing model
Engine loading, need to redesign experimental rig when more reengining, therefore the scope of application of experimental rig is narrower；
3) data that open source literature can be found has related only to engine replacing part, adds without being related to specific load
Carry put, the regulation of load mode and loading force, therefore existing experimental rig is not perfect enough.
The content of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide applied to single-shot fixed wing aircraft slow test
Engine loading device and method, engine and propeller load are applied by engine loading device, it is quiet for the full machine of aircraft
Power is tested, and experimentation cost is cheap, applied widely.
The object of the present invention is achieved like this：
A kind of engine loading device applied to single-shot fixed wing aircraft slow test, including loading support, engine
Simulating piece, slow test need simulation load to include propeller pulling force F, the total force G of engine and propeller and propeller
Moment of torsion M, the moment of torsion M form couple to simulate using upward pulling force F1 and downward pulling force F2,
The loading support includes pedestal, the left socle on the left of pedestal front end, the right branch on the right side of pedestal front end
Frame, and the after-poppet located at pedestal rear end, the upper end of the after-poppet be provided with can adjustment position up and down T-shaped bearing, T-shaped branch
Seat upper end be provided with can left and right adjustment position bearing one；
The simulation of engine part includes the quarter bend transversely set, and the quarter bend both ends are threaded with vertically respectively
The upper screw rod set, the lower end of the upper screw rod are sequentially connected the first force snesor, lower screw rod, and first force snesor is used for
Screw rod, the size of lower screw rod loading force in detection, the lower screw clearance is matched with left socle, the anti-rotation that right support is provided with
Hole, screw thread is combined with loading nut on the lower screw rod, wherein, the loading nut of quarter bend left end is located above left socle, quarter bend
The loading nut of right-hand member is located at below right support, and the both ends of the quarter bend upper surface connect respectively can be before the adjustment position of left and right
Engine link, the front end of the front engine link are extended forwardly into outside quarter bend, the middle part of the rear end face of the quarter bend
Connection can left and right adjustment position rear engine link, between rear engine link and quarter bend be provided with apart from adjusting pad
Block, front engine link, rear engine link are used to simulation of engine part being connected to engine link；
The lower surface connection of the quarter bend can left and right adjustment position the counterweight screw rod extended downwardly, spiral shell on counterweight screw rod
Line connects balancing weight, and rotating weight block can adjust position of the balancing weight along counterweight screw rod axial direction, in the upper surface of the quarter bend
Portion's connection can left and right adjustment position bearing two, be respectively articulated with pull bar on the bearing one, bearing two, two pull bars it is opposite
End is threadedly coupled double threaded screw respectively, wherein, pull bar on bearing two can upper and lower adjustment position, be connected between two pull bar
Length adjustment mechanism, the second force snesor, second force snesor are used for the size of loading force between two pull bars of detection；
The propeller pulling force F is simulated by length adjustment mechanism, two pull bars, the total force of the engine and propeller
G is simulated by balancing weight, and the upward pulling force F1 is simulated by screw rod, lower screw rod, loading nut on the quarter bend left end, institute
Downward pulling force F2 is stated to simulate by screw rod, lower screw rod, loading nut on the quarter bend right-hand member.
Preferably, the length adjustment mechanism include double threaded screw, slip-knot nut, the slip-knot nut include nut body with
And the slip-knot body located at the longitudinal section of nut body front end in " work " font, the rear end of the nut body and the front end spiral shell of double threaded screw
Line is connected, and the rear end of the double threaded screw is connected with the pull rod screw on bearing one, and the front end of the nut body sets end plate, institute
State and slide opening is set on end plate, mid diameter contraction section and the slide opening gap of the slip-knot body coordinate, and form slip-knot structure, the work
The rear end of knot body is limited in the end plate of nut body front end, and the front end of the slip-knot body passes through with the rear end flanges of the second force snesor
Screw is fixedly connected, and the front end of second force snesor is connected with the pull rod screw on bearing two.
Preferably, the bearing two is U-shaped, and bar hole, the bearing two are vertically provided with respectively on two walls of bearing two
On pull bar by hinge in two bar holes, make the pull bar can upper and lower adjustment position.
Preferably, the T-shaped bearing by provided with vertical borehole jack on after-poppet, the T-shaped vertical hole hole wall of bearing
It is upper to be provided with bar hole relatively, and pass through bar hole, after-poppet to form the positioning to T-shaped bearing by bolt, and downward can be gone up
Whole position.
Preferably, the pedestal, left socle, right support, after-poppet are welded by shaped steel, the bottom peace of the pedestal
The castor that can be moved and lock equipped with four.
Preferably, the nut for being connected with upper screw flight is fixed with the quarter bend, and is set coaxial with nut bore
Be used for upper screw rod step down through hole；Anti-rotation bearing is fixed in the left socle, right support upper end respectively, in the anti-rotation bearing
The through hole coaxial with anti-rotating hole is set.
Preferably, the quarter bend lower surface connection can left and right adjustment position balancing weight mounting bracket, the counterweight
Screw rod is fixed in balancing weight mounting bracket.
Preferably, position has been respectively fixedly connected in the upper surface of the quarter bend, lower surface, rear end face and T-shaped bearing upper surface
Adjust cushion block, be transversely provided with T-slot on the position adjustment cushion block, for installing T-bolt, the bearing one, bearing two,
Front engine link, rear engine link and balancing weight mounting bracket are installed to pair by T-bolt and nut respectively
The T-shaped cushion block answered, and can transversely adjustment position.
Preferably, the bearing one, the upper end of bearing two are respectively provided with the journal stirrup being hinged with pull bar, wherein, it is described
The journal stirrup of bearing two is provided with the bar hole being used for pull bar hinge, the pull bar of bearing two is vertically adjusted position
Put.
A kind of engine loading method applied to single-shot fixed wing aircraft slow test, one kind is taken to be fixed applied to single-shot
The engine loading device of wing aircraft slow test, method comprise the following steps：
1) simulation of engine part and experimental prototype are subjected to Virtual assemble in three-dimensional software, selected under virtual assembly environment
The balancing weight of approrpiate wts is selected, and adjusts its position along counterweight screw rod axial direction, the position of adjustment counterweight screw rod transversely, selection
The distance adjustment cushion block of suitable thickness, make weight and position of centre of gravity and actual engine weight and the center of gravity position of simulation of engine part
Put unanimously, determine center of gravity weight adjusting parameter：The weight and lengthwise position of balancing weight, the lateral attitude of counterweight screw rod, distance are adjusted
The thickness of whole cushion block；According to the relative position of engine and propeller, line of pull application point and action direction adjusting parameter are determined：
The vertical position of the lateral attitude of bearing one and bearing two, T-shaped bearing and the upper connecting rod of bearing two；
2) each adjusting parameter drawn according to previous step, the relative position of adjustment simulation of engine part each parts in kind
Put, weight and position of centre of gravity, the propeller line of pull active position and effect side of simulation of engine part are just caused after being adjusted in place
It is consistent to the weight center of gravity position with actual engine, propeller line of pull active position and action direction, and then simulate hair
The gravity G of motivation and propeller；
3) simulation of engine part is installed to starting for experimental prototype by front engine link, rear engine link
On machine link；Adjustment length governor motion and respectively load nut so that the reading of each force snesor is zero；
4) adjustment length governor motion and nut is respectively loaded, simulates the moment of torsion M of propeller pulling force F and propeller.
By adopting the above-described technical solution, the present invention has the advantages that：
1) on the premise of test requirements document is met, experimentation cost and empirical risk are reduced；
2) the simulation of engine part weight center of gravity position in experimental rig of the present invention, pulling force line position and direction are equal
It is adjustable, therefore the present invention can be used for the engine load of simulating different model, the experimental rig that designs of the present invention reduce into
It is this while, also adaptable stronger, the characteristics of scope of application is wider, and use is more flexible；
3) data that open source literature can be found has related only to simulation of engine part, without being related to specific loading dress
Put, the regulation of load mode and loading force, simulation of engine part and loading device are integrated together by the present invention, using screw mandrel spiral shell
Maternal formula loads and integrates force sensor, and load mode is simple and convenient, the adjustment of loading force size is flexible, while line of pull
The position of load(ing) point, direction and size are adjustable so that experimental rig function of the invention is more, and application is stronger.
4) in addition to gravitational load, remaining load is loaded using feed screw nut, is matched somebody with somebody force sensor in structure, can be looked into real time
Loading force size is seen and adjusts, test effect is more preferable, and be particularly suitable for use in light aerocraft.
Brief description of the drawings
Fig. 1 is the structural representation of engine loading device；
Fig. 2 is the structural representation of loading support；
Fig. 3 is the structural representation of one line of vision of simulation of engine part；
Fig. 4 is the structural representation of another line of vision of simulation of engine part；
Fig. 5 is slow test load schematic；
Fig. 6 is the structural representation of slip-knot nut；
Fig. 7 is the connection diagram of slip-knot nut.
Reference
In accompanying drawing, support is loaded：101- bearings one, 102- position adjustment cushion blocks, 103-T type bearings, 104- after-poppets,
105- castors, 106- pull bars, 107- double threaded screws, 108- anti-rotation bearings, 111- bolts, 112- nuts, 113-T type bolts,
114- nuts, 115- bearing pins；
Simulation of engine part：The force snesors of 201- second, 202- pull bars, 203- bearings two, 204- position adjustment cushion blocks,
The upper screw rods of 205-, 206- nuts, 207- quarter bends, 208- front engine links, 209- cushion blocks one, the force snesors of 210- first,
Screw rod under 211-, 212- balancing weights, 213- balancing weight mounting brackets, 214- position adjustment cushion blocks, 215- position adjustment cushion blocks,
216- rear engine links, 217- slip-knot nuts, nut body 217-01, slip-knot body are 217-02, and 218- is apart from adjusting pad
Block, 219- front engine links, screw rod under 220-, 221- anti-rotation bearings, the upper screw rods of 222-, the force snesors of 223- first,
231- bearing pins, 232-T type bolts, 233- nuts, 234-T type bolts, 235- nuts, 236-T type bolts, 237- nuts, 238-
Nut, 239-T type bolts, 240- loading nuts, 241- loading nuts.
Embodiment
Embodiment
A kind of engine loading device applied to single-shot fixed wing aircraft slow test, including loading support, engine
Simulating piece, engine and propeller load as shown in figure 5, mainly include propeller pulling force F, engine and propeller gravity G with
And the moment of torsion M (being simulated in the present invention using a pair of couples, F1 and F2 in Fig. 5) of propeller.In addition to gravitational load, its over-carriage
Lotus is loaded using feed screw nut, matches somebody with somebody force sensor in structure, can be with real time inspection and adjustment loading force size.
The loading support includes pedestal, the left socle on the left of pedestal front end, the right branch on the right side of pedestal front end
Frame, and the after-poppet located at pedestal rear end, the upper end of the after-poppet be provided with can adjustment position up and down T-shaped bearing, T-shaped branch
Seat upper end be provided with can left and right adjustment position bearing one.Pedestal, left socle, right support, after-poppet are welded by shaped steel,
Base bottom is provided with four castors 105, and the castor 105 can make the movement of support become quick aspect by use demand,
Support is fixed firmly to ground by and can.Through hole is provided with left socle, right support, for the He of screw rod 211 under simulation of engine part
Lower screw rod 220 is by while being welded with anti-rotation bearing 108 and anti-rotation bearing 221, for preventing lower spiral shell on left socle, right support
Bar 220 and lower screw rod 211 are rotated in loading and (loaded using feed screw nut), and the upper rear end of after-poppet 104 is provided with T-shaped bearing
103, be provided with U-type groove on T-shaped bearing 103, T-shaped bearing 103 can slide up and down on after-poppet 104, and by bolt 111 and
Nut 112 is fixed.The T-shaped top of bearing 103 is fixed with position adjustment cushion block 102, and T-slot is provided with T-shaped cushion block 102, for installing T
Type bolt 113.Bearing 1 is installed on T-shaped cushion block 102 by T-bolt 113 and nut 114.Pull bar 106 passes through bearing pin
115 are arranged on bearing 1, and double threaded screw 107 is connected on pull bar 106 by end thread.
Simulation of engine part mainly by force snesor, pull bar, bearing, quarter bend, T-shaped cushion block, engine link, screw rod,
Balancing weight, slip-knot nut, T-bolt and cushion block etc. form, structure on two sides almost symmetry.The both ends of quarter bend 207 are drilled with through hole, are used for
Install screw rod 205 and upper screw rod 222.Upper screw rod 205 and upper screw rod 222 are connected by nut 206 and quarter bend 207.Upper screw rod
First force snesor 210 is installed between 205 and lower screw rod 211, the first power biography is installed between screw rod 222 and lower screw rod 220
Sensor 223, the size of screw rod loading force can be shown.207 upper and lower end face of quarter bend and rear end face are respectively welded position adjustment pad
Block 204, position adjustment cushion block 214 and position adjustment cushion block 215.Position adjustment cushion block 204, position adjustment cushion block 214 and position
T-slot is provided with adjustment cushion block 215, for installing T-bolt.The simulation of engine part passes through front engine link 208, preceding
Engine link 219, rear engine link 216 and cushion block 1 are connected on fuselage on engine link, preceding to start
Machine link 208 and front engine link 219 are connected on position adjustment cushion block 204 by T-bolt 232 and nut 233,
Rear engine link 216 is connected to position adjustment cushion block 215 by distance adjustment cushion block 218 and T-bolt 236, nut 237
On.Balancing weight 212 is threadedly attached on the counterweight screw rod of balancing weight mounting bracket 213, and rotating weight block 212 can adjust
Axial direction (short transverse) position of balancing weight 212 on the counterweight screw rod of balancing weight mounting bracket 213.Balancing weight mounting bracket 213
It is installed to by T-bolt 239 and nut 238 on position adjusting pad block 214.Bearing 2 203 passes through T-bolt 234 and nut
235 are installed on position adjusting pad block 204.Pull bar 202 is installed on bearing 2 203 by bearing pin 231, is opened on bearing 2 203
There is U-type groove, for adjusting pull bar 202 on bearing 2 203 along the position of short transverse.The one end of second force snesor 201 passes through
It is threadedly coupled on pull bar 202, the other end is connected by flange with the one end of slip-knot nut 217.
Referring to Fig. 6, Fig. 7, the length adjustment mechanism includes double threaded screw, slip-knot nut, and the slip-knot nut includes spiral shell
The parent 217-01 and slip-knot body 217-02 located at the longitudinal section of nut body front end in " work " font, the rear end of the nut body
It is connected with the nose threads of double threaded screw, the rear end of the double threaded screw is connected with the pull rod screw on bearing one, the nut
The front end of body sets end plate, and slide opening is set on the end plate, and mid diameter contraction section and the slide opening gap of the slip-knot body coordinate,
Slip-knot structure is formed, the rear end of the slip-knot body is limited in the end plate of nut body front end, can transmit the axial force in a direction,
The front end flange of the slip-knot body is fixedly connected with the rear end flanges of the second force snesor by screw, second force snesor
Front end be connected with the pull rod screw on bearing two.Slip-knot body 217-02 and nut body 217-01 can be rotated mutually circumferentially,
Axially mutual translation.During installation, nut body 217-01 retreats to slip-knot body 217-02 flange ends toward diagram right side, by double threaded screw
107 and slip-knot nut 217 be adjusted to coaxially, rotating nuts body 217-01, double threaded screw 107 and nut body 217-01 are connected by screw thread
Be connected in one, during rotating nuts body 217-01, " screw rod extendable room during loading " shown in Fig. 7 is gradually reduced, and " adjust away from
From " gradually increase, until slip-knot body 217-02 configured left boss compresses with inner convex platform on the right side of nut body 217-01, continue rotating nuts
Body 217-01,107 are further tensed, and closely produce axial tension.The nut body 217-01 endoporus face of cylinder has enough screw threads to grow
Degree with adapt to loading when double threaded screw 107 and slip-knot nut 217 it is moving axially relative.
It is worth noting that：
1) be related in said structure T-bolt connection position represent two be connected between relative position it is adjustable,
And then the simulation of engine part in the present invention can be made to be connected on different engine links, that is, it is different to simulate installation dimension
Engine installation；
2) weight of simulation of engine part can be changed by changing the weight of balancing weight 212, select the balancing weight of approrpiate wts
212 make simulation of engine part weight consistent with actual engine weight；Change balancing weight 212 in balancing weight mounting bracket 213 to match somebody with somebody
Along the position in vertical (height) direction on weight screw rod, can adjust simulation of engine part center of gravity fuselage vertically on position
Put；Balancing weight mounting bracket 213 can be adjusted in a lateral direction along the length direction of position adjustment cushion block 214 by unclamping nut 238
Position, and then adjust position of the simulation of engine part center of gravity along horizontal (left and right) direction of fuselage；Change distance adjustment cushion block 218
Thickness can adjust position of the simulation of engine part center of gravity along fuselage longitudinal direction (front and rear) direction.Pass through above-mentioned several local tune
It is whole, and then the different more money engines in weight center of gravity position can be simulated；
3) on the one hand position of the T-shaped bearing 103 on loading support on after-poppet 104 vertically is adjustable, bearing
One 101 position on position adjusting pad block 102 in transverse direction is adjustable, and another aspect bearing 2 203 is in simulation of engine part
On in transverse direction position it is adjustable, position of the pull bar 202 on bearing 203 vertically is adjustable, therefore, simulation of engine part
Line of pull application point and action direction it is also adjustable.
In summary, the weight center of gravity position of the simulation of engine part designed in apparatus of the present invention, mounting interface and pulling force
Line loading direction and position are adjustable, and this simulation of engine part can be used for simulating the engine of different model, i.e., a set of loading
Device (simulation of engine part and loading support) can simulate more money engines, the load of propeller.
A kind of engine loading method applied to single-shot fixed wing aircraft slow test, one kind is taken to be fixed applied to single-shot
The engine loading device of wing aircraft slow test, this method comprise the following steps：
1) simulation of engine part and experiment complete machine are subjected to Virtual assemble in three-dimensional software, lowered in virtual assembly environment
The whole weight of balancing weight 212 and its counterweight screw rod of balancing weight mounting bracket 213 vertically on position, adjustment balancing weight installation
The horizontal direction position of support 213, adjustment distance adjustment the thickness of cushion block 218, make simulation of engine part weight and position of centre of gravity with
Actual engine weight and position of centre of gravity are consistent, according to the relative position of engine and propeller, determine propeller line of pull
Application point and action direction record the adjusting parameter (relative position) of each parts, so as to each zero on simulation of engine part
The position of part is adjusted；Said process can also be completed by theoretical calculation；
2) (adjusting parameter includes two parts, and 1. center of gravity weight adjusts the adjusting parameter of each adjustment part drawn according to previous step
Parameter：The weight and lengthwise position of balancing weight 212, the lateral attitude of balancing weight mounting bracket 213, distance adjust cushion block 218
Thickness, 2. line of pull application point and action direction adjusting parameter：Bearing 1 and the lateral attitude of bearing 2 203, T-shaped bearing 103
And the vertical position of bearing pin 115), the relative position of adjustment simulation of engine part each parts in kind, just make after being adjusted in place
Obtain weight and position of centre of gravity, propeller line of pull active position and action direction and the weight of actual engine of simulation of engine part
It is consistent with action direction to measure position of centre of gravity, propeller line of pull active position, (difference can be simulated using different adjusting parameters
Engine)；
3) simulation of engine part is passed through into the front engine link 208 on simulation of engine part, front engine link
219th, rear engine link 216 and cushion block 1 are installed on the engine link on experimental prototype fuselage；
4) support (shown in Fig. 2) left socle, right support and the lower screw rod 220 on simulation of engine part and lower screw rod will be loaded
211 connections, the slip-knot nut 217 on simulation of engine part is connected with the double threaded screw 107 on loading support, adjustment connection spiral shell
Line it is elastic so that the reading of each force snesor is zero.Loading after-poppet 104 is fixed to ground by castor 105；
5) engine, the propeller load, i.e. pulling force and moment of torsion applied according to test requirements document, respectively by tightening slip-knot spiral shell
Mother 217 (control pulling force F) and loading nut 240 (control pulling force F1), loading nut 241 (control pulling force F2), sense each power
Device reading is consistent with desired loaded load (propeller torque need couple F1 and F2 to be multiplied by the arm of force do simple computation).Such as Fig. 4
Shown, quarter bend 207 is threadably secured with upper screw rod 205, and when tightening loading nut 241, upper screw rod 205 pulls down quarter bend 207,
Pulling force F2 is produced to simulation of engine part；Similarly, when tightening loading nut 240, lower screw rod 211 drives upper screw rod 205 to transport upwards
Dynamic, upper screw rod 205 pushes up quarter bend 207 upwards, and producing pulling force F1, pulling force F1 and pulling force F2 to simulation of engine part forms couple, i.e.,
Propeller torque load；
6) can the magnitude of load of each load(ing) point of electrodeless adjustment in real time as needed during testing；
7) when needing to simulate different model engine, repeat the above steps 1) to 6).
Finally illustrate, preferred embodiment above is merely illustrative of the technical solution of the present invention and unrestricted, although logical
Cross above preferred embodiment the present invention is described in detail, it is to be understood by those skilled in the art that can be
Various changes are made to it in form and in details, without departing from claims of the present invention limited range.
Claims (10)
1. a kind of engine loading device applied to single-shot fixed wing aircraft slow test, it is characterised in that including loading branch
Frame, simulation of engine part, slow test need simulation load include propeller pulling force F, engine and propeller total force G and
The moment of torsion M, the moment of torsion M of propeller form couple to simulate using upward pulling force F1 and downward pulling force F2,
The loading support includes pedestal, the left socle on the left of pedestal front end, the right support on the right side of pedestal front end, with
And the after-poppet located at pedestal rear end, the upper end of the after-poppet be provided with can adjustment position up and down T-shaped bearing, T-shaped bearing
Upper end be provided with can left and right adjustment position bearing one；
The simulation of engine part includes the quarter bend transversely set, and the quarter bend both ends are threaded with respectively vertically to be set
Upper screw rod, the lower end of the upper screw rod is sequentially connected the first force snesor, lower screw rod, and first force snesor is used to detect
The size of upper screw rod, lower screw rod loading force, the lower screw clearance is matched with left socle, the anti-rotating hole that right support is provided with, institute
State screw thread on lower screw rod and be combined with loading nut, wherein, the loading nut of quarter bend left end is located above left socle, quarter bend right-hand member
Loading nut be located at right support lower section, the both ends of the quarter bend upper surface connect respectively can left and right adjustment position front engine
Link, the front end of the front engine link are extended forwardly into outside quarter bend, and the middle part connection of the rear end face of the quarter bend can
With the rear engine link of left and right adjustment position, distance adjustment cushion block, preceding hair are provided between rear engine link and quarter bend
Motivation link, rear engine link are used to simulation of engine part being connected to engine link；
The lower surface connection of the quarter bend can left and right adjustment position the counterweight screw rod extended downwardly, screw thread connects on counterweight screw rod
Balancing weight is connect, rotating weight block can adjust position of the balancing weight along counterweight screw rod axial direction, connect in the middle part of the upper surface of the quarter bend
Connect can left and right adjustment position bearing two, pull bar, the opposite end point of two pull bars have been respectively articulated with the bearing one, bearing two
Be not threadedly coupled double threaded screw, wherein, pull bar on bearing two can upper and lower adjustment position, be connected with length between two pull bar
Governor motion, the second force snesor, second force snesor are used for the size of loading force between two pull bars of detection；
The propeller pulling force F is simulated by length adjustment mechanism, two pull bars, and the total force G of the engine and propeller leads to
Balancing weight simulation is crossed, the upward pulling force F1 is simulated by screw rod, lower screw rod, loading nut on the quarter bend left end, described
Downward pulling force F2 is simulated by screw rod, lower screw rod, loading nut on the quarter bend right-hand member.
2. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
It is characterised by, the length adjustment mechanism includes double threaded screw, slip-knot nut, and the slip-knot nut includes nut body and is located at
The longitudinal section of nut body front end is in the slip-knot body of " work " font, and the rear end of the nut body and the nose threads of double threaded screw connect
Connect, the rear end of the double threaded screw is connected with the pull rod screw on bearing one, and the front end of the nut body sets end plate, the end
Slide opening is set on plate, and mid diameter contraction section and the slide opening gap of the slip-knot body coordinate, and form slip-knot structure, the slip-knot body
Rear end be limited in the end plate of nut body front end, the front end of the slip-knot body passes through screw with the rear end flanges of the second force snesor
It is fixedly connected, the front end of second force snesor is connected with the pull rod screw on bearing two.
3. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
It is characterised by, the bearing two is U-shaped, distinguishes on two walls of bearing two and is vertically provided with bar hole, the drawing on the bearing two
Bar, in two bar holes, makes the pull bar can upper and lower adjustment position by hinge.
4. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
Be characterised by, the T-shaped bearing by provided with vertical borehole jack on after-poppet, it is relative on the T-shaped vertical hole hole wall of bearing
Bar hole, after-poppet is passed through to form the positioning to T-shaped bearing provided with bar hole, and by bolt, and can upper and lower adjustment position.
5. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
It is characterised by, the pedestal, left socle, right support, after-poppet are welded by shaped steel, and the bottom of the pedestal is provided with four
The individual castor that can be moved and lock.
6. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
It is characterised by, is fixed with the nut for being connected with upper screw flight on the quarter bend, and sets and nut bore is coaxial is used for
The through hole stepped down to upper screw rod；Anti-rotation bearing is fixed in the left socle, right support upper end respectively, set in the anti-rotation bearing with
The coaxial through hole of anti-rotating hole.
7. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
Be characterised by, the connection of the lower surface of the quarter bend can left and right adjustment position balancing weight mounting bracket, the counterweight screw rod consolidates
It is scheduled in balancing weight mounting bracket.
8. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 7, its
It is characterised by, position adjustment pad has been respectively fixedly connected in upper surface, lower surface, rear end face and the T-shaped bearing upper surface of the quarter bend
Block, T-slot is transversely provided with the position adjustment cushion block, for installing T-bolt, the bearing one, bearing two, preceding start
Machine link, rear engine link and balancing weight mounting bracket are installed to corresponding T-shaped by T-bolt and nut respectively
Cushion block, and can transversely adjustment position.
9. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1, its
It is characterised by, the bearing one, the upper end of bearing two are respectively provided with the journal stirrup being hinged with pull bar, wherein, the bearing two
Journal stirrup be provided with and be used for bar hole with pull bar hinge, allow the pull bar of bearing two vertically adjustment position.
10. a kind of engine loading method applied to single-shot fixed wing aircraft slow test, it is characterised in that take claim
A kind of engine loading device applied to single-shot fixed wing aircraft slow test described in 1, this method comprise the following steps：
1) simulation of engine part and experimental prototype are subjected to Virtual assemble in three-dimensional software, select to close under virtual assembly environment
The balancing weight of suitable weight, and its position along counterweight screw rod axial direction is adjusted, the position of adjustment counterweight screw rod transversely, selection is properly
The distance adjustment cushion block of thickness, make the weight and position of centre of gravity and actual engine weight and position of centre of gravity one of simulation of engine part
Cause, determine center of gravity weight adjusting parameter：The weight and lengthwise position of balancing weight, the lateral attitude of counterweight screw rod, apart from adjusting pad
The thickness of block；According to the relative position of engine and propeller, line of pull application point and action direction adjusting parameter are determined：Bearing
One and the vertical position of the lateral attitude of bearing two, T-shaped bearing and the upper connecting rod of bearing two；
2) each adjusting parameter drawn according to previous step, the relative position of adjustment simulation of engine part each parts in kind, is adjusted
It is whole in place after just cause the weight and position of centre of gravity of simulation of engine part, propeller line of pull active position and action direction with it is true
The weight center of gravity position of real engine, propeller line of pull active position are consistent with action direction, so simulate engine and
The gravity G of propeller；
3) engine that simulation of engine part is installed to experimental prototype by front engine link, rear engine link connects
Connect on frame；Adjustment length governor motion and respectively load nut so that the reading of each force snesor is zero；
4) adjustment length governor motion and nut is respectively loaded, simulates the moment of torsion M of propeller pulling force F and propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710993386.4A CN107651216B (en) | 2017-10-23 | 2017-10-23 | Engine loading device and method applied to static test of single fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710993386.4A CN107651216B (en) | 2017-10-23 | 2017-10-23 | Engine loading device and method applied to static test of single fixed wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107651216A true CN107651216A (en) | 2018-02-02 |
| CN107651216B CN107651216B (en) | 2023-06-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710993386.4A Active CN107651216B (en) | 2017-10-23 | 2017-10-23 | Engine loading device and method applied to static test of single fixed wing aircraft |
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| CN109018428A (en) * | 2018-05-07 | 2018-12-18 | 上海交通大学 | A kind of engine installation structure load-carrying properties test device |
| CN109398754A (en) * | 2018-12-07 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of integral wing tank rolling vibration test counterweight fixture |
| CN109827723A (en) * | 2019-01-25 | 2019-05-31 | 苏州为鹿测试技术有限公司 | The full machine intensity of fixed wing aircraft and modal test flexible support system |
| CN110654568A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Hub couple loading device |
| CN110803296A (en) * | 2019-10-15 | 2020-02-18 | 中国直升机设计研究所 | Helicopter full-mechanical static test lift force system dummy |
| CN111439391A (en) * | 2020-04-22 | 2020-07-24 | 中国飞机强度研究所 | Lateral restraint device for double engines |
| CN111762337A (en) * | 2020-07-06 | 2020-10-13 | 西安飞机工业（集团）有限责任公司 | Loading method and loading device for fatigue test of aircraft engine frame |
| CN112461468A (en) * | 2020-11-18 | 2021-03-09 | 中国核动力研究设计院 | Seismic test equipment pipe connection load simulation device and simulation method |
| CN113607403A (en) * | 2021-09-06 | 2021-11-05 | 北京空间机电研究所 | Height-adjustable spacecraft storage box simulation loading static test device and method |
| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
| CN114383934A (en) * | 2022-01-10 | 2022-04-22 | 中航飞机起落架有限责任公司 | Loading device and method for hook-and-loop lock ring test of landing gear |
| CN114527008A (en) * | 2022-01-14 | 2022-05-24 | 成都飞机工业（集团）有限责任公司 | Aircraft wing folding gravity load simulation loading device and method |
| CN115014769A (en) * | 2021-11-23 | 2022-09-06 | 中国直升机设计研究所 | Torque loading device of engine mounting bracket |
| CN113708565B (en) * | 2021-08-27 | 2023-05-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Installation fixing device and method for various engine interfaces |
| CN115014769B (en) * | 2021-11-23 | 2024-09-24 | 中国直升机设计研究所 | Torque loading device of engine mounting bracket |
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| CN110654568A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Hub couple loading device |
| CN110803296A (en) * | 2019-10-15 | 2020-02-18 | 中国直升机设计研究所 | Helicopter full-mechanical static test lift force system dummy |
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| CN112461468A (en) * | 2020-11-18 | 2021-03-09 | 中国核动力研究设计院 | Seismic test equipment pipe connection load simulation device and simulation method |
| CN113708565B (en) * | 2021-08-27 | 2023-05-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Installation fixing device and method for various engine interfaces |
| CN113607403B (en) * | 2021-09-06 | 2022-04-29 | 北京空间机电研究所 | Height-adjustable spacecraft storage box simulation loading static test device and method |
| WO2023029148A1 (en) * | 2021-09-06 | 2023-03-09 | 北京空间机电研究所 | Height-adjustable spacecraft storage tank simulated loading static experiment device and method |
| CN113607403A (en) * | 2021-09-06 | 2021-11-05 | 北京空间机电研究所 | Height-adjustable spacecraft storage box simulation loading static test device and method |
| CN115014769A (en) * | 2021-11-23 | 2022-09-06 | 中国直升机设计研究所 | Torque loading device of engine mounting bracket |
| CN115014769B (en) * | 2021-11-23 | 2024-09-24 | 中国直升机设计研究所 | Torque loading device of engine mounting bracket |
| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
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| CN114383934A (en) * | 2022-01-10 | 2022-04-22 | 中航飞机起落架有限责任公司 | Loading device and method for hook-and-loop lock ring test of landing gear |
| CN114383934B (en) * | 2022-01-10 | 2023-11-21 | 中航飞机起落架有限责任公司 | Landing gear hook ring lock ring test loading device and method |
| CN114527008A (en) * | 2022-01-14 | 2022-05-24 | 成都飞机工业（集团）有限责任公司 | Aircraft wing folding gravity load simulation loading device and method |
| CN114527008B (en) * | 2022-01-14 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Device and method for simulating loading of folding gravity load of aircraft wing |
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