CN207403957U - Engine loading device applied to single-shot fixed wing aircraft slow test - Google Patents
Engine loading device applied to single-shot fixed wing aircraft slow test Download PDFInfo
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- CN207403957U CN207403957U CN201721366625.5U CN201721366625U CN207403957U CN 207403957 U CN207403957 U CN 207403957U CN 201721366625 U CN201721366625 U CN 201721366625U CN 207403957 U CN207403957 U CN 207403957U
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Abstract
The utility model discloses a kind of engine loading devices applied to single-shot fixed wing aircraft slow test, including loading stent, simulation of engine part, simulation load includes the torque M of propeller pulling force F, the total force G of engine and propeller and propeller, loading stent includes pedestal, left socle, right support, after-poppet, and the upper end of after-poppet is equipped 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, thread fitting has 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 end is located at below right support, engine link is set on quarter bend, clump weight, bearing two, bearing one, pull rod has been respectively articulated on bearing two, length adjustment mechanism is connected between two pull rods, second force snesor, the device experiment is of low cost, it is applied widely.
Description
Technical field
The utility model is related to aircraft slow test technical field, more particularly to applied to single-shot fixed wing aircraft static(al)
The engine loading device of experiment.
Background technology
Problem existing in the prior art is：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
The load that motivation generates is the important component of test load.Presently, there are the problem of be 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, adjust it 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
With the related data and document of engine loading device, (the utility model is mounted on machine mainly for engine for motivation slow test
The aircraft of body forepart can inquire two for the patent of engine loading device of the engine on wing：One kind flies
Machine slow test engine loading simulation part --- utility model 201220087091.3, aircraft wing slow test engine
Alternate device --- utility model patent 201310607947.4, the two patents relate only to simulation of engine part, are not directed to
To load charger).To sum up, there are following defects for the prior art：
1) using actual engine full machine slow test is of high cost, risk is big, 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, therefore the narrow scope of application of experimental rig when more reengining；
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 adjusting of load mode and loading force, therefore existing experimental rig is incomplete.
Utility model content
The purpose of the utility model is to overcome the deficiencies in the prior art, provide and are tried applied to single-shot fixed wing aircraft static(al)
The engine loading device tested applies engine and propeller load, for the full machine static(al) of aircraft by engine loading device
Experiment, experimentation cost is cheap, applied widely.
What the purpose of this utility model was realized in：
A kind of engine loading device applied to single-shot fixed wing aircraft slow test, including loading stent, engine
Simulating piece, slow test need simulation load to include propeller pulling force F, the total force G of engine and propeller and propeller
Torque M, the torque M form couple to simulate using upward pulling force F1 and downward pulling force F2,
The loading stent 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 arranged on pedestal rear end, the upper end of the after-poppet are equipped with the T-shaped bearing that can adjust position up and down, T-shaped branch
The upper end of seat is equipped with the bearing one that can control adjustment position；
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 equipped with
Hole, thread fitting has 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 end is located at below right support, and the both ends of the quarter bend upper surface are connected respectively before can controlling adjustment position
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 control the rear engine link of adjustment position, be equipped between rear engine link and quarter bend 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 face connection of the quarter bend can control the counterweight screw rod extended downwardly of adjustment position, spiral shell on counterweight screw rod
Line connects clump weight, and rotating weight block can adjust position of the clump weight along counterweight screw rod axial direction, in the upper surface of the quarter bend
Portion's connection can control the bearing two of adjustment position, be respectively articulated with pull rod on the bearing one, bearing two, two pull rods it is opposite
End is threadedly coupled double threaded screw respectively, wherein, the pull rod on bearing two can adjust position up and down, be connected between two pull rod
Length adjustment mechanism, the second force snesor, second force snesor are used for the size of loading force between two pull rods of detection；
The propeller pulling force F is simulated by length adjustment mechanism, two pull rods, the total force of the engine and propeller
G is simulated by clump 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 end.
Preferably, the length adjustment mechanism include double threaded screw, slip-knot nut, the slip-knot nut include nut body with
And arranged on the longitudinal section of nut body front end in the slip-knot body of " work " font, the rear end of the nut body and the front end spiral shell of double threaded screw
Line connects, 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
It states and slide opening is set on end plate, mid diameter contraction section and the slide opening clearance fit of the slip-knot body 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, is vertically equipped with bar hole, the bearing two on two walls of bearing two respectively
On pull rod two bar holes are articulated with by axis pin, make the pull rod that can adjust position up and down.
Preferably, the T-shaped bearing is sleeved on by the vertical hole being equipped on after-poppet, the T-shaped vertical hole hole wall of bearing
It is upper opposite equipped with bar hole, and pass through bolt and bar hole, after-poppet is passed through to form the positioning to T-shaped bearing, 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
There are four the castors that can be moved and lock for dress.
Preferably, the nut for being connected with upper screw flight is fixed on 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 lower face connection of the quarter bend can control the clump weight mounting bracket of adjustment position, the counterweight
Screw rod is fixed in clump weight mounting bracket.
Preferably, position has been respectively fixedly connected in the upper surface of the quarter bend, lower face, rear end face and T-shaped bearing upper surface
Adjust cushion block, T-slot be transversely provided on position adjustment cushion block, for installing T-bolt, the bearing one, bearing two,
Front engine link, rear engine link and clump weight mounting bracket are installed to pair respectively by T-bolt and nut
The T-shaped cushion block answered, and can transversely adjust position.
Preferably, the bearing one, the upper end of bearing two are respectively provided with the journal stirrup hinged with pull rod, wherein, it is described
The journal stirrup of bearing two is equipped with for the bar hole hinged with pull rod axis pin, and the pull rod of bearing two is allow vertically to adjust position
It puts.
A kind of engine loading method applied to single-shot fixed wing aircraft slow test takes one kind 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, are selected under virtual assembly environment
The clump 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, makes the weight of simulation of engine part and position of centre of gravity and actual engine weight and center of gravity position
It puts unanimously, determines center of gravity weight adjusting parameter：The weight and lengthwise position of clump weight, the lateral position 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 action point and action direction adjusting parameter are determined：
The vertical position of two upper connecting rod of the lateral position of bearing one and bearing two, T-shaped bearing and bearing；
2) each adjusting parameter drawn according to previous step, the opposite position of adjustment simulation of engine part each parts in kind
It puts, just so that the weight and position of centre of gravity of simulation of engine part, propeller line of pull active position and effect side after being adjusted in place
To with actual engine weight center of gravity position, propeller line of pull active position and action direction it is consistent, 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 adjusting mechanism and respectively load nut so that the reading of each force snesor is zero；
4) adjustment length adjusting mechanism and nut is respectively loaded, simulates the torque M of propeller pulling force F and propeller.
By adopting the above-described technical solution, the utility model has the advantages that：
1) on the premise of test requirements document is met, experimentation cost and empirical risk are reduced；
2) the utility model is related to experimental rig in simulation of engine part weight center of gravity position, pulling force line position and side
To adjustable, therefore the utility model can be used for the engine load for simulating different model, the experiment of the utility model design
While cost is reduced, also adaptable stronger, the scope of application is wider for device, uses more flexible feature；
3) data that open source literature can be found has related only to simulation of engine part, without being related to specifically loading dress
It puts, the adjusting of load mode and loading force, simulation of engine part and loading device are integrated together by the utility model, using silk
Stem nut mode loads and integrates force sensor, and load mode is simple and convenient, the adjustment of loading force size is flexible, draws simultaneously
The position of line of force load(ing) point, direction and size are adjustable so that the experimental rig function of the utility model is more, and application is more
By force.
4) in addition to gravitational load, remaining load is loaded using feed screw nut, with force sensor in structure, can be looked into real time
Loading force size is seen and adjusts, test effect is more preferable, is particularly suitable for light aerocraft.
Description of the drawings
Fig. 1 is the structure diagram of engine loading device；
Fig. 2 is the structure diagram of loading stent；
Fig. 3 is the structure diagram of one visual direction of simulation of engine part；
Fig. 4 is the structure diagram of another visual direction of simulation of engine part；
Fig. 5 is slow test load schematic；
Fig. 6 is the structure diagram of slip-knot nut；
Fig. 7 is the connection diagram of slip-knot nut.
Reference numeral
In attached drawing, stent is loaded：101- bearings one, 102- positions adjustment cushion block, 103-T type bearings, 104- after-poppets,
105- castors, 106- pull rods, 107- double threaded screws, 108- anti-rotation bearings, 111- bolts, 112- nuts, 113-T type bolts,
114- nuts, 115- axis pins；
Simulation of engine part：The second force snesors of 201-, 202- pull rods, 203- bearings two, 204- positions adjustment cushion block,
The upper screw rods of 205-, 206- nuts, 207- quarter bends, 208- front engine links, 209- cushion blocks one, the first force snesors of 210-,
Screw rod under 211-, 212- clump weights, 213- clump weight mounting brackets, 214- positions adjustment cushion block, 215- positions adjustment cushion block,
Engine link after 216-, 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 first force snesors of 223-,
231- axis 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.
Specific embodiment
Embodiment
A kind of engine loading device applied to single-shot fixed wing aircraft slow test, including loading stent, 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 torque M (being simulated in the utility model using a pair of of couple, F1 and F2 in Fig. 5) of propeller.In addition to gravitational load,
Over-carriage lotus is loaded using feed screw nut, can be with real time inspection and adjustment loading force size with force sensor in structure.
The loading stent 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 arranged on pedestal rear end, the upper end of the after-poppet are equipped with the T-shaped bearing that can adjust position up and down, T-shaped branch
The upper end of seat is equipped with the bearing one that can control adjustment position.Pedestal, left socle, right support, after-poppet are welded by shaped steel,
There are four castor 105, the castor 105 can make the movement of stent become quick aspect by use demand for base bottom installation,
Stent can be fixed firmly to ground again.Through hole is provided on left socle, right support, for 211 He of screw rod 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 104 upper rear end of after-poppet is equipped 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 pass through bolt 111 and
Nut 112 is fixed.T-shaped 103 top of bearing is fixed with position adjustment cushion block 102, T-slot is provided on T-shaped cushion block 102, for installing T
Type bolt 113.Bearing 1 is installed to by T-bolt 113 and nut 114 on T-shaped cushion block 102.Pull rod 106 passes through axis pin
115 are mounted on bearing 1, and double threaded screw 107 is connected to by end thread on pull rod 106.
Simulation of engine part mainly by force snesor, pull rod, bearing, quarter bend, T-shaped cushion block, engine link, screw rod,
The compositions such as clump weight, slip-knot nut, T-bolt and cushion block, structure on two sides almost symmetry.207 both ends of quarter bend 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 between 205 and lower screw rod 211 is installed, the first power biography is installed between screw rod 222 and lower screw rod 220
Sensor 223 can show the size of screw rod loading force.207 upper and lower end face of quarter bend and rear end face are respectively welded position adjusting 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 on 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 to position by T-bolt 232 and nut 233 and adjust on cushion block 204,
Engine link 216 is connected to position by distance adjustment cushion block 218 and T-bolt 236, nut 237 and adjusts cushion block 215 afterwards
On.Clump weight 212 is threadedly attached on the counterweight screw rod of clump weight mounting bracket 213, and rotating weight block 212 can adjust
Axial direction (short transverse) position of clump weight 212 on 213 counterweight screw rod of clump weight mounting bracket.Clump 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 rod 202 is installed to by axis pin 231 on bearing 2 203, is opened on bearing 2 203
There is U-type groove, for adjusting pull rod 202 on bearing 2 203 along the position of short transverse.Second force snesor, 201 one end passes through
It is threadedly coupled on pull rod 202, the other end is connected by flange with 217 one end of slip-knot nut.
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
Parent 217-01 and arranged on the longitudinal section of nut body front end be in " work " font slip-knot body 217-02, 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, the mid diameter contraction section of the slip-knot body and slide opening clearance fit are set on the end plate,
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 transfer 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,
Axial mutually 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 is compressed 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 generate axial tension.Nut body 217-01 endoporus cylindrical surface has enough screw threads long
The axial relative movement of double threaded screw 107 and slip-knot nut 217 when degree is to adapt to loading.
It is worth noting that：
1) involved in said structure to T-bolt connect position represent two be connected between relative position it is adjustable,
And then the simulation of engine part in the utility model can be made to be connected on different engine links, that is, simulate installation dimension
The installation of different engines；
2) weight of simulation of engine part can be changed by changing the weight of clump weight 212, select the clump weight of approrpiate wts
212 make simulation of engine part weight consistent with actual engine weight；Change clump weight 212 in clump 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
It puts；Cushion block 214 length direction adjustment clump weight mounting bracket 213 can be adjusted in a lateral direction along position 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 the tune in above-mentioned several places
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 stent 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 rod 202 on bearing 203 vertically is adjustable, therefore, simulation of engine part
Line of pull action point and action direction it is also adjustable.
In conclusion the weight center of gravity position of the simulation of engine part designed in the utility model device, install interface and
Line of pull loading direction and position are adjustable, 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 stent) can simulate more money engines, the load of propeller.
A kind of engine loading method applied to single-shot fixed wing aircraft slow test takes one kind 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, are lowered in virtual assembly environment
Whole 212 weight of clump weight and its 213 counterweight screw rod of clump weight mounting bracket vertically on position, adjustment clump weight installation
213 horizontal direction position of stent, adjustment distance adjustment 218 thickness of cushion block, 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
Action 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；The above 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 clump weight 212, the lateral position of clump weight mounting bracket 213, distance adjust cushion block 218
Thickness, 2. line of pull action point and action direction adjusting parameter：2 203 lateral position of bearing 1 and bearing, T-shaped bearing 103
And the vertical position of axis pin 115), the relative position of adjustment simulation of engine part each parts in kind just makes 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 front engine link 208, the front engine link on simulation of engine part
219th, rear engine link 216 and cushion block 1 are installed on the engine link on experimental prototype fuselage；
It 4) will loading stent (shown in Fig. 2) left socle, right support and the lower screw rod 220 on simulation of engine part and lower screw rod
Slip-knot nut 217 on simulation of engine part is connected, adjustment connection spiral shell by 211 connections with the double threaded screw 107 on loading stent
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 torque 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 couple F1 and F2 is needed 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 generated 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 generating pulling force F1, pulling force F1 and pulling force F2 to simulation of engine part forms couple, i.e.,
Propeller torque load；
It 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 intended for describing the technical solutions of the present application, but not for limiting the present application, to the greatest extent
Pipe has been described in detail the utility model by above preferred embodiment, but those skilled in the art should manage
Solution, can in the form and details make it various changes, without departing from the utility model claims book institute
The scope of restriction.
Claims (9)
1. a kind of engine loading device applied to single-shot fixed wing aircraft slow test, which is characterized 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 torque M, the torque M of propeller form couple to simulate using upward pulling force F1 and downward pulling force F2,
The loading stent is including 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 arranged on pedestal rear end, the upper end of the after-poppet are equipped with the T-shaped bearing that can adjust position up and down, T-shaped bearing
Upper end is equipped with the bearing one that can control adjustment position；
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 for detecting
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 equipped with, institute
Stating thread fitting on lower screw rod has loading nut, wherein, the loading nut of quarter bend left end is located above left socle, quarter bend right end
Loading nut is located at below right support, and the both ends of the quarter bend upper surface connect the front engine that can control adjustment position respectively
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 equipped 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 face connection of the quarter bend can control the counterweight screw rod extended downwardly of adjustment position, and screw thread connects on counterweight screw rod
Clump weight is connect, rotating weight block can adjust position of the clump weight along counterweight screw rod axial direction, connect in the middle part of the upper surface of the quarter bend
The bearing two of adjustment position can be controlled by connecing, and pull rod, the opposite end point of two pull rods have been respectively articulated on the bearing one, bearing two
Double threaded screw is not threadedly coupled, wherein, the pull rod on bearing two can adjust position up and down, and length is connected between two pull rod
Adjusting mechanism, the second force snesor, second force snesor are used for the size of loading force between two pull rods of detection；
The propeller pulling force F is simulated by length adjustment mechanism, two pull rods, and the total force G of the engine and propeller leads to
Clump 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 end.
2. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1,
It is characterized in that, the length adjustment mechanism includes double threaded screw, slip-knot nut, and the slip-knot nut includes nut body and is arranged on
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
It connects, 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 clearance fit of the slip-knot body 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,
It is characterized in that, the bearing two is U-shaped, distinguishes on two walls of bearing two and is vertically equipped with bar hole, the drawing on the bearing two
Bar is articulated with two bar holes by axis pin, makes the pull rod that can adjust position up and down.
4. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1,
It is characterized in that, the T-shaped bearing is sleeved on by the vertical hole being equipped on after-poppet, opposite on the T-shaped vertical hole hole wall of bearing
Equipped with bar hole, and pass through bolt and bar hole, after-poppet is passed through to form the positioning to T-shaped bearing, and position can be adjusted up and down.
5. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1,
It is characterized in that, the pedestal, left socle, right support, after-poppet are welded by shaped steel, and the bottom of the pedestal is equipped with four
A 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,
It is characterized in that, is fixed with the nut for being connected with upper screw flight on the quarter bend, and set 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,
It is characterized in that, the lower face connection of the quarter bend can control the clump weight mounting bracket of adjustment position, and the counterweight screw rod is consolidated
It is scheduled in clump weight mounting bracket.
8. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 7,
It is characterized in that, position adjusting pad has been respectively fixedly connected in upper surface, lower face, rear end face and the T-shaped bearing upper surface of the quarter bend
Block is transversely provided with T-slot on position adjustment cushion block, and for installing T-bolt, the bearing one, bearing two preceding start
Machine link, rear engine link and clump weight mounting bracket are installed to corresponding T-shaped by T-bolt and nut respectively
Cushion block, and can transversely adjust position.
9. a kind of engine loading device applied to single-shot fixed wing aircraft slow test according to claim 1,
It being characterized in that, the bearing one, the upper end of bearing two are respectively provided with the journal stirrup hinged with pull rod, wherein, the bearing two
Journal stirrup be equipped with for the bar hole hinged with pull rod axis pin, the pull rod of bearing two is allow vertically to adjust position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721366625.5U CN207403957U (en) | 2017-10-23 | 2017-10-23 | Engine loading device applied to single-shot fixed wing aircraft slow test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721366625.5U CN207403957U (en) | 2017-10-23 | 2017-10-23 | Engine loading device applied to single-shot fixed wing aircraft slow test |
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| CN207403957U true CN207403957U (en) | 2018-05-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201721366625.5U Active CN207403957U (en) | 2017-10-23 | 2017-10-23 | Engine loading device applied to single-shot fixed wing aircraft slow test |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN110104206A (en) * | 2019-04-22 | 2019-08-09 | 北京零壹空间技术研究院有限公司 | Steering engine load simulator |
| CN118618728A (en) * | 2024-06-18 | 2024-09-10 | 中国航发成都发动机有限公司 | Complete machine dummy for aircraft engine packaging box identification test |
-
2017
- 2017-10-23 CN CN201721366625.5U patent/CN207403957U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN110104206A (en) * | 2019-04-22 | 2019-08-09 | 北京零壹空间技术研究院有限公司 | Steering engine load simulator |
| CN118618728A (en) * | 2024-06-18 | 2024-09-10 | 中国航发成都发动机有限公司 | Complete machine dummy for aircraft engine packaging box identification test |
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Inventor after: Xu Liang Inventor after: Zhang Jin Inventor after: Huang Shengying Inventor after: Dong Bo Inventor after: Chen Guo Inventor after: Zeng Hui Inventor after: Jia Deng Inventor after: Yu Jianbo Inventor after: Liu Xiaofei Inventor after: Luo You Inventor after: Hu Hanjie Inventor after: Zeng Xianjun Inventor before: Xu Liang Inventor before: Zhang Jin Inventor before: Huang Shengying Inventor before: Dong Bo Inventor before: Chen Guo Inventor before: Zeng Hui Inventor before: Jia Deng Inventor before: Yu Jianbo Inventor before: Liu Xiaofei Inventor before: Luo You Inventor before: Hu Hanjie Inventor before: Zeng Xianjun |