CN108725838A - A kind of guided flight vehicle launching simulation platform - Google Patents
A kind of guided flight vehicle launching simulation platform Download PDFInfo
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- CN108725838A CN108725838A CN201810400259.3A CN201810400259A CN108725838A CN 108725838 A CN108725838 A CN 108725838A CN 201810400259 A CN201810400259 A CN 201810400259A CN 108725838 A CN108725838 A CN 108725838A
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- hinge
- low level
- sliding rail
- vertical frame
- sliding
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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
Abstract
The present invention relates to a kind of guided flight vehicle launching simulation platforms, belong to mechanized equipment technical field.It solves guided flight vehicle launching simulation platform in the prior art the guided flight vehicle of different weight or volume is needed to build different test platforms, the technical issues of being costly and inefficient.Multi-functional guided flight vehicle launching simulation platform includes hinge variable system, load simulation system, main Erecting System, plays vertical frame and vehicle frame, and hinge variable system includes multiple upper hinges and multiple lower hinges；The turning end for playing vertical frame is hinged with vehicle frame, and the other end is rotated around turning end；One end of main Erecting System is hinged by upper hinge and vehicle frame, and the other end is hinged by lower hinge with vertical frame is played；Load simulation system is detachably connected with vertical frame sliding is played；It upper hinge and states lower hinge and is located on same vertical plane.Guided flight vehicle launching simulation platform provided by the invention realizes the analog study of different model aircraft.
Description
Technical field
The present invention relates to mechanized equipment technical field more particularly to a kind of multi-functional guided flight vehicle launching simulation platforms.
Background technology
Guided flight vehicle flat pad is the equipment for integrating transport, storage, transmitting.
Existing guided flight vehicle launching simulation platform builds the guided flight vehicle needs of different weight or volume
Different test platforms, is costly and inefficient, and cannot be satisfied the simulation requirement of guided flight vehicle transmitting, can not be guided flight
The Project R&D of device provides reliable guarantee.
Invention content
The object of the present invention is to provide a kind of guided flight vehicle launching simulation platforms, solve guided flight vehicle in the prior art
Launching simulation platform needs the guided flight vehicle of different weight or volume to build different test platforms, of high cost and effect
The low technical problem of rate.
The present invention is achieved by the following technical solutions：
The present invention provides a kind of guided flight vehicle launching simulation platform, including hinge variable system, load simulation system,
Main Erecting System plays vertical frame and vehicle frame, and hinge variable system includes multiple upper hinges and multiple lower hinges；Play the turning end of vertical frame
It is hinged with vehicle frame；One end of main Erecting System is hinged by upper hinge with vertical frame is played, and the other end is hinged by lower hinge and vehicle frame；
Load simulation system is detachably connected with vertical frame sliding is played；Along the length direction of vehicle frame, multiple upper hinges and multiple lower hinge positions
In on same vertical plane.
In simulation process, the turning end for playing vertical frame is hinged with vehicle frame, and one end of main Erecting System is hinged with lower hinge,
The other end and upper hinge are hinged successively, and test is not same as above position of articulating point and plays perpendicular ginseng to playing perpendicular speed, perpendicular stroke, stressing conditions etc.
Several influences；Change the lower hinge articulated position of main Erecting System one end, the other end of main Erecting System is cut with scissors with upper hinge successively
It connects, test is not same as above influence of the position of articulating point to playing perpendicular speed, playing the parameters such as perpendicular stroke, stressing conditions；Based on above-mentioned test side
Method, change successively with the hinged lower position of articulating point in main Erecting System one end, and change respectively hinged with the main Erecting System other end
Upper position of articulating point, obtain and be not same as above hinge and lower position of articulating point to the shadow that plays perpendicular speed, play the parameters such as perpendicular stroke, stressing conditions
It rings；Change the position of hinge by above-mentioned hinge variable system, perpendicular performance can be played to the synthesis of main Erecting System and studied
Test.Since load simulation system is detachably connected with vertical frame sliding is played, during aircraft simulation, based on above-mentioned
Test method, by change load simulation system load and load situation, different weight and barycenter position can be simulated
The aircraft set；
Guided flight vehicle launching simulation platform provided by the invention can reach to meet to have led by variation position of articulating point and erect
The optimal either stroke of system stress is minimum or plays perpendicular most fast optimal test result, can also test different main Erecting Systems
To playing the influence of perpendicular process, for example, different Erecting organ researchs, difference Erecting System are studied, different hybrid powers quickly rise and erect
System research etc..In addition, being not necessarily to build different test platforms for the guided flight vehicle of different weight or centroid position, make
It is not only at low cost but also efficient with simulation system provided by the invention, it disclosure satisfy that the requirement of guided flight vehicle launching simulation,
Reliable guarantee is provided for the Project R&D of guided flight vehicle.
Preferably, launching simulation platform further include sliding rail, sliding block described in clamping mechanism and multiple sliding blocks with upper hinge one by one
It is corresponding；；Upper hinge is fixedly connected with a slide block, and sliding rail is fixedly connected with vertical frame is played, and sliding block is located on sliding rail and is slided with sliding rail and connected
It connects；Clamping mechanism includes fixture block, card slot and snib；Fixture block is located at sliding block side and is fixedly connected with a slide block, and card slot is located at sliding rail
Above and it is located at sliding rail side, snib can be fixedly connected on by card slot on fixture block.
Preferably, upper hinge has been distributed on the girder of vertical frame bottom center；Lower hinge is distributed on central frame beam girder.
Preferably, launching simulation platform further includes secondary Erecting System, hinge variable system further include multiple upside hinges and
Multiple downside hinges；Upside hinge has been distributed in the side of vertical frame, and downside hinge is distributed in the side of vehicle frame, upside hinge with state
Downside hinge is located on same vertical plane；Secondary Erecting System one end is hinged with upside hinge, and the other end is hinged with downside hinge；On
Side hinge and downside hinge are located on same vertical plane.
Preferably, load simulation system includes multiple clump weights；Clump weight is detachably connected with vertical frame sliding is played.
Preferably, clump weight includes coarse adjustment clump weight and accurate adjustment clump weight；Coarse adjustment clump weight can with a vertical frame sliding sliding
Dismantling connection, accurate adjustment clump weight are detachably connected with coarse adjustment clump weight；The weight of coarse adjustment clump weight is more than the weight of accurate adjustment clump weight
Amount.
Preferably, load simulation system further includes slide unit pedestal, high-order slide unit and low level slide unit；Slide unit pedestal and a vertical frame
It is fixedly connected, high-order slide unit is vertical with low level slide unit；Low level slide unit is slidably connected with slide unit pedestal, high-order sliding block and low level slide unit
It is slidably connected.
Preferably, high-order slide unit includes high-order sliding rail and high-order sliding block, and low level slide unit includes low level sliding rail and low level sliding block；
Low level sliding rail is fixedly connected with slide unit pedestal, and low level sliding block is slidably connected with low level sliding rail；High-order sliding rail is fixed with low level sliding block
Connection, high-order sliding block are slidably connected with high-order sliding rail.
Preferably, it is equipped with stroke controlling unit on low level sliding rail and high-order sliding rail, stroke controlling unit is equipped with stroke
Switch；Open high-order travel switch, high-order sliding block sliding mode on high-order sliding rail；Close high-order travel switch, high-order sliding block
It is stationary state in high-order sliding rail；Low level travel switch is opened, low level sliding block is in sliding mode on low level sliding rail；Close low level
Travel switch, low level sliding block are in stationary state on low level sliding rail.
Preferably, vehicle frame is equipped with oil supply system, walking turns to brake system and trailer interface；Trailer interface is fixed on vehicle
Frame front end；Oil supply system is located at trailer interface rear end and is fixedly connected with vehicle frame；Walking steering be located at trailer interface and
Between oil supply system, and it is fixedly connected with vehicle frame.
Preferably, above-mentioned guided flight vehicle launching simulation platform further includes suspension, and the suspension is mainly by oil gas
Spring is constituted, and different hydro-pneumatic spring parameters can be verified to car launcher damping effect in different road surface walks by detection,
Find optimized parameter.
Preferably, above-mentioned guided flight vehicle launching simulation platform further includes leveling system, which includes leveling oil
Cylinder, vehicle frame reserve leveling at six and install interface, can be used for or 6 leveling at 4 points.
Compared with prior art, beneficial effects of the present invention are：
Guided flight vehicle Launching Simulation System provided by the invention can be reached by variation position of articulating point and meet stress most
Excellent either stroke is minimum or the optimal test result that is combined with Erecting organ.By changing load, can study
Different model aircraft plays perpendicular position；By changing load situation, the optimal transmitting of the aircraft of different barycenter can be studied
Position；By changing different main Erecting Systems, it can be used for studying different Erecting organs, different Erecting Systems, different mixing
Influence of the quick Erecting System of power to perpendicular process.Analog platform simple structure provided by the invention, is easy to retest, and
Have versatility, the development of different model can be competent at.
It in the present invention, can also be combined with each other between above-mentioned each technical solution, to realize more preferred assembled schemes.This
Other feature and advantage of invention will illustrate in the following description, also, certain advantages can become from specification it is aobvious and
It is clear to, or understand through the implementation of the invention.The purpose of the present invention and other advantages can by specification, claims with
And it realizes and obtains in specifically noted content in attached drawing.
Description of the drawings
Attached drawing is only used for showing the purpose of specific embodiment, and is not considered as limitation of the present invention, in entire attached drawing
In, identical reference mark indicates identical component.
Fig. 1 is the structural schematic diagram for the guided flight vehicle flat pad that the embodiment of the present invention one provides；
Fig. 2 is the graphics for the guided flight vehicle flat pad that the embodiment of the present invention one provides；
Fig. 3 is the structural schematic diagram of hydro-pneumatic spring in the guided flight vehicle flat pad that the embodiment of the present invention one provides；
Fig. 4 is the structural schematic diagram of clump weight in the guided flight vehicle flat pad that the embodiment of the present invention one provides.
Reference numeral：
1- vehicle frames；2- walkings turn to brake system；3- suspension；4- load simulation systems；5- hinge variable systems；6-
Main Erecting System；7- oil supply systems；8- leveling systems；9- accurate adjustment clump weights；10- coarse adjustment clump weights；11- plays vertical frame.
Specific implementation mode
Specifically describing the preferred embodiment of the present invention below in conjunction with the accompanying drawings, wherein attached drawing constitutes the application part, and
It is used to illustrate the principle of the present invention together with embodiments of the present invention, be not intended to limit the scope of the present invention.
Embodiment one
A kind of guided flight vehicle launching simulation platform is present embodiments provided, as shown in Figures 1 to 4, including hinge is variable
System 5, load simulation system 4, main Erecting System 6, rise vertical frame 11 and vehicle frame 1, hinge variable system 5 include multiple upper hinges and
Multiple lower hinges；Turning end and the vehicle frame 1 for playing vertical frame 11 are hinged；It is cut with scissors by lower hinge and vehicle frame 1 one end of main Erecting System 6
It connects, the other end is hinged by upper hinge with vertical frame 11 is played；Load simulation system 4 is detachably connected with the sliding of vertical frame 11 is played；Along vehicle
The length direction of frame 1, multiple upper hinges are stated lower hinge and are located on same vertical plane with multiple.
In simulation process, turning end and the vehicle frame 1 for playing vertical frame 11 are hinged, one end of main Erecting System 6 and lower hinge
Hinged, the other end and upper hinge are hinged successively, and test is not same as above position of articulating point to playing perpendicular speed, perpendicular stroke, stressing conditions etc.
Play the influence of perpendicular parameter；Change the lower position of articulating point of 6 one end of main Erecting System, the other end of main Erecting System 6 successively with upper hinge
Point articulated, test is not same as above influence of the position of articulating point to playing perpendicular speed, playing the parameters such as perpendicular stroke, stressing conditions；On this basis,
Change successively with the hinged lower position of articulating point in 6 one end of main Erecting System, position of articulating point under often changing once, main Erecting System 6
The other end all changes upper position of articulating point and obtains different upper position of articulating point by main Erecting System and hinge variable system successively
Influence with lower position of articulating point to playing perpendicular speed, playing the parameters such as perpendicular stroke, stressing conditions, and then the synthesis of Erecting System is risen perpendicular
Performance carries out research test.On the basis of above-mentioned test method, load simulation system 4 is slided with a vertical frame 11 detachably to be connected
It connects, during aircraft simulation, the load by changing load simulation system 4 can be realized to different weight aircraft
Analog study, the load situation by changing load simulation system 4 can realize that the simulation to different centroid position aircraft is ground
Study carefully.In addition, guided flight vehicle launching simulation platform provided by the invention can also be used to test different main Erecting Systems 6 to rising
The influence of perpendicular process, for example, different Erecting organs (twin-tub rise perpendicular, three cylinders rise perpendicular, two-tank method rise it is perpendicular) different Erecting Systems, no
With quick Erecting System of hybrid power etc..
Guided flight vehicle launching simulation platform provided by the invention, for different weight or volume guided flight vehicle without
Different test platforms need to be built, it is at low cost and efficient, it disclosure satisfy that the requirement of guided flight vehicle launching simulation, Neng Gouwei
The Project R&D of guided flight vehicle provides reliable guarantee.
The excessive overstocked hinge of setting will certainly influence the support performance of vertical frame 11 on playing vertical frame 11, as shown in Fig. 2,
In order to preferably prove rise perpendicular performance of the hinge variable system 5 to Erecting System, slide unit may include sliding rail, clamping mechanism and more
A sliding block, sliding block are corresponded with upper hinge；Upper hinge is fixedly connected with a slide block, and sliding rail is fixedly connected with vertical frame 11 is played, sliding block
It is slidably connected on sliding rail and with sliding rail；Clamping mechanism includes multiple fixture blocks, card slot and snib；Fixture block be located at sliding block side and
It is fixedly connected with a slide block, card slot is located at sliding rail side and on sliding rail, and snib is connected to by card slot on fixture block；Card slot and card
Stops is located at homonymy and stop block slides in card slot.
Illustratively, five pieces of sliding blocks are equipped at equal intervals on the sliding rail for playing vertical frame 11, are equipped with the on five sliding blocks successively
Hinge on one, hinge on second, hinge in third, hinge, five sliding blocks are equipped with respective sliding on hinge and the 5th on the 4th
Section, hinge can be slided to hinge on the 5th in respectively sliding section on first, meanwhile, on the sliding rail in sliding section
Equipped with clamping mechanism, sliding block is blocked by clamping mechanism and is fixed on sliding rail；Under on vehicle frame corresponding with vertical frame 11 is played 1
Hinge is followed successively by hinge, four times hinges and the five times hinges under first time hinge, second time hinge, third；When test is different
When influence of the position of articulating point to main Erecting System 6, it is divided into different situations：The first situation is：One end of main Erecting System 6 with
First time hinge is hinged, and the other end is hinged successively with hinge on hinge on first to the 5th respectively, is slided when needing to measure above hinge
When moving some position of articulating point in section, upper hinge can be slided and be fixed in respectively sliding section, need to test for example, working as
When hinge slides a certain position of articulating point in section on first, hinge slides into designated position in sliding rail on first, at this moment,
On the sliding rail of sliding block both sides, snib is screwed on the fixture block of card slot respectively, fixes the position of hinge on first, is then carried out
Erecting System plays perpendicular performance test；Situation is in second：One end of main Erecting System 6 and second time hinge are hinged, the other end
It is hinged successively with hinge on hinge on first to the 5th respectively, when needing accurate adjustment, hinge can be slided, clamping mechanism is passed through
It is fixed in test point, Erecting System is carried out to it plays perpendicular performance test；Other situations and both the above test case phase
Together, the hinged situation of Erecting System and hinge is followed successively by：Hinge is hinged under one end of main Erecting System 6 and third, the other end point
One end and the four times hinges for not carrying out hinged, main Erecting System 6 with hinge on hinge on first to the 5th are hinged, the other end point
One end and the five times hinges for not carrying out hinged, main Erecting System 6 with hinge on hinge on first to the 5th are hinged, the other end point
It is not hinged with hinge on hinge on first to the 5th；By the hinge of above five kinds of main Erecting Systems 6 be hinged situation and its
The hinge of main Erecting System in respectively sliding section is hinged situation, can find out main Erecting System 6 meet stress it is optimal or
Person stroke is minimum or the optimal test result that is combined with Erecting organ.By the way that hinge on first to the 5th is set to cunning
It on rail, and is fixed using card slot, fixture block and snib, can either ensure the support performance of vertical frame 11, meanwhile, pass through change
Hinge is perpendicular for rising for main Erecting System 6 to hinge on the 5th and first time hinge to the position of articulating point of the five times hinges on first
Performance study provides safeguard.
In order to preferably realize the perpendicular simulation process of Erecting System, while ensureing that the support of vertical frame 11 and vehicle frame 1 is made
With upper hinge can be distributed on the girder of 11 bottom center of vertical frame；Lower hinge can be distributed in 1 middle girder of vehicle frame；
Hinge under being arranged by the upper hinge of setting on the girder for playing 11 bottom center of vertical frame and in 1 middle girder of vehicle frame, has led perpendicular
6 one end of system is hinged with upper hinge, and the other end is hinged with lower hinge, and when having carried out perpendicular, Erecting System is by playing 11 bottom of vertical frame
The girder in portion center applies active force to playing vertical frame 11, plays the whole uniform force of vertical frame 11.
In view of the problem that double Erecting System synchronization onwards are erected, launching simulation platform further includes secondary Erecting System, and hinge is variable
System 5 further includes multiple upside hinges and multiple downside hinges, and upside hinge has been distributed in the side of vertical frame 11, downside hinge point
Cloth is in the side of vehicle frame 1；Secondary Erecting System one end is hinged with upside hinge, and the other end is hinged with downside hinge；Along the length of vehicle frame
Direction is spent, multiple upside hinges and multiple downside hinges are located on same vertical plane.Upside hinge is respectively on the first to the 5th
Side hinge；Downside hinge is respectively the first to the 5th downside hinge；When the double Erecting System synchronization onwards of progress are perpendicular, main Erecting System
6 one end and first time hinge are hinged, and hinge is hinged on the other end and first, and secondary Erecting System one end is cut with scissors with hinge under the first side
It connects, hinge is hinged on the other end and the first side, and main Erecting System 6 and secondary Erecting System have been carried out at the same time and have erected, and record to have led and erect
The perpendicular performance parameter of system 6 and secondary Erecting System；By changing being hinged for main Erecting System 6 and upper hinge and lower hinge respectively
Position and the articulated position for changing secondary Erecting System and hinge under hinge on side and side respectively simultaneously, may be implemented to different location
Hinge carry out double Erecting System synchronization onwards respectively and erect process studies, change different Erecting Systems, Erecting System can be carried out
Synchronism and control strategy research, hybrid power quick Erecting System research etc..
In order to simulate the aircraft of different model, load simulation system 4 may include multiple clump weights；Clump weight with rise it is perpendicular
The sliding of frame 11 is detachably connected.Specifically, during aircraft simulation, due to needing aircraft model and structure to be simulated poor
Very not big, also difference is very big for the weight and centroid position of aircraft, and multiple clump weights and the quantity by adjusting clump weight is arranged
Achieve the purpose that simulate different weight aircraft；In addition, clump weight to play the connection type of vertical frame 11 be the different aircraft of realization
The key factor of simulation, the weight and centroid position of the aircraft of different weight and the aircraft of different structure are different, institute
It is also differed with the position of the quantity of the clump weight of needs and clump weight on playing vertical frame 11, clump weight is slided with vertical frame 11 is played
It is detachably connected, clump weight can be fixed to any test point position in vertical frame 11, test the aircraft of different barycenter.With
Clump weight substitutes different aircraft and carries out simulation test, and test process is not only convenient, flexible, but also is widely used, repeatability
By force.
In order to more accurately simulate different model aircraft, as shown in figure 4, above-mentioned clump weight includes 10 He of coarse adjustment clump weight
Accurate adjustment clump weight 9；Coarse adjustment clump weight 10 is detachably connected with the sliding of vertical frame 11 is played, and accurate adjustment clump weight 9 can with coarse adjustment clump weight 10
Dismantling connection；The weight of coarse adjustment clump weight 10 is more than the weight of accurate adjustment clump weight 9.Match specifically, setting clump weight to coarse adjustment
Pouring weight 10 and accurate adjustment clump weight 9, and the weight of coarse adjustment clump weight 10 is more than the weight of accurate adjustment clump weight 9, with coarse adjustment clump weight 10
Lock the weight range of aircraft；The accurate weight that aircraft is determined with accurate adjustment clump weight 9, by adjusting 10 He of coarse adjustment clump weight
The quantity of accurate adjustment clump weight 9 achievees the purpose that simulate different weight aircraft；In addition, accurate adjustment clump weight 9 is located at coarse adjustment clump weight
It is detachably connected on 10 and with coarse adjustment clump weight 10, in this way, can by adjusting the whole centroid position of multiple coarse adjustment clump weights 10
It, can be with by adjusting centroid position of the multiple accurate adjustment clump weights 9 on coarse adjustment clump weight 10 to lock the barycenter range of aircraft
Realize the accurate adjustment of barycenter.In addition, accurate adjustment clump weight 9 is arranged on coarse adjustment clump weight 10, without that will rise in vertical frame 11
The load area setting of load simulation system 4 is excessive, improves the structural compactness of load simulation system 4.
To realize sliding of the clump weight on playing vertical frame 11, load simulation system 4 further include slide unit pedestal, high-order slide unit and
Low level slide unit；Slide unit pedestal is fixedly connected with vertical frame 11 is played, and high-order slide unit is vertical with low level slide unit；Low level slide unit and slide unit pedestal
It is slidably connected, high-order sliding block is slidably connected with low level slide unit.
Illustratively, slide unit pedestal be fixed on the girder of vertical frame 11 and with play the parallel fixation of vertical frame 11, low level slide unit
It is fixed on slide unit pedestal, high-order slide unit is fixedly connected with low level slide unit, and the girder direction that low level slide unit plays vertical frame 11 with this is flat
Row, high-order slide unit is vertical with 11 girder direction of vertical frame is played, and clump weight is detachably connected on high-order slide unit；It is fixed in high-order sliding block
In the case of, clump weight with low level slide unit sliding, may be implemented with rise 11 girder parallel direction of vertical frame on sliding；?
In the case of low level sliding block is fixed, clump weight with high-order slide unit sliding, may be implemented with rise a 11 girder Vertical Square of vertical frame
Upward sliding；By clump weight by with play that 11 girder of vertical frame is parallel or Vertical Square upward sliding, and then realize different
Test process of the aircraft of centroid position on playing vertical frame 11, to realize load simulation system simulation different model flight
The purpose of device.
The realization method of above-mentioned high position slide unit and low level slide unit is as follows：High-order slide unit includes high-order sliding rail and high-order sliding block,
Low level slide unit includes low level sliding rail and low level sliding block；Low level sliding rail is fixedly connected with slide unit pedestal, low level sliding block and low level sliding rail
It is slidably connected；High-order sliding rail is fixedly connected with low level sliding block, and high-order sliding block is slidably connected with high-order sliding rail.Since clump weight is removable
That unloads is fixed on high-order sliding block, and when clump weight needs the adjusting position on playing 11 girder direction of vertical frame, low level sliding block is low
It is slided in the sliding rail of position and is fixed to test point position；When clump weight needs to raise section in the direction vertical with 11 girder of vertical frame is played
When setting, high-order sliding block slides in high-order sliding rail and is fixed to test point position；It is slided in low level sliding rail by low level sliding block
It is slided in high-order sliding rail with high-order sliding block, clump weight can be fixed on any test point in vertical frame 11, to clump weight
The aircraft of different centroid positions can be used for simulating.
In order to preferably control the sliding of low level sliding block and high-order sliding block, row is equipped on low level sliding rail and high-order sliding rail
Process control unit, stroke controlling unit are equipped with travel switch；High-order travel switch is opened, high-order sliding block is on high-order sliding rail
Sliding mode；High-order travel switch is closed, high-order sliding block is in stationary state on high-order sliding rail；Low level travel switch is opened, it is low
Position sliding block is in sliding mode on low level sliding rail；Low level travel switch is closed, low level sliding block is in stationary state on low level sliding rail.
When simulating some aircraft, adjusting low level sliding block makes it be slided in low level sliding rail, and adjusting high-order sliding block keeps it sliding in a high position
It is slided on rail, multiple clump weights is fixed on to the centroid position of aircraft by the high-order sliding block of adjusting and low level sliding block, at this point, needing
High-order sliding block and low level sliding block are fixed, its sliding is prevented, closes the travel switch on low level sliding rail, low level sliding block is in
Stationary state；The travel switch on high-order sliding rail is simultaneously closed off, high-order sliding block is in stationary state；Thus will be on high-order sliding block
Clump weight is fixed on the centroid position of aircraft.Stroke controlling unit is respectively set on high-order sliding rail and low level sliding rail being capable of essence
The really sliding position of control clump weight provides to accurately simulate the aircraft of different centroid positions for Project R&D work
It ensures.
In order to further improve guided flight vehicle launching simulation platform, as shown in Figure 1, vehicle frame 1 be equipped with oil supply system 7,
Walking turns to brake system 2, trailer interface；Wherein, trailer interface is located at 1 front end of vehicle frame, for being mounted with tractor；Oil sources
System 7 is located at 1 front end of vehicle frame, trailer interface rear end and is fixedly connected as welded on the car body, and the power walked for vehicle frame 1 supplies
It answers；Walking turns to brake system 2 and is located among trailer interface and oil supply system 7, for controlling walking states and direction of travel.Oil
Source system 7 includes motor, hydraulic pump, fuel tank, oil filter and control valve etc., is the important group of guided flight vehicle launching simulation platform
At part, when the launching simulation platform needs preventing test, it can power needed for effective supply analog platform, walk simultaneously
Steering can control direction of traffic, realize preventing test purpose.When guided flight vehicle launching simulation platform is needed by other
When vehicle is drawn, the analog platform is articulated on tractor by trailer interface, tractor drives analog platform to be transported
It is dynamic, when without being drawn, analog platform is unloaded down from tractor.
In order to improve the damping effect of flat pad, as shown in Figure 1, the guided flight vehicle launching simulation platform further includes hanging
Extension system 3, which is mainly made of hydro-pneumatic spring, as shown in figure 3, suspension arrangement includes：Hydro-pneumatic spring bearing, oil gas
Spring, upper swing arm and lower swing arm, hydro-pneumatic spring are made of wherein gas chamber and hydraulic cylinder, and hydro-pneumatic spring bearing is used to support oil gas bullet
Spring adjusts the height of hydro-pneumatic spring by the main oil pocket fuel feeding of down journal to hydro-pneumatic spring, meets vehicle attitude control and is wanted with what is be turned up
It asks.Different hydro-pneumatic spring parameters can be verified to car launcher damping effect in different road surface walks by detecting, and found most
Excellent parameter.
In order to cope with different work condition environments, as shown in Figure 1, the guided flight vehicle Launching Simulation System further includes leveling system
System 8, the leveling system 8 include mainly leveling cyclinder.As shown in Figure 1, interface is installed in leveling at car body reserved six, it can be used at 4 points
Or 6 leveling, interface form are flanged joint；The present invention uses four leg supporting leg leveling, four supporting leg leveling that can both move simultaneously
Make, and can be with single movement, in order to cope with different work condition environments.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.
Claims (10)
1. a kind of guided flight vehicle launching simulation platform, which is characterized in that including：Hinge variable system, load simulation system, master
Erecting System plays vertical frame and vehicle frame, and the hinge variable system includes multiple upper hinges and multiple lower hinges；
The turning end of described vertical frame is hinged with vehicle frame；
One end of the main Erecting System is hinged by upper hinge with vertical frame is played, and the other end is hinged by lower hinge and vehicle frame；
The load simulation system is detachably connected with vertical frame sliding is played；
Along the length direction of vehicle frame, multiple upper hinges are located at multiple lower hinges on same vertical plane.
2. guided flight vehicle launching simulation platform according to claim 1, which is characterized in that the launching simulation platform is also
Including sliding rail, clamping mechanism and multiple sliding blocks, the sliding block is corresponded with upper hinge；
The upper hinge is fixedly connected with a slide block, and the sliding rail is fixedly connected with vertical frame is played, and sliding block is located on sliding rail and and sliding rail
It is slidably connected；
The clamping mechanism includes stop block, fastening groove and locking bolt；
The stop block is located at sliding block side and is fixedly connected with a slide block, and fastening groove is located on sliding rail, and locking bolt passes through fastening groove
It is detachably connected with stop block.
3. guided flight vehicle launching simulation platform according to claim 1, which is characterized in that the upper hinge has been distributed in
On the girder of vertical frame bottom center；The lower hinge is distributed on central frame beam girder.
4. guided flight vehicle launching simulation platform according to claim 3, which is characterized in that the launching simulation platform is also
Including secondary Erecting System, the hinge variable system further includes multiple upside hinges and multiple downside hinges, the distribution of upside hinge
In the side for playing vertical frame, downside hinge is distributed in the side of vehicle frame；
Described pair Erecting System one end is hinged with upside hinge, and the other end is hinged with downside hinge；
Along the length direction of vehicle frame, multiple upside hinges and multiple downside hinges are located on same vertical plane.
5. guided flight vehicle launching simulation platform according to claim 1, which is characterized in that the load simulation system packet
Include multiple clump weights；The clump weight is detachably connected with vertical frame sliding is played.
6. guided flight vehicle launching simulation platform according to claim 5, which is characterized in that the clump weight includes coarse adjustment
Clump weight and accurate adjustment clump weight；
The coarse adjustment clump weight is detachably connected with vertical frame sliding is played, and the accurate adjustment clump weight and the sliding of coarse adjustment clump weight are detachable
Connection；
The weight of the coarse adjustment clump weight is more than the weight of accurate adjustment clump weight.
7. guided flight vehicle launching simulation platform according to claim 5, which is characterized in that the load simulation system is also
Including slide unit pedestal, high-order slide unit and low level slide unit；
The slide unit pedestal is fixedly connected with vertical frame is played, and the high position slide unit is vertical with low level slide unit；
The low level slide unit is slidably connected with slide unit pedestal, and the high position sliding block is slidably connected with low level slide unit.
8. guided flight vehicle launching simulation platform according to claim 7, which is characterized in that the high position slide unit includes height
Position sliding rail and high-order sliding block, the low level slide unit includes low level sliding rail and low level sliding block；
The low level sliding rail is fixedly connected with slide unit pedestal, and the low level sliding block is slidably connected with low level sliding rail；
The high position sliding rail is fixedly connected with low level sliding block, and the high position sliding block is slidably connected with high-order sliding rail.
9. guided flight vehicle launching simulation platform according to claim 8, which is characterized in that the low level sliding rail and a high position
Stroke controlling unit is equipped on sliding rail, the stroke controlling unit is equipped with travel switch；
High-order travel switch is opened, high-order sliding block is in sliding mode on high-order sliding rail, closes high-order travel switch, high-order sliding block
It is in stationary state in high-order sliding rail.
Low level travel switch is opened, low level sliding block is in sliding mode on low level sliding rail, closes low level travel switch, low level sliding block
It is in stationary state on low level sliding rail.
10. according to the guided flight vehicle launching simulation platform described in claim 1 to 9, which is characterized in that the vehicle frame is equipped with
Oil supply system, walking turn to brake system and trailer interface；
The trailer interface is fixed on vehicle frame front end；
The oil supply system is located at trailer interface rear end and is fixedly connected with vehicle frame；
The walking turns to brake system and is fixedly connected between trailer interface and oil supply system, and with vehicle frame.
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| CN201810400259.3A CN108725838B (en) | 2018-04-28 | 2018-04-28 | System leads aircraft transmission simulation platform |
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| CN201810400259.3A CN108725838B (en) | 2018-04-28 | 2018-04-28 | System leads aircraft transmission simulation platform |
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| CN108725838B CN108725838B (en) | 2020-06-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115655004A (en) * | 2022-09-30 | 2023-01-31 | 北京理工大学 | Device and method for erecting movable lower support point |
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