CN107462115A - A kind of guided missile simulation emission test system - Google Patents
A kind of guided missile simulation emission test system Download PDFInfo
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- CN107462115A CN107462115A CN201710658247.6A CN201710658247A CN107462115A CN 107462115 A CN107462115 A CN 107462115A CN 201710658247 A CN201710658247 A CN 201710658247A CN 107462115 A CN107462115 A CN 107462115A
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- China
- Prior art keywords
- guided missile
- hydraulic actuator
- missile simulation
- test system
- compression spring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
- F42B35/02—Gauging, sorting, trimming or shortening cartridges or missiles
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a kind of guided missile simulation emission test system, including the fixed mount and base frame that transverse horizontal is placed；The right upper portion of the fixed mount is fixedly installed a hydraulic actuator, and the expansion link of the hydraulic actuator bottom is connected with a force snesor, and the bottom of the force snesor is connected with a quick release hook；The left side central portion of the fixed mount is fixedly installed a compression spring；The quick release hook is connected by a pulling force rope with the left part of the compression spring；It is fixedly installed a hollow launching tube simulating piece directly over the base frame, the left end opening of the launching tube simulating piece and is connected inserted with a guided missile simulation part, the left end of guided missile simulation part by pull rope with the left part of the compression spring.The present invention is simple in construction, easy to operate, can safe and reliable emitting performance of the detection guided missile in its supporting launch canister, the test period is short, and cost is low, is adapted to wide popularization and application.
Description
Technical field
The present invention relates to missile performance checking test technical field, more particularly to a kind of guided missile simulation emission test system
System.
Background technology
At present, supporting led at it, it is necessary to be tested using formal live ammunition to detect guided missile under normal conditions
Service behaviour when launching in launching tube is played, wherein needing to test different size of thrust of the guided missile in missile propulsive plant
Under, speed when being flown out from the emission port of launch canister.
Tested for formal live ammunition, before the test, it is necessary to give missile propulsive plant fuel investment, in emission process,
Fuel combustion in missile propulsive plant and be converted into kinetic energy, so as to promote guided missile complete transmitting action.In view of the live ammunition is tested
Belong to priming system experiment (priming system is equipped with gunpowder or explosive, after by environmental stimuli produce burning or blast, with the gunpowder that ignites,
Ignition charge does the disposable component of mechanical work and the general name of device), therefore, exist in implementation process larger
Danger, and the reasonability and reliability that guided missile and its supporting transmitting barrel structure are constantly verified by test of many times are needed,
The cycle length of test arrangement, test number (TN) is more, and the cost of test of many times is high, while also needs in specific test site ability
Implement, therefore, it is impossible to detect emitting performance of the guided missile in its supporting launching tube safe, reliable, efficiently.
Therefore, at present there is an urgent need to develop a kind of technology, it can with safe, reliable, efficient detect guided missile in its institute
Emitting performance in supporting launching tube, the test period is short, and experimentation cost is low, is adapted to widely popularization and application.
The content of the invention
In view of this, it is an object of the invention to provide a kind of guided missile simulation emission test system, its is simple in construction, operation side
Just, operated by the transmitting of simulated missile, can with safe, reliable, efficient detect guided missile in its supporting launch canister
In emitting performance, the test period is short, and experimentation cost is low, be adapted to widely popularization and application, be of great practical significance.
Therefore, the invention provides a kind of guided missile simulation emission test system, including the fixed mount placed of transverse horizontal and
Base frame；
The right upper portion of the fixed mount is fixedly installed a hydraulic actuator, and the hydraulic actuator bottom is stretched
Bar is connected with a force snesor, and the bottom of the force snesor is connected with a quick release hook；
The left side central portion of the fixed mount is fixedly installed a compression spring；
The quick release hook is connected by a pulling force rope with the left part of the compression spring；
A hollow launching tube simulating piece, the launching tube simulating piece are fixedly installed directly over the base frame
Left end opening and pass through pull rope and the compression spring inserted with a guided missile simulation part, the left end of the guided missile simulation part
Left part be connected.
Wherein, the left side central portion of the fixed mount is fixedly installed the hollow guiding pipe of a cross direction profiles, described hollow
It is oriented to pipe outer wall and is cased with the compression spring, the left end of the compression spring protrudes from the left end of the hollow guiding pipe.
Wherein, the quick release hook is connected with one end of the pulling force rope, and the other end of the pulling force rope runs through institute
The left part for stating compression spring described in hollow guiding Guan Houyu is connected.
Wherein, the right side central of the fixed mount is fixedly installed a fixed pulley, and the pulling force rope is slided calmly through described
Left part after wheel with the compression spring is connected.
Wherein, the center line of the launching tube simulating piece overlaps with the center line of the compression spring.
Wherein, the left and right ends of the launching tube simulating piece pass through a hoop bracket and the base frame top surface respectively
It is fixed together.
Wherein, also horizontally disposed on the position between the fixed mount and base frame to have foam-rubber cushion, the pull rope passes through
Wear the foam-rubber cushion.
Wherein, two pairs of optoelectronic switch sensors that left and right is spaced apart, each pair institute are additionally provided with the top of the base frame
State the left side that the launching tube simulating piece is symmetrically distributed in before and after optoelectronic switch sensor；
Each optoelectronic switch sensor is connected with same data collecting instrument.
Wherein, it is additionally provided with multiple tachogenerators at the top of the base frame, it is right before and after the multiple tachogenerator
Claim the left side for being distributed in the launching tube simulating piece.
Wherein, in addition to a control unit, described control unit are connected with a data collecting instrument；
The data collecting instrument, is connected with force snesor, and acquisition is detected for gathering the force snesor in real time
The value of thrust that the hydraulic actuator is exported, is then sent to described control unit；
Described control unit, be connected with the hydraulic actuator, for control the hydraulic actuator incrementally increase to
The pulling force of outer output, and the value of thrust that the hydraulic actuator that the data collecting instrument is sent is exported is received, and by described in
Value of thrust that the value of thrust that hydraulic actuator is exported is exported compared with default value of thrust, when the hydraulic actuator or
When person is equal to default value of thrust, the hydraulic actuator is controlled to keep pulling force output size constant.
The technical scheme provided by the invention more than, compared with prior art, the present invention proposes a kind of guided missile
Analog transmissions pilot system, its is simple in construction, easy to operate, is operated by the transmitting of simulated missile, can be with safe and reliable, high
Emitting performance of the detection guided missile in effect ground in its supporting launch canister, the test period is short, and experimentation cost is low, is adapted to extensive
Ground popularization and application, are of great practical significance.
For guided missile simulation emission test system provided by the invention, it reliably simulation test guided missile can send out in guided missile
Under the different size of thrust of motivation, speed when being flown out from the emission port of launch canister.
For guided missile simulation emission test system provided by the invention, it, can be by guided missile simulation by setting foam-rubber cushion
The kinetic energy absorption of part, protection and recovery to guided missile simulation part are realized, avoids guided missile simulation part from being damaged.
Brief description of the drawings
Fig. 1 is a kind of dimensional structure diagram of guided missile simulation emission test system provided by the invention；
Fig. 2 is a kind of front view of guided missile simulation emission test system provided by the invention；
Fig. 3 is a kind of top view of guided missile simulation emission test system provided by the invention；
Fig. 4 is the data acquisition in a kind of guided missile simulation emission test system provided by the invention in one embodiment
Instrument gathers the principle schematic of simultaneously step voltage signal caused by two pairs of optoelectronic switch sensors of real-time display；
In figure, 1 is compression spring, and 2 be fixed mount, and 3 be hydraulic actuator, and 4 be force snesor, and 5 be quick release hook, 6
For pulling force rope, 7 be fixed pulley, and 8 be foam-rubber cushion, and 9 be pull rope, and 10 be optoelectronic switch sensor, and 11 be launching tube simulating piece, 12
For hoop bracket, stand based on 13,14 be hollow guiding pipe.
Embodiment
In order that those skilled in the art more fully understand the present invention program, below in conjunction with the accompanying drawings with embodiment to this
Invention is described in further detail.
Referring to Fig. 1 to Fig. 3, a kind of guided missile simulation emission test system provided by the invention, for the transmitting of simulated missile,
The detection of the emitting performance to guided missile in its supporting launching tube is realized, specifically includes the fixed mount 2 of transverse horizontal placement
With base frame 13, the fixed mount 2 is located at the left side of the base frame 13；
The right upper portion of the fixed mount 2 is fixedly installed a hydraulic actuator 3, the bottom of hydraulic actuator 3
Expansion link is connected with a force snesor 4, and the bottom of the force snesor 4 is connected with a quick release hook 5；
The left side central portion of the fixed mount 2 is fixedly installed a compression spring 1, and concrete structure is：The fixed mount 2
Left side central portion is fixedly installed the hollow guiding pipe 14 of a cross direction profiles, and the outer wall of hollow guiding pipe 14 is cased with the compression
Spring 1, the left end of the compression spring 1 protrude from the left end of the hollow guiding pipe 14；It is it should be noted that hollow by this
Guide pipe 14, it can prevent compression spring 1 from destabilization problems occurring in compression process, to the compressive deformation process of compression spring 1
It is oriented to.
The quick release hook 5 is connected by a pulling force rope 6 with the left part of the compression spring 1, is specially：Institute
One end that quick release hook 5 is stated with the pulling force rope 6 is connected, and the other end of the pulling force rope 6 runs through the hollow guiding pipe
Left part after 14 with the compression spring 1 is connected；
The surface of the base frame 13 is fixedly installed a hollow launching tube simulating piece 11, the transmitting cylinder mould
Intend the left end opening of part 11 and (be specially inserted with a guided missile simulation part：The guided missile simulation part and the launching tube simulating piece
The right side wall of the inner chamber of 11 cross direction profiles having is in contact), the left end (i.e. head) of the guided missile simulation part is led by one
Messenger 9 is connected with the left part of the compression spring 1.
In the present invention, it is necessary to illustrate, the shape of actual missile of the guided missile simulation part with needing simulated test,
Size, weight are corresponding to the same, and especially gravity centre distribution is also consistent.The launching tube simulating piece 11 is with needing simulated test
Shape, the size of actual missile launching tube are corresponding to the same, especially need and the shape of the inner chamber of actual missile launching tube, big
It is small corresponding to the same.
In the present invention, in specific implementation, the center line of the launching tube simulating piece 11 and the center of the compression spring 1
Line overlaps.
In the present invention, in specific implementation, in order to allow the launching tube simulating piece 11 to be fixed on the base frame 13
Surface, the left and right ends of the launching tube simulating piece 11 pass through a hoop bracket 12 and the top surface of base frame 13 respectively
It is fixed together.
In the present invention, in specific implementation, the right side central of the fixed mount 2 is fixedly installed a fixed pulley 7, described
Pulling force rope 6 is connected after passing through the fixed pulley 7 with the left part of the compression spring 1.Therefore, the fixed pulley 7 is used to change
Become the direction for the pulling force that the hydraulic actuator 3 exports so that the pulling force effect direction and the compression that hydraulic actuator 3 exports
The compression direction of spring 1 is vertical, while ensures that value of thrust is constant.
It should be noted that in specific implementation, an annular guiding groove is distributed with the surrounding outer wall of fixed pulley 7,
The pulling force rope 6 passes through the guiding groove.
In the present invention, it is also horizontally disposed on the position between the fixed mount 2 and base frame 13 to have in specific implementation
Foam-rubber cushion 8, the pull rope 9 run through the foam-rubber cushion 8.
In the present invention, it is necessary to which explanation, coordinates, specifically between the foam-rubber cushion 8 and the pull rope 9 for gap
For：With being provided with through hole on the opposite position of pull rope 9 on the foam-rubber cushion 8, shape, the size of the through hole are more than described lead
Shape, the size of messenger 9.
In the present invention, in specific implementation, the top of base frame 13 is additionally provided with two pairs of light that left and right is spaced apart
Electric switch sensor 10, a left side for the launching tube simulating piece 11 is symmetrically distributed in before and after optoelectronic switch sensor 10 described in each pair
Side.
The optoelectronic switch sensor 10, the emission port for measuring guided missile simulation part from the left end of launching tube simulating piece 11 fly
Speed when going out.
In specific implementation, each optoelectronic switch sensor 10 is connected with same data collecting instrument, the data
Acquisition Instrument is used to gather and step voltage signal caused by optoelectronic switch sensor described in real-time display.Therefore, user can root
According to the step voltage signal, the muzzle velocity for obtaining guided missile simulation part is directly calculated.
It should be noted that the step voltage signal refers to that at a time, magnitude of voltage is undergone mutation, jumped by a value
Change to the voltage signal that another value is formed.Under normal conditions, the level that each optoelectronic switch sensor 10 is exported is
Low level (be specially 0V), when guided missile simulation part sent from launching tube simulating piece 11 and during by optoelectronic switch sensor 10,
Optoelectronic switch sensor 10 can export a high level (being, for example, 6V) moment, so as to form step voltage signal.
It is shown in Figure 4, in specific experiment, measurement in advance obtain the top of base frame 13 laterally between left and right every and
The distance between front and rear two pairs of symmetrical optoelectronic switch sensors 10 S, when in simulated test, guided missile simulation part successively flies
Two pairs of optoelectronic switch sensors 10 are crossed, are correspondingly formed two pairs of step voltage signals and the real-time display on data collecting instrument, such as Fig. 4
First pair of shown step voltage signal (i.e. step voltage signal 1) and second pair of step voltage signal (i.e. step voltage signal
2), the time point of high level is respectively t1 and t2 in two pairs of step voltage signals, thus, it is possible to obtain guided missile simulation part successively flies
The time difference Δ t (difference for subtracting t1 equal to t2) of two groups of optoelectronic switch sensors 10 is crossed, then further according to speed calculation formula v=S/
Δ t, you can be calculated the average speed that guided missile simulation part flies over two pairs of optoelectronic switch sensors 10, i.e. guided missile simulation part
Muzzle velocity.
It should be noted that the optoelectronic switch sensor 10 is not limited to four shown in Fig. 1, according to the needs of user,
It can also be any number of.In addition, the optoelectronic switch sensor 10 could alternatively be other, any one can measure guided missile
The part that tests the speed of speed when the emission port of simulating piece from the left end of launching tube simulating piece 11 flies out, such as can be multiple sensings that test the speed
Device, the left side of the launching tube simulating piece 11, at this time, data collecting instrument are symmetrically distributed in before and after the multiple tachogenerator
Directly the velocity amplitude when emission port of guided missile simulation part from the left end of launching tube simulating piece 11 flies out can be obtained from tachogenerator.
In the present invention, in order to drive hydraulic actuator 3, stable kinetic energy is provided for hydraulic actuator 2, for this hair
Bright, the hydraulic actuator 3 is connected with a hydraulic power source (such as hydraulic power unit).Wherein, the hydraulic power source is used to provide surely
Fixed pressure and flow, and output hydraulic pressure energy；Hydraulic energy from hydraulic power source can be converted to machinery by the hydraulic actuator 2
Can, and outwards export pulling force.
In specific implementation, the hydraulic power source is preferably hydraulic power unit, and hydraulic power unit, as medium, is for institute using hydraulic oil
The hydraulic power source that hydraulic actuator 3 provides stable pressure and flow is stated, maximum 50kN pulling force can be provided at.
It should be noted that in the present invention, the hydraulic actuator 3, for being provided out pulling force, specially to outside
The pulling force rope 6 and compression spring 1 being connected provide pulling force；
The force snesor 4, the value of thrust outwards exported for measuring the hydraulic actuator 3 that is, can be to pulling force rope 6
And the value of thrust that the compression spring 1 connected applies；
The quick release hook 5, under control of the user, pulling force rope 6 quickly to be departed from the quick release hook 5
Connection, so as to by the elastic potential energy abrupt release of the compression spring after compression；It should be noted that for the quick release hook
5, it includes safety pin and unhook, before release, has the anti-locking hook of safety pin to disengage, (i.e. power passes when disengagement is required
When the value of thrust that the detection of sensor 4 obtains is equal to the default value of thrust of user), user first pulls out safety pin, pulls and breaks off relations, you can
Quick release hook is opened with moment, so as to realize the function of abrupt release.
The pulling force rope 6, for directly transmitting the pulling force that outwards exports of hydraulic actuator 3 to compression spring 1；
The compression spring 1, under the external pull for being applied in the hydraulic actuator 3 acts on, form compression and become
Shape, and elastic potential energy is produced by compression, during release, acted on by the transmission of pull rope 9, can be by elastic potential
The kinetic energy for the guided missile simulation part that can be converted into launching tube simulating piece 11；
The pull rope 9, for the kinetic energy for being converted the elastic potential energy of 1 abrupt release of compression spring, real-time delivery
To the guided missile simulation part inserted in the launching tube simulating piece 11, so that guided missile simulation part can be from the launching tube
The moment of simulating piece 11 emits；
The foam-rubber cushion 8, for after guided missile simulation part can emit from the moment of launching tube simulating piece 11, leading to
The buffering metamorphosis of sponge after an impact is crossed, the kinetic energy absorption of guided missile simulation part can be realized the guarantor to guided missile simulation part
Shield and recovery, avoid guided missile simulation part from being damaged.It should be noted that the height of the foam-rubber cushion 8 is higher than the guided missile mould
Intend the height of part.
It should also be noted that, for the present invention, the pulling force that can be applied by hydraulic actuator 3 to compression spring 1, and
Acted on by the energy transmission of pull rope 9, the pulling force effect for compressing actuator 3 and effect can be ultimately transferred to the transmitting
Cylinder simulating piece 11 in guided missile simulation part, to guided missile simulation part formed moment pulling force, then real-time testing guided missile simulation part from
The speed when emission port of the left end of launching tube simulating piece 11 flies out.Therefore, the present invention can simulate actual missile and truly lead
Emitting performance corresponding under the different size thrust of engine, that is, simulated missile are played in its supporting guided missile hair
Emitting performance in shooting cylinder, and the speed when emission port of simulation test guided missile from launch canister left end flies out.
In the present invention, in specific implementation, guided missile simulation emission test system provided by the invention also includes a control
Unit, described control unit are connected with a data collecting instrument；
The data collecting instrument, it is connected with force snesor 4, acquisition is detected for gathering the force snesor 4 in real time
The value of thrust that is exported of the hydraulic actuator 3, be then sent to described control unit；
Described control unit, it is connected with the hydraulic actuator 3, for controlling the hydraulic actuator 3 to incrementally increase
The pulling force (such as since output pulling force size is 0N, controlling the stroke of hydraulic actuator) outwards exported, and receive the number
The value of thrust that the hydraulic actuator 3 sent according to Acquisition Instrument is exported, and the value of thrust that the hydraulic actuator 3 is exported
Compared with default value of thrust, when the value of thrust that the hydraulic actuator 3 is exported or during equal to default value of thrust, control
The hydraulic actuator 3 keeps pulling force output size constant, no longer increases pulling force.Therefore, the present invention is by control unit, and ties
The effect of sensor 4 with joint efforts, it is possible to achieve the accurate control of the value of thrust exported to the hydraulic actuator 3.
In specific implementation, when the value of thrust that the hydraulic actuator 3 is exported reaches default value of thrust, pressure can be discharged
Contracting spring 1 so that guided missile simulation part moment flies out from launching tube simulating piece 11.
It should be noted that the default value of thrust can be configured in advance according to the needs of user, it is particularly preferred as
The thrust size formed equal to actual missile engine, therefore, the present invention can meet the actual missile engine of different thrusts
Analog transmissions demand.
For guided missile simulation emission test system provided by the invention, its specific installation and debugging and verification process can
To comprise the following steps：
1st, compression spring 1, hydraulic actuator 3 and fixed pulley 7 are arranged on fixed mount 2, force snesor 4 is arranged on hydraulic pressure
The telescopic rod end of the bottom of actuator 3, quick release hook 5 are connected to the lower section of force snesor 4；
2nd, optoelectronic switch sensor 10 and hoop bracket 12 are arranged on base frame 13, then by launching tube simulating piece
11 are placed in hoop bracket 12, adjust the position of the left end opening (i.e. guided missile simulation part exports) of launching tube simulating piece, make light
Electric switch sensor 10 is located at the exit of launching tube simulating piece 11, is advisable with not blocking the light of optoelectronic switch sensor, so
Launching tube simulating piece 11 is fixed afterwards；
3rd, foam-rubber cushion 8 is placed between base frame 13 and fixed mount 2, then will traction close to the side of fixed mount 2
One end of rope 9 is connected with the movable end (i.e. left end) of compression spring 1, and the other end is connected with the head of guided missile simulation part 11, simultaneously
Make pull rope 9 through the through hole on foam-rubber cushion 8；
4th, fixed mount 2, the relative position of base frame 13 are adjusted, makes the center line and compression spring of launching tube simulating piece 11
1 center line overlaps, and when pull rope 9 is in exceptionally straight state, guided missile simulation part is close to the inner chamber of launching tube simulating piece 11
Tail end；
5th, after the relative position of fixed mount 2, base frame 13 determines, two-part structure is fixed on foundation platform；
Then the movable end (i.e. left end) of compression spring 1 is connected with the release end of quick release hook 5 using pulling force rope 6, pulling force should be made
Rope 6 passes through fixed pulley 7, and is located in the guiding groove of fixed pulley 7, and the pulling force rope 6 connected, which should try one's best, is in tensioned state, keeps away
Exempt from the loss of travel of hydraulic actuator 3；
6th, force snesor 4 and optoelectronic switch sensor 10 are connected with data collecting instrument, whether detection signal is normal；
7th, hydraulic power unit is opened, adjusts the pressure of hydraulic power unit；
8th, turn-on data Acquisition Instrument, the pulling force of the output of force snesor 4 and the signal of optoelectronic switch sensor are monitored in real time；
9th, pulling force is slowly exported using control unit control hydraulic actuator 3, until reaching to the pulling force of compression spring 1
Untill default value of thrust F；
10th, the position of guided missile simulation part is adjusted, guided missile simulation part is located at the inner chamber tail end of launching tube simulating piece, makes simultaneously
Pull rope 9 is in tension；
11st, the safety pin on quick release hook 5 is pulled out, then opens release hook, makes the abrupt release of pulling force rope 6, simultaneously
The moment of compression spring 1 ejects, and pulls guided missile simulation part to be moved in launching tube simulating piece 11；
12nd, when guided missile simulation part passes through optoelectronic switch sensor 10, step voltage signal is produced, can be in data collecting instrument
Upper real-time display, by the step signal, time of the guided missile simulation part by specific length is obtained, calculates and obtains guided missile simulation part
Muzzle velocity.
Understood based on above-mentioned technical proposal, for guided missile simulation emission test system provided by the invention, with prior art
Compare, have the following advantages：
1st, the present invention simulates the transmitting scene of actual missile by the use of mechanical driver unit as the power source of emission test,
Compared to the priming system test method of routine, this method will not be limited by test site, can effectively reduce experiment
Cost, shorten the test period, while also improve the security of experiment；
2nd, the optoelectronic switch sensor that the present invention uses has high sensitivity, fast response time (response time is less than 1ms)
The advantages that, the measurement of relative broad range emission rate can be achieved, the structure of the guided missile simulation part under different tests requirement can be met
The quantitative appraisal of performance；
3rd, the present invention can be adapted to by changing compression spring, hydraulic actuator and the launching tube simulating piece of different size
Different quality, different bores, different emission rates guided missile simulation test demand；
4th, use fixed pulley in the present invention, can be by the action direction and compression spring of the pulling force of hydraulic actuator output
Compression direction is mutually perpendicular to, and so as to be advantageous to the release movement of quick release hook, it also avoid the transmitting production to guided missile simulation part
Raw interference；
5th, the present invention is come the launching tube simulating piece that is fixedly clamped by two hoop brackets, therefore, is adapted to different straight
The installation of the launching tube simulating piece in footpath is fixed, and has good versatility.
In summary, compared with prior art, a kind of guided missile simulation emission test system provided by the invention, its structure
Simply, it is easy to operate, operated by the transmitting of simulated missile, it is supporting at it can with safe, reliable, efficient to detect guided missile
Emitting performance in launch canister, the test period is short, and experimentation cost is low, is adapted to widely popularization and application, has great life
Produce practice significance.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of guided missile simulation emission test system, it is characterised in that the fixed mount (2) and basic platform placed including transverse horizontal
Frame (13)；
The right upper portion of the fixed mount (2) is fixedly installed a hydraulic actuator (3), hydraulic actuator (3) bottom
Expansion link be connected with a force snesor (4), the bottom of the force snesor (4) is connected with a quick release hook (5)
Connect；
The left side central portion of the fixed mount (2) is fixedly installed a compression spring (1)；
The quick release hook (5) is connected by a pulling force rope (6) with the left part of the compression spring (1)；
A hollow launching tube simulating piece (11), the transmitting cylinder mould are fixedly installed directly over the base frame (13)
Intend the left end opening of part (11) and inserted with a guided missile simulation part, the left end of the guided missile simulation part by pull rope (9) with
The left part of the compression spring (1) is connected.
2. guided missile simulation emission test system as claimed in claim 1, it is characterised in that in the left side of the fixed mount (2)
Portion is fixedly installed the hollow support pipe (14) of a cross direction profiles, and hollow guiding pipe (14) outer wall is cased with the compression bullet
Spring (1), the left end of the compression spring (1) protrude from the left end of the hollow guiding pipe (14).
3. guided missile simulation emission test system as claimed in claim 1, it is characterised in that the quick release hook (5) and institute
The one end for stating pulling force rope (6) is connected, the other end of the pulling force rope (6) through the hollow guiding pipe (14) afterwards with the pressure
The left part of contracting spring (1) is connected.
4. guided missile simulation emission test system as claimed in claim 1, it is characterised in that in the right side of the fixed mount (2)
Portion is fixedly installed a fixed pulley (7), the pulling force rope (6) through the fixed pulley (7) afterwards with the compression spring (1)
Left part is connected.
5. guided missile simulation emission test system as claimed in claim 1, it is characterised in that the launching tube simulating piece (11)
Center line overlaps with the center line of the compression spring (1).
6. guided missile simulation emission test system as claimed in claim 1, it is characterised in that the launching tube simulating piece (11)
Left and right ends are fixed together by a hoop bracket (12) and the base frame (13) top surface respectively.
7. the guided missile simulation emission test system as any one of claim 1 to 6, it is characterised in that the fixed mount
(2) also horizontally disposed on the position between base frame (13) to have foam-rubber cushion (8), the pull rope (9) runs through the sponge
Pad (8).
8. the guided missile simulation emission test system as any one of claim 1 to 6, it is characterised in that the basic platform
Two pairs of optoelectronic switch sensors (10) that left and right is spaced apart, optoelectronic switch sensor described in each pair are additionally provided with the top of frame (13)
(10) the front and rear left side for being symmetrically distributed in the launching tube simulating piece (11)；
Each optoelectronic switch sensor (10) is connected with same data collecting instrument.
9. the guided missile simulation emission test system as any one of claim 1 to 6, it is characterised in that the basic platform
Multiple tachogenerators are additionally provided with the top of frame (13), the transmitting cylinder mould is symmetrically distributed in before and after the multiple tachogenerator
Intend the left side of part (11).
10. the guided missile simulation emission test system as any one of claim 1 to 6, it is characterised in that also including one
Control unit, described control unit are connected with a data collecting instrument；
The data collecting instrument, it is connected with force snesor (4), acquisition is detected for gathering the force snesor (4) in real time
The value of thrust that is exported of the hydraulic actuator (3), be then sent to described control unit；
Described control unit, it is connected with the hydraulic actuator (3), for controlling the hydraulic actuator (3) to incrementally increase
The pulling force outwards exported, and the value of thrust that the hydraulic actuator (3) that the data collecting instrument is sent is exported is received, and will
The value of thrust that the hydraulic actuator (3) is exported is compared with default value of thrust, when the hydraulic actuator (3) is exported
Value of thrust or during equal to default value of thrust, control the hydraulic actuator (3) to keep pulling force output size constant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710658247.6A CN107462115A (en) | 2017-08-04 | 2017-08-04 | A kind of guided missile simulation emission test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710658247.6A CN107462115A (en) | 2017-08-04 | 2017-08-04 | A kind of guided missile simulation emission test system |
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| Publication Number | Publication Date |
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| CN107462115A true CN107462115A (en) | 2017-12-12 |
Family
ID=60548510
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| CN201710658247.6A Pending CN107462115A (en) | 2017-08-04 | 2017-08-04 | A kind of guided missile simulation emission test system |
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| CN108413807A (en) * | 2018-05-04 | 2018-08-17 | 山西华洋吉禄科技股份有限公司 | A kind of simulated missile is quickly from the device in cabin |
| CN109029873A (en) * | 2018-05-02 | 2018-12-18 | 成都润博科技有限公司 | Vehicle, airborne 140 caliber missile propulsive plant device for detecting water pressure |
| CN114894358A (en) * | 2022-03-31 | 2022-08-12 | 中国人民解放军国防科技大学 | Recoil indirect testing device and testing method |
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| CN109029873A (en) * | 2018-05-02 | 2018-12-18 | 成都润博科技有限公司 | Vehicle, airborne 140 caliber missile propulsive plant device for detecting water pressure |
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