CN207365824U - A kind of guided missile simulation emission test system - Google Patents
A kind of guided missile simulation emission test system Download PDFInfo
- Publication number
- CN207365824U CN207365824U CN201720965112.XU CN201720965112U CN207365824U CN 207365824 U CN207365824 U CN 207365824U CN 201720965112 U CN201720965112 U CN 201720965112U CN 207365824 U CN207365824 U CN 207365824U
- Authority
- CN
- China
- Prior art keywords
- guided missile
- hydraulic actuator
- missile simulation
- test system
- compression spring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model discloses a kind of guided missile simulation emission test system, including the fixed frame and base frame that transverse horizontal is placed；The right upper portion of the fixed frame is fixedly installed a hydraulic actuator, and the telescopic rod 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 frame 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 traction rope with the left part of the compression spring.The utility model is simple in structure, easy to operate, can emitting performance of the safe and reliable detection guided missile in its supporting launch canister of institute, the test period is short, and cost is low, suitable wide popularization and application.
Description
Technical field
Missile performance checking test technical field is the utility model is related to, more particularly to a kind of guided missile simulation emission test
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
Working performance 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 flying 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 that 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 explosion, with the gunpowder that ignites,
Ignition charge does the disposable component of mechanical work and the general name of device), therefore, there are larger in implementation process
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, test of many times it is of high cost, while also need 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 is gone out, it can detect guided missile safe, reliable, efficiently in its institute
Emitting performance in supporting launching tube, the test period is short, and experimentation cost is low, is adapted to widely promote and apply.
Utility model content
In view of this, the purpose of this utility model is to provide a kind of guided missile simulation emission test system, its is simple in structure, behaviour
Facilitate, operated by the transmitting of simulated missile, guided missile can be detected safe, reliable, efficiently in its supporting guided missile hair
Emitting performance in shooting cylinder, the test period is short, and experimentation cost is low, is adapted to widely promote and apply, has great production practices
Meaning.
For this reason, the utility model provides a kind of guided missile simulation emission test system, including the fixation that transverse horizontal is placed
Frame and base frame；
The right upper portion of the fixed frame 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 frame 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 traction 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 frame 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 frame 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 is overlapped 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 frame and base frame to have foam-rubber cushion, the traction 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, a control unit is further included, described control unit is 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, is 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 solution provided by the utility model more than as it can be seen that compared with prior art, the utility model proposes
A kind of guided missile simulation emission test system, its is simple in structure, easy to operate, is operated by the transmitting of simulated missile, can safely,
Reliably, emitting performance of the guided missile in its supporting launch canister is efficiently detected, the test period is short, and experimentation cost is low,
It is adapted to widely promote and apply, is of great practical significance.
For guided missile simulation emission test system provided by the utility model, it can reliably simulation test guided missile lead
Under the different size of thrust for playing engine, speed when flying out from the emission port of launch canister.
For guided missile simulation emission test system provided by the utility model, it, can be by guided missile by setting foam-rubber cushion
The kinetic energy absorption of simulating piece, realizes protection and recycling to guided missile simulation part, 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 utility model；
Fig. 2 is a kind of front view of guided missile simulation emission test system provided by the utility model；
Fig. 3 is a kind of top view of guided missile simulation emission test system provided by the utility model；
Fig. 4 is the data in a kind of guided missile simulation emission test system provided by the utility model in one embodiment
The principle schematic for the step voltage signal that Acquisition Instrument gathers and two pairs of optoelectronic switch sensors of real-time display produce；
In figure, 1 is compression spring, and 2 be fixed frame, 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 traction rope, and 10 be optoelectronic switch sensor, and 11 be launching tube simulating piece, 12
It is basic rack for hoop bracket, 13,14 be hollow guiding pipe.
Embodiment
In order to make those skilled in the art more fully understand the utility model, below in conjunction with the accompanying drawings and embodiment
The utility model is described in further detail.
Referring to Fig. 1 to Fig. 3, a kind of guided missile simulation emission test system provided by the utility model, for simulated missile
Transmitting, realizes the detection of the emitting performance to guided missile in its supporting launching tube, specifically includes consolidating for transverse horizontal placement
Determine frame 2 and base frame 13, the fixed frame 2 is located at the left side of the base frame 13；
The right upper portion of the fixed frame 2 is fixedly installed a hydraulic actuator 3,3 bottom of hydraulic actuator
Telescopic rod 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 frame 2 is fixedly installed a compression spring 1, and concrete structure is：The fixed frame 2
Left side central portion is fixedly installed the hollow guiding pipe 14 of a cross direction profiles, and 14 outer wall of hollow guiding pipe 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, can prevent compression spring 1 from destabilization problems occurring in compression process, the compressive deformation process to compressing 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 cavity 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.
, it is necessary to illustrate in the utility model, actual missile of the guided missile simulation part with needing simulation test
Shape, size, weight are corresponding to the same, and especially gravity centre distribution is also consistent.The launching tube simulating piece 11 is simulated with needing
Shape, the size of the actual missile launching tube of experiment are corresponding to the same, especially need and the inner cavity of actual missile launching tube
Shape, size are corresponding to the same.
In the utility model, in specific implementation, the center line of the launching tube simulating piece 11 and the compression spring 1
Center line overlaps.
In the utility model, 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 base frame 13 respectively
Top surface is fixed together.
In the utility model, in specific implementation, the right side central of the fixed frame 2 is fixedly installed a fixed pulley 7,
The 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
In the direction for changing the pulling force that the hydraulic actuator 3 exports so that pulling force effect direction that hydraulic actuator 3 exports and described
It is vertical to compress the compression direction of spring 1, while ensures that value of thrust is constant.
It should be noted that in specific implementation, an annular guiding groove is distributed with the 7 surrounding outer wall of fixed pulley,
The pulling force rope 6 passes through the guiding groove.
In the utility model, in specific implementation, also level is set on the position between the fixed frame 2 and base frame 13
Foam-rubber cushion 8 is equipped with, the traction rope 9 runs through the foam-rubber cushion 8.
, it is necessary to which explanation, is clearance fit between the foam-rubber cushion 8 and the traction rope 9 in the utility model, tool
Body is：With being provided with through hole on 9 opposite position of traction rope on the foam-rubber cushion 8, the shape of the through hole, size are more than described
Shape, the size of traction rope 9.
In the utility model, in specific implementation, the top of base frame 13 is additionally provided with left and right is spaced apart two
To optoelectronic switch sensor 10, the launching tube simulating piece 11 is symmetrically distributed in before and after optoelectronic switch sensor 10 described in each pair
The left side.
The optoelectronic switch sensor 10, the emission port for measuring guided missile simulation part from 11 left end of launching tube simulating piece 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 for the step voltage signal gathered and optoelectronic switch sensor described in real-time display produces.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 simulation 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, which could alternatively be any other one kind, can measure guided missile
The component that tests the speed of speed when the emission port of simulating piece from 11 left end of launching tube simulating piece 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
The velocity amplitude when emission port of guided missile simulation part from 11 left end of launching tube simulating piece flies out can be directly obtained from tachogenerator.
In the utility model, in order to drive hydraulic actuator 3, the kinetic energy of stabilization is provided for hydraulic actuator 2, for this
Utility model, the hydraulic actuator 3 are connected with a hydraulic power source (such as hydraulic power unit).Wherein, the hydraulic power source is used for
Stable pressure and flow, and output hydraulic pressure energy are provided；The hydraulic actuator 2 can change the hydraulic energy from hydraulic power source
For mechanical energy, 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
State hydraulic actuator 3 and the pressure of stabilization and the hydraulic power source of flow are provided, the pulling force of maximum 50kN can be provided at.
It should be noted that in the utility model, the hydraulic actuator 3, for being provided out pulling force, specially to
The pulling force rope 6 and compression spring 1 of outer link connection provide pulling force；
The force snesor 4, the value of thrust outwards exported for measuring the hydraulic actuator 3 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 that the elastic potential energy abrupt release by compressed compression spring；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 fulfill the function of abrupt release.
The pulling force rope 6, compression spring 1 is given for directly transmitting the pulling force that hydraulic actuator 3 outwards exports；
The compression spring 1, under the external pull effect that the hydraulic actuator 3 is applied, forming compression and becoming
Shape, and elastic potential energy is produced by compression, during release, acted on by the transmission of traction 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 traction rope 9, for the kinetic energy for being converted the elastic potential energy for compressing 1 abrupt release of spring, real-time delivery
To the guided missile simulation part being inserted into the launching tube simulating piece 11, so that guided missile simulation part can be from the launching tube
11 moment of simulating piece emits；
The foam-rubber cushion 8, for after guided missile simulation part can be emitted from 11 moment of launching tube simulating piece, 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 recycling, 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 utility model, the drawing that can be applied by hydraulic actuator 3 to compression spring 1
Power, and acted on by the energy transmission of traction rope 9, the pulling force effect for compressing actuator 3 and effect can be ultimately transferred to institute
The guided missile simulation part in launching tube simulating piece 11 is stated, the pulling force of moment is formed to guided missile simulation part, then real-time testing guided missile mould
The speed when emission port of plan part from the left end of launching tube simulating piece 11 flies out.Therefore, the utility model, which can simulate, truly leads
Bullet emitting performance corresponding under the different size thrust of actual missile engine, that is, simulated missile are matched somebody with somebody at it
Emitting performance in the launch canister of set, and the speed when emission port of simulation test guided missile from launch canister left end flies out
Degree.
In the utility model, in specific implementation, guided missile simulation emission test system provided by the utility model further includes
One control unit, described control unit are connected with a data collecting instrument；
The data collecting instrument, is connected with force snesor 4, and 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, 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 utility model is by control unit,
And combine the effect of force snesor 4, 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 utility model can meet the actual missile hair of different thrusts
The analog transmissions demand of motivation.
For guided missile simulation emission test system provided by the utility model, its specific installation and debugging and authenticated
Journey, may comprise steps of：
1st, compression spring 1, hydraulic actuator 3 and fixed pulley 7 are installed on fixed frame 2, force snesor 4 is installed on hydraulic pressure
The telescopic rod end of 3 bottom of actuator, quick release hook 5 are connected to the lower section of force snesor 4；
2nd, optoelectronic switch sensor 10 and hoop bracket 12 are installed 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 frame 2, then will traction close to the side of fixed frame 2
One end of rope 9 is connected with compressing the movable end (i.e. left end) of spring 1, and the other end is connected with the head of guided missile simulation part 11, at the same time
Make traction rope 9 through the through hole on foam-rubber cushion 8；
4th, fixed frame 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 traction rope 9 is in exceptionally straight state, guided missile simulation part is close to the inner cavity of launching tube simulating piece 11
Tail end；
5th, after the relative position of fixed frame 2, base frame 13 determines, two-part structure is fixed on foundation platform；
Then the movable end (i.e. left end) for compressing 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, monitors the pulling force of the output of force snesor 4 and the signal of optoelectronic switch sensor in real time；
9th, pulling force is slowly exported using control unit control hydraulic actuator 3, until reaching to the pulling force for compressing 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 cavity tail end of launching tube simulating piece, makes at the same time
Traction rope 9 is in tension；
11st, the safety pin on quick release hook 5 is pulled out, then opens release hook, makes 6 abrupt release of pulling force rope, at the same time
The pop-up of 1 moment of spring is compressed, pulls the movement in launching tube simulating piece 11 of guided missile simulation part；
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, obtains time of the guided missile simulation part by specific length, calculates and obtain guided missile simulation part
Muzzle velocity.
Understood based on above-mentioned technical proposal, it is and existing for guided missile simulation emission test system provided by the utility model
Technology compares, and has the following advantages：
1st, power source of the utility model by the use of mechanical driver unit as emission test, simulates the launching site of actual missile
Scape, compared to conventional priming system test method, this method will not be limited be subject to 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 utility model uses has high sensitivity, (response time is less than fast response time
1ms) the advantages that, it can be achieved that the measurement of relative broad range emission rate, can meet the guided missile simulation part under different tests requirement
The quantitative appraisal of structural behaviour；
3rd, the utility model can by replacing the compression spring, hydraulic actuator and launching tube simulating piece of different size,
The simulation test demand of guided missile that adapt to different quality, different bores, different emission rates；
4th, fixed pulley is used in the utility model, action direction and the compression bullet of the pulling force that hydraulic actuator can be exported
The compression direction of spring is mutually perpendicular to, so as to be conducive to the release movement of quick release hook, it also avoid the hair to guided missile simulation part
Penetrate generation interference；
5th, the utility model therefore, is adapted to not come the launching tube simulating piece that is fixedly clamped by two hoop brackets
Installation with the launching tube simulating piece of diameter is fixed, and has good versatility.
In conclusion compared with prior art, a kind of guided missile simulation emission test system provided by the utility model, its
It is simple in structure, it is easy to operate, operated by the transmitting of simulated missile, guided missile can be detected safe, reliable, efficiently and be matched somebody with somebody at it
Emitting performance in the launch canister of set, the test period is short, and experimentation cost is low, is adapted to widely promote and apply, has great
Production practices meaning.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
For art personnel, on the premise of the utility model principle is not departed from, some improvements and modifications can also be made, these improve and
Retouching also should be regarded as the scope of protection of the utility model.
Claims (10)
1. a kind of guided missile simulation emission test system, it is characterised in that the fixed frame (2) and basic platform placed including transverse horizontal
Frame (13)；
The right upper portion of the fixed frame (2) is fixedly installed a hydraulic actuator (3), hydraulic actuator (3) bottom
Telescopic rod 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 frame (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 traction 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 frame (2)
Portion is fixedly installed the hollow guiding 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 2, 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 frame (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 is overlapped 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 frame
(2) also horizontally disposed on the position between base frame (13) to have foam-rubber cushion (8), the traction 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 basis 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 basis 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 further include one
Control unit, described control unit are connected with a data collecting instrument；
The data collecting instrument, is connected with force snesor (4), and 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, 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 |
|---|---|---|---|
| CN201720965112.XU CN207365824U (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 |
|---|---|---|---|
| CN201720965112.XU CN207365824U (en) | 2017-08-04 | 2017-08-04 | A kind of guided missile simulation emission test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207365824U true CN207365824U (en) | 2018-05-15 |
Family
ID=62423028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720965112.XU Active CN207365824U (en) | 2017-08-04 | 2017-08-04 | A kind of guided missile simulation emission test system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207365824U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107462115A (en) * | 2017-08-04 | 2017-12-12 | 天津航天瑞莱科技有限公司 | A kind of guided missile simulation emission test system |
-
2017
- 2017-08-04 CN CN201720965112.XU patent/CN207365824U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107462115A (en) * | 2017-08-04 | 2017-12-12 | 天津航天瑞莱科技有限公司 | A kind of guided missile simulation emission test system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105973611B (en) | A kind of visualization in-cylinder direct-jet Fast Compression combustion experimental device | |
| CN107462115A (en) | A kind of guided missile simulation emission test system | |
| CN101957290B (en) | Fatigue testing machine applied to tension test piece and method thereof | |
| CN106093194B (en) | The test device and amount sign method for lower quasi-brittle material stress wave attentuation rule of exploding | |
| CN207095814U (en) | Simulate target dynamic characteristic test system under the military-civil equipment strong impact environment of high speed | |
| CN107421706B (en) | Diversified test platform for dynamic characteristics of target in strong impact environment | |
| CN104089833B (en) | A kind of pneumatic type is imitated son (big gun) and is launched the material impact assay device hit | |
| CN206095834U (en) | Experimental facilities is impacted to multi -functional high speed | |
| CN207365824U (en) | A kind of guided missile simulation emission test system | |
| CN201373801Y (en) | High speed particles impact testing device | |
| CN110296828A (en) | Portable combined pressure relief valve monitor station and detection method | |
| CN106353180A (en) | Explosive wave simulating device with adjustable positive pressure acting time | |
| CN101539388B (en) | Simulated underwater launcher based on momentum transfer principle | |
| CN101498637B (en) | High-speed particle impact test apparatus | |
| CN204740118U (en) | High pressure transmission pin -connected panel collision test device | |
| CN109668712A (en) | A kind of model emitter and its application | |
| CN206281908U (en) | A kind of removable ejection type extra high voltage network grounding test apparatus | |
| CN208443587U (en) | A kind of collision protection mechanism | |
| CN104597280A (en) | Negative pressure ejection cover pull umbrella testing device and method | |
| CN114112741A (en) | Anchoring body dynamic load impact resistance in-situ measurement device and testing method | |
| CN103868647B (en) | A kind of cannon breech pressure measures the dynamic calibration apparatus of sensor | |
| KR100491227B1 (en) | Simulator of rocket thrust generation | |
| CN109104901B (en) | Cylinder analog transmissions experimental rig | |
| CN111122091A (en) | Device for eddy current damper impact loading experiment and experiment method thereof | |
| CN110261055A (en) | A kind of large-scale precision impact test system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |