CN109104909B - Guided missile adapter static pressure test apparatus - Google Patents
Guided missile adapter static pressure test apparatus Download PDFInfo
- Publication number
- CN109104909B CN109104909B CN200810077692.4A CN200810077692A CN109104909B CN 109104909 B CN109104909 B CN 109104909B CN 200810077692 A CN200810077692 A CN 200810077692A CN 109104909 B CN109104909 B CN 109104909B
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- adapter
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Abstract
The present invention relates to guided missile test devices, disclose a kind of guided missile adapter static pressure test apparatus, comprising: simulated missile cylinder [1] is fixed on pedestal ingot bar [10]；It is mounted in the cylindrical concave of simulated missile cylinder [1] by test adapter [9]；Simulated missile body [2] is located at by the top of test adapter [9], there are four displacement meter [7] for its surrounding tool, and simulated missile body [2], sensor connector [3], force snesor [4], sensor adapter [5], pressure type actuator [6] are sequentially connected；It is locked up and down between sensor connector [3] and force snesor [4] and with two lock nuts [8] between force snesor [4] and sensor adapter [5].The present invention solves the test problem of guided missile adapter, achieves structure and is simple and convenient to operate, simulates the beneficial effects such as accurate, repeatable application.
Description
Technical field
The present invention relates to guided missile test device, especially a kind of static pressure test apparatus of guided missile adapter.
Background technique
The connection type of the previous emitters such as guided missile and launching tube is all by guide rail, sliding block, plays machine admittedly
The hard way of contact connection such as structure, each connecting component geometric dimension is designed according to required precision,
And it is present, certain beforehand research type of missile is to be fixed on guided missile by " soft " way of contact using adapter
In launching tube, connection type with before make a big difference.The adapter be by polyurethane foam plastics,
Three kinds of combinations of materials of sponge plate and linen form, and the guided missile positioning of the compositions such as embedded spring, positioning pin
Mechanism.Every adapter is in semicircular structure, and guided missile has region at three that need to utilize adapter in launching tube
Installation fixation is carried out, every place around guided missile and need to be fixed in launching tube with 4 adapters, overall
It is safe reliable in launching tube that installation requirement should ensure that guided missile is mounted on, and ensures again smooth when MISSILE LAUNCHING
Cylinder out.There is adapter biggish plasticity technically to need to design the adaptation of suitable thickness
Adapter has suitable deformation and generates it appropriately to guided missile after device just can ensure that guided missile loading launching tube
Support reaction, it is ensured that guided missile is reliable and stable in launching tube；On the other hand, ensure that the support reaction exists again
Guided missile when going out cylinder caused frictional force cannot it is excessive and influence guided missile smoothly go out cylinder.
Therefore, adapter is the novel critical component in bullet, cylinder combination and separation process, structure size
The design of parameter must determine there is essence with previous cylinder combination by many experimental results
Difference, thus test objective and method are also very different.But it there is no the similar present invention at present
Battery of tests device.
Summary of the invention
In order to solve the problems, such as that the prior art there is no guided missile adapter experimental rig, it is an object of the invention to
A kind of guided missile adapter static pressure test apparatus is provided.Using the present invention, it can establish and a set of be suitble to this not advise
The then static pressure test apparatus of the guided missile adapter of cyclic structure, and its pressure and deformation can be measured
Between relationship.
In order to achieve the above object of the invention, the present invention is that technical solution used by solving its technical problem is
A kind of guided missile adapter static pressure test apparatus is provided, which includes:
Simulated missile cylinder is fixed on as on pedestal ingot bar；Simulated missile cylinder is mounted on by test adapter
In the cylindrical concave of body；The simulated missile body of semi-cylindrical is located at by the top of test adapter,
Central point is opposite with the central point of simulated missile cylinder；Four symmetrical orientation above simulated missile body
There are four displacement meter, their displacement measuring points to be symmetrically installed for upper installation；Simulated missile body passes through sensor
Connector is connected to force snesor；The upper bed-plate of pressure type actuator is fixed on test portal frame crossbeam by screw
On upper ingot bar；The end head of pressure type actuator has the piston rod that can keep upper and lower vertical telescopic, the piston
Bar is connect by sensor adapter with force snesor；The simulated missile body passes through sensor connector
Between force snesor and force snesor passes through between sensor adapter and the piston rod of actuator
Two lock nuts are connected to lock up and down；The pressure type actuator is connect with the hydraulic oil vehicle of periphery；
The force snesor is connect with the YJ-X4 static resistance deformeter of periphery；The displacement meter and periphery
MDAC displacement measurement system connection.
The upper back of above-mentioned simulated missile body is plane, and there are four be fixedly connected tool with sensor connector
Mounting hole；Its underpart is semi-circular cylindrical body outstanding, and diameter is identical as guided missile outer diameter is modeled；Circle
It bores along radial there are two pilot hole, angle and is pressed from both sides by two guide pins on test adapter on cylindricality convex surface
Angle is consistent.The top of above-mentioned simulated missile cylinder has cylindrical concave surface, cylindrical concave radius
It matches with by the outer diameter of test adapter, the bottom of simulated missile cylinder is provided with threaded hole, passes through spiral shell
Nail is connected with as pedestal ingot bar, is fixed on test room floor as pedestal ingot bar.
Guided missile adapter static pressure test apparatus of the present invention due to taking above-mentioned technical solution, solve
The deformation of adapter irregular complex structure and the test problem of load relation, can be used for plurality of specifications,
The test of the guided missile adapter of a variety of density and multiple Curve guide impeller batch models, test result are guided missile
The design and improvement of adapter provide reliable foundation.The present invention achieve structure be simple and convenient to operate,
Simulation is accurate, repeats the beneficial effects such as application.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of guided missile adapter static pressure test apparatus of the present invention；
Fig. 2 is the outline drawing of simulated missile cylinder；
Fig. 3 is the outline drawing of simulated missile body；
Fig. 4 is the structural schematic diagram of sensor connector；
Fig. 5 is the structural schematic diagram of sensor adapter；
Fig. 6 is to utilize the adapter deformation of apparatus of the present invention test measurement and load relation figure.
Specific embodiment
Guided missile adapter static pressure test apparatus of the present invention mainly includes the test tool of simulated missile cylinder, mould
The test tool of quasi- missile airframe, and force loading section and deformation measurement part.
Illustrate the preferred embodiment of the present invention with reference to the accompanying drawing.
Fig. 1 is the structural schematic diagram of guided missile adapter static pressure test apparatus of the present invention；Such as the embodiment of Fig. 1
Shown, simulated missile cylinder test tool includes simulated missile cylinder 1, simulated missile body test tool packet
Simulated missile body 2 is included, force loading section includes sensor connector 3, force snesor 4, sensor turn
Connector 5, pressure type actuator 6, lock nut 8 and its peripheral part loading equipemtn, power and deformation measurement
Part includes: force snesor 4 and its peripheral part dynamometry instrument；Displacement meter 7 and its outer part quartile
Shift measurement instrument.
Now the configuration connection relationship of the device is described as follows, which includes:
Upper and lower two block castings block, comprising: ingot bar 11 on pedestal ingot bar 10 and test portal frame crossbeam, as solid
The experiment porch of fixed adapter static pressure test apparatus of the present invention；Simulated missile cylinder 1 is fixed on the bottom of lower part
On seat ingot bar 10；It is mounted in the cylindrical concave of simulated missile cylinder 1, simulates by test adapter 9
The diameter of the cylindrical concave of guided missile cylinder 1 matches with by the outer diameter of test adapter 9；Semi-cylindrical
Simulated missile body 2 be located at by the top of test adapter 9, central point and simulated missile cylinder 1
Central point it is opposite, the diameter of cylindrical convex surface with to be modeled missile airframe outer through identical；Simulated missile
It is bored along radial there are two pilot hole, angle and by test adapter 9 in 2 cylindrical convex surface of body
Two guide pin angles are consistent, when test, are adapted to when simulated missile body 2 is moved down into contact by test
When device 9, the phase on the cylindrical surface of simulated missile body 2 is accurately entered by positioning pin on test adapter 9
In the dowel hole answered, slid after preventing adapter stress；Above simulated missile body 2 four it is symmetrical
Orientation on installation there are four displacement meter 7 (Indicate A, B, C, D tetra-
A displacement meter, is symmetrically installed), their displacement measuring points are symmetrically installed；Simulated missile body 2 passes through sensing
Device connector 3 is connected to force snesor 4；The upper bed-plate of pressure type actuator 6 is fixed on test gantry by screw
On frame crossbeam on ingot bar 11 (portal frame is fixed on test room floor by two columns), end head has
The piston rod of upper and lower vertical telescopic can be kept, which passes through sensor adapter 5 and force snesor 4
Connection；(pass through sensor connector 3) between above-mentioned simulated missile body 2 and force snesor 4, Yi Jili
The connection for (passing through sensor adapter 5) between sensor 4 and the piston rod of actuator 6 is locked with two
About 8 nut locks, and prevents simulated missile body tooling in loading procedure from twisting.Above-mentioned pressure type is made
Dynamic device 6 is connect with the hydraulic oil vehicle of periphery, for applying pressure to missile airframe 2；Above-mentioned force snesor 4
It is connect with the YJ-X4 static resistance deformeter of periphery, for measuring the size of the pressure；Above-mentioned displacement meter 7
It is connect with the MDAC displacement measurement system of periphery, by 9 four orientation of test adapter when for measuring force
Static displacement deformation, test result takes its average value.
Fig. 2 is the outline drawing of simulated missile cylinder 1, and upper part has a cylindrical concave surface, diameter with
It is matched by the outer diameter of test adapter 9.The bottom of simulated missile cylinder 1 is provided with threaded hole, passes through
Screw is connected with as pedestal ingot bar 10, is fixed on test room floor as pedestal ingot bar 10, it is ensured that mould
Quasi- guided missile cylinder level is fixed reliable.
Fig. 3 is the outline drawing of simulated missile body 2, and back is plane, and there are four connect tool with sensor
First 3 mounting holes being fixedly connected；Its underpart is semi-circular cylindrical body outstanding, the diameter and quilt of cylindrical body
Simulated missile body outer diameter is identical；Bored along radial there are two pilot hole in cylindrical convex surface, angle with
It is consistent by two guide pin angles on test adapter 9.
Fig. 4 is the structural schematic diagram of sensor connector 3, including a circular pedestal, base center tool
There is a vertical axis.Central shaft is connect by lock nut 8 with force snesor 4；On its pedestal,
The fixation hole of installation simulated missile body 2 there are four having around central axis.
Fig. 5 is the structural schematic diagram of sensor adapter 5, has internal screw thread in the axis of the upper end, with pressure
The piston rod of formula actuator 6 connects.There is external screw thread on the axis of its lower end, pass through lock nut 8 and power
Sensor 4 is connected and is locked.
The course of work of the invention is described further below.
Simulated missile body 2 is connected with force snesor 4 by sensor connector 3, and by lock nut 8
Locking prevents lower half portion mechanism when test from generating torsion.The internal screw thread on 5 top of sensor adapter with
The piston rod of pressure type actuator 6 is connected, and lower part is connected for external screw thread with force snesor 4, and by locking spiral shell
Mother locks, and prevents top half mechanism when test from generating torsion.The various adaptations that design has been produced
Device sample as shown in Figure 1, is placed on simulated missile cylinder 1, is tested respectively；Pass through hydraulic oil
The piston rod of vehicle control pressure type actuator moves down simulated missile body 2, applies pressure to adapter；
Record pressure value is carried out simultaneously and carries out displacement measurement, records load and deformation values；Deformation under load is drawn to close
It is curve, relationship between the deformation of analysis adapter and its support reaction (i.e. load)；Each feature of weight analysis
Point, deformation and support reaction size when including under initial mounting state, various overload situations, judges whether
Meet design requirement；The state closest to design requirement is determined from various specifications test result,
It is analyzed, Curve guide impeller, and tested again, so repeatedly repeatedly, until after Curve guide impeller
Until adapter meets requirement.
Experimental rig of the invention is to certain beforehand research type of missile adapter plurality of specifications, a variety of density and more
The testpieces of a Curve guide impeller batch has carried out experimental study, finally determines that a certain specification is comparatively ideal leads
Adapter state is played, primarily determines and enters the first sample stage for the formal specification of the model.Illustrate the test
Device has admirably achieved expected purpose.
Fig. 6 be using the adapter deformation of apparatus of the present invention test measurement and load relation figure, it is horizontal in figure
Coordinate representation deformation values, ordinate indicate pressure value (i.e. support reaction value), and curve indicates that adapter is pressurized
Power and deformation relationship, wherein F0, F, F1, F2,2F2 are adapter pair under the various feature operating conditions of guided missile
The support reaction load value that body generates.Curve graph obviously indicate this to adapter deformation and its to body
The corresponding support reaction size generated, showing each characteristic point to be includes initial static installation condition and various mistakes
Adapter deflection and corresponding support reaction size relation under the conditions of load.It is deformed by adapter and it is to body
The support reaction size relation of generation, to carry out judging whether adapter meets guided missile actual operation requirements, if
It is unsatisfactory for, then adapter is improved, then tested, until achieving the goal, it is seen then that the present invention
Expected results are reached.
Claims (6)
1. a kind of guided missile adapter static pressure test apparatus, comprising: simulated missile cylinder [1] is fixed on pedestal casting
On block [10]；It is mounted in the cylindrical concave of simulated missile cylinder [1] by test adapter [9]；Semicircle
Cylindrical simulated missile body [2] is located at by the top of test adapter [9], central point and simulated missile
The central point of cylinder [1] is opposite；Four are equipped in the four symmetrical orientation in simulated missile body [2] top
A displacement meter [7], their displacement measuring points are symmetrically installed；Simulated missile body [2] passes through sensor connector
[3] force snesor [4] are connected to；The upper bed-plate of pressure type actuator [6] is fixed on test portal frame by screw
On crossbeam ingot bar [11]；The end head of pressure type actuator [6] has the piston that can keep upper and lower vertical telescopic
Bar, the piston rod are connect by sensor adapter [5] with force snesor [4]；The simulated missile bullet
Body [2] is connect with sensor adapter [5] by four screws, sensor adapter [5] and force snesor [4]
Between by another locking spiral shell of lock nut [8] locking and force snesor [4] and sensor adapter [5]
Mother's locking, sensor adapter [5] upper end is connect with the piston rod of pressure type actuator [6]；The pressure type
Actuator [6] is connect with the hydraulic oil vehicle of periphery；The YJ-X4 of the force snesor [4] and periphery is static
Resistance strain gauge connection；The displacement meter [7] is connect with the MDAC displacement measurement system of periphery.
2. adapter static pressure test apparatus as described in claim 1, it is characterised in that: the simulation
The top of guided missile cylinder [1] is with cylindrical concave surface, cylindrical concave radius and by test adapter
[9] outer diameter matches.
3. adapter static pressure test apparatus as claimed in claim 1 or 2, it is characterised in that: described
The bottom of simulated missile cylinder [1] is provided with threaded hole, is connected by screw with pedestal ingot bar [10], bottom
Seat ingot bar [10] is fixed on test room floor.
4. adapter static pressure test apparatus as described in claim 1, it is characterised in that: the simulation
The upper back of missile airframe [2] is plane, and there are four the mounting holes being fixedly connected with sensor connector [3] for tool；
Its underpart be semi-circular cylindrical body outstanding, the diameter of cylindrical body be modeled missile airframe outside through identical；
It is bored along radial there are two pilot hole in cylindrical convex surface, angle is oriented to by test adapter [9] two
It is consistent to sell angle.
5. adapter static pressure test apparatus as described in claim 1, it is characterised in that: the sensing
Device connector [3] has circular pedestal, and base center has a vertical axis；Central shaft passes through locking
Nut [8] is connect with force snesor [4]；On its pedestal, there are four installation simulations to lead for tool around central axis
Play the fixation hole of body [2].
6. adapter static pressure test apparatus as described in claim 1, it is characterised in that: the sensing
There is internal screw thread in the axis of device adapter [5] upper end, connect with the piston rod of pressure type actuator [6]；Under it
There is external screw thread on the axis at end, connect and lock with force snesor [4] by lock nut [8].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810077692.4A CN109104909B (en) | 2008-11-18 | 2008-11-18 | Guided missile adapter static pressure test apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810077692.4A CN109104909B (en) | 2008-11-18 | 2008-11-18 | Guided missile adapter static pressure test apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109104909B true CN109104909B (en) | 2012-10-24 |
Family
ID=64870254
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810077692.4A Active CN109104909B (en) | 2008-11-18 | 2008-11-18 | Guided missile adapter static pressure test apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109104909B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109084969A (en) * | 2018-06-21 | 2018-12-25 | 湖北三江航天江北机械工程有限公司 | MISSILE LAUNCHING air deflector entirety Static Load Test Method |
| CN109373812A (en) * | 2018-12-04 | 2019-02-22 | 内蒙动力机械研究所 | A kind of launching tube resilient cushion displacement measuring device |
| CN110243499A (en) * | 2019-06-21 | 2019-09-17 | 上海燕兴科技实业有限公司 | Adapter vacuum suction experimental rig |
| CN113092233A (en) * | 2021-03-10 | 2021-07-09 | 上海复合材料科技有限公司 | Static load test system suitable for cartridge adapter and test method thereof |
| CN114414378A (en) * | 2022-03-29 | 2022-04-29 | 北京航天和兴科技股份有限公司 | Detection system and method for missile adapter of missile packing box |
| CN114486533A (en) * | 2022-04-18 | 2022-05-13 | 天津航天和兴科技有限公司 | Partitioned intelligent test system for missile adapter and test method thereof |
| CN114486549A (en) * | 2022-04-01 | 2022-05-13 | 北京航天和兴科技股份有限公司 | Static pressure test device for missile adapter |
| CN114857996A (en) * | 2022-06-30 | 2022-08-05 | 成都航天万欣科技有限公司 | System and method for detecting comprehensive performance of launching box |
-
2008
- 2008-11-18 CN CN200810077692.4A patent/CN109104909B/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109084969A (en) * | 2018-06-21 | 2018-12-25 | 湖北三江航天江北机械工程有限公司 | MISSILE LAUNCHING air deflector entirety Static Load Test Method |
| CN109373812A (en) * | 2018-12-04 | 2019-02-22 | 内蒙动力机械研究所 | A kind of launching tube resilient cushion displacement measuring device |
| CN109373812B (en) * | 2018-12-04 | 2024-03-12 | 内蒙动力机械研究所 | Transmitting cylinder shock pad displacement measuring device |
| CN110243499A (en) * | 2019-06-21 | 2019-09-17 | 上海燕兴科技实业有限公司 | Adapter vacuum suction experimental rig |
| CN113092233A (en) * | 2021-03-10 | 2021-07-09 | 上海复合材料科技有限公司 | Static load test system suitable for cartridge adapter and test method thereof |
| CN114414378A (en) * | 2022-03-29 | 2022-04-29 | 北京航天和兴科技股份有限公司 | Detection system and method for missile adapter of missile packing box |
| CN114414378B (en) * | 2022-03-29 | 2022-06-03 | 北京航天和兴科技股份有限公司 | Detection system and method for missile adapter of missile packing box |
| CN114486549A (en) * | 2022-04-01 | 2022-05-13 | 北京航天和兴科技股份有限公司 | Static pressure test device for missile adapter |
| CN114486533A (en) * | 2022-04-18 | 2022-05-13 | 天津航天和兴科技有限公司 | Partitioned intelligent test system for missile adapter and test method thereof |
| CN114857996A (en) * | 2022-06-30 | 2022-08-05 | 成都航天万欣科技有限公司 | System and method for detecting comprehensive performance of launching box |
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