CN109186919A - A kind of experimental rig impacting igniting composite testing for solid propellant rocket - Google Patents
A kind of experimental rig impacting igniting composite testing for solid propellant rocket Download PDFInfo
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- CN109186919A CN109186919A CN201811225644.5A CN201811225644A CN109186919A CN 109186919 A CN109186919 A CN 109186919A CN 201811225644 A CN201811225644 A CN 201811225644A CN 109186919 A CN109186919 A CN 109186919A
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- Prior art keywords
- jump bit
- solid propellant
- propellant rocket
- test stand
- impact
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention proposes a kind of experimental rig that igniting composite testing is impacted for solid propellant rocket, is made of vertical test stand, auxiliary arc plate, impact loading device, jump bit, electromagnetism hook and control system；Solid propellant rocket to be measured is by assisting arc plate to be vertically mounted on vertical test stand top；Impact loading device includes support frame, top rotating shaft mechanism and connecting rod；Connecting rod one end is cooperated by bearing and shaft, and the connecting rod other end is fixedly connected with jump bit；The axis of solid propellant rocket to be measured is in the swinging plane of jump bit, and when jump bit front end circular arc shock surface and vertical test stand top plan contact, jump bit axis is perpendicular to vertical test stand top plan.The impact position and height that the present invention passes through design jump bit, solid propellant rocket be can be realized in the impact test of actual ignition state, meet diameter≤ф 220mm, quality≤25kg, thrust≤20kN, the requirement of shock loading 2500g-6000g engine impact test, and stable action, timing are accurate.
Description
Technical field
The present invention relates to Solid Rocket Engine Test technical fields, specially a kind of to impact for solid propellant rocket
The experimental rig for composite testing of lighting a fire.
Background technique
Solid propellant rocket is in actual working state, and in some flight time sequence, engine is because of stage separation, meeting
It is subjected to a very big overload impact, it is contemplated that engine belongs to larger priming system, in order to ensure engine operation can
It leans on, just impact reliability must further be examined under ignition condition.
Current impact test does not all carry out under actual working state, it is difficult to accurately reflect solid propellant rocket point
Impact reliability under fiery state.For accurate simulation solid propellant rocket actual working state, it is necessary to be given in specified timing
One specified size of solid propellant rocket, vertical direction shock loading from bottom to top.
At present in disclosed technical data, there is no impact igniting composite testing to solid propellant rocket to be situated between
It continues, is reported without relevant device.
Summary of the invention
In order to solve the problems existing in the prior art, the present invention proposes a kind of compound for solid propellant rocket impact igniting
The experimental rig of test makes the vertical direction of pendulum generation from bottom to top by Platform Designing using pendulum impact test platform
Shock loading, and meet shock loading requirement.
The technical solution of the present invention is as follows:
A kind of experimental rig impacting igniting composite testing for solid propellant rocket, it is characterised in that: by standing
Formula test stand, auxiliary arc plate, impact loading device, jump bit, electromagnetism hook and control system composition；
The vertical test stand is truss structure, is vertically mounted on testing stand；Solid propellant rocket to be measured passes through
Auxiliary arc plate is vertically mounted on vertical test stand top；
The impact loading device is vertically mounted on testing stand, and is in vertical test stand side；Impact loading device
Including support frame, top rotating shaft mechanism and connecting rod；Support frame as described above uses truss structure, is vertically fixedly mounted on testing stand
On, top rotating shaft mechanism is mounted at the top of support frame；Connecting rod is mounted on the rotating shaft mechanism of top, and connecting rod one end passes through bearing
Cooperate with shaft, the connecting rod other end is fixedly connected with jump bit；
The impact direction of the jump bit is vertical with connecting rod；There is lifting lug in jump bit side, cooperates for linking up with electromagnetism；
The axis of solid propellant rocket to be measured is in the swinging plane of jump bit, can be by adjusting vertical test stand
With the relative altitude of support frame, when contacting jump bit front end circular arc shock surface and vertical test stand top plan, jump bit axis
Line is perpendicular to vertical test stand top plan；
The control system can control the sling height of electromagnetism hook and the release timing of electromagnetism hook.
Further preferred embodiment, a kind of test dress impacting igniting composite testing for solid propellant rocket
It sets, it is characterised in that: the attachment lug of solid propellant rocket to be measured and vertical test stand top plan is in jump bit movement
The impact position of plane two sides, jump bit and vertical test stand top plan is located at the side of attachment lug line.
Further preferred embodiment, a kind of test dress impacting igniting composite testing for solid propellant rocket
It sets, it is characterised in that: after solid propellant rocket to be measured is mounted on vertical test stand top, engine jet pipe axis is to engaging lug
The other side of piece line deflects, and jet-stream wind in solid propellant rocket practical work process is avoided to influence jump bit.
Further preferred embodiment, a kind of test dress impacting igniting composite testing for solid propellant rocket
It sets, it is characterised in that: jump bit front end is circular arc shock surface；There is axial screw in jump bit rear end, for increasing counterweight, improves punching
Hit load.
Further preferred embodiment, a kind of test dress impacting igniting composite testing for solid propellant rocket
It sets, it is characterised in that: the back side at the top of support frame in jump bit swaying direction is provided perpendicular to jump bit swinging plane
Crossbeam, it is dangerous for preventing during test jump bit reversely to fall appearance.
Beneficial effect
The experimental rig for solid propellant rocket impact igniting composite testing that the present invention designs mainly includes vertical
Test stand, jump bit and impact loading device can be realized solid-rocket hair by designing the impact position and height of jump bit
Motivation meets diameter≤ф 220mm, quality≤25kg, thrust≤20kN, shock loading in the impact test of actual ignition state
The requirement of 2500g-6000g engine impact test, and stable action, timing are accurate.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1: impact conditions schematic diagram；
Fig. 2: test initial state schematic diagram；
Fig. 3: jump bit schematic diagram；
Fig. 4: rotating shaft mechanism schematic diagram at the top of impact loading device；
Fig. 5: vertical test stand schematic top plan view；
Wherein: 1, assisting arc plate；2, vertical test stand；3, impact loading device；4, jump bit；5, electromagnetism is linked up with；6, solid
Body rocket tube；7, impact position；8, attachment lug.
Specific embodiment
The embodiment of the present invention is described below in detail, the embodiment is exemplary, it is intended to it is used to explain the present invention, and
It is not considered as limiting the invention.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " up time
The orientation or positional relationship of the instructions such as needle ", " counterclockwise " is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of
The description present invention and simplified description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with spy
Fixed orientation construction and operation, therefore be not considered as limiting the invention.
Current embodiment require that capableing of the simulator of simulated implementation >=2500g shock loading and bearing platform, and can be real
Now specify the impact of timing assigned direction.According to requiring, the present embodiment devises impact igniting composite test device, when specified
Interior engine assigned direction of giving specifies magnitude impact.
As depicted in figs. 1 and 2, this is used for the experimental rig of solid propellant rocket impact igniting composite testing by vertical examination
Test frame 2, auxiliary arc plate 1, impact loading device 3, jump bit 4, electromagnetism hook 5 and control system composition.
The vertical test stand 2 is truss structure, is vertically mounted on testing stand by foundation bolt；Solid fire to be measured
Arrow engine is by assisting arc plate 1 to be vertically mounted on vertical test stand top, it is ensured that engine is in normal installation condition.
The impact loading device 3 is vertically mounted on testing stand by foundation bolt, and is in vertical test stand side.
Impact loading device includes support frame, top rotating shaft mechanism and connecting rod；Support frame as described above uses truss structure, passes through lower margin
Bolt is vertically fixedly mounted on testing stand, and top rotating shaft mechanism is mounted at the top of support frame；Connecting rod is mounted on top shaft
In mechanism, connecting rod one end is cooperated by bearing and shaft, and the connecting rod other end is fixedly connected with jump bit.
The impact direction of the jump bit is vertical with connecting rod；Jump bit structure is as shown in figure 3, jump bit side is hung
Ear, for facilitating lifting with electromagnetism hook cooperation；Jump bit front end is circular arc shock surface；There is axial screw in jump bit rear end, uses
In increasing counterweight, shock loading can be increased during test by way of increasing counterweight.
The axis of solid propellant rocket to be measured is in the swinging plane of jump bit, can be by adjusting vertical test stand
With the relative altitude of support frame, when contacting jump bit front end circular arc shock surface and vertical test stand top plan, jump bit axis
Line is perpendicular to vertical test stand top plan, to guarantee impact direction from bottom to top.
As shown in figure 5, the attachment lug of solid propellant rocket to be measured and vertical test stand top plan is in jump bit
The impact position of plane of movement two sides, jump bit and vertical test stand top plan is located at the side of attachment lug line, in this way
Jump bit impact position and installation site can be eliminated closely leads to the insecurity factor of bolt falling excessively.In addition, solid fire to be measured
After arrow engine is mounted on vertical test stand top, engine jet pipe axis is deflected to the other side of attachment lug line, is avoided
Jet-stream wind influences jump bit in solid propellant rocket practical work process.
The control system can control the sling height of electromagnetism hook and the release timing of electromagnetism hook, before test,
Electromagnetism hook is hung up jump bit in appropriate height by the lifting lug on jump bit, and electromagnetism hook is discharged in specified timing, punching
The vertical test stand of hammer falling impacts reaches impact igniting composite testing test requirements document.The height of jump bit release simultaneously is different,
Shock loading caused by it is also different, can adjust impact magnitude by adjusting release altitude.
As shown in figure 4, the back side at the top of support frame in jump bit swaying direction is provided perpendicular to jump bit swing
The crossbeam of plane can prevent jump bit during test from reversely falling and damage to testing crew.
Mounting process installs vertical test stand, engine and impact loading device as shown in Figure 1 when test, makes impact hammer head
The lifting lug side that portion position face is impacted, auxiliary arc plate embrace engine.Jump bit electromagnetism hook is mentioned into finger before test
Fixed height savings energy, and it is at stationary state.When test, when proceeding to specified timing, release punching is linked up with by electromagnetism
Hammer makes it impact lifting lug part by the movement of falling object, completes the impact of the specified impact magnitude of assigned direction.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (5)
1. a kind of experimental rig for impacting igniting composite testing for solid propellant rocket, it is characterised in that: by vertical test
Frame, auxiliary arc plate, impact loading device, jump bit, electromagnetism hook and control system composition；
The vertical test stand is truss structure, is vertically mounted on testing stand；Solid propellant rocket to be measured passes through auxiliary
Arc plate is vertically mounted on vertical test stand top；
The impact loading device is vertically mounted on testing stand, and is in vertical test stand side；Impact loading device includes
Support frame, top rotating shaft mechanism and connecting rod；Support frame as described above uses truss structure, is vertically fixedly mounted on testing stand,
Top rotating shaft mechanism is mounted at the top of support frame；Connecting rod be mounted on top rotating shaft mechanism on, connecting rod one end by bearing with
Shaft cooperation, the connecting rod other end are fixedly connected with jump bit；
The impact direction of the jump bit is vertical with connecting rod；There is lifting lug in jump bit side, cooperates for linking up with electromagnetism；
The axis of solid propellant rocket to be measured is in the swinging plane of jump bit, can be by adjusting vertical test stand and branch
The relative altitude of support, when contacting jump bit front end circular arc shock surface and vertical test stand top plan, jump bit axis hangs down
Directly in vertical test stand top plan；
The control system can control the sling height of electromagnetism hook and the release timing of electromagnetism hook.
2. a kind of experimental rig for impacting igniting composite testing for solid propellant rocket according to claim 1, special
Sign is: the attachment lug of solid propellant rocket to be measured and vertical test stand top plan is in jump bit plane of movement two
The impact position of side, jump bit and vertical test stand top plan is located at the side of attachment lug line.
3. a kind of experimental rig for impacting igniting composite testing for solid propellant rocket according to claim 2, special
Sign is: after solid propellant rocket to be measured is mounted on vertical test stand top, engine jet pipe axis is to attachment lug line
Other side deflection, avoid in solid propellant rocket practical work process jet-stream wind from influencing jump bit.
4. a kind of experimental rig for impacting igniting composite testing for solid propellant rocket according to claim 1, special
Sign is: jump bit front end is circular arc shock surface；There is axial screw in jump bit rear end, for increasing counterweight, improves shock loading.
5. a kind of experimental rig for impacting igniting composite testing for solid propellant rocket according to claim 1, special
Sign is: the back side at the top of support frame in jump bit swaying direction is provided perpendicular to the crossbeam of jump bit swinging plane,
For preventing jump bit during test from reversely falling appearance danger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811225644.5A CN109186919B (en) | 2018-10-21 | 2018-10-21 | Test device for impact ignition composite test of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811225644.5A CN109186919B (en) | 2018-10-21 | 2018-10-21 | Test device for impact ignition composite test of solid rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109186919A true CN109186919A (en) | 2019-01-11 |
| CN109186919B CN109186919B (en) | 2020-08-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811225644.5A Active CN109186919B (en) | 2018-10-21 | 2018-10-21 | Test device for impact ignition composite test of solid rocket engine |
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| Country | Link |
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| CN (1) | CN109186919B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110715784A (en) * | 2019-12-12 | 2020-01-21 | 天津航天瑞莱科技有限公司 | Power device ignition test method under vibration environment condition |
| CN113465933A (en) * | 2021-06-29 | 2021-10-01 | 西安零壹空间科技有限公司 | Internal pressure and external load composite static force testing device for solid rocket engine |
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| JPH02236435A (en) * | 1989-03-10 | 1990-09-19 | Nec Corp | Impulsive acceleration tester |
| JPH10170390A (en) * | 1996-12-13 | 1998-06-26 | Nec Corp | Impact tester |
| EP1923688A1 (en) * | 2006-11-18 | 2008-05-21 | Sebert Schwingungstechnik GmbH | Device for testing the behaviour of objects during acceleration processes |
| CN105067213A (en) * | 2015-07-16 | 2015-11-18 | 北京强度环境研究所 | Large-scale structure vibration characteristic test pulse excitation apparatus and application method thereof |
| CN106197927A (en) * | 2016-06-24 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aero-engine ratchet impact strength test device |
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2018
- 2018-10-21 CN CN201811225644.5A patent/CN109186919B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02236435A (en) * | 1989-03-10 | 1990-09-19 | Nec Corp | Impulsive acceleration tester |
| JPH10170390A (en) * | 1996-12-13 | 1998-06-26 | Nec Corp | Impact tester |
| EP1923688A1 (en) * | 2006-11-18 | 2008-05-21 | Sebert Schwingungstechnik GmbH | Device for testing the behaviour of objects during acceleration processes |
| CN105067213A (en) * | 2015-07-16 | 2015-11-18 | 北京强度环境研究所 | Large-scale structure vibration characteristic test pulse excitation apparatus and application method thereof |
| CN106197927A (en) * | 2016-06-24 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aero-engine ratchet impact strength test device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110715784A (en) * | 2019-12-12 | 2020-01-21 | 天津航天瑞莱科技有限公司 | Power device ignition test method under vibration environment condition |
| CN110715784B (en) * | 2019-12-12 | 2020-04-24 | 天津航天瑞莱科技有限公司 | Power device ignition test method under vibration environment condition |
| CN113465933A (en) * | 2021-06-29 | 2021-10-01 | 西安零壹空间科技有限公司 | Internal pressure and external load composite static force testing device for solid rocket engine |
| CN113465933B (en) * | 2021-06-29 | 2024-03-29 | 西安零壹空间科技有限公司 | Internal pressure and external load composite static force testing device of solid rocket engine |
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| CN109186919B (en) | 2020-08-14 |
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Inventor after: Li Bin Inventor after: Fu Dongli Inventor after: Han Liliang Inventor after: Zhu Ziwen Inventor after: Lei Hai Inventor after: Liu Xing Inventor after: Qu Youyang Inventor after: Liu Bo Inventor after: Liu Chang Inventor after: Wang Zhe Inventor after: Cui Yujie Inventor before: Zhu Ziwen Inventor before: Han Liliang Inventor before: Lei Hai Inventor before: Liu Xing Inventor before: Qu Youyang Inventor before: Liu Bo Inventor before: Liu Chang Inventor before: Wang Zhe Inventor before: Cui Yujie Inventor before: Fu Dongli |
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