CN110307104A - Two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device and test method - Google Patents
Two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device and test method Download PDFInfo
- Publication number
- CN110307104A CN110307104A CN201910598728.1A CN201910598728A CN110307104A CN 110307104 A CN110307104 A CN 110307104A CN 201910598728 A CN201910598728 A CN 201910598728A CN 110307104 A CN110307104 A CN 110307104A
- Authority
- CN
- China
- Prior art keywords
- test
- engine
- test engine
- overload
- cantilever beam
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device and test methods, wherein experimental rig includes: counterweight engine, rotary shaft, rotating platform, test engine and experimental rig of changing direction；The rotary shaft is fixed on rotating platform center, and for the driving unit for driving the rotary shaft to rotate, the counterweight engine and test engine are fixed on the rotating platform along the axisymmetry；The quality of the counterweight engine be equal to test engine and change direction experimental rig quality and；The experimental rig of changing direction crosses section for driving the test engine to rotate around its own axis, with adjust that test engine bears overload, thus the circumferential different overload fire trials crossed on section of simulation test engine；Wherein, test method is easy to operate.
Description
Technical field
The present invention relates to solid propellant rockets to overload igniting experimental technique field, and in particular to a kind of two-freedom rotation
Solid propellant rocket overload point fire test device and test method.
Background technique
Modern military, national defence are higher and higher to the maneuverability requirement of solid propellant rocket.Solid propellant rocket
Mobility it is better, it is meant that the ability for bearing motor-driven overload is stronger.Due to overload to the influence process of engine flow field with
And overload is complicated to the Influencing Mechanism of insulation erosion rate, causes its computer sim- ulation difficulty larger, therefore solid propellant rocket
Overload fire trial occupies important status in the research of solid propellant rocket.
Under normal circumstances, when solid propellant rocket is applied to aerospace, since it bears in entire flight course
The direction of overload, size be it is changeable, in order to simulate overload of the solid propellant rocket under different flight operating conditions, need on ground
Solid propellant rocket is carried out on face and overloads fire trial, and then is required in solid propellant rocket overload point fire test device
Solid propellant rocket has direction regulating power.
Existing solid propellant rocket overload point fire test device as shown in Figure 1, disadvantage is that: solid-rocket
It can only be rotated around the rotary shaft 2 at 5 center of rotating platform after engine (test engine 6) installation is fixed, bear the side of overload
To rotation center is directed to always during the whole test process, so that the section excessively of test engine 6 is constant always.
Solid propellant rocket could be changed by only being connect using the positioning tool of different directions with solid propellant rocket
Installation condition, but each direction be required to corresponding tooling position will lead to experimental rig complicate.For same direction
Discontinuity overload, can not obtain efficiency test data in primary test, and the overload test of different directions need more it is solid
Body rocket engine carries out fire trial, and cost expenses are huge.
Summary of the invention
In view of this, the present invention provides a kind of two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device,
Rotary system is set on test engine, it can be around own axes rotation, to adjust test engine in overload point
That overload is born during fire test crosses section.
The technical solution of two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device of the invention are as follows:
Two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device, comprising: counterweight engine, rotary shaft, rotation
Turn platform, test engine and experimental rig of changing direction；The rotary shaft is fixed on rotating platform center, and the driving unit is used
In driving rotary shaft rotation, the counterweight engine and test engine are fixed on rotating platform along the axisymmetry
On；The quality of the counterweight engine be equal to test engine and change direction experimental rig quality and；The test of changing direction
Device for drive the test engine around its own axis rotate, with adjust test engine bear overload cross section,
To the circumferential different overload fire trials crossed on section of simulation test engine.
As a preferred embodiment, the experimental rig of changing direction includes rotary system；Described rotary system one end is fixed
On the rotating platform, the other end and test engine transmission cooperate, for driving the test engine around its own axis
Line rotation.
As a preferred embodiment, the experimental rig of changing direction further includes Thrust Measuring System；The thrust measurement system
System is fixed on the rotating platform, and measurement end and the test engine front skirt contradict and cooperate, and starts for measuring the test
The thrust of machine.
As a preferred embodiment, the rotary system include bearing B, sleeve B, engines gear shaft, motor gear axis,
Connection ring and motor；The engines gear shaft is coaxially fixed on the rear skirt periphery of test engine；The sleeve B coaxial package
It is the tube structure of both ends aperture, both ends pass through bearing B respectively and are supported on engine gear in the periphery of test engine
The periphery of axis and the front skirt periphery of test engine open up fan-shaped pylone, the electricity within the scope of the sleeve B circumferential direction set angle
Machine gear shaft is mounted on the output end of motor and engages across the fan-shaped pylone of sleeve B circumferential direction with the engines gear shaft；Institute
It states sleeve B and is fixedly connected by connection ring with the Thrust Measuring System；Wherein, the motor is fixedly mounted on rotating platform
On.
It as a preferred embodiment, further include the above cantilever beam of a pair, each pair of cantilever beam includes left cantilever beam and right cantilever
Beam, the fixing end of left cantilever beam and the fixing end of right cantilever beam in each pair of cantilever beam are separately fixed at the same radial direction of rotary shaft
Two opposite sides；The counterweight engine and test engine pass through left cantilever beam respectively and right cantilever beam is symmetrically fixed on rotation
The two opposite sides of axis.
As a preferred embodiment, the rotary system further includes test tool, and described test tool one end and test are sent out
The front skirt of motivation is fixedly connected, and the other end and the Thrust Measuring System are face contact.
As a preferred embodiment, the driving unit uses motor.
As a preferred embodiment, the engines gear shaft is the multi-diameter shaft of both ends open, is relatively large in diameter end and institute
State the engagement of motor gear axis.
In addition, the present invention also provides a kind of two-freedom SPINNING SOLID ROCKET MOTORs to overload igniting test method, it should
Method is easy to implement, can effectively adjust test engine overload born during fire trial overload direction.
The technical solution of two-freedom SPINNING SOLID ROCKET MOTOR overload igniting test method of the invention are as follows:
Two-freedom SPINNING SOLID ROCKET MOTOR overload igniting test method, includes the following steps:
Step 1: it is subjected to practical overload when testing according to test engine, determines the length of each pair of cantilever beam free end,
Each pair of cantilever beam is fixedly connected with the sleeve B of test engine periphery and counterweight engine respectively；
Step 2: starting driving unit driving rotating platform rotation drives the counterweight engine being fixed thereon, test hair
Motivation and experimental rig of changing direction are rotated around rotary shaft；
Step 3: test engine bears overload under rotational case, and test engine ignition operation carries out overload igniting
Test；
Step 4: according to test engine actual overload requirement, determine test engine around the rotation direction of its own and
Rotational angle；
Step 5: starting motor drives motor gear axis to rotate around own axes, and then drives engines gear shaft around certainly
Body axis rotation, so that test engine rotation direction determined by the step 4 be driven to determine in own axes spin step 4
Rotational angle.
The utility model has the advantages that
(1) rotary system is set on test engine of the present invention, test engine can be adjusted in overload fire trial
The section of crossing that overload is born in journey can satisfy to obtain the test data overloaded on test engine circumferential direction different directions
Overload test demand on test engine circumferential direction different directions.
Detailed description of the invention
Fig. 1 is solid propellant rocket overload point fire test device in the prior art.
Fig. 2 is two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device in the present invention.
Fig. 3 is the partial cutaway view that rotary system is connect with solid propellant rocket in the present invention.
Fig. 4 is the partial schematic diagram that rotary system is connect with solid propellant rocket in the present invention.
Wherein, 1- counterweight engine, 2- rotary shaft, 3- cantilever beam, the left cantilever beam of 31-, the right cantilever beam of 32-, 4- thrust are surveyed
Amount system, 5- rotating platform, 6- test engine, 7- rotary system, 8- bearing B, 9- sleeve B, 10- engines gear shaft, 11-
Motor gear axis, 12- driving unit, 13- connection ring, 14- test tool, 15- motor
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
Embodiment 1:
A kind of two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device is present embodiments provided, test is started
Rotary system is set on machine, solid propellant rocket can be made while there is rotary shaft and central axis on rotating platform
The rotation of line two-freedom, what adjusting test engine bore to overload during overloading fire trial crosses section.
As shown in Fig. 2, the overload point fire test device includes counterweight engine 1, rotary shaft 2, rotating platform 5, test hair
Motivation 6 and experimental rig of changing direction；Rotating platform 5 is disc structure, and through-hole A is arranged in center；Rotary shaft 2 is fixed on rotary flat
Through-hole A is stretched out in the through-hole A of platform 5 and both ends, and one end is connected with driving unit 12, remembers that the end is bottom end, opposite with bottom end
It is that symmetry axis is fixed on rotary shaft 2 on rotating platform 5 that one end, which is top, counterweight engine 1 and test engine 6 with rotary shaft 2,
Two sides；Wherein, for driving unit 12 for driving rotary shaft 2 to rotate, rotary shaft 2 drives rotating platform 5 to turn around the axis of rotary shaft 2
It is dynamic, the quality of counterweight engine 1 be equal to test engine 6 and experimental rig of changing direction quality and, for being test engine 6
With experimental rig counterweight of changing direction, it is made to stablize rotation on rotating platform 5；Experimental rig of changing direction is for driving test to start
Machine 6 is rotated around its own axis, section is crossed with adjust that test engine 6 bears overload, so that simulation test engine 6 is circumferential
Overload fire trial on different directions；Two-freedom rotation finger to finger test engine 6 in the present embodiment can be simultaneously around rotation
Rotary shaft and the rotation of center axis on platform.
Further, driving unit 12 uses motor.
Further, counterweight engine 1 and test engine 6 pass through a pair of above cantilever beam 3 and 2 phase of rotary shaft respectively
Even, the stability rotated for enhancing counterweight engine 1 and test engine 6 with rotating platform 5.Each pair of cantilever beam 3 includes a left side
Cantilever beam 31 and right cantilever beam 32, the fixing end of the left cantilever beam 31 in each pair of cantilever beam 3 and the fixing end point of right cantilever beam 32
It is not fixed on the same radial two opposite sides of rotary shaft 2；Counterweight engine 1 and test engine 6 are that solid-rocket starts
Machine is arranged symmetrically in the two sides of rotary shaft 2；Wherein, the front skirt of counterweight engine 1 is fixed on rotating platform 5, rear skirt with
Left 31 free end of cantilever beam is fixedly linked, and 6 front skirt of test engine is supported on rotating platform 5 by experimental rig of changing direction,
Its rear skirt is fixedly connected with right 32 free end of cantilever beam.
Further, experimental rig of changing direction includes Thrust Measuring System 4；Thrust Measuring System 4 is fixed on rotating platform 5
On, measurement end and 6 front skirt of test engine contradict, for measuring the thrust of test engine 6.
Further, experimental rig of changing direction further includes rotary system 7, one end of which is fixed on rotating platform 5, the other end
It is driven cooperation (such as gear drive, V belt translation, chain conveyer and the Worm Wheel System kind of drive) with test engine 6, is used
It is rotated in driving test engine 6 around its own axis.
Further, as shown in Figures 3 and 4, rotary system 7 includes bearing B8, sleeve B9, engines gear shaft 10, motor
Gear shaft 11, connection ring 13, test tool 14 and motor 15；Engines gear shaft 10 is coaxially fixedly mounted on test engine 6
Rear skirt periphery；Sleeve B9 coaxial package is the tube structure of both ends aperture, both ends point in the periphery of test engine 6
Be not supported on the periphery of engines gear shaft 10 and the front skirt periphery of test engine 6 by bearing B8, right cantilever beam 32 from
It is fixed on sleeve B9 by end, opens up fan-shaped pylone within the scope of sleeve B9 circumferential direction set angle, motor gear axis 11 is mounted on electricity
The output end of machine 15 is simultaneously engaged across the fan-shaped pylone of sleeve B9 circumferential direction with engines gear shaft 10；Sleeve B9 passes through connection ring 13
It is fixedly connected with Thrust Measuring System 4, Thrust Measuring System 4 is fixedly connected with rotating platform 5, and then is realized test engine
6 are fixed on rotating platform 5, can rotate with rotating platform 5 around rotary shaft 2 but also rotate around own rotation axis；Wherein, motor
15 are fixedly mounted on rotating platform 5.
Further, rotary system 7 further includes test tool 14, and one end is fixedly connected with the front skirt of test engine 6,
The other end and Thrust Measuring System 4 are face contact, and guarantee test engine 6 can both be rotated with engines gear shaft 10 and be rotated
Thrust suffered by it can effectively be passed to Thrust Measuring System 4 again (because 6 front skirt end of test engine is hemispherical, to lead
It is point contact when it being caused to contact with Thrust Measuring System 4, is unable to effective force).
Further, engines gear shaft 10 is the multi-diameter shaft of both ends open, is relatively large in diameter end and motor gear axis 11
Engagement, the power of engines gear shaft 10 is acted on for carrying motor gear axis 11.
Embodiment 2:
A kind of two-freedom SPINNING SOLID ROCKET MOTOR overload igniting test method is present embodiments provided, this method is real
Apply simplicity, can effectively adjust solid propellant rocket overload born during fire trial overload direction.
The test method includes the following steps:
Step 1: the overload size being subjected to when being tested according to actual tests engine 6 determines the length of cantilever beam 3, will
Cantilever beam 3 is fixedly connected with the sleeve B9 of 6 periphery of test engine and counterweight engine 1 respectively；
Step 2: starting driving unit 12 drives rotating platform 5 to rotate, and drives the counterweight engine 1 being fixed thereon, examination
It issues after examination and approval motivation 6 and experimental rig of changing direction is rotated around rotary shaft 2；
Step 3: test engine 6 bears to overload (centripetal force) under rotational case, 6 ignition operation of test engine, into
Row overload fire trial；
Step 4: being required according to the actual overload of test engine 6, determine rotation direction of the test engine 6 around its own
And rotational angle；
Step 5: starting motor 15 drives motor gear axis 11 to rotate around own axes, and then drives engines gear shaft
10 rotate around own axes, since engines gear shaft 10 is fixedly connected with test engine 6, finally make test engine 6 around
Rotational angle determined by own axes rotation direction spin step 4 determined by the step 4, to change test engine
6 circumferential receiving overloads cross section.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (9)
1. two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device characterized by comprising counterweight engine
(1), rotary shaft (2), rotating platform (5), test engine (6) and experimental rig of changing direction；The rotary shaft (2) is fixed on rotation
Turn platform (5) center, the driving unit (12) is for driving the rotary shaft (2) to rotate, the counterweight engine (1) and examination
Motivation (6) is issued after examination and approval symmetrically to be fixed on rotating platform (5) along the rotary shaft (2)；The quality of the counterweight engine (1) is equal to
The quality of test engine (6) and experimental rig of changing direction and；The experimental rig of changing direction is for driving the test to start
Machine (6) is rotated around its own axis, to adjust the section excessively that test engine (6) bear overload, thus simulation test engine
(6) the circumferential different overload fire trials crossed on section.
2. two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as described in claim 1, which is characterized in that
The experimental rig of changing direction includes rotary system (7)；Described rotary system (7) one end is fixed on rotating platform (5), another
End cooperates with the test engine (6) transmission, for driving the test engine (6) to rotate around its own axis.
3. two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as claimed in claim 1 or 2, feature exist
In the experimental rig of changing direction further includes Thrust Measuring System (4)；The Thrust Measuring System (4) is fixed on rotating platform
(5) on, measurement end and the test engine (6) front skirt contradict and cooperate, for measuring pushing away for the test engine (6)
Power.
4. two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as claimed in claim 2, which is characterized in that
The rotary system (7) includes bearing B (8), sleeve B (9), engines gear shaft (10), motor gear axis (11), connection ring
(13) and motor (15)；The engines gear shaft (10) is coaxially fixed on the rear skirt periphery of test engine (6)；The sleeve
B (9) coaxial package is the tube structure of both ends aperture, both ends pass through bearing B respectively in the periphery of test engine (6)
(8) it is supported on the periphery of engines gear shaft (10) and the front skirt periphery of test engine (6), the sleeve B (9) circumferentially sets
Fan-shaped pylone is opened up in angular range, the motor gear axis (11) is mounted on the output end of motor (15) and passes through sleeve B (9)
Circumferential fan-shaped pylone is engaged with the engines gear shaft (10)；The sleeve B (9) passes through connection ring (13) and the thrust
Measuring system (4) is fixedly connected；Wherein, the motor (15) is fixedly mounted on rotating platform (5).
5. the two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as described in claim 1,2 or 4, feature
It is, further includes the above cantilever beam of a pair (3), each pair of cantilever beam (3) includes left cantilever beam (31) and right cantilever beam (32), each pair of
The fixing end of left cantilever beam (31) in cantilever beam (3) and the fixing end of right cantilever beam (32) are separately fixed at rotary shaft (2)
Same radial two opposite sides；The counterweight engine (1) and test engine (6) are outstanding by left cantilever beam (31) and the right side respectively
Arm beam (32) is symmetrically fixed on the two opposite sides of rotary shaft (2).
6. two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as claimed in claim 4, which is characterized in that
The rotary system (7) further includes test tool (14), and the front skirt of described test tool (14) one end and test engine (6) is solid
Fixed connection, the other end and the Thrust Measuring System (4) are face contact.
7. two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as described in claim 1, which is characterized in that
The driving unit (12) uses motor.
8. the two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device as described in claim 4 or 6, feature exist
In the engines gear shaft (10) is the multi-diameter shaft of both ends open, is relatively large in diameter end and the motor gear axis (11) is nibbled
It closes.
9. two-freedom SPINNING SOLID ROCKET MOTOR overload igniting test method, it uses igniting as claimed in claim 4
Experimental rig, which comprises the steps of:
Step 1: being subjected to practical overload when testing according to test engine (6), determine the length of each pair of cantilever beam (3) free end
Degree, each pair of cantilever beam (3) is fixedly connected with the sleeve B (9) of test engine (6) periphery and counterweight engine (1) respectively；
Step 2: starting driving unit (12) driving rotating platform (5) rotation, drive the counterweight engine (1) being fixed thereon,
Test engine (6) and experimental rig of changing direction are rotated around rotary shaft (2)；
Step 3: test engine (6) bears overload under rotational case, and test engine (6) ignition operation carries out overload point
Fire test；
Step 4: according to the actual overload requirement of test engine (6), determining rotation direction of the test engine (6) around its own
And rotational angle；
Step 5: starting motor (15) drives motor gear axis (11) to rotate around own axes, and then drives engines gear shaft
(10) it is rotated around own axes, so that test engine (6) rotation direction determined by the step 4 be driven to rotate around own axes
The rotational angle determined in step 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910598728.1A CN110307104B (en) | 2019-07-04 | 2019-07-04 | Two-degree-of-freedom rotary solid rocket engine overload ignition test device and test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910598728.1A CN110307104B (en) | 2019-07-04 | 2019-07-04 | Two-degree-of-freedom rotary solid rocket engine overload ignition test device and test method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110307104A true CN110307104A (en) | 2019-10-08 |
| CN110307104B CN110307104B (en) | 2020-07-14 |
Family
ID=68078143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910598728.1A Active CN110307104B (en) | 2019-07-04 | 2019-07-04 | Two-degree-of-freedom rotary solid rocket engine overload ignition test device and test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110307104B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113465928A (en) * | 2021-07-19 | 2021-10-01 | 北京理工大学 | Adjustable fixing frame for mounting multi-model solid engine under multiple swinging angles |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8584514B2 (en) * | 2010-05-18 | 2013-11-19 | Dresser-Rand Company | Axial loading device and method for magnetically-supported rotor systems |
| CN109236499A (en) * | 2018-11-02 | 2019-01-18 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method |
| CN109252982A (en) * | 2018-11-19 | 2019-01-22 | 北京理工大学 | The test method that solid propellant rocket nonlinear instability burns under overload condition |
| CN109488486A (en) * | 2018-11-06 | 2019-03-19 | 西安航天动力测控技术研究所 | A kind of spoke type clamp device and installation method for the full-scale solid propellant rocket of taper |
| CN109578169A (en) * | 2018-11-27 | 2019-04-05 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket dynamic centrifugal overload point fire test device and test method |
| CN110145410A (en) * | 2019-06-06 | 2019-08-20 | 北京理工大学 | A kind of end combustion powder charge solid propellant rocket for overloading experiment |
-
2019
- 2019-07-04 CN CN201910598728.1A patent/CN110307104B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8584514B2 (en) * | 2010-05-18 | 2013-11-19 | Dresser-Rand Company | Axial loading device and method for magnetically-supported rotor systems |
| CN109236499A (en) * | 2018-11-02 | 2019-01-18 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method |
| CN109488486A (en) * | 2018-11-06 | 2019-03-19 | 西安航天动力测控技术研究所 | A kind of spoke type clamp device and installation method for the full-scale solid propellant rocket of taper |
| CN109252982A (en) * | 2018-11-19 | 2019-01-22 | 北京理工大学 | The test method that solid propellant rocket nonlinear instability burns under overload condition |
| CN109578169A (en) * | 2018-11-27 | 2019-04-05 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket dynamic centrifugal overload point fire test device and test method |
| CN110145410A (en) * | 2019-06-06 | 2019-08-20 | 北京理工大学 | A kind of end combustion powder charge solid propellant rocket for overloading experiment |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113465928A (en) * | 2021-07-19 | 2021-10-01 | 北京理工大学 | Adjustable fixing frame for mounting multi-model solid engine under multiple swinging angles |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110307104B (en) | 2020-07-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205642791U (en) | Wind -tunnel is with toper motion simulation device of rotatory guided missile | |
| CN103123292B (en) | Folding wings pneumatic loading unfolding experiment device | |
| CN105424476B (en) | A kind of spherical plain bearing rod end dual-axis rotation load detection device | |
| CN107966264A (en) | One kind is used for hypersonic wind tunnel rolling forced vibration dynamic derivative experimental rig | |
| CN104596714B (en) | Ship propulsion shafting whirling vibration and twisting vibration simulation experiment device | |
| CN104807646B (en) | Solid propellant rocket is centrifuged the erecting device of overload test | |
| CN108825407A (en) | A kind of solid propellant rocket ground high overload test device | |
| CN107719696A (en) | A kind of dynamic characteristics synchronous testing device of axially compact type aircraft propeller | |
| CN107966265A (en) | One kind is used for hypersonic wind tunnel pitching yaw forced vibration dynamic derivative experimental rig | |
| CN110307104A (en) | Two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device and test method | |
| CN109540452A (en) | A kind of rotating missile arrow Three Degree Of Freedom angular movement simulation test device | |
| CN104165726A (en) | Calibration device for dynamometer | |
| CN113551910B (en) | Helicopter rotor system matched bearing testing machine and method | |
| JPH03238376A (en) | Simulation tester for wind power generation | |
| CN110606222A (en) | Pneumatic characteristic testing device for single rotor system of suspended Mars aircraft | |
| CN114061953B (en) | Bearing test device for butterfly separator | |
| CN212567790U (en) | Rotor unbalance fault simulation test bed | |
| CN109596358A (en) | A kind of full-automatic bearing vibration velocity test device | |
| CN113108972B (en) | Constant velocity ball cage universal joint contact force test bench and test method thereof | |
| CN105738086B (en) | A kind of aerial engine fan axis rotation moment of flexure loading method | |
| CN109060379A (en) | Rear driving axle transmission efficiency test method | |
| CN106468245B (en) | Wind driven generator dome support frame test device | |
| CN111829781A (en) | Joint bearing compound motion test device | |
| CN204575330U (en) | The erecting device of the centrifugal overload test of solid propellant rocket | |
| CN114813030B (en) | Wind tunnel high rotator rotating speed posture adjusting and correcting capability test board |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |