CN109236499A - A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method - Google Patents
A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method Download PDFInfo
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- CN109236499A CN109236499A CN201811302990.9A CN201811302990A CN109236499A CN 109236499 A CN109236499 A CN 109236499A CN 201811302990 A CN201811302990 A CN 201811302990A CN 109236499 A CN109236499 A CN 109236499A
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- rotatable cabin
- cabin
- rotatable
- fixed
- shaft
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Classifications
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- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Centrifugal Separators (AREA)
Abstract
The present invention proposes that a kind of solid propellant rocket varied angle is centrifuged overload point fire test device and test method, experimental rig include centrifuge transmission system, centrifugal basket arm system, counterweight cabin, instrument room and rotatable cabin；Rotatable cabin is arranged in the hollow structure of pivoted arm outer end, and rotatable cabin side is connect by shaft with pivoted arm；Rotatable cabin is also hinged by spiral regulating device and pivoted arm, by adjusting the length of spiral regulating device, is able to drive rotatable cabin around the shaft rotation connecting with pivoted arm.The present invention solves the nonadjustable problem of engine installation angle degree.The experimental rig structure novel, strong innovation, by verification experimental verification, engine installation and debugging are convenient, safe and reliable, meet centrifugation of the engine under varied angle overload and overload test-fired requirement.
Description
Technical field
The present invention relates to a kind of solid propellant rocket varied angles to be centrifuged overload point fire test device, belongs to solid-rocket hair
Motivation centrifugation overload igniting experimental technique field.
Background technique
Centrifugation overload fire trial occupation ratio in solid propellant rocket development process of solid propellant rocket is heavier
The status wanted.In order to simulate the different flight overload conditions of solid propellant rocket, need to carry out the axial load factor examination of engine
Test, transverse acceleration test and compbined test, therefore be centrifuged overload point fire test device need to have test adjustable angle function.
The centrifugation overload test of original different angle uses following testing program: supporting arc using the tooling of different angle
Seat adjusts the installation condition of engine with cluster engine zoarium, realizes the comprehensive adjustment of transverse acceleration and axial load factor value.I.e.
Each experimental viewpoint requires to support arc-shaped seat and cluster engine fit by corresponding tooling, causes to be tried in transformation angle
When testing, repeated disassembled and assembled tooling is needed, causes debugging link more, working efficiency is low.
Summary of the invention
In order to solve the problems existing in the prior art, the present invention proposes a kind of solid propellant rocket varied angle centrifugation overload point
Fire test device can be realized varied angle centrifugation overload point fire test device pivoting, and can lock in a certain angle,
To realize that engine installation condition is adjustable, meet the overload test demand of solid propellant rocket different angle.
The technical solution of the present invention is as follows:
A kind of solid propellant rocket varied angle centrifugation overload point fire test device, including centrifuge transmission system,
Centrifugal basket arm system, counterweight cabin and instrument room；Centrifugal basket arm system is mounted on centrifuge biography after being fixedly connected with counterweight cabin
In dynamic system, centrifuge transmission system is able to drive the rotation of centrifugal basket arm system, and instrument room is arranged in centrifugal basket arm system
Top is not rotated with centrifugal basket arm system；
It is characterized by also including rotatable cabins；
The pivoted arm outer end of the centrifugal basket arm system is hollow structure；
Frame-type hollow cylindrical rotatable cabin is arranged in the hollow structure of pivoted arm outer end, and rotatable cabin side passes through shaft
It is connect with pivoted arm two sides；The central axis of shaft intersects with the central axis upright of rotatable cabin, and intersection point is in rotatable cabin
Heart position；Rotational plane of the central axis of shaft also parallel with centrifugal basket arm system；Shaft one end is further fixed on angle quarter
Scale can show the rotational angle of rotatable cabin；
The connecting lugs that rotatable cabin also passes through both ends are hinged with the end of a spiral regulating device respectively, two spirals
The other end of formula regulating device is respectively articulated with two connecting lugs being fixed on pivoted arm, and the length of spiral regulating device
It is adjustable；By adjusting the length of spiral regulating device, rotatable cabin is able to drive around the shaft rotation connecting with pivoted arm two sides；
There is the bracket of fixed rocket motor machine clamp in rotatable cabin, machine clamp can be started to consolidate hollow circuit cylinder frame-type
It is scheduled in rotatable cabin, and keeps engine toolholder central axis conllinear with rotatable cabin central axis；Fixed rocket motor function to be measured
It is enough to be coaxially fixed in fixed rocket motor machine clamp.
Further preferred embodiment, a kind of solid propellant rocket varied angle centrifugation overload point fire test device,
Be characterized in that: connecting cylinder and two piece of the spiral regulating device by both ends with reversed internal screw thread are with externally threaded company
Extension bar composition；One is hinged with externally threaded connecting rod one end and the connecting lugs that are fixed on pivoted arm, other end external screw thread with
Connecting cylinder one end screw-internal thread fit；Another is cut with scissors with externally threaded connecting rod one end with the connecting lugs being fixed on rotatable cabin
It connects, other end external screw thread and connecting cylinder other end screw-internal thread fit；When connecting cylinder rotation, two connecting rods are in the same direction or reversed same
Moved further.
The centrifugation of solid propellant rocket varied angle, which is carried out, using above-mentioned experimental rig overloads test-fired method, feature
It is: the following steps are included:
Step 1: fixed rocket motor machine clamp being placed horizontally on a certain platform or ground, by fixed rocket engine
It lifts in fixed rocket motor machine clamp, and is fixedly connected；
Step 2: rotating rotatable cabin around the shaft to rotatable cabin axis and centrifuge pivoted arm system by spiral regulating device
System rotational plane plumbness；Angle dial is returned to zero, and locks rotatable cabin；
Step 3: machine clamp will be started to overturn equipped with solid propellant rocket using crane, machine clamp will be started to fill vertically
Enter in rotatable cabin, and is fixedly and coaxially connected with rotatable cabin；
Step 4: rotatable cabin shaft is unlocked, according to the overload of solid propellant rocket require, determine rotatable cabin around
The rotational angle of shaft；
Step 5: according to determining rotational angle, adjusting the length of spiral regulating device, rotatable cabin is made to go to corresponding angles
It is locked after degree；
Step: 6: centrifuge transmission system drives the rotation of centrifugal basket arm system, carries out centrifugation overload fire trial；
Step 7: being required according to next overload of solid propellant rocket, determine the angle of rotation of rotatable cabin around the shaft
Degree；Then repeat step 5 and step 6；Until completing all centrifugations overloads fire trial.
Beneficial effect
The present invention proposes a kind of solid propellant rocket varied angle centrifugation overload point fire test device, solves engine peace
Fill the nonadjustable problem of angle.The experimental rig structure novel, strong innovation, by verification experimental verification, engine installation and debugging side
Just, securely and reliably, meet centrifugation of the engine under varied angle overload and overload test-fired requirement.
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: solid propellant rocket varied angle is centrifuged overload point fire test device structure chart；
Wherein: 1, counterweight cabin；2, instrument room；3, centrifugal basket arm system；4, the first connecting lugs；5, the first spiral tune
Regulating device；6, the second connecting lugs；7, start machine clamp；8, solid propellant rocket；9, rotatable cabin；10, third connecting lugs；
11, the second spiral regulating device；12, the 4th connecting lugs；13, centrifuge transmission system.
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.
Furthermore, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Therefore, define " first ", the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
One of the present embodiment solid propellant rocket varied angle is centrifuged overload point fire test device, can be realized angle
Degree centrifugation overload point fire test device pivoting, and can be locked in a certain angle, to realize engine installation condition
It is adjustable, meet the overload test demand of solid propellant rocket different angle.
As shown in Figure 1, the solid propellant rocket varied angle is centrifuged overload point fire test device, including centrifuge power train
System, centrifugal basket arm system, counterweight cabin and instrument room；Centrifugal basket arm system is mounted on centrifuge after being fixedly connected with counterweight cabin
In transmission system, centrifuge transmission system is able to drive the rotation of centrifugal basket arm system, and instrument room is arranged in centrifuge pivoted arm system
System top, does not rotate with centrifugal basket arm system.
In the present embodiment, it further includes rotatable cabin that solid propellant rocket varied angle, which is centrifuged overload point fire test device,.Frame
Posture hollow cylindrical rotatable cabin is arranged in the hollow structure of pivoted arm outer end, and rotatable cabin side passes through shaft and pivoted arm two sides
Face connection；The central axis of shaft intersects with the central axis upright of rotatable cabin, and intersection point is in rotatable cabin center；Shaft
Central axis also parallel with centrifugal basket arm system rotational plane；Shaft one end is further fixed on angle dial, Neng Gouxian
Show the rotational angle of rotatable cabin.
The connecting lugs that rotatable cabin also passes through both ends are hinged with the end of a spiral regulating device respectively, two spirals
The other end of formula regulating device is respectively articulated with two connecting lugs being fixed on pivoted arm, and the length of spiral regulating device
It is adjustable；By adjusting the length of spiral regulating device, rotatable cabin is able to drive around the shaft rotation connecting with pivoted arm two sides.
Connecting cylinder and two piece of the spiral regulating device by both ends with reversed internal screw thread are with externally threaded connection
Bar composition；One hinged with externally threaded connecting rod one end and the connecting lugs that are fixed on pivoted arm, other end external screw thread and company
Connect cylinder one end screw-internal thread fit；Another is hinged with externally threaded connecting rod one end and the connecting lugs that are fixed on rotatable cabin,
Other end external screw thread and connecting cylinder other end screw-internal thread fit；When connecting cylinder rotation, two connecting rods are in the same direction or reverse sync
It is mobile.
There is the bracket of fixed rocket motor machine clamp in rotatable cabin, machine clamp can be started to consolidate hollow circuit cylinder frame-type
It is scheduled in rotatable cabin, and keeps engine toolholder central axis conllinear with rotatable cabin central axis；Fixed rocket motor function to be measured
It is enough to be coaxially fixed in fixed rocket motor machine clamp.
In the present embodiment, rotatable cabin can be used as the test platform of engine, and can be with pivoting, to realize
Engine installation condition is adjustable within the scope of 0 °~90 °, and (motor power is directed toward centrifugal rotary shaft at 0 °, and thrust is directed toward at 90 °
Ground), realize the test demand of engine transverse direction and the opposite variation of axial load factor.
Spiral regulating device is additionally used in the present embodiment, can not only pass through the length of the spiral regulating device of adjusting
Realize regulatory function of the engine installation condition within the scope of certain angle, and can be by adjusting spiral regulating device
Self-locking function prevents rotatable cabin from rotating during engine ignition.
The test-fired method of solid propellant rocket varied angle centrifugation overload is carried out using above-mentioned experimental rig specifically to wrap
Include following steps:
Step 1: fixed rocket motor machine clamp being placed horizontally on a certain platform or ground, by fixed rocket engine
It lifts in fixed rocket motor machine clamp, and is fixedly connected；
Step 2: rotating rotatable cabin around the shaft to rotatable cabin axis and centrifuge pivoted arm system by spiral regulating device
System rotational plane plumbness；Angle dial is returned to zero, and locks rotatable cabin；
Step 3: machine clamp will be started to overturn equipped with solid propellant rocket using crane, machine clamp will be started to fill vertically
Enter in rotatable cabin, and is fixedly and coaxially connected with rotatable cabin；
Step 4: rotatable cabin shaft is unlocked, according to the overload of solid propellant rocket require, determine rotatable cabin around
The rotational angle of shaft；
Step 5: according to determining rotational angle, adjusting the length of spiral regulating device, rotatable cabin is made to go to corresponding angles
It is locked after degree；
Step: 6: centrifuge transmission system drives the rotation of centrifugal basket arm system, carries out centrifugation overload fire trial；
Step 7: being required according to next overload of solid propellant rocket, determine the angle of rotation of rotatable cabin around the shaft
Degree；Then repeat step 5 and step 6；Until completing all centrifugations overloads fire trial.
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 (3)
1. a kind of solid propellant rocket varied angle is centrifuged overload point fire test device, including centrifuge transmission system, centrifuge
Boom system, counterweight cabin and instrument room；Centrifugal basket arm system is mounted on centrifuge transmission system after being fixedly connected with counterweight cabin
In, centrifuge transmission system is able to drive the rotation of centrifugal basket arm system, and instrument room is arranged in above centrifugal basket arm system, no
It is rotated with centrifugal basket arm system；
It is characterized by also including rotatable cabins；
The pivoted arm outer end of the centrifugal basket arm system is hollow structure；
Frame-type hollow cylindrical rotatable cabin is arranged in the hollow structure of pivoted arm outer end, and rotatable cabin side by shaft and turns
The connection of arm two sides；The central axis of shaft intersects with the central axis upright of rotatable cabin, and intersection point is in rotatable cabin centre bit
It sets；Rotational plane of the central axis of shaft also parallel with centrifugal basket arm system；Shaft one end is further fixed on angle dial,
It can show the rotational angle of rotatable cabin；
The connecting lugs that rotatable cabin also passes through both ends are hinged with the end of a spiral regulating device respectively, two spiral tune
The other end of regulating device is respectively articulated with two connecting lugs being fixed on pivoted arm, and the length of spiral regulating device can
It adjusts；By adjusting the length of spiral regulating device, rotatable cabin is able to drive around the shaft rotation connecting with pivoted arm two sides；
There is the bracket of fixed rocket motor machine clamp in rotatable cabin, machine clamp can be started to be fixed on hollow circuit cylinder frame-type
In rotatable cabin, and keep engine toolholder central axis conllinear with rotatable cabin central axis；Fixed rocket engine to be measured can be same
Axis is fixed in fixed rocket motor machine clamp.
2. a kind of solid propellant rocket varied angle is centrifuged overload point fire test device according to claim 1, feature exists
In: connecting cylinder and two piece of the spiral regulating device by both ends with reversed internal screw thread are with externally threaded connecting rod group
At；One hinged with externally threaded connecting rod one end and the connecting lugs that are fixed on pivoted arm, other end external screw thread and connecting cylinder
One end screw-internal thread fit；Another hinged with externally threaded connecting rod one end and the connecting lugs that are fixed on rotatable cabin, another
Hold external screw thread and connecting cylinder other end screw-internal thread fit；When connecting cylinder rotation, two connecting rods are in the same direction or reverse sync is mobile.
3. a kind of test-fired using the progress solid propellant rocket varied angle centrifugation overload of experimental rig described in claim 1
Method, it is characterised in that: the following steps are included:
Step 1: fixed rocket motor machine clamp being placed horizontally on a certain platform or ground, by fixed rocket engine lifting
Enter in fixed rocket motor machine clamp, and is fixedly connected；
Step 2: rotating rotatable cabin around the shaft to rotatable cabin axis and centrifugal basket arm system by spiral regulating device and turn
Dynamic plane plumbness；Angle dial is returned to zero, and locks rotatable cabin；
Step 3: machine clamp will be started to overturn equipped with solid propellant rocket using crane, machine clamp will be started to be vertically loaded into rotation
Turn in cabin, and is fixedly and coaxially connected with rotatable cabin；
Step 4: rotatable cabin shaft being unlocked, is required according to the overload of solid propellant rocket, determines rotatable cabin around the shaft
Rotational angle；
Step 5: according to determining rotational angle, the length of spiral regulating device is adjusted, after so that rotatable cabin is gone to corresponding angle
Locking；
Step 6: centrifuge transmission system drives the rotation of centrifugal basket arm system, carries out centrifugation overload fire trial；
Step 7: being required according to next overload of solid propellant rocket, determine the rotational angle of rotatable cabin around the shaft；And
Step 5 and step 6 are repeated afterwards；Until completing all centrifugations overloads fire trial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811302990.9A CN109236499A (en) | 2018-11-02 | 2018-11-02 | A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811302990.9A CN109236499A (en) | 2018-11-02 | 2018-11-02 | A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109884267A (en) * | 2019-01-29 | 2019-06-14 | 北京理工大学 | The experimental provision and method measured for propellant multi-angle burn rate under overload condition |
| CN110307104A (en) * | 2019-07-04 | 2019-10-08 | 北京灵动飞天动力科技有限公司 | Two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device and test method |
| RU200539U1 (en) * | 2020-07-07 | 2020-10-28 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ Военная академия Ракетных войск стратегического назначения имени Петра Великого МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATING MODES OF A ROCKET ENGINE FOR SOLID FUEL |
| CN112012852A (en) * | 2020-09-02 | 2020-12-01 | 西安航天动力测控技术研究所 | Reverse-injection protection and collection device and method for solid rocket engine |
| CN112594095A (en) * | 2020-12-07 | 2021-04-02 | 西安航天动力测控技术研究所 | Solid rocket engine real-time variable-angle centrifugal overload ignition test device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109884267A (en) * | 2019-01-29 | 2019-06-14 | 北京理工大学 | The experimental provision and method measured for propellant multi-angle burn rate under overload condition |
| CN110307104A (en) * | 2019-07-04 | 2019-10-08 | 北京灵动飞天动力科技有限公司 | Two-freedom SPINNING SOLID ROCKET MOTOR overload point fire test device and test method |
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| CN112012852B (en) * | 2020-09-02 | 2021-06-18 | 西安航天动力测控技术研究所 | Reverse-injection protection and collection device and method for solid rocket engine |
| CN112594095A (en) * | 2020-12-07 | 2021-04-02 | 西安航天动力测控技术研究所 | Solid rocket engine real-time variable-angle centrifugal overload ignition test device |
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Application publication date: 20190118 |