CN109252978A - A kind of control bar type change propulsive solid engines - Google Patents
A kind of control bar type change propulsive solid engines Download PDFInfo
- Publication number
- CN109252978A CN109252978A CN201811013127.1A CN201811013127A CN109252978A CN 109252978 A CN109252978 A CN 109252978A CN 201811013127 A CN201811013127 A CN 201811013127A CN 109252978 A CN109252978 A CN 109252978A
- Authority
- CN
- China
- Prior art keywords
- control rod
- throat
- bar type
- type change
- solid engines
- 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.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention discloses a kind of control bar type change propulsive solid engines, in nozzle throat, control rod is set, pass through rotating and reverse for motor, control rod is adjusted in the position of nozzle throat using gear mechanism, to change the sectional area of nozzle throat, can effectively adjustable jet tube throat sectional area, to realize the change propulsive of solid engines；Since control rod is designed in throat, combustion chamber powder charge will not be had an impact, passive quality is smaller.
Description
Technical field
The invention belongs to Solid Rocket Motor Technology fields, and in particular to a kind of control bar type change propulsive solid starts
Machine.
Background technique
Solid propellant rocket structure is simple, is easy to store, and has strong with survival ability fastly convenient for Flexible deployment, reaction
Advantage.Since its is at low cost, maintenance cost is few, solid engines have become the main propulsioning means of ordnance missile.Change propulsive skill
Art is an important development direction of solid propellant rocket, and compared with the scheduled engine of thrust, Variable Thrust Engine can be with
Its thrust is adjusted as needed, the mobility and flexibility of guided missile can be greatly improved, and improves the penetration ability and machine of guided missile
Dynamic interdiction capability, makes guided missile be able to carry out more complicated task and striking capabilities, has wide application prospect.
The method of control Thrust of Solid Rocket Motor includes that pulsed motor, flame-out engine, quality addition type start
Machine, variable nozzle throat area engine etc..Currently, realizing that the research of change propulsive is more by adjustable jet tube throat opening area, such as
Larynx hydrant change propulsive scheme changes the operating pressure of combustion chamber, to realize solid engines by changing nozzle throat area
Change propulsive.However, the structure of traditional larynx hydrant Variable Thrust Engine is complex, change propulsive mechanism needs, which extend to, to be started
Chain-drive section is unfavorable for the design of combustion chamber powder charge；Particularly with the solid engines of large scale big L/D ratio, longer pintle meeting
Lead to the bias in nozzle throat, the complexity of structure also will increase biggish passive quality.
Summary of the invention
In view of this, can solve tradition the object of the present invention is to provide a kind of control bar type change propulsive solid engines
The problem that structure is complicated for Variable Thrust Engine, passive quality is larger.
A kind of control bar type change propulsive solid engines, the throat of SRM Nozzle (1) are equipped with N number of control rod
(3)；Wherein, N is 2 multiple；Circumferential direction of the control rod (3) along throat section is evenly arranged at equal intervals；It stretches one end of control rod (3)
Enter into throat, the other end is external in jet pipe (1), and is provided with transmission component；Motor (4) passes through transmission component drive control stick
(3) along the radial motion of the throat.
Preferably, the transmission component is nibbled for the motor gear (41) on linear gear (33), with the transmission shaft of motor (4)
It closes.
Preferably, one end that the control rod (3) extend into throat is cylindrical section.
Preferably, the control rod (3) is placed in jet pipe (1) by the cylindrical hole that jet pipe (1) corresponding position opens up.
Preferably, control rod (3) and the cylindrical hole of jet pipe (1) use twice radial direction seal ring (2).
The invention has the following beneficial effects:
A kind of control bar type change propulsive solid engines of the invention are arranged control rod in nozzle throat, pass through motor
It rotates and reverse, adjusts control rod in the position of nozzle throat using gear mechanism, thus change the sectional area of nozzle throat, it can
With the sectional area of effective adjustable jet tube throat, to realize the change propulsive of solid engines；Since control rod is designed in throat, no
Combustion chamber powder charge can be had an impact, passive quality is smaller.
Detailed description of the invention
Fig. 1 is control bar type change propulsive solid engines structural schematic diagram of the invention；
Fig. 2 is control rod structural schematic diagram of the invention；
Fig. 3 is motor schematic diagram of the invention；
Wherein, 1-jet pipe；2-sealing rings；3-control rods；4-motors；31-cylindrical sections；32-seal grooves；33-is straight
Line gear；41-motor gears；42-motor output shafts；43-motor hosts.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
Fig. 1 gives the schematic diagram of control bar type change propulsive solid engines of the invention, the larynx of SRM Nozzle 1
Portion is equipped with N number of control rod 3, and (wherein, in order to guarantee the symmetry of motor power, N must be 2 multiple, and control rod 3 exists
Throat is spacedly distributed)；Radial direction of the control rod 3 along throat section is arranged；One end of control rod 3 is extend into throat, the other end
Outside jet pipe 1, and it is provided with transmission component；Motor 4 is by transmission component drive control stick 3 along the radial motion.
Specifically, the transmission component of the other end is straight as shown in Fig. 2, one end that control rod 3 extend into throat is cylindrical section
Line gear；Motor 4 includes motor gear 41, motor output shaft 42 and motor host 43；The linear gear and motor tooth of control rod 3
41 cooperation of wheel, by the positive and negative rotation of motor 4 come the movement of drive control stick 3.Control rod 3 is opened up by 1 corresponding position of jet pipe
Cylindrical hole is placed in jet pipe 1；The cylindrical hole of control rod 3 and jet pipe 1 uses twice radial direction seal ring 2, guarantees engine operation
In the process fire will not be worn from 3 position of control rod.
The working principle of control bar type change propulsive solid engines of the invention are as follows:
When control rod 3 does not stretch out in the cylindrical hole of jet pipe 1 completely, 1 throat opening area of jet pipe is maximum, engine operation pressure
Strong minimum, motor power is minimum；When needing to increase the thrust of engine, motor 4 is only needed to rotate forward, drives the straight of control rod 3
Line gear movement, makes control rod 3 to 1 internal motion of jet pipe, the sectional area of 1 throat of jet pipe reduces therewith, engine operation pressure
It increases, so as to cause the increase of motor power.Conversely, when control rod has stretched out cylindrical hole and reached maximum, 1 larynx of jet pipe
The sectional area in portion is minimum, engine operation pressure highest, and motor power is maximum；When needing to reduce the thrust of engine, only
Motor reversal is needed, the linear gear movement of control rod 3 is driven, control rod 3 is made constantly to enter jet pipe cylindrical hole, 1 throat of jet pipe
Sectional area increases with it, and engine operation pressure declines therewith, so as to cause the decline of motor power.
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 (5)
1. a kind of control bar type change propulsive solid engines, which is characterized in that the throat of SRM Nozzle (1) is equipped with N
A control rod (3)；Wherein, N is 2 multiple；Circumferential direction of the control rod (3) along throat section is evenly arranged at equal intervals；Control rod (3)
One end extend into throat, the other end is external in jet pipe (1), and is provided with transmission component；Motor (4) is driven by transmission component
The radial motion of dynamic control rod (3) along the throat.
2. a kind of control bar type change propulsive solid engines as described in claim 1, which is characterized in that the transmission component is
Linear gear (33) is engaged with the motor gear (41) on the transmission shaft of motor (4).
3. a kind of control bar type change propulsive solid engines as described in claim 1, which is characterized in that the control rod (3)
The one end for extending into throat is cylindrical section.
4. a kind of control bar type change propulsive solid engines as described in claim 1, which is characterized in that the control rod (3)
It is placed in jet pipe (1) by the cylindrical hole that jet pipe (1) corresponding position opens up.
5. a kind of control bar type change propulsive solid engines as claimed in claim 4, which is characterized in that control rod (3) and spray
The cylindrical hole for managing (1) uses twice radial direction seal ring (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811013127.1A CN109252978A (en) | 2018-08-31 | 2018-08-31 | A kind of control bar type change propulsive solid engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811013127.1A CN109252978A (en) | 2018-08-31 | 2018-08-31 | A kind of control bar type change propulsive solid engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109252978A true CN109252978A (en) | 2019-01-22 |
Family
ID=65049516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811013127.1A Pending CN109252978A (en) | 2018-08-31 | 2018-08-31 | A kind of control bar type change propulsive solid engines |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109252978A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657043A (en) * | 2019-09-09 | 2020-01-07 | 南京航空航天大学 | Mechanical disturbance type throat offset pneumatic vectoring nozzle |
| CN113788139A (en) * | 2021-10-26 | 2021-12-14 | 上海磐拓航空科技服务有限公司 | Method for accurately controlling aircraft track through multifunctional pneumatic control surface |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1283253A (en) * | 1997-08-12 | 2001-02-07 | 太空通道有限公司 | Ejector ramjet engine |
| CN103423032A (en) * | 2013-08-28 | 2013-12-04 | 南京理工大学 | Solid rocket ramjet fuel gas flow regulation device driven by linear motor |
| CN104612858A (en) * | 2015-01-29 | 2015-05-13 | 南京理工大学 | Adjustable double-pulse solid rocket engine jet pipe testing device |
| CN106050477A (en) * | 2016-07-28 | 2016-10-26 | 湖北航天技术研究院总体设计所 | Combined throat liner spraying pipe of solid rocket engine and manufacturing method |
| CN106286013A (en) * | 2016-08-26 | 2017-01-04 | 南京理工大学 | Electric plunger valve type solid rocket ramjet gas flow adjusting means |
-
2018
- 2018-08-31 CN CN201811013127.1A patent/CN109252978A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1283253A (en) * | 1997-08-12 | 2001-02-07 | 太空通道有限公司 | Ejector ramjet engine |
| CN103423032A (en) * | 2013-08-28 | 2013-12-04 | 南京理工大学 | Solid rocket ramjet fuel gas flow regulation device driven by linear motor |
| CN104612858A (en) * | 2015-01-29 | 2015-05-13 | 南京理工大学 | Adjustable double-pulse solid rocket engine jet pipe testing device |
| CN106050477A (en) * | 2016-07-28 | 2016-10-26 | 湖北航天技术研究院总体设计所 | Combined throat liner spraying pipe of solid rocket engine and manufacturing method |
| CN106286013A (en) * | 2016-08-26 | 2017-01-04 | 南京理工大学 | Electric plunger valve type solid rocket ramjet gas flow adjusting means |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657043A (en) * | 2019-09-09 | 2020-01-07 | 南京航空航天大学 | Mechanical disturbance type throat offset pneumatic vectoring nozzle |
| CN110657043B (en) * | 2019-09-09 | 2022-02-08 | 南京航空航天大学 | Mechanical disturbance type throat offset pneumatic vectoring nozzle |
| CN113788139A (en) * | 2021-10-26 | 2021-12-14 | 上海磐拓航空科技服务有限公司 | Method for accurately controlling aircraft track through multifunctional pneumatic control surface |
| CN113788139B (en) * | 2021-10-26 | 2024-05-24 | 上海磐拓航空科技服务有限公司 | Method for precisely controlling track of aircraft by using multifunctional pneumatic control surface |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190122 |