CN107503863A - A kind of nozzle thrust governor motion of solid propellant rocket - Google Patents
A kind of nozzle thrust governor motion of solid propellant rocket Download PDFInfo
- Publication number
- CN107503863A CN107503863A CN201710796363.4A CN201710796363A CN107503863A CN 107503863 A CN107503863 A CN 107503863A CN 201710796363 A CN201710796363 A CN 201710796363A CN 107503863 A CN107503863 A CN 107503863A
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- Prior art keywords
- jet pipe
- hole
- section
- probe
- fitting section
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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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
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- 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 belongs to Design of Solid Propellant Rocket Engine field, it is related to a kind of nozzle thrust governor motion of solid propellant rocket.It includes jet pipe mounting seat (2) and jet pipe (4), it is characterised in that：By a breathing area governor motion being made up of actuation mechanism (1), probe (3) and sealing ring (5).The invention provides a kind of nozzle thrust governor motion of solid propellant rocket, reduce energy loss, simplify system, reduce system dimension and space requirement, reduce system weight.
Description
Technical field
The invention belongs to Design of Solid Propellant Rocket Engine field, is related to a kind of nozzle thrust regulation of solid propellant rocket
Mechanism.
Background technology
During solid propellant rocket use, it is often necessary to adjust thrust to adapt to different applying working conditions.It is existing
In technology, typically it is laid out using symmetrical jet pipe, the angle that presence can change between symmetrical jet pipe, passes through the size of adjustment angle
So as to form different synthesis thrust, the technology exist larger energy liquidate loss, system complex, size is big, the peace that needs
Fill the problem of space is big, redundancy weight is big.
The content of the invention
The purpose of the present invention is：A kind of nozzle thrust governor motion of solid propellant rocket is provided, to reduce energy
Loss, simplify system, reduction system size and space requirement, reduce system weight.
The present invention technical solution be：A kind of nozzle thrust governor motion of solid propellant rocket, including jet pipe
Mounting seat 2 and jet pipe 4, jet pipe mounting seat 2 is with the air collecting chamber 2c with combustion chamber, air collecting chamber 2c left side wall and right side wall
It is parallel, there is jet pipe that screwed hole 2d is installed on air collecting chamber 2c right side wall, described jet pipe 4 is Laval nozzle, the left end of jet pipe 4
External screw thread be screwed into jet pipe installation screwed hole 2d；It is characterized in that：There is one by 5 groups of actuation mechanism 1, probe 3 and sealing ring
Into breathing area governor motion；Actuation mechanism 1 is fixed by screws on air collecting chamber 2c left side wall, on an air collecting chamber 2c left side
There are a through hole 2a, through hole 2a and jet pipe installation screwed hole 2d coaxial in side wall, there is the sealing of annular on through hole 2a inwall
Groove 2b, sealing ring 5 are located in seal groove 2b；Described probe 3 is from left to right divided into 2 sections, is column sealed section of 3a and cone respectively
Shape fitting section 3c, column sealed section of 3a external diameter is less than taper fitting section 3c maximum outside diameter, taper fitting section 3c external diameter from
Left-to-right gradually convergence, the cone angle of taper fitting section 3c 4 left sections of converging portion inner chambers of cone angle and jet pipe is consistent, the left section of receipts of jet pipe 4
The length for holding back section inner chamber is more than taper fitting section 3c length；The left end of probe 3 pass through through hole 2a after with inside actuation mechanism 1
Axis connection is driven, the external diameter of probe 3 coordinates with through hole 2a internal diameter gap；Under the driving of actuation mechanism 1, probe 3 can be left
Move right, taper fitting section 3c and jet pipe 4 distance is changed, taper fitting section 3c and jet pipe 4 distance are nearer, ventilation
Area is smaller；Taper fitting section 3c and jet pipe 4 distance are more remote, and breathing area is bigger, realizes the regulation of breathing area.
A kind of nozzle thrust governor motion of solid propellant rocket, including a jet pipe mounting seat 2 and 2~6 sprays
Pipe 4, jet pipe mounting seat 2 is with the air collecting chamber 2c with combustion chamber, and air collecting chamber 2c left side wall is parallel with right side wall, in gas collection
There is 2~6 jet pipes installation screwed hole 2d being uniformly distributed along the circumference on chamber 2c right side wall, the axis of above-mentioned circumference is solid-rocket
The axis of engine, jet pipe installation screwed hole 2d quantity are identical with the quantity of jet pipe 4；Described jet pipe 4 is Laval nozzle,
The external screw thread of the left end of jet pipe 4 is screwed into jet pipe installation screwed hole 2d；It is characterized in that：There are 2~6 structure identical ventilation faces
Product governor motion, each breathing area governor motion are made up of actuation mechanism 1, probe 3 and sealing ring 5, breathing area regulation machine
The quantity of structure is identical with the quantity of jet pipe 4, the position of each breathing area governor motion and the position correspondence of a jet pipe 4；Make
Motivation structure 1 is fixed by screws on air collecting chamber 2c left side wall, there is through hole 2a on air collecting chamber 2c left side wall, through hole 2a with
Jet pipe installation screwed hole 2d is coaxial, there is the seal groove 2b of annular on through hole 2a inwall, and sealing ring 5 is located in seal groove 2b；
Described probe 3 is from left to right divided into 2 sections, is column sealed section of 3a and taper fitting section 3c respectively, and column sealed section of 3a's is outer
Footpath is less than taper fitting section 3c maximum outside diameter, and taper fitting section 3c external diameter is from left to right gradually restrained, taper fitting section 3c
4 left sections of converging portion inner chambers of cone angle and jet pipe cone angle it is consistent, the length of 4 left sections of converging portion inner chambers of jet pipe is more than taper fitting section
3c length；The left end of probe 3 pass through through hole 2a after with the driving axis connection inside actuation mechanism 1, the external diameter and through hole of probe 3
2a internal diameter gap coordinates；Under the driving of actuation mechanism 1, probe 3 can move left and right, and make taper fitting section 3c and jet pipe 4
Distance change, taper fitting section 3c and jet pipe 4 distance it is nearer, breathing area is smaller；Taper is bonded section 3c and jet pipe 4
Distance it is more remote, breathing area is bigger, realizes the regulation of breathing area；When carrying out the regulation of breathing area, all jet pipes 4 are logical
The summation of gas area keeps constant.
It is an advantage of the invention that：A kind of nozzle thrust governor motion of solid propellant rocket is provided, reduces energy
Loss, simplifies system, reduces system dimension and space requirement, reduce system weight.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention.
Fig. 2 is the structural representation of jet pipe mounting seat in the present invention.
Fig. 3 is the structural representation of middle probe of the present invention.
Embodiment
The present invention is described in further details below.Referring to Fig. 1 to Fig. 3, a kind of jet pipe of solid propellant rocket pushes away
Power governor motion, including jet pipe mounting seat 2 and jet pipe 4, jet pipe mounting seat 2 is with the air collecting chamber 2c with combustion chamber, gas collection
Chamber 2c left side wall is parallel with right side wall, has jet pipe to install screwed hole 2d on air collecting chamber 2c right side wall, and described jet pipe 4 is
Laval nozzle, the external screw thread of the left end of jet pipe 4 are screwed into jet pipe installation screwed hole 2d；It is characterized in that：There is one by making motivation
The breathing area governor motion that structure 1, probe 3 and sealing ring 5 form；Actuation mechanism 1 is fixed by screws in an air collecting chamber 2c left side
In side wall, there are a through hole 2a, through hole 2a and jet pipe installation screwed hole 2d coaxial on air collecting chamber 2c left side wall, in through hole 2a
Inwall on have the seal groove 2b of annular, sealing ring 5 is located in seal groove 2b；Described probe 3 is from left to right divided into 2 sections, point
It is not column sealed section of 3a and taper fitting section 3c, column sealed section of 3a maximum outside diameter of the external diameter less than taper fitting section 3c,
Taper fitting section 3c external diameter is from left to right gradually restrained, taper fitting section 3c cone angle and 4 left sections of converging portion inner chambers of jet pipe
Cone angle is consistent, and the length of 4 left sections of converging portion inner chambers of jet pipe is more than taper fitting section 3c length；The left end of probe 3 passes through through hole
Coordinate after 2a with the driving axis connection inside actuation mechanism 1, the external diameter of probe 3 with through hole 2a internal diameter gap；In actuation mechanism 1
Driving under, probe 3 can move left and right, make taper fitting section 3c and jet pipe 4 distance change, taper fitting section 3c and
The distance of jet pipe 4 is nearer, and breathing area is smaller；Taper fitting section 3c and jet pipe 4 distance are more remote, and breathing area is bigger, realizes
The regulation of breathing area.
A kind of nozzle thrust governor motion of solid propellant rocket, including a jet pipe mounting seat 2 and 2~6 sprays
Pipe 4, jet pipe mounting seat 2 is with the air collecting chamber 2c with combustion chamber, and air collecting chamber 2c left side wall is parallel with right side wall, in gas collection
There is 2~6 jet pipes installation screwed hole 2d being uniformly distributed along the circumference on chamber 2c right side wall, the axis of above-mentioned circumference is solid-rocket
The axis of engine, jet pipe installation screwed hole 2d quantity are identical with the quantity of jet pipe 4；Described jet pipe 4 is Laval nozzle,
The external screw thread of the left end of jet pipe 4 is screwed into jet pipe installation screwed hole 2d；It is characterized in that：There are 2~6 structure identical ventilation faces
Product governor motion, each breathing area governor motion are made up of actuation mechanism 1, probe 3 and sealing ring 5, breathing area regulation machine
The quantity of structure is identical with the quantity of jet pipe 4, the position of each breathing area governor motion and the position correspondence of a jet pipe 4；Make
Motivation structure 1 is fixed by screws on air collecting chamber 2c left side wall, there is through hole 2a on air collecting chamber 2c left side wall, through hole 2a with
Jet pipe installation screwed hole 2d is coaxial, there is the seal groove 2b of annular on through hole 2a inwall, and sealing ring 5 is located in seal groove 2b；
Described probe 3 is from left to right divided into 2 sections, is column sealed section of 3a and taper fitting section 3c respectively, and column sealed section of 3a's is outer
Footpath is less than taper fitting section 3c maximum outside diameter, and taper fitting section 3c external diameter is from left to right gradually restrained, taper fitting section 3c
4 left sections of converging portion inner chambers of cone angle and jet pipe cone angle it is consistent, the length of 4 left sections of converging portion inner chambers of jet pipe is more than taper fitting section
3c length；The left end of probe 3 pass through through hole 2a after with the driving axis connection inside actuation mechanism 1, the external diameter and through hole of probe 3
2a internal diameter gap coordinates；Under the driving of actuation mechanism 1, probe 3 can move left and right, and make taper fitting section 3c and jet pipe 4
Distance change, taper fitting section 3c and jet pipe 4 distance it is nearer, breathing area is smaller；Taper is bonded section 3c and jet pipe 4
Distance it is more remote, breathing area is bigger, realizes the regulation of breathing area；When carrying out the regulation of breathing area, all jet pipes 4 are logical
The summation of gas area keeps constant.
The present invention operation principle be：Probe 3 is axially moveable under the driving of actuation mechanism 1, makes taper fitting section 3c
Changed with the distance of 4 left sections of converging portion walls of jet pipe, so that the breathing area between jet pipe 4 and probe 3 becomes
Change, thrust caused by jet pipe 4 is by the gas pressure that nozzle block 2, probe 3, each part surfaces externally and internally of jet pipe 4 are born along jet pipe axle
Line is made a concerted effort, therefore breathing area changes between jet pipe 4 and probe 3, and gas pressure distribution everywhere can become therewith
Change, so as to thrust size caused by adjustable jet tube 4.
In the presence of 2~6 each comfortable actuation mechanisms 1 of structure identical breathing area governor motion, according to predetermined
Program adjusts the position of probe 3, and the regulation program of probe 3 is ensured in 2~6 structure identical breathing area governor motions
Breathing area summation it is constant, the needs that thrust size is produced according to each jet pipe are set, each breathing area governor motion
Cooperating can make solid propellant rocket produce different thrust, realize that thrust is adjusted.
Embodiment 1
A kind of nozzle thrust governor motion of solid propellant rocket, including jet pipe mounting seat 2 and jet pipe 4, jet pipe installation
Seat 2 is with the air collecting chamber 2c with combustion chamber, and air collecting chamber 2c left side wall is parallel with right side wall, in air collecting chamber 2c right side wall
On have jet pipe that screwed hole 2d is installed, described jet pipe 4 be Laval nozzle, and the external screw thread of the left end of jet pipe 4 is screwed into jet pipe and installs spiral shell
In pit 2d；It is characterized in that：By a breathing area governor motion being made up of actuation mechanism 1, probe 3 and sealing ring 5.Make
Motivation structure 1 uses hydraulic actuator.Actuation mechanism 1 can also use combustion gas actuator or electric actuator.
Embodiment 2
A kind of nozzle thrust governor motion of solid propellant rocket, including a jet pipe mounting seat 2 and 3 jet pipes 4, spray
Pipe mounting seat 2 is with the air collecting chamber 2c with combustion chamber, and air collecting chamber 2c left side wall is parallel with right side wall, air collecting chamber 2c's
There is the 3 jet pipes installation screwed hole 2d being uniformly distributed along the circumference on right side wall, the axis of above-mentioned circumference is the axle of solid propellant rocket
Line, jet pipe installation screwed hole 2d quantity are identical with the quantity of jet pipe 4；Described jet pipe 4 is Laval nozzle, the left end of jet pipe 4
External screw thread be screwed into jet pipe installation screwed hole 2d；It is characterized in that：There are 3 structure identical breathing area governor motions, often
Individual breathing area governor motion is made up of actuation mechanism 1, probe 3 and sealing ring 5.Actuation mechanism 1 uses electric actuator.
Claims (2)
1. a kind of nozzle thrust governor motion of solid propellant rocket, including jet pipe mounting seat (2) and jet pipe (4), jet pipe peace
Seat (2) is filled with the air collecting chamber (2c) with combustion chamber, the left side wall of air collecting chamber (2c) is parallel with right side wall, in air collecting chamber
Have jet pipe that screwed hole (2d) is installed on the right side wall of (2c), described jet pipe (4) be Laval nozzle, jet pipe (4) left end outside
It is screwed into jet pipe installation screwed hole (2d)；It is characterized in that：There is one by actuation mechanism (1), probe (3) and sealing ring
(5) the breathing area governor motion of composition；Actuation mechanism (1) is fixed by screws on air collecting chamber (2c) left side wall, is being collected
There is a through hole (2a) on the left side wall of air cavity (2c), through hole (2a) installs screwed hole (2d) coaxially with jet pipe, at through hole (2a)
Inwall on have the seal groove (2b) of annular, it is interior that sealing ring (5) be located at seal groove (2b)；Described probe (3) from left to right divides
It is column sealed section (3a) and taper fitting section (3c) respectively for 2 sections, the external diameter of column sealed section (3a) is less than taper fitting section
The maximum outside diameter of (3c), the external diameter of taper fitting section (3c) are from left to right gradually restrained, the cone angle of taper fitting section (3c) and spray
The cone angle of pipe (4) left section of converging portion inner chamber is consistent, and the length of jet pipe (4) left section of converging portion inner chamber is more than taper fitting section (3c)
Length；The left end of probe (3) through through hole (2a) the driving axis connection internal with actuation mechanism (1) afterwards, the external diameter of probe (3) with
The internal diameter gap of through hole (2a) coordinates；Under the driving of actuation mechanism (1), probe (3) can move left and right, and taper is bonded section
(3c) and the distance of jet pipe (4) change, and taper fitting section (3c) and the distance of jet pipe (4) are nearer, and breathing area is smaller；Cone
Shape fitting section (3c) and the distance of jet pipe (4) are more remote, and breathing area is bigger, realizes the regulation of breathing area.
2. a kind of nozzle thrust governor motion of solid propellant rocket, including a jet pipe mounting seat (2) and 2~6 sprays
Manage (4), jet pipe mounting seat (2) is put down with the air collecting chamber (2c) with combustion chamber, the left side wall of air collecting chamber (2c) with right side wall
OK, there is 2~6 jet pipes installation screwed hole (2d) being uniformly distributed along the circumference on air collecting chamber (2c) right side wall, above-mentioned circumference
Axis is the axis of solid propellant rocket, and the quantity of jet pipe installation screwed hole (2d) is identical with the quantity of jet pipe (4)；Described
Jet pipe (4) is Laval nozzle, and the external screw thread of jet pipe (4) left end is screwed into jet pipe installation screwed hole (2d)；It is characterized in that：Have
2~6 structure identical breathing area governor motions, each breathing area governor motion is by actuation mechanism (1), probe (3)
Formed with sealing ring (5), the quantity of breathing area governor motion is identical with the quantity of jet pipe (4), and each breathing area adjusts machine
The position of structure and the position correspondence of a jet pipe (4)；Actuation mechanism (1) is fixed by screws in air collecting chamber (2c) left side wall
On, there is through hole (2a) on air collecting chamber (2c) left side wall, through hole (2a) installs screwed hole (2d) coaxially with jet pipe, in through hole
There is the seal groove (2b) of annular on the inwall of (2a), sealing ring (5) is located in seal groove (2b)；Described probe (3) from a left side to
The right side is divided into 2 sections, is column sealed section (3a) and taper fitting section (3c) respectively, and the external diameter of column sealed section (3a) pastes less than taper
The maximum outside diameter of section (3c) is closed, the external diameter of taper fitting section (3c) is from left to right gradually restrained, the cone angle of taper fitting section (3c)
Consistent with the cone angle of jet pipe (4) left section of converging portion inner chamber, the length of jet pipe (4) left section of converging portion inner chamber is more than taper fitting section
The length of (3c)；The left end of probe (3) passes through driving axis connection of the through hole (2a) afterwards with actuation mechanism (1) inside, probe (3)
The internal diameter gap of external diameter and through hole (2a) coordinates；Under the driving of actuation mechanism (1), probe (3) can move left and right, and make taper
Fitting section (3c) and the distance of jet pipe (4) change, and taper fitting section (3c) and the distance of jet pipe (4) are nearer, breathing area
It is smaller；Taper fitting section (3c) and the distance of jet pipe (4) are more remote, and breathing area is bigger, realizes the regulation of breathing area；Carry out
During the regulation of breathing area, the summation of all jet pipe (4) breathing areas keeps constant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710796363.4A CN107503863A (en) | 2017-09-06 | 2017-09-06 | A kind of nozzle thrust governor motion of solid propellant rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710796363.4A CN107503863A (en) | 2017-09-06 | 2017-09-06 | A kind of nozzle thrust governor motion of solid propellant rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107503863A true CN107503863A (en) | 2017-12-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710796363.4A Pending CN107503863A (en) | 2017-09-06 | 2017-09-06 | A kind of nozzle thrust governor motion of solid propellant rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107503863A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871784A (en) * | 2018-04-27 | 2018-11-23 | 北京航天动力研究所 | A kind of fixation device for the test of liquid rocket engine thrust chamber air-flow |
| CN109027504A (en) * | 2018-10-25 | 2018-12-18 | 天津市源翔市政工程有限公司 | A kind of gas pipeline flow regulator |
| CN112780448A (en) * | 2021-01-26 | 2021-05-11 | 北京灵动飞天动力科技有限公司 | Thrust adjusting mechanism of solid rocket engine |
| CN114877378A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Inner ring detonation combustion chamber |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871784A (en) * | 2018-04-27 | 2018-11-23 | 北京航天动力研究所 | A kind of fixation device for the test of liquid rocket engine thrust chamber air-flow |
| CN109027504A (en) * | 2018-10-25 | 2018-12-18 | 天津市源翔市政工程有限公司 | A kind of gas pipeline flow regulator |
| CN112780448A (en) * | 2021-01-26 | 2021-05-11 | 北京灵动飞天动力科技有限公司 | Thrust adjusting mechanism of solid rocket engine |
| CN114877378A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Inner ring detonation combustion chamber |
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Application publication date: 20171222 |
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