CN111649100A - Floating support device of missile ramjet - Google Patents
Floating support device of missile ramjet Download PDFInfo
- Publication number
- CN111649100A CN111649100A CN202010419754.6A CN202010419754A CN111649100A CN 111649100 A CN111649100 A CN 111649100A CN 202010419754 A CN202010419754 A CN 202010419754A CN 111649100 A CN111649100 A CN 111649100A
- Authority
- CN
- China
- Prior art keywords
- wedge
- component
- ramjet
- seat
- shaped
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
- F16F15/067—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs using only wound springs
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M1/00—Frames or casings of engines, machines or apparatus; Frames serving as machinery beds
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2230/00—Purpose; Design features
- F16F2230/0011—Balancing, e.g. counterbalancing to produce static balance
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Connection Of Plates (AREA)
Abstract
The invention provides a missile ramjet floating support device, which comprises: a ramjet component, a nacelle unit, a screw component, a wedge block component, a spring component, a wedge seat component, and a shoe component; the screw rod component, the wedge-shaped block component, the spring component, the wedge-shaped seat component and the cushion seat component form a supporting unit; the supporting units are uniformly arranged at the front end of the cabin body unit along the circumferential direction; the screw rod component can extrude the spring component and enable the elastic force of the spring component to act on the wedge-shaped block component; the wedge shoe member is capable of pushing the wedge shoe member; the wedge shoe member is configured to maintain contact with a surface of the ramjet member as guided by the wedge shoe member. The invention can avoid the thrust eccentricity phenomenon of the ramjet.
Description
Technical Field
The invention relates to the technical field of missile launching, in particular to a missile ramjet floating support device.
Background
The existing missile ramjet and the cabin body are usually supported only in a small range at the tail part, and when the shell of the existing missile ramjet is heated and expands along the axial direction when the ramjet is ignited to work, the ramjet is separated from the cabin body so as to ensure the safety of the missile structure, but the tail part of the ramjet is in a suspended state and lacks of floating support positioning, so that the ramjet generates a thrust eccentricity phenomenon.
Patent document CN110666726A discloses a floating support device, which mainly includes a ball head shaft, a ball head sleeve, a copper sleeve, a rotating sleeve, a threaded tightening sleeve, a connecting pin, a joint bearing, a bearing seat and a gland. The device adjusts the maximum static friction force of the movable ball head shaft by screwing the screw tightening sleeve on the conical surface; using a ball head shaft to obtain a spatial rotational degree of freedom; the zero-setting of the position of the device is achieved by the cooperation of the conical pin and the inner hole of the ball stud. The floating support device is matched with the gravity balance device for use, the pose of the assembly body is adjusted only by manually overcoming the maximum static friction force set by the device, and time and labor are saved. The operation is convenient and fast, and the device can be directly used by hands without learning and training after the installation is finished; with six degrees of freedom. The prior art needs a missile ramjet floating support device.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a missile ramjet floating support device.
According to the invention, the missile ramjet floating support device comprises: a ramjet component 1, a cabin unit 2, a screw component 3, a wedge block component 4, a spring component 5, a wedge seat component 6 and a shoe component 7; the screw rod component 3, the wedge-shaped block component 4, the spring component 5, the wedge-shaped seat component 6 and the cushion seat component 7 form a supporting unit; the supporting units are uniformly arranged at the front end of the cabin body unit 2 along the circumferential direction; the screw rod component 3 can extrude the spring component 5, and the elastic force of the spring component 5 acts on the wedge-shaped block component 4; said wedge shoe member 6 being capable of pushing the wedge shoe member 4; the wedge shoe member 4 is capable of maintaining contact with the surface of the ramjet component 1 as guided by the wedge shoe member 6.
Preferably, the pad member 7 is mounted to an outer surface of the cabin unit 2.
Preferably, the wedge shoe member 4 is mounted to the front end surface of the cabin unit 2.
Preferably, the shoe member 7 includes: a pad seat through hole; the shoe through hole is provided inside the shoe member 7.
Preferably, the wedge-shaped seat member 6 extends into the cabin unit 2; the wedge seat member 6 includes: dovetail grooves and dovetail tenons of the wedge seats; the dovetail groove of the wedge-shaped seat is matched with the dovetail tenon of the wedge-shaped seat; the dovetail groove of the wedge-shaped seat is arranged on the right side surface of the wedge-shaped seat component 6; the dovetail is provided on the left side of the dovetail seat member 6.
Preferably, said wedge-shaped block member 4 comprises: a wedge-shaped block counter bore; the shoe member 7 includes: a pad through hole and a pad screw; the counter bore of the wedge-shaped block is coaxial with the through hole of the cushion seat.
Preferably, the ramjet engine member 1 comprises: a ramjet engine; when the ramjet is ignited to work and expands axially, the wedge-shaped block component 4 moves radially under the extrusion of the spring component 5 and is always kept in contact with the surface of the ramjet, and the tail of the ramjet is supported in a floating mode.
Compared with the prior art, the invention has the following beneficial effects:
the missile ramjet floating support device provided by the invention can ensure that the tail part of the ramjet is not in a suspended state when the ramjet is ignited to work, and the floating support positioning is always carried out, so that the phenomenon of thrust eccentricity of the ramjet is avoided.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic view of the structural framework of the present invention.
In the figure:
ramjet engine component 1 spring component 5
Wedge-shaped seat component 6 of cabin unit 2
Screw member 3 shoe member 7
Wedge-shaped block member 4
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
According to the invention, the missile ramjet floating support device comprises: a ramjet component 1, a cabin unit 2, a screw component 3, a wedge block component 4, a spring component 5, a wedge seat component 6 and a shoe component 7; the screw rod component 3, the wedge-shaped block component 4, the spring component 5, the wedge-shaped seat component 6 and the cushion seat component 7 form a supporting unit; the supporting units are uniformly arranged at the front end of the cabin body unit 2 along the circumferential direction; the screw rod component 3 can extrude the spring component 5, and the elastic force of the spring component 5 acts on the wedge-shaped block component 4; said wedge shoe member 6 being capable of pushing the wedge shoe member 4; the wedge shoe member 4 is capable of maintaining contact with the surface of the ramjet component 1 as guided by the wedge shoe member 6.
Preferably, the pad member 7 is mounted to an outer surface of the cabin unit 2.
Preferably, the wedge shoe member 4 is mounted to the front end surface of the cabin unit 2.
Preferably, the shoe member 7 includes: a pad seat through hole; the shoe through hole is provided inside the shoe member 7.
Preferably, the wedge-shaped seat member 6 extends into the cabin unit 2; the wedge seat member 6 includes: dovetail grooves and dovetail tenons of the wedge seats; the dovetail groove of the wedge-shaped seat is matched with the dovetail tenon of the wedge-shaped seat; the dovetail groove of the wedge-shaped seat is arranged on the right side surface of the wedge-shaped seat component 6; the dovetail is provided on the left side of the dovetail seat member 6.
Preferably, said wedge-shaped block member 4 comprises: a wedge-shaped block counter bore; the shoe member 7 includes: a pad through hole and a pad screw; the counter bore of the wedge-shaped block is coaxial with the through hole of the cushion seat.
Preferably, the ramjet engine member 1 comprises: a ramjet engine; when the ramjet is ignited to work and expands axially, the wedge-shaped block component 4 moves radially under the extrusion of the spring component 5 and is always kept in contact with the surface of the ramjet, and the tail of the ramjet is supported in a floating mode.
Specifically, in one embodiment, as shown in fig. 1, the pad seat 7 and the wedge seat 6 are respectively installed on the outer surface and the front end surface of the cabin body 2, the pad seat 7 is internally provided with a through hole, the wedge seat 6 extends into the cabin body 2, and the right side surface is provided with a dovetail groove; the left side surface of the wedge block 4 is provided with a dovetail joint which is matched with a dovetail groove on the wedge seat 6, and a counter bore on the top of the wedge block 4 is coaxial with the through hole of the cushion seat 7; the screw 3 is mounted on a shoe 7 and presses against a spring 5 in a counter bore of the wedge 4, thereby urging the wedge 4 into contact with the surface of the ram engine 1, as shown in figure 1.
Further, when the ramjet engine 1 is ignited to work and expands axially, the wedge-shaped block 4 moves radially under the extrusion of the spring 5 and is always in contact with the surface of the ramjet engine 1, so that the tail of the ramjet engine 1 is supported in a floating mode.
The missile ramjet floating support device provided by the invention can ensure that the tail part of the ramjet is not in a suspended state when the ramjet is ignited to work, and the floating support positioning is always carried out, so that the phenomenon of thrust eccentricity of the ramjet is avoided.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (8)
1. A missile ramjet floating support device is characterized by comprising: the device comprises a ramjet component (1), a cabin unit (2), a screw component (3), a wedge block component (4), a spring component (5), a wedge seat component (6) and a cushion seat component (7);
the screw rod component (3), the wedge-shaped block component (4), the spring component (5), the wedge-shaped seat component (6) and the cushion seat component (7) form a supporting unit;
the supporting units are uniformly arranged at the front end of the cabin body unit (2) along the circumferential direction;
the screw rod component (3) can extrude the spring component (5) and enables the elastic force of the spring component (5) to act on the wedge-shaped block component (4);
the wedge-shaped seat component (6) can push the wedge-shaped block component (4);
the wedge-shaped block member (4) is capable of maintaining contact with the surface of the ramjet member (1) guided by the wedge-shaped seat member (6).
2. Missile ramjet floating support according to claim 1, characterized in that the pad member (7) is mounted to the outer surface of the nacelle unit (2).
3. The missile ramjet floating support device as claimed in claim 1, wherein the wedge block member (4) is mounted to a front end surface of the nacelle unit (2).
4. The missile ramjet floating support device as claimed in claim 1, characterized in that the shoe member (7) comprises: a pad seat through hole;
the cushion seat through hole is arranged inside the cushion seat component (7).
5. Missile ramjet floating support device according to claim 1, characterized in that the wedge seat member (6) protrudes into the nacelle unit (2);
the wedge-shaped seat member (6) comprises: dovetail grooves and dovetail tenons of the wedge seats;
the dovetail groove of the wedge-shaped seat is matched with the dovetail tenon of the wedge-shaped seat;
the dovetail groove of the wedge-shaped seat is arranged on the right side surface of the wedge-shaped seat component (6);
the dovetail of the dovetail seat is arranged on the left side surface of the dovetail seat component (6).
6. Missile ramjet floating support device according to claim 1, characterized in that said wedge-shaped block member (4) comprises: a wedge-shaped block counter bore;
the shoe member (7) includes: a pad through hole and a pad screw;
the counter bore of the wedge-shaped block is coaxial with the through hole of the cushion seat.
7. The missile ramjet floating support device of claim 1,
the ramjet engine component (1) comprises: a ramjet engine;
when the ramjet is ignited to work and expands axially, the wedge-shaped block component (4) moves towards the radial direction under the extrusion of the spring component (5) and is always kept in contact with the surface of the ramjet, and the floating support for the tail of the ramjet is realized.
8. A missile ramjet floating support device is characterized by comprising: the device comprises a ramjet component (1), a cabin unit (2), a screw component (3), a wedge block component (4), a spring component (5), a wedge seat component (6) and a cushion seat component (7);
the screw rod component (3), the wedge-shaped block component (4), the spring component (5), the wedge-shaped seat component (6) and the cushion seat component (7) form a supporting unit;
the supporting units are uniformly arranged at the front end of the cabin body unit (2) along the circumferential direction;
the screw rod component (3) can extrude the spring component (5) and enables the elastic force of the spring component (5) to act on the wedge-shaped block component (4);
the wedge-shaped seat component (6) can push the wedge-shaped block component (4);
the wedge-shaped block component (4) can be kept in contact with the surface of the stamping engine component (1) under the guidance of the wedge-shaped seat component (6);
the pad seat component (7) is arranged on the outer surface of the cabin unit (2);
the wedge-shaped block component (4) is arranged on the front end surface of the cabin body unit (2);
the shoe member (7) includes: a pad seat through hole;
the cushion seat through hole is arranged inside the cushion seat component (7);
the wedge-shaped seat component (6) extends into the cabin unit (2);
the wedge-shaped seat member (6) comprises: dovetail grooves and dovetail tenons of the wedge seats;
the dovetail groove of the wedge-shaped seat is matched with the dovetail tenon of the wedge-shaped seat;
the dovetail groove of the wedge-shaped seat is arranged on the right side surface of the wedge-shaped seat component (6);
the dovetail joint of the wedge-shaped seat is arranged on the left side surface of the wedge-shaped seat component (6);
the wedge-shaped block member (4) comprises: a wedge-shaped block counter bore;
the shoe member (7) includes: a pad through hole and a pad screw;
the wedge-shaped block counter bore is coaxial with the cushion seat through hole;
the ramjet engine component (1) comprises: a ramjet engine;
when the ramjet is ignited to work and expands axially, the wedge-shaped block component (4) moves towards the radial direction under the extrusion of the spring component (5) and is always kept in contact with the surface of the ramjet, and the floating support for the tail of the ramjet is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010419754.6A CN111649100B (en) | 2020-05-18 | 2020-05-18 | Floating support device of missile ramjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010419754.6A CN111649100B (en) | 2020-05-18 | 2020-05-18 | Floating support device of missile ramjet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111649100A true CN111649100A (en) | 2020-09-11 |
| CN111649100B CN111649100B (en) | 2022-02-08 |
Family
ID=72345714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010419754.6A Active CN111649100B (en) | 2020-05-18 | 2020-05-18 | Floating support device of missile ramjet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111649100B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070252314A1 (en) * | 2006-04-28 | 2007-11-01 | Kazuhisa Yama | Vibration damper |
| CN202088006U (en) * | 2011-07-22 | 2011-12-28 | 北京北内设备工具有限公司 | Hydraulic locking self-adaptive bearing |
| CN102601629A (en) * | 2012-02-22 | 2012-07-25 | 盐城市鑫益达精密机械有限公司 | Mechanical self-locking floating support mechanism |
| CN207508714U (en) * | 2017-11-02 | 2018-06-19 | 内蒙古北方重工业集团有限公司 | The element floating support device adjusted with wedge mechanism |
-
2020
- 2020-05-18 CN CN202010419754.6A patent/CN111649100B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070252314A1 (en) * | 2006-04-28 | 2007-11-01 | Kazuhisa Yama | Vibration damper |
| CN202088006U (en) * | 2011-07-22 | 2011-12-28 | 北京北内设备工具有限公司 | Hydraulic locking self-adaptive bearing |
| CN102601629A (en) * | 2012-02-22 | 2012-07-25 | 盐城市鑫益达精密机械有限公司 | Mechanical self-locking floating support mechanism |
| CN207508714U (en) * | 2017-11-02 | 2018-06-19 | 内蒙古北方重工业集团有限公司 | The element floating support device adjusted with wedge mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111649100B (en) | 2022-02-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8083177B2 (en) | Means for preventing the rotation of a pin supporting a turbine engine suspension member | |
| EP1872895A3 (en) | Self-aligning tools and a mandrel with retension sleeve | |
| US9573694B2 (en) | Engine fastener for an aircraft | |
| CN109110162B (en) | Separation speed on-orbit adjustable device and manufacturing method thereof | |
| US20170305003A1 (en) | Extraction device for extracting a trim weight from a rotor blade | |
| CN111649100B (en) | Floating support device of missile ramjet | |
| CN112629805B (en) | Low-damping pitching dynamic supporting device for wind tunnel free oscillation test | |
| CN104677201A (en) | Pucker rudder development mechanism for quickly adjusting attack angle | |
| CN108019214A (en) | A kind of support boots of shield machine propulsion device | |
| CN114200634A (en) | Space camera directional reflector assembly | |
| CN204495199U (en) | The folding rudder development mechanism of a kind of rapid adjustment angle of attack | |
| CN104713426B (en) | The laterally folded aerofoil of a kind of sliding wedge formula | |
| CN104590545A (en) | Three-directional self-adapted connection device for axial separation of aircraft fairing | |
| CN110666726A (en) | Floating support device | |
| CN113319551B (en) | Automatic loading device for bearing press-fitting and bearing press-fitting method | |
| CN207905808U (en) | A kind of support boots of shield machine propulsion device | |
| CN211281514U (en) | Unmanned aerial vehicle rocket booster guide structure that drops | |
| CN208736662U (en) | A kind of rotatable shaft that complying with end deflection deformation is to bearing | |
| CN107354865A (en) | Prevent the bearing that bridge topples | |
| CN109747867B (en) | Vector adjustment mechanism for electric thruster | |
| US3159221A (en) | Clamp ring | |
| CN111271375A (en) | Novel joint bearing | |
| CN214741730U (en) | Carrier rocket engine sways strutting arrangement and trip machine wabbler mechanism | |
| CN107608066B (en) | Locking device applied to module butt joint and butt joint locking method thereof | |
| JP2019074125A (en) | damper |
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 |