CN113945124A - Fairing air conditioner interface - Google Patents
Fairing air conditioner interface Download PDFInfo
- Publication number
- CN113945124A CN113945124A CN202111148308.7A CN202111148308A CN113945124A CN 113945124 A CN113945124 A CN 113945124A CN 202111148308 A CN202111148308 A CN 202111148308A CN 113945124 A CN113945124 A CN 113945124A
- Authority
- CN
- China
- Prior art keywords
- lock pin
- pipe orifice
- cover
- spring
- interface
- 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
Images
Classifications
-
- 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)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Air-Flow Control Members (AREA)
Abstract
The invention provides a dome air conditioning interface, comprising: the device comprises a cover, a pipe orifice, a rotating shaft, a lock pin and a spring; the pipe orifice comprises a pipe orifice inner ring and a pipe orifice outer ring; the first end of the opening cover is connected with the first end of the outer ring of the pipe orifice through a rotating shaft so as to open or close the pipe orifice in the fairing; the second end of the opening cover is provided with at least two lock pin mounting racks at intervals, and two ends of the lock pin are respectively connected with the opening cover through the two lock pin mounting racks; the spring is sleeved on the lock pin and used for resetting the lock pin; a sliding groove is formed in the second end of the pipe orifice outer ring, and the locking hole is communicated with one end of the sliding groove; wherein the locking hole is used for locking the lock pin when the cover closes the nozzle, and the sliding groove is used for guiding the lock pin during the closing process of the cover. This air conditioner interface can realize flap self-closing to effectively reduce the unable risk of closing of air conditioner interface flap.
Description
Technical Field
The invention relates to the field of carrier rockets, in particular to a fairing air conditioner interface.
Background
The carrier rocket fairing air-conditioning interface is used for being connected with a ground air-conditioning pipeline in a launching preparation stage and plugging the air-conditioning interface by adopting a cover after being separated from the ground air-conditioning pipeline. At present, a carrier rocket fairing air conditioner interface is arranged outside a fairing, and a cover has the risk of being incapable of being closed after a ground air conditioner pipeline is separated from the fairing air conditioner interface. If the covering cap can not be effectively closed, the closed environment of the effective load in the fairing can be damaged in the flight process of the carrier rocket, and the covering cap can fall off under the action of vibration and air flow, so that the hidden danger of redundancy is formed. In addition, the external fairing air conditioning interface can form fairing protrusions, which affect the aerodynamic characteristics of the carrier rocket.
In order to realize the automatic closing of the air conditioner interface opening cover and reduce the risk that the air conditioner interface opening cover cannot be closed, the design of the air conditioner interface of the fairing is very important.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a dome air conditioner interface.
The invention provides a dome air conditioning interface, comprising: the device comprises a cover, a pipe orifice, a rotating shaft, a lock pin and a spring; the pipe orifice comprises a pipe orifice inner ring and a pipe orifice outer ring, the pipe orifice inner ring is fixedly connected with the fairing, and the pipe orifice outer ring is connected with the opening cover through the rotating shaft and the lock pin; the first end of the cover cap is connected with the first end of the outer ring of the pipe orifice through a rotating shaft, and the cover cap is used for rotating around the rotating shaft relative to the pipe orifice so as to open or close the pipe orifice in the fairing; at least two lock pin mounting frames are arranged at the second end of the opening cover at intervals, two ends of each lock pin are respectively connected with the opening cover through the two lock pin mounting frames, and the two ends of each lock pin are slidably connected with the two lock pin mounting frames; a circle of bulges are arranged on the lock pin in the circumferential direction between the lock pin mounting frames; the spring is sleeved on the lock pin, one end of the spring props against the bulge, the other end of the spring props against the lock pin mounting rack close to the center of the opening cover, and the spring is used for enabling the lock pin to reset; a sliding groove is formed in the second end of the pipe orifice outer ring, and the locking hole is communicated with one end of the sliding groove; the locking hole is used for locking the lock pin when the mouth cover closes the nozzle, and the sliding groove is used for guiding the lock pin in the closing process of the mouth cover so as to facilitate the lock pin to enter the locking hole.
According to one embodiment of the invention, the device further comprises a torsion spring, wherein the torsion spring is sleeved on the rotating shaft; one support arm of the torsion spring is limited through the pipe orifice, and the other support arm of the torsion spring is limited through the opening cover.
According to one embodiment of the invention, the torsion spring comprises two torsion springs which are symmetrically arranged on two sides of the rotating shaft.
According to one embodiment of the invention, the first end of the opening cover is provided with a limiting groove perpendicular to the axial direction of the rotating shaft, and one arm of the torsion spring is placed in the limiting groove to limit one arm of the torsion spring; and the first end of the pipe orifice outer ring is correspondingly provided with a support so as to limit the other support arm of the torsion spring.
According to one embodiment of the invention, the limiting groove is formed by arranging two straight plates perpendicular to the axial direction of the rotating shaft at intervals; the support is a straight plate parallel to the axial direction of the pipe orifice.
According to one embodiment of the invention, the end of the lock pin remote from the edge of the flap is provided with a split collar for limiting the lock pin from coming out of the two lock pin mounting brackets towards the edge of the flap.
According to one embodiment of the invention, the lock pin is provided with a retainer ring clamping groove along the circumferential direction of the lock pin, the retainer ring clamping groove is a circle of groove, and the retainer ring clamping groove is used for installing the split retainer ring.
According to one embodiment of the invention, the lock pin is a stepped shaft with a thin shaft at one end and a thick shaft at the other end; the thin shaft of the lock pin is connected with the lock pin mounting bracket close to the center of the cover, and the thick shaft of the lock pin is connected with the lock pin mounting bracket far away from the center of the cover; the spring is sleeved on the thin shaft of the lock pin; the transition end surfaces of the thin shaft and the thick shaft form the bulge.
In another aspect, the present invention provides a fairing including the above air conditioning interface.
In a further aspect, the invention provides a launch vehicle comprising the air conditioning interface described above, or comprising the fairing described above.
According to the fairing air-conditioning interface, the opening cover is arranged inside the fairing, and the opening cover is pushed away towards the inside of the fairing when the ground air-conditioning pipeline is connected with the fairing air-conditioning interface. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover automatically closes the through hole of the pipe orifice under the action of gravity. Because the flap is inside opening at the radome fairing, consequently, carrier rocket takes off the back, according to Bernoulli's principle, because the gaseous high-speed flow in the radome fairing outside can make the flap more laminate the mouth of pipe, makes the flap automatic production sealed trend. Meanwhile, the cover cap and the pipe orifice are locked by the lock pin, the sealing state of the cover cap is reinforced, the influence of the cover cap on the environment of the effective load in the fairing due to the fact that the cover cap cannot be sealed is reduced, and the reliability of launching tasks is improved. Meanwhile, the aerodynamic shape of the carrier rocket is optimized, and the flight control capability of the carrier rocket is improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a perspective view of a launch vehicle fairing according to one embodiment of the invention;
FIG. 2 is a schematic diagram of a closed and open state of a cover of a cowling air conditioning interface in accordance with an embodiment of the present invention;
FIG. 3 is a schematic view of a closed state of a cover of the cowling air conditioning interface in accordance with one embodiment of the present invention;
FIG. 4 is a cross-sectional view taken along the line C-C of the right side view of FIG. 3;
FIG. 5 is an enlarged view of A in FIG. 4;
fig. 6 is an enlarged view of B in fig. 4.
Description of reference numerals:
1-opening cover, 2-locking pin, 3-spring, 4-split retainer ring, 5-nozzle, 6-torsion spring, 7-rotating shaft, 51-locking hole, 52-chute, 8-fairing, 9-air conditioner interface, 10-locking pin mounting rack, 11-lug plate, 12-limiting groove, 13-support, 14-nozzle inner ring and 15-nozzle outer ring.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purposes of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the elements or regions in the figures may be exaggerated relative to other elements or regions to help improve understanding of embodiments of the present invention.
The directional terms used in the following description are used in the illustrated directions, and do not limit the specific configurations of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as appropriate to those of ordinary skill in the art.
Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc., and are not particularly meant to imply a sequential or chronological meaning, and should not be taken as limiting. Like terms refer to like elements throughout the description.
In describing the present invention below, it is possible to use only "rockets", "launch vehicles" or "missiles" in a scenario description, which is for convenience of description only and the meaning is not limited to the specific words used. Generally, rockets of the invention include both launch vehicles for carrying satellites or spacecraft or other detectors, and weapons such as missiles, rocket projectiles of all types for carrying military loads, and similar products capable of launching payloads into the air. Those skilled in the art, in interpreting the above specific terms, should not be construed as limiting the vehicle to only one of a launch vehicle or a missile, depending on the specific terms used in describing the scenario, thereby narrowing the scope of the present invention.
It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention.
FIG. 1 is a perspective view of a launch vehicle fairing according to one embodiment of the invention; FIG. 2 is a schematic diagram of a closed and open state of a cover of a cowling air conditioning interface in accordance with an embodiment of the present invention; FIG. 3 is a schematic view of a closed state of a cover of the cowling air conditioning interface in accordance with one embodiment of the present invention; FIG. 4 is a cross-sectional view taken along the line C-C of the right side view of FIG. 3; FIG. 5 is an enlarged view of A in FIG. 4; fig. 6 is an enlarged view of B in fig. 4.
As shown in fig. 1 to 6, the present invention provides a dome air conditioning interface, comprising: the device comprises a cover 1, a nozzle 5, a rotating shaft 7, a lock pin 2 and a spring 3. The nozzle 1 comprises a nozzle inner ring 14 and a nozzle outer ring 15, the nozzle inner ring 14 is fixedly connected with the fairing 8, and the nozzle outer ring 15 is connected with the opening cover 1 through the rotating shaft 7 and the lock pin 2. Wherein the first end of flap 1 is connected through the pivot with the first end of mouth of pipe outer lane 15, and flap 1 is used for revolving about pivot 7 for mouth of pipe 5 to open or closed mouth of pipe 5 inside the radome fairing. At least two lockpin mounting brackets 10 are arranged at the second end of the opening cover 1 at intervals, the two ends of the lockpin 2 are respectively connected with the opening cover 1 through the two lockpin mounting brackets 10, and the two ends of the lockpin 2 are slidably connected with the two lockpin mounting brackets 10. The lock pin 2 is provided with a circle of bulges in the circumferential direction between the lock pin mounting frames 10, the spring 3 is sleeved on the lock pin 2, one end of the spring 3 is propped against the bulges, the other end of the spring 3 is propped against the lock pin mounting frame close to the center of the opening cover 1, and the spring 3 is used for enabling the lock pin 2 to reset. The second end of the nozzle outer ring 15 is provided with a sliding groove 52, and the locking hole 51 is communicated with one end of the sliding groove 52. The locking hole 51 is used for locking the lock pin 2 when the mouth cover 1 closes the nozzle 5, and the sliding groove 52 is used for guiding the lock pin 2 in the closing process of the mouth cover 1, so that the lock pin 2 can conveniently enter the locking hole 51.
Specifically, currently, the air-conditioning interface of the launch vehicle fairing is arranged outside the fairing, and the flap is usually of a flap structure and opens or closes the air-conditioning interface outside the fairing. When the ground air-conditioning pipeline is connected with the air-conditioning interface of the fairing, the opening cover needs to be opened manually. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover is closed under the action of the torsion spring, and the opening cover is limited to rebound through the tongue spring when closed. However, there is a risk that the flap cannot be closed after the ground air conditioning duct is separated from the cowling air conditioning interface. If the covering cap can not be effectively closed, the closed environment of the effective load in the fairing can be damaged in the flight process of the carrier rocket, and the covering cap can fall off under the action of vibration and air flow, so that the hidden danger of redundancy is formed. In addition, the external fairing air conditioning interface can form fairing protrusions, which affect the aerodynamic characteristics of the carrier rocket.
In this embodiment, the cover 1 of the air-conditioning interface 8 is disposed inside the cowling 8, and when the ground air-conditioning pipeline is connected to the cowling air-conditioning interface, the lock pin 2 is pulled out of the lock hole 51, and the cover 1 is rotated around the rotating shaft 7 to open toward the inside of the cowling. After the air-conditioning pipeline is connected with the air-conditioning interface of the fairing, the opening cover 1 is supported by the air-conditioning pipeline to keep an open circulation state. After ground air conditioner pipeline and radome fairing air conditioner interface separation, flap 1 revolutes 7 to 5 directions rotations of mouth of pipe, treat that flap 1 contacts mouth of pipe 5 to the flap when closing mouth of pipe 5 completely, make lockpin 2 remove certain distance (for example, artifical pulling lockpin 2) to flap 1 central direction, spring 3 receives extrusion deformation this moment, lockpin 2 reachs locking hole 51 under the guide of spout 52, when flap 1 closes completely, spring 3 kick-backs, make lockpin 2 reset, the one end that lockpin 2 kept away from flap 1 center gets into the locking hole and is locked by locking hole 51.
In this embodiment, the spring 3 may be a cylindrical compression spring.
The air conditioner interface that this embodiment provided is to the inside rotation of radome fairing when opening because flap 1, so, carrier rocket take off the back, according to bernoulli's principle, because the high-speed flow of radome fairing outside gas can make flap 1 laminate mouth of pipe 5 more, makes flap 1 automatic production sealed trend. Simultaneously, utilize lockpin 2 to lock flap 1 and mouth of pipe 5, strengthened the encapsulated situation of flap, reduced the risk that flap 1 can't be closed, also consequently reduced because flap 1 can't seal up the influence to the inside payload's of radome fairing environment, improved the reliability of launching task. Meanwhile, the aerodynamic shape of the carrier rocket is optimized, and the flight control capability of the carrier rocket is improved.
Further, when the rocket motor is vertically placed and the nozzle 5 is closed by the cover 1, the first end of the cover 1 is the upper part of the cover 1, and the second end of the cover 1 is the lower part of the cover 1, i.e. the locking pin 2 is arranged at the lower part of the cover 1 along the radial direction of the cover 1. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover 1 rotates towards the direction of the opening cover 5 around the rotating shaft 7 under the action of gravity, the lock pin 2 is extruded by the opening cover 3 to displace towards the center direction of the opening cover 1 along the radial direction of the opening cover 1, and the spring 3 is extruded. The lock pin 2 reaches the lock hole 51 under the guidance of the slide groove 52, and the spring 3 rebounds to return the lock pin 2 to be locked by the lock hole 51.
The air conditioner interface that this embodiment provided can realize air conditioner flap self-closing to automatic and mouth of pipe locking.
Further, one end of the lock pin 2, which is far away from the center of the cover 1, is spherical, so that the lock pin 2 can be smoothly displaced towards the center of the cover 1 and locked in the locking hole 51 under the guiding action of the sliding groove 52 after contacting the sliding groove 52.
Further, the flap 1 has a plate-shaped structure, and the overall weight of the cowling can be further reduced.
As shown in fig. 6, the cowling air conditioning interface, in addition to the flap, nozzle, shaft, latch and spring, also includes a torsion spring 6 according to one embodiment of the present invention. The torsional spring 6 is sleeved on the rotating shaft 7, one support arm of the torsional spring 6 is limited through the pipe orifice 1, and the other support arm of the torsional spring 6 is limited through the opening cover 1.
Specifically, the two arms at the end of the torsion spring 6 may be straight arms or wound in a hook shape. The torsion spring 6 acts in a direction to restrict the opening of the flap 1. After the air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover 1 rotates towards the direction of the pipe orifice 5 around the rotating shaft 7 under the action of gravity and the torsion spring 6, and when the opening cover 1 contacts the pipe orifice 5 and the opening cover 1 completely closes the pipe orifice 5, the lock pin 2 enters the locking hole 51 under the guiding action of the sliding groove 52, so that the opening cover 1 closes the pipe orifice 5. According to the radome fairing air conditioner interface that this embodiment provided, the flap circles round to the mouth of pipe direction under the combined action of gravity and torsional spring to get into the locking hole and lock under the spout guide effect, can realize that the flap self-closing mouth of pipe, and locked by the mouth of pipe.
The present embodiment does not limit the number of the torsion springs 6, and may include two torsion springs symmetrically installed at both sides of the rotation shaft 7.
Further, the first end of the opening cover 1 is provided with a limiting groove 12 perpendicular to the axial direction of the rotating shaft 7, and one arm of the torsion spring 6 is placed in the limiting groove 12 to limit one arm of the torsion spring 6. The first end of the outer ring of the pipe orifice 5 is correspondingly provided with a support seat to limit the other support arm of the torsion spring 6.
Furthermore, the limiting groove 12 is formed by two straight plates perpendicular to the axial direction of the rotating shaft 7 at intervals, and the limiting groove 12 can also be a groove perpendicular to the axial direction of the rotating shaft 7. The support 13 is a straight plate parallel to the axial direction of the nozzle 5.
As shown in fig. 5, according to an embodiment of the present invention, the end of the lock pin 2 away from the edge of the flap 1 is provided with a split collar 4, and the split collar 4 is used for limiting the lock pin 2 from coming out of the two lock pin mounting brackets 10 toward the edge of the flap 1.
Specifically, when the flap 1 is opened, the lock pin 2 is pulled out of the lock hole 51, and the spring 3 is deformed by being pressed. After flap 1 opened, spring 3 kick-backs, and split ring 4 supports the lockpin mounting bracket, deviates from flap 1 edge under the effort that the spring rebounded when preventing lockpin 2 from reseing. The circlip 4 may be a circlip for a shaft.
Furthermore, the lock pin 2 is provided with a check ring clamping groove along the axial direction, and the check ring clamping groove is a circle of groove and used for installing a split check ring 4.
As shown in fig. 4, according to one embodiment of the present invention, the lock pin 2 is a stepped shaft having a thin shaft at one end and a thick shaft at the other end. The thin shaft of the lock pin 2 is connected with a lock pin mounting bracket close to the center of the opening cover 1, and the thick shaft of the lock pin 2 is connected with a lock pin mounting bracket far away from the center of the opening cover 1. The spring 3 is sleeved on the thin shaft of the lock pin 2. The transition end surfaces of the thin shaft and the thick shaft of the lock pin 2 form a bulge.
Specifically, one end of the spring 3 abuts against a bulge formed by the transition end surfaces of the thin shaft and the thick shaft of the lock pin 2, and the other end abuts against the lock pin mounting rack 10 close to the center of the opening cover 1. When the lock pin 2 displaces towards the center of the opening cover 1, the spring 3 is extruded and deformed, and after the lock pin 2 is released, the lock pin 2 is reset under the action of the spring 3.
Further, the two sides of the first end of the opening cover 1 and the two sides of the first end of the pipe orifice 5 are respectively provided with an ear plate 11 for connecting the opening cover 1 with the pipe orifice 5 through a rotating shaft 7.
The invention is described by taking the nozzle and the flap as circular shapes, but the invention is not limited to the claimed scope. For example, the through hole and the cover of the nozzle are polygonal. Also, the present invention is not limited to the connection between the nozzle and the cowling, and the nozzle and the cowling may be integrally formed.
In another aspect, the present invention provides a fairing including the above air conditioning interface. The fairing provided by the invention comprises the air conditioning structure, so that the technical effect is correspondingly achieved.
In another aspect, the invention provides a launch vehicle comprising the air conditioning interface. The carrier rocket provided by the invention has corresponding technical effects due to the fact that the carrier rocket comprises the air conditioning structure.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A dome air conditioning interface, comprising: the device comprises a cover, a pipe orifice, a rotating shaft, a lock pin and a spring; the pipe orifice comprises a pipe orifice inner ring and a pipe orifice outer ring, the pipe orifice inner ring is fixedly connected with the fairing, and the pipe orifice outer ring is connected with the opening cover through the rotating shaft and the lock pin;
the first end of the cover cap is connected with the first end of the outer ring of the pipe orifice through a rotating shaft, and the cover cap is used for rotating around the rotating shaft relative to the pipe orifice so as to open or close the pipe orifice in the fairing;
at least two lock pin mounting frames are arranged at the second end of the opening cover at intervals, two ends of each lock pin are respectively connected with the opening cover through the two lock pin mounting frames, and the two ends of each lock pin are slidably connected with the two lock pin mounting frames;
a circle of bulges are arranged on the lock pin in the circumferential direction between the lock pin mounting frames; the spring is sleeved on the lock pin, one end of the spring props against the bulge, the other end of the spring props against the lock pin mounting rack close to the center of the opening cover, and the spring is used for enabling the lock pin to reset;
a sliding groove is formed in the second end of the pipe orifice outer ring, and the locking hole is communicated with one end of the sliding groove; the locking hole is used for locking the lock pin when the mouth cover closes the nozzle, and the sliding groove is used for guiding the lock pin in the closing process of the mouth cover so as to facilitate the lock pin to enter the locking hole.
2. The air conditioner interface of claim 1 further comprising a torsion spring, said torsion spring being sleeved on said shaft; one support arm of the torsion spring is limited through the pipe orifice, and the other support arm of the torsion spring is limited through the opening cover.
3. The air conditioner interface of claim 2, comprising two torsion springs symmetrically mounted on both sides of the rotating shaft.
4. The air conditioner interface of claim 2, wherein the first end of the flap is provided with a limit groove perpendicular to the axial direction of the rotating shaft, and one arm of the torsion spring is placed in the limit groove to limit the one arm of the torsion spring;
and the first end of the pipe orifice outer ring is correspondingly provided with a support so as to limit the other support arm of the torsion spring.
5. The air conditioner interface of claim 4, wherein the limiting groove is formed by two straight plates perpendicular to the axial direction of the rotating shaft at intervals; the support is a straight plate parallel to the axial direction of the pipe orifice.
6. An air conditioning interface as claimed in any of claims 1 to 5 wherein the end of the pin remote from the edge of the flap is provided with a split collar to limit the pin from escaping from the two pin mounts towards the edge of the flap.
7. The air conditioner interface of claim 6, wherein the lock pin is provided with a retainer ring slot along a circumferential direction of the lock pin, the retainer ring slot is a ring of groove, and the retainer ring slot is used for installing the split retainer ring.
8. The air conditioning interface of claim 1, wherein the locking pin is a stepped shaft with a thin shaft at one end and a thick shaft at the other end; the thin shaft of the lock pin is connected with the lock pin mounting bracket close to the center of the cover, and the thick shaft of the lock pin is connected with the lock pin mounting bracket far away from the center of the cover; the spring is sleeved on the thin shaft of the lock pin; the transition end surfaces of the thin shaft and the thick shaft form the bulge.
9. A fairing comprising an air conditioning interface as claimed in any one of claims 1 to 8.
10. A launch vehicle comprising an air conditioning interface according to any of claims 1 to 8, or comprising a fairing according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111148308.7A CN113945124A (en) | 2021-09-29 | 2021-09-29 | Fairing air conditioner interface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111148308.7A CN113945124A (en) | 2021-09-29 | 2021-09-29 | Fairing air conditioner interface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113945124A true CN113945124A (en) | 2022-01-18 |
Family
ID=79329548
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111148308.7A Pending CN113945124A (en) | 2021-09-29 | 2021-09-29 | Fairing air conditioner interface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113945124A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115218729A (en) * | 2022-07-06 | 2022-10-21 | 蓝箭航天空间科技股份有限公司 | A vent flap for carrier rocket radome |
-
2021
- 2021-09-29 CN CN202111148308.7A patent/CN113945124A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115218729A (en) * | 2022-07-06 | 2022-10-21 | 蓝箭航天空间科技股份有限公司 | A vent flap for carrier rocket radome |
| CN115218729B (en) * | 2022-07-06 | 2023-06-09 | 蓝箭航天空间科技股份有限公司 | Ventilating port cover for fairing of carrier rocket |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11505318B2 (en) | Container retention and release apparatus having integral swaybrace and retention features | |
| CN113945124A (en) | Fairing air conditioner interface | |
| US20140319283A1 (en) | Canisterized satellite dispenser | |
| US10377510B1 (en) | Enhanced fairing mechanisms for launch systems | |
| CN216745740U (en) | Fairing air conditioner interface and carrier rocket | |
| US4717093A (en) | Penguin missile folding wing configuration | |
| US10858102B2 (en) | Container retention and release apparatus for use with aircraft | |
| US9540110B2 (en) | Aeroplane equipped with an internal escape hatch incorporating a pressure regulating system | |
| CN109573115A (en) | Radome fairing opening device | |
| EP2389315B1 (en) | A nozzle for a refuelling probe | |
| US11021898B2 (en) | Aircraft bypass turbojet engine with opening fitted with a hinge with gooseneck fitting | |
| CN112357129A (en) | Inclined-pushing axial separation device for fairing | |
| EP3470325B1 (en) | Devices and methods for diverting moisture from a support member | |
| US10814997B2 (en) | Support device for actuator, air intake system and aircraft | |
| GB2577540A (en) | Joint for connecting aircraft structures | |
| US11434020B2 (en) | Assembly for an aircraft, said assembly having a pylon and a reservoir containing an extinguishing fluid | |
| US20200164983A1 (en) | Container retention and release apparatus having integral swaybrace and retention features | |
| US8839807B2 (en) | Rapid response self-closing pressure equalization vent | |
| WO2023234994A1 (en) | Passively jettisoned control surface restraint and cover for tactical flight vehicles | |
| CN111457796A (en) | Lock catch and cover of automatic closing cover for spaceflight and carrier rocket | |
| US6684569B2 (en) | Self-closing access door | |
| EP3798133B1 (en) | Linkage supporting a door of an aircraft propulsion system | |
| US20180237170A1 (en) | Capture system and method | |
| CN218296917U (en) | Ventilation opening cover | |
| CN115218729B (en) | Ventilating port cover for fairing of carrier rocket |
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 |