CN114248922B - Air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading - Google Patents
Air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading Download PDFInfo
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- CN114248922B CN114248922B CN202111511221.1A CN202111511221A CN114248922B CN 114248922 B CN114248922 B CN 114248922B CN 202111511221 A CN202111511221 A CN 202111511221A CN 114248922 B CN114248922 B CN 114248922B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T30/00—Transportation of goods or passengers via railways, e.g. energy recovery or reducing air resistance
Abstract
The invention provides a head-stopping section structure of an air drop light-duty self-propelled vehicle, which is specially designed for being matched with a tail part to install an air drop accessory mechanism and preventing an aviation anti-diving training simulator from slipping off the head part when the simulator is turned over in the air after being thrown in the air. The invention does not need to install any parts, only depends on an S-shaped appearance structure and is matched with the reverse S-shaped appearance of the release mechanism, thereby innovatively solving the problems that the tail of the underwater self-propelled device goes out of the barrel first during throwing, the parachute in the air throwing device is ejected out, the parachute is opened immediately, the whole underwater self-propelled device is driven to turn over 180 degrees in the air, the release mechanism cannot slip from the head under the condition that the whole underwater self-propelled device is rocked immediately in the air falling process, and the device can be released from the release mechanism suddenly in the air flight state of the aviation anti-diving training simulator after the barrel is released, and can be reliably released after water is added.
Description
Technical Field
The invention belongs to the field of underwater autopilot research, and particularly relates to an air-drop light autopilot rotation-stopping head section structure suitable for head loading.
Background
The conventional underwater autopilot is assembled with an air-drop accessory by adopting an installation mode of a tail loading release mechanism, but the mode is not suitable for an aviation anti-diving training simulator.
The aviation anti-diving training simulator is a novel light underwater self-propelled device capable of being thrown in air, and is a disposable movable target with the functions of simulating submarine underwater maneuvering characteristics, radiation noise characteristics, sound reflection characteristics and magnetic abnormality characteristics. The head of the aviation anti-diving training simulator needs to bear the parachute opening dynamic load, so that the aviation anti-diving training simulator keeps a normal and stable flying posture in the air, immediately enters an underwater navigation posture, and can be safely and reliably released and separated when entering water. The novel light underwater autopilot is a slender cylindrical structure, so that a head-loaded aerial delivery accessory mechanism needs to be specially developed in the design of an aerial delivery device.
The existing air drop accessory mechanism designed for the aviation anti-diving training simulator enables the head of the underwater self-propelled vehicle to bear the dynamic load of opening the umbrella, and the release mechanism is also hooped at the front end of the head section; the parachute is wrapped and distributed at the tail section by a parachute bag, and the release mechanism is connected with the parachute through a rope belt. When the air drop device is installed on the underwater autopilot, the tail part faces downwards and the head faces upwards, and the air drop device is installed in the throwing barrel. However, a series of problems can occur when launching an aero-anti-submarine training simulator.
When the device is put in, the tail part of the underwater autopilot firstly goes out of the barrel, the parachute in the air drop device is ejected out, and then the parachute is opened, so that the whole underwater autopilot can be driven to turn over for 180 degrees in the air; at this time, the release mechanism installed at the head of the underwater autopilot is connected with the parachute at the tail of the underwater autopilot only through two parachute ropes. If the release mechanism mounted on the head is slightly swung during the aerial overturn, the release mechanism may slip off the head.
Therefore, a special design of the light air-drop self-propelled vehicle rotation-stopping head section structure suitable for head loading is needed, so that not only can the drag reduction requirements of the self-propelled vehicle during normal assembly of internal equipment and navigation be met, but also the requirement of air-drop during air-drop on overturning and drop prevention can be met.
Disclosure of Invention
In order to solve the problem that the existing air-drop accessory mechanism applicable to the aviation anti-diving training simulator cannot meet the requirements of normal assembly of internal equipment of the air-drop device and drag reduction in navigation, and cannot meet the requirements of air overturning and drop prevention in air-drop, the invention provides an air-drop light-weight air-drop self-aircraft rotation-stopping head section structure applicable to head loading, which is mainly developed aiming at various small-size and light-weight air-drop self-aircraft head section structures capable of air-drop.
The technical scheme of the invention is as follows: an air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading comprises a head section shell 2, a head section internal assembly 3 and a head section supporting structure 4;
the head section shell 2 is in sealing connection with the middle section shell 5 of the autopilot through the head section supporting structure 4, and meanwhile, the head section supporting structure 4 can support the head section internal assembly 3;
the head section shell 2 forms a head section S-shaped fluid line shape through fitting curves with two opposite circle centers, and the circle centers are not on the central axis of the head section shell 2 and are symmetrically distributed along the central axis of the head section shell 2.
The invention further adopts the technical scheme that: the shape of the head section shell 2 is symmetrically designed along the axis of the head section shell 2; on the section of the axis of the head section shell 2, the shape of the head section shell 2 is two sections of irregular curves symmetrical along the central line; each section of irregular curve is divided into a first connection section 6, a second connection section 7 and a third connection section 8.
The invention further adopts the technical scheme that: the first connecting section 6 is a convex curve, one end of the first connecting section is in smooth transition with the end part of the middle section shell 5, and the other end of the first connecting section is in smooth transition with the end part of the second connecting section 7; the centers of the two first connecting sections 6 are positioned in the head section shell 2, are not positioned on the axis of the head section shell 2, and are symmetrically distributed along the axis of the head section shell 2.
The invention further adopts the technical scheme that: the second connecting section 7 is a concave curve, and one end which is not connected with the first connecting section 6 is in smooth transition with the end part of the third connecting section 8; the circle centers of the two second connecting sections 7 are positioned outside the head section shell 2 and are symmetrically distributed along the axis of the head section shell 2.
The invention further adopts the technical scheme that: the third connecting section 8 consists of a straight line section and an arc line section with the end part smoothly transiting with the end part of the second connecting section 7, and the other end of the arc line section smoothly transits with one end of the straight line section; the straight line segment is perpendicular to the central line, and the end parts of the straight line segments of the two third connecting segments 8 are connected to form a cross-section line of the head segment shell 2 with the front end closed.
Effects of the invention
The invention has the technical effects that: the rotation-stopping head section structure designed by the invention can inhibit the simulator from swinging or rotating to be suddenly released caused by various random factors in the air flight process after the air drop device is opened by 180 degrees by designing the head section S-shaped structure on the premise of no hard rotation-stopping device, and can easily and effectively get rid of a release mechanism assembled on the head section by the action of water pressure after the air anti-diving training simulator is used for water entering, thereby smoothly completing water entering separation. Under the condition that a rotation stopping structure or other parts are not newly added, the device can meet the conditions that parts inside a normal simulator are reliably installed and positioned accurately only through head line shapes, and under the premise that the head section external line shapes constructed through positive and negative double-circle fitting, namely the S-shaped parts with non-coaxial line circle centers, are matched with a linear matching releasing mechanism, the device can meet the conditions that the device is suddenly separated from the releasing mechanism in the air flight state of the aviation anti-diving training simulator after being discharged, and can reliably release the device after being discharged into water.
In conclusion, the invention is a precondition and guarantee that the aviation anti-diving training simulator has normal air posture and normal water-entering navigation, and establishes an effective foundation for smoothly forming fight force for the product.
Drawings
Fig. 1: the head section and the disengaging device of the aviation anti-diving training simulator are structurally simplified;
fig. 2: the head section of the aviation anti-diving training simulator and the stress principle diagram of the releasing device.
In the figure: 1-a release mechanism; 2-a head section housing; 3-head section internal components; 4-a head section support structure; 5-a middle section shell; 6-a first connection section; 7-a second connection section; 8-a third connecting section.
Detailed Description
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, based on the embodiments of the invention, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the invention.
In addition, the embodiments of the present invention and the features of the embodiments may be combined with each other without collision.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
Referring to fig. 1-2, the technical scheme of the invention is as follows: the utility model provides a light-duty autogenous ware of air drop that is applicable to head loading ends a section structure, head section casing forms head section "S" shape fluid line shape through the fitting curve of two opposite centre of a circle, and interior circle centre of a circle a1, a2 are not on the simulator axis moreover.
The head section is S-shaped in fluid line shape, the front end is round and linear, the requirement of the fluid line shape of the self-propulsion device can be met, positive pressure formed on the shell by the release mechanism matched with the head section shell body is radiated on the S-shaped line shape of the head section shell body, and the positive pressure is uniformly distributed on the surface of the shell body around the normal direction of the outer circle centers b1 and b 2.
The shell is internally provided with a thin wall, and the rear section of the shell is provided with a head section supporting structure which is connected with the rear section and plays a role in supporting, and the connection, the supporting and the sealing of the head section supporting structure and the rear section are ensured.
The device forms a head section S-shaped fluid line shape through two fitting curves with opposite circle centers, and the circle centers a1 and a2 of the inner circle are not on the central axis of the simulator, so that components of the matched release mechanism 1 rotating around the central axis X in the process of aerial overturning and random swinging are greatly reduced. Because the release mechanism 1 is mainly tied at the tail part of the training simulator through two umbrella ropes, positive pressure formed on the shell by the release mechanism 1 matched with the head section shell 2 acts on the 2"S' shape line shape of the head section shell in a radiation way, and is uniformly distributed on the surface of the shell around the normal direction of the outer centers b1 and b 2; due to the concave structure design of the head, the aviation anti-diving training simulator rotates after being discharged from the cylinder or loads various outward forces on the releasing mechanism 1 in flight, in particular Y, Z which can release the releasing mechanism 1 is effectively blocked. The large pin is embedded in the release mechanism 1, so that the parachute at the tail of the aviation anti-diving training simulator is prevented from being separated from the release mechanism in the air under the overturning of 180 degrees before the parachute is opened and the disturbance of random air flow in the air after the parachute is opened; the small round bulge structure can resist the impact of opening an umbrella in the air and entering water, and the head section supporting structure 4 is correspondingly designed in the head section shell 2, so that the requirement of connecting force between the aviation anti-diving training simulator in the X direction and the sections is met, and the requirement of sealing between the sections can be ensured.
After the aviation anti-diving training simulator enters water, the device is released, the S-shaped fluid line shape with the round front end and the concave middle can meet the drag reduction requirement on water flow in the autonomous navigation process.
Claims (3)
1. The head section structure of the air drop light-duty self-propelled vehicle suitable for head loading is characterized by comprising a head section shell (2), a head section internal assembly (3) and a head section supporting structure (4);
the head section shell (2) is in sealing connection with the middle section shell (5) of the self-propelled device through the head section supporting structure (4), and meanwhile the head section supporting structure (4) can support the head section internal assembly (3);
the head section shell (2) forms an S-shaped fluid line shape of the head section through two fitting curves with opposite circle centers, and the circle centers are not on the central axis of the head section shell (2) and are symmetrically distributed along the central axis of the head section shell (2); on the section of the axis of the head section shell (2), the shape of the head section shell (2) is two sections of irregular curves symmetrical along the central line; each section of irregular curve is divided into a first connecting section (6), a second connecting section (7) and a third connecting section (8);
the first connecting section (6) is a convex curve, one end of the first connecting section is in smooth transition with the end part of the middle section shell (5), and the other end of the first connecting section is in smooth transition with the end part of the second connecting section (7);
the second connecting section (7) is a concave curve, and one end which is not connected with the first connecting section (6) is in smooth transition with the end part of the third connecting section (8);
the third connecting section (8) consists of a straight line section and an arc line section with the end part smoothly transiting with the end part of the second connecting section (7), and the other end of the arc line section smoothly transits with one end of the straight line section; the straight line segments are perpendicular to the central line, and the ends of the straight line segments of the two third connecting segments (8) are connected to form a section line of the head segment shell (2) with the front end closed; the release mechanism is matched with the first connecting section and connected with a parachute arranged at the tail section of the self-propelled device through a rope belt.
2. An air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading as claimed in claim 1, wherein the circle centers of the two first connecting sections (6) are positioned in the head section shell (2) and are symmetrically distributed along the axis of the head section shell (2) along the axes which are not positioned on the head section shell (2).
3. The head-stop section structure of the air-drop light-duty self-propelled vehicle suitable for head loading according to claim 1, wherein the circle centers of the two second connecting sections (7) are positioned outside the head section shell (2) and symmetrically distributed along the axis of the head section shell (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111511221.1A CN114248922B (en) | 2021-12-06 | 2021-12-06 | Air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111511221.1A CN114248922B (en) | 2021-12-06 | 2021-12-06 | Air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114248922A CN114248922A (en) | 2022-03-29 |
| CN114248922B true CN114248922B (en) | 2023-08-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111511221.1A Active CN114248922B (en) | 2021-12-06 | 2021-12-06 | Air-drop light-duty self-propelled vehicle rotation-stopping head section structure suitable for head loading |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191517157A (en) * | 1915-12-06 | 1920-05-27 | Francis Ranken | Darts for use from Aircraft and Means for Carrying and Releasing the same. |
| GB1181159A (en) * | 1966-10-28 | 1970-02-11 | Forsvarets Fabriksverk | Improvements in or relating to Shells |
| GB1281903A (en) * | 1969-10-02 | 1972-07-19 | Hawker Siddeley Aviation Ltd | Improvements in or relating to the dropping of airborne loads |
| RU2232973C1 (en) * | 2003-04-28 | 2004-07-20 | Федеральное государственное унитарное предприятие "Государственное научно-производственное предприятие "Регион" | Roll-stabilized aerial bomb |
| US10112691B1 (en) * | 2017-06-12 | 2018-10-30 | The Boeing Company | Releasable forward section of an underwater vehicle |
| CN110775223A (en) * | 2019-11-07 | 2020-02-11 | 中国船舶重工集团公司第七0五研究所 | Self-inflating recovery device for small and light self-propelled device |
-
2021
- 2021-12-06 CN CN202111511221.1A patent/CN114248922B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191517157A (en) * | 1915-12-06 | 1920-05-27 | Francis Ranken | Darts for use from Aircraft and Means for Carrying and Releasing the same. |
| GB1181159A (en) * | 1966-10-28 | 1970-02-11 | Forsvarets Fabriksverk | Improvements in or relating to Shells |
| GB1281903A (en) * | 1969-10-02 | 1972-07-19 | Hawker Siddeley Aviation Ltd | Improvements in or relating to the dropping of airborne loads |
| RU2232973C1 (en) * | 2003-04-28 | 2004-07-20 | Федеральное государственное унитарное предприятие "Государственное научно-производственное предприятие "Регион" | Roll-stabilized aerial bomb |
| US10112691B1 (en) * | 2017-06-12 | 2018-10-30 | The Boeing Company | Releasable forward section of an underwater vehicle |
| CN110775223A (en) * | 2019-11-07 | 2020-02-11 | 中国船舶重工集团公司第七0五研究所 | Self-inflating recovery device for small and light self-propelled device |
Non-Patent Citations (1)
| Title |
|---|
| 鱼雷空投附件振动试验相关问题探讨;张志民;田树红;曹小娟;曾小凡;;鱼雷技术(第04期);全文 * |
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| CN114248922A (en) | 2022-03-29 |
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