CN115127407A - Rocket hood separator based on spring - Google Patents
Rocket hood separator based on spring Download PDFInfo
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- CN115127407A CN115127407A CN202210954684.3A CN202210954684A CN115127407A CN 115127407 A CN115127407 A CN 115127407A CN 202210954684 A CN202210954684 A CN 202210954684A CN 115127407 A CN115127407 A CN 115127407A
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- sliding rod
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- 238000000926 separation method Methods 0.000 claims abstract description 9
- 230000000149 penetrating effect Effects 0.000 claims 1
- 230000007246 mechanism Effects 0.000 description 9
- 230000006835 compression Effects 0.000 description 6
- 238000007906 compression Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 3
- 235000012633 Iberis amara Nutrition 0.000 description 3
- 230000000452 restraining effect Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 241000446313 Lamella Species 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
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Classifications
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- 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
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Vibration Dampers (AREA)
Abstract
The application discloses a rocket head cover separating device based on a spring, wherein a rocket is provided with a rocket body and a head cover hinged with the rocket body, and the head cover is provided with two separable shells; be equipped with rocket hood separator between the rocket body and the casing, rocket hood separator includes: the device comprises a first supporting base station, a second supporting base station, a sliding rod and an elastic element; the first support base station is arranged on the arrow body and provided with a stroke groove along a first direction, and a clamping groove is annularly arranged at the edge of the stroke groove; the second supporting base station is arranged on the shell and corresponds to the first supporting base station; one end of the sliding rod is connected with the stroke groove in a sliding mode, and the other end of the sliding rod is connected with one side, close to the first supporting base, of the second supporting base; the elastic element is sleeved on the sliding rod, one end of the elastic element is propped against the clamping groove, and the other end of the elastic element is connected with one side, close to the second supporting base, of the sliding rod. This application only utilizes elastic element acting to make two casings to keeping away from the swing of arrow body direction, realizes the split separation of hood, greatly reduced use cost.
Description
Technical Field
The present disclosure relates generally to the field of rocket technology, and more particularly to a spring-based rocket head cover separation device.
Background
The head fairing is usually called as a head cover for short, is a commonly adopted composition structure of rockets, missiles and the like, can effectively improve aerodynamic appearance, reduce aerodynamic resistance and improve firing range, and can protect products in the warhead in the flight process. Most rockets require protection of the hood throughout flight, but in certain applications, the hood needs to be unlocked and separated for subsequent functions.
At present, different hood materials cause great difference in the adopted hood technical scheme, the hood materials can generally adopt a non-metal hood and a metal hood according to different use environments, and common hood throwing modes comprise a split type, a crushing type and an integral type. The common split type cover throwing scheme is large in structural size, complex in composition, high in cost and incapable of adapting to rockets with small structural sizes, and therefore the rocket head cover separating device based on the springs effectively solves the problems.
Disclosure of Invention
In view of the above-identified deficiencies or inadequacies in the prior art, it would be desirable to provide a spring-based rocket nose cap breakaway apparatus that is low in cost, small in size, and simple in construction.
In a first aspect, the present application provides a spring-based rocket head cover detachment apparatus, the rocket having a rocket body and a head cover hinged to both sides of the rocket body; the hood has two separable shells; be provided with rocket nose cover separator between rocket body and the casing, rocket nose cover separator includes:
a first support base station disposed on the rocket body; the first support base station is provided with a stroke groove; the stroke groove is arranged along a first direction, and a clamping groove is annularly arranged at the edge of the stroke groove;
the second supporting base station is arranged on the shell and corresponds to the first supporting base station;
the sliding rod is connected with the stroke groove in a sliding mode, and the other end of the sliding rod is connected with one side, close to the first supporting base, of the second supporting base;
the elastic element is sleeved on the sliding rod; one end of the elastic element is abutted in the clamping groove, and the other end of the elastic element is connected with one side of the sliding rod, which is close to the second supporting base station;
when the rocket needs to be covered, the elastic element can drive the sliding rod to push the second supporting base station, so that the second supporting base station pushes the shell to swing in the direction far away from the rocket body, and the head cover is separated in a split mode.
According to the technical scheme provided by the embodiment of the application, the first supporting base station comprises:
the rotating base is arranged on the rocket body; the rotating base is provided with a placing groove, and a notch of the placing groove is arranged towards the second supporting base station;
the ejector rod is provided with a supporting section and a mounting section; the supporting section is close to the rotating base relative to the mounting section, and the supporting section and the placing groove are movably arranged; the mounting section is internally provided with the stroke groove;
and one end of the stroke limiting rod is arranged in the stroke groove, and the other end of the stroke limiting rod is positioned outside the stroke groove and is provided with the clamping groove.
According to the technical scheme provided by the embodiment of the application, the stroke limiting rod is provided with a through hole which is arranged corresponding to the stroke groove; the sliding rod penetrates through the through hole and is inserted into the stroke groove in a sliding mode.
According to the technical scheme provided by the embodiment of the application, the second supporting base station comprises:
the ball head seat is arranged on the shell;
the bulb is movably connected with one side, far away from the hood, of the bulb seat;
one end of the ball head adapter rod is connected with one side, away from the ball head seat, of the ball head, and the other end of the ball head adapter rod is connected with one end, away from the stroke groove, of the sliding rod.
According to the technical scheme provided by the embodiment of the application, one end of the sliding rod, which is close to the stroke groove, is provided with a limiting protruding part along the circumferential direction of the sliding rod.
According to the technical scheme provided by the embodiment of the application, the elastic element has two states; when the elastic element is in a first state, the sliding rod abuts against the bottom of the stroke slot; when the elastic element is in the second state, the limiting bulge part is abutted to one end, close to the stroke groove, of the stroke limiting rod.
According to the technical scheme provided by the embodiment of the application, the safety device further comprises a safety pin, wherein the safety pin can sequentially penetrate through the stroke limiting rod and the sliding rod; the safety pin is used for locking the sliding rod to slide.
According to the technical scheme provided by the embodiment of the application, one end of the shell, which is close to the arrow body, is connected with the rotating support through the rotating support leg; the rotating support is arranged on the arrow body side wall.
According to the technical scheme provided by the embodiment of the application, a rotating shaft is arranged in the rotating support; the rotating shaft is rotatably connected with the rotating supporting legs, and the rotating supporting legs are used for driving the shell to swing around the rotating shaft.
In summary, this technical scheme specifically discloses a rocket hood separator based on spring, forms rocket hood separator's installation space between the separable casing on rocket body and the hood in this application, and rocket hood separator includes: the device comprises a first supporting base station, a second supporting base station, a sliding rod and an elastic element. The first support base station is arranged on the arrow body, and is provided with a stroke groove arranged along a first direction, and a clamping groove is annularly arranged at the edge of the stroke groove; the second supporting base station is arranged on the head cover and corresponds to the first supporting base station; one end of the sliding rod is connected with the stroke groove in a sliding mode, the other end of the sliding rod is connected with one side, close to the first supporting base station, of the second supporting base station, an elastic element is sleeved on the outer wall of the sliding rod, the initial state of the elastic element is in a compression state, one end of the elastic element in the compression state abuts against the clamping groove, and the other end of the elastic element is connected with one side, close to the second supporting base station, of the sliding rod. When the rocket needs to throw the cover, the elastic element deforms and can drive the sliding rod to slide in the stroke groove, so that the second supporting base platform pushes the shell to swing in the direction far away from the rocket body, and the head cover is separated in a split mode.
The first supporting base station and the second supporting base station are utilized to form a compression space of the elastic element, and the elastic element is enabled to continuously keep a compression state before the rocket is thrown; when the rocket needs to be covered, the restraint force of the head cover on the elastic element is relieved, the elastic element deforms and drives the sliding rod connected with the elastic element to slide in the stroke groove, and meanwhile, the sliding rod is connected with the second supporting base station, so that the second supporting base station can push the shell to swing in the direction far away from the rocket body, the head cover is separated, and the use cost is greatly reduced. In addition, in the process of cover throwing, the movement speed of the elastic element is smooth, and the interference on the rocket body task load is small when the head cover is separated.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic illustration of the use of a spring-based rocket head cover separation device.
FIG. 2 is a schematic diagram of a spring-based rocket head cover release.
Reference numbers in the figures: 1. rotating the base; 2. a top rod; 3. a slide bar; 4. a travel limit rod; 5. a safety pin; 6. an elastic element; 7. a ball head adapter rod; 8. a ball head; 9. a ball cup seat; 10. a head cover; 11. rotating the support legs; 12. rotating the support; 13. a rocket body.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. 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. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example 1
Referring to FIG. 1, a schematic view of a first embodiment of a spring-based rocket head cover release mechanism is provided, the rocket having a rocket body 13 and a head cover 10 hinged to both sides of rocket body 13, head cover 10 having two separable shells, where head cover 10 is of the type, for example, a two-piece head cover; a rocket head cover separating device is arranged between the rocket body 13 and the shell, and comprises:
the first supporting base station is arranged on the rocket body 13; the first supporting base station is provided with a stroke groove; the stroke groove is arranged along the first direction, and a clamping groove is annularly arranged at the edge of the stroke groove;
the second supporting base station is arranged on the shell and corresponds to the first supporting base station;
one end of the sliding rod 3 is connected with the stroke groove in a sliding mode, and the other end of the sliding rod 3 is connected with one side, close to the first supporting base, of the second supporting base;
the elastic element 6 is sleeved on the sliding rod 3; one end of the elastic element 6 is propped against the clamping groove, and the other end of the elastic element is connected with one side of the slide bar 3 close to the second supporting base station;
when the rocket needs to be covered, the elastic element 6 can drive the sliding rod 3 to slide in the stroke groove, so that the second supporting base platform pushes the shell to swing towards the direction far away from the rocket body 13, and the head cover 10 is separated from each other.
In the present embodiment, as shown in fig. 1 and 2, since the head cover 10 has two separable shells, a rocket head cover separating device is provided between each of the two shells and the rocket body 13 to realize the split separation of the head cover; the first supporting base station is arranged on the rocket body 13 and is provided with a stroke groove arranged along a first direction, wherein the first direction is a direction perpendicular to the rocket body 13, the stroke groove is used for accommodating the sliding rod 3, and the stroke groove forms a sliding space of the sliding rod 3 so that the sliding rod 3 can slide in the stroke groove;
the second supporting base station is arranged on the shell and is arranged corresponding to the first supporting base station, the design structure enables the slide bar 3 to match the second supporting base station with the first supporting base station, and meanwhile, a compression space of the elastic element is formed between the first supporting base station and the second supporting base station;
one end of the slide bar 3 is connected with the stroke groove in a sliding manner, the other end of the slide bar is connected with the second supporting base station, and the slide bar 3 is used for driving the second supporting base station to move towards the shell along the first direction, so that the shell swings; after the two shells are driven by the second supporting base station to swing in the direction away from the rocket body 13, the two-petal type hood can be separated.
The elastic element 6 is a working element of the device, and as the hood 10 is externally provided with a release mechanism, when the release mechanism is not started, the hood 10 and the second support base connected with the hood 10 have a restraining force on the elastic element 6 under the action of the release mechanism, so that the elastic element 6 is always in a compressed state, and the hood 10 is ensured not to be bounced by the elastic element 6. Here, the type of release mechanism, for example, is an explosive bolt; when the device works, the release mechanism is started, the hood 10 no longer has a restraining force on the elastic element 6, the elastic element 6 deforms, the compression state is switched to a natural state, and the sliding rod 3 is driven to move along the stroke slot in the direction far away from the rocket body 13 in the process, so that the sliding rod 3 can drive the second rotating base to move, wherein the elastic element 6 is of a type such as a spring.
The elastic element 6 is in a compressed state under the restriction of the first supporting base and the second supporting base, when the release mechanism is released, the hood 10 is in a separable state, at this time, the hood 10 and the second supporting base connected with the hood 10 no longer have a restraining force on the elastic element 6, the elastic element 6 can be switched from the compressed state to a natural state, and in the process, the elastic element 6 drives the sliding rod 3 to push the second supporting base to further complete the action of pushing the shell to separate.
As shown in fig. 1, specifically, the first support base includes:
the rocket body 13 is provided with a rotating base 1, the rotating base 1 is provided with a placing groove with a notch facing to the second supporting base station, the rotating base 1 is used for supporting the ejector rod 2, and the placing groove forms a placing space of a supporting section of the ejector rod 2;
One end of the stroke limiting rod 4 is arranged in the stroke groove, the other end of the stroke limiting rod 4 is positioned outside the stroke groove and is provided with a clamping groove, and the elastic element 6 can be abutted in the clamping groove in a compressed state;
wherein, the through-hole that corresponds the setting with the stroke groove is seted up to stroke gag lever post 4 inside, and the through-hole is used for holding slide bar 3, and slide bar 3 can run through the through-hole and insert and locate the stroke groove, and the stroke gag lever post 4 is close to the activity that the one end in stroke groove is used for spacing slide bar 3, makes slide bar 3 can not deviate from in the stroke groove when sliding.
As shown in fig. 1, specifically, the second support base includes:
the ball head seat 9, the ball head seat 9 is set in body, the ball head seat 9 is used for supporting the body;
the ball head 8 is movably connected with one side of the ball head seat 9, which is far away from the shell, and the ball head 8 is used for indirectly pushing the shell to swing;
the ball head adapter rod 7, ball head adapter rod 7 one end and ball head 8 are kept away from one side of ball head seat 9 and are connected, and its other end is connected with the one end that the stroke groove was kept away from to slide bar 3, and ball head adapter rod 7 is used for supporting ball head 8.
The flexible sliding space of the slide rod 3, the ball head 8 and the ball head seat 9 is formed between the ball head seat 9 and the rotating base 1, and the design structure can ensure that the phenomenon of blocking can not occur when the slide rod 3 drives the ball head adapter rod 7 and the ball head 8 to move towards the shell.
As shown in fig. 1, one end of the slide bar 3 close to the stroke slot is provided with a limit protrusion along the circumferential direction thereof, and the limit protrusion is used for preventing the slide bar 3 from falling out of the stroke slot.
As shown in fig. 1, the elastic element 6 has two states, wherein the first state is a compressed state and the second state is a natural state; when the elastic element 6 is in the first state, the elastic element 6 does not drive the sliding rod 3 to move along the first direction, and at the moment, the tail end of the sliding rod 3 abuts against the bottom of the stroke slot; after the release mechanism is released, the elastic element 6 drives the slide rod 3 to move in the direction close to the hood 10 along the first direction, so as to push the second support base platform, so that the shell swings, the split type hood 10 is separated, when the limiting bulge at the bottom of the slide rod 3 is abutted to one end, close to the stroke slot, of the limiting rod 4, the slide rod 3 stops sliding, and at the moment, the elastic element 6 is in the second state.
As shown in fig. 2, the safety device further comprises a safety pin 5, the safety pin 5 can sequentially penetrate through the stroke limiting rod 4 and the sliding rod 3, the safety pin 5 is used for preventing the elastic element 6 in a compressed state from driving the sliding rod 3 to move when the device is not started, the safety pin 5 plays a role in locking the sliding of the sliding rod 3, and when the device works, the safety pin 5 needs to be removed in advance.
As shown in fig. 1, the end of the casing close to the rocket body 13 is connected with the rotating support 12 through the rotating support leg 11, the rotating support 12 is arranged on the side wall of the rocket body 13, because the head cover 10 has two separable casings, and the two casings are both connected with the rocket body 13 through hinges, the rotating support leg 11 can drive the casing to swing along the rotating shaft in the direction far away from the rocket body 13 when the casing is pushed by the second supporting base.
Wherein, be provided with the pivot in the rotation support 12, the pivot is used for driving the swing of hood 10, and the pivot rotates with rotation landing leg 11 to be connected, makes rotation landing leg 11 can drive the casing and take place the swing, realizes the separation of split structure.
The specific operation work is as follows:
firstly, when the rocket needs to throw the cover, a releasing mechanism is started, at the moment, the elastic element 6 starts to be converted into a second state from a first state, in the process, the elastic element 6 can drive the sliding rod 3, the ball head adapter rod 7 and the ball head 8 to move towards the direction close to the head cover 10, and the ball head 8 indirectly pushes the shell to swing; the hood 10 is provided with rotating legs 11, and two shells of the pushed hood 10 swing around a rotating shaft on a rotating support 12 under the guidance of the rotating legs 11, so that split separation of the split hood is realized; the separation process in this application utilizes elastic element 6's deformation to turn into two casings and revolves the pivot rotation on the rotation support 12, accomplishes the separation of two lamella formula headcaps, greatly reduced use cost.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (9)
1. A spring-based rocket head cover separating device, wherein the rocket is provided with a rocket body (13) and a head cover (10) hinged with the rocket body (13) at two sides; the hood (10) has two separable shells; a rocket head cover separating device is arranged between the rocket body (13) and the shell, and is characterized in that the rocket head cover separating device comprises:
a first support base disposed on the rocket body (13); the first support base station is provided with a stroke groove; the stroke groove is arranged along a first direction, and a clamping groove is annularly arranged at the edge of the stroke groove;
the second supporting base station is arranged on the shell and corresponds to the first supporting base station;
one end of the sliding rod (3) is connected with the stroke groove in a sliding mode, and the other end of the sliding rod (3) is connected with one side, close to the first supporting base, of the second supporting base;
the elastic element (6), the said elastic element (6) is set on the slide bar (3); one end of the elastic element (6) is abutted to the clamping groove, and the other end of the elastic element is connected with one side, close to the second supporting base, of the sliding rod (3);
when the rocket needs to be covered, the elastic element (6) can drive the sliding rod (3) to push the second supporting base station, so that the second supporting base station pushes the shell to swing in the direction far away from the rocket body (13), and the hood (10) is separated in a split mode.
2. A spring-based rocket nose cap launching device as recited in claim 1, wherein said first support platform comprises:
the rotating base (1), the rotating base (1) is arranged on the rocket body (13); the rotating base (1) is provided with a placing groove, and the notch of the placing groove faces the second supporting base station;
the ejector rod (2), the said ejector rod (2) has supporting section and mounting section; the supporting section is close to the rotating base (1) relative to the mounting section, and the supporting section and the placing groove are movably arranged; the mounting section is provided with the stroke groove;
the stroke limiting device comprises a stroke limiting rod (4), one end of the stroke limiting rod (4) is arranged in the stroke groove, and the other end of the stroke limiting rod is located outside the stroke groove and provided with the clamping groove.
3. The rocket nose cover separating device based on spring as claimed in claim 2, wherein said travel limiting rod (4) is provided with a through hole corresponding to the travel slot; the sliding rod (3) penetrates through the through hole and is inserted into the stroke groove in a sliding mode.
4. A spring-based rocket nose cap launching device as recited in claim 2, wherein said second support platform comprises:
the ball head seat (9), the said ball head seat (9) is set up on the said body;
the ball head (8), the ball head (8) and one side of the ball head seat (9) far away from the shell are movably connected;
the ball head adapter rod (7), one end of the ball head adapter rod (7) is connected with one side of the ball head (8) far away from the ball head seat (9), and the other end of the ball head adapter rod is connected with one end of the slide rod (3) far away from the stroke groove.
5. A spring-based rocket nose cap launching device according to claim 1, wherein the end of the sliding rod (3) near the travel slot is provided with a limit protrusion along its circumference.
6. A spring-based rocket nose cap launching device according to claim 5, wherein said elastic element (6) has two states; when the elastic element (6) is in a first state, the sliding rod (3) abuts against the bottom of the travel groove; when the elastic element (6) is in the second state, the limiting bulge part is abutted to one end, close to the stroke groove, of the stroke limiting rod (4).
7. A spring-based rocket nose cap separation device according to claim 2, further comprising a safety pin (5), said safety pin (5) being capable of sequentially penetrating said travel limiting rod (4) and said sliding rod (3); the safety pin (5) is used for locking the sliding rod (3) to slide.
8. A spring-based rocket nose cap release device according to claim 1, wherein the end of the housing near the rocket body (13) is connected to a rotating support (12) by means of a rotating leg (11); the rotating support (12) is arranged on the side wall of the rocket body (13).
9. A spring-based rocket nose cap launching device according to claim 8, wherein said rotating mount (12) has a rotating shaft disposed therein; the rotating shaft is rotatably connected with the rotating supporting legs (11), and the rotating supporting legs (11) are used for driving the shell to swing around the rotating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210954684.3A CN115127407A (en) | 2022-08-10 | 2022-08-10 | Rocket hood separator based on spring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210954684.3A CN115127407A (en) | 2022-08-10 | 2022-08-10 | Rocket hood separator based on spring |
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| Publication Number | Publication Date |
|---|---|
| CN115127407A true CN115127407A (en) | 2022-09-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210954684.3A Pending CN115127407A (en) | 2022-08-10 | 2022-08-10 | Rocket hood separator based on spring |
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| Country | Link |
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| CN (1) | CN115127407A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6494406B1 (en) * | 1998-12-24 | 2002-12-17 | National Space Development Agency Of Japan | Rocket fairing and method of opening the same |
| CN101995192A (en) * | 2010-08-24 | 2011-03-30 | 湖北航天技术研究院总体设计所 | Head-body separation device with guide function |
| CN210942314U (en) * | 2019-08-12 | 2020-07-07 | 重庆零壹空间科技集团有限公司 | Elastic separation mechanism |
| CN211685687U (en) * | 2019-12-27 | 2020-10-16 | 北京星际荣耀空间科技有限公司 | Stage cold separation structure for carrying rocket |
| CN112815789A (en) * | 2021-01-21 | 2021-05-18 | 山东宇航技术有限公司 | Fairing horizontal throwing separation device with spring pushing and punching functions |
| CN113203326A (en) * | 2021-04-28 | 2021-08-03 | 北京星途探索科技有限公司 | Hinge structure is thrown soon to radome fairing |
| CN113218255A (en) * | 2021-04-28 | 2021-08-06 | 北京星途探索科技有限公司 | Separation mechanism with adjustable radome separation power |
| CN113340159A (en) * | 2021-06-10 | 2021-09-03 | 北京星途探索科技有限公司 | Self-adjusting type rotating throwing fairing separating mechanism |
-
2022
- 2022-08-10 CN CN202210954684.3A patent/CN115127407A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6494406B1 (en) * | 1998-12-24 | 2002-12-17 | National Space Development Agency Of Japan | Rocket fairing and method of opening the same |
| CN101995192A (en) * | 2010-08-24 | 2011-03-30 | 湖北航天技术研究院总体设计所 | Head-body separation device with guide function |
| CN210942314U (en) * | 2019-08-12 | 2020-07-07 | 重庆零壹空间科技集团有限公司 | Elastic separation mechanism |
| CN211685687U (en) * | 2019-12-27 | 2020-10-16 | 北京星际荣耀空间科技有限公司 | Stage cold separation structure for carrying rocket |
| CN112815789A (en) * | 2021-01-21 | 2021-05-18 | 山东宇航技术有限公司 | Fairing horizontal throwing separation device with spring pushing and punching functions |
| CN113203326A (en) * | 2021-04-28 | 2021-08-03 | 北京星途探索科技有限公司 | Hinge structure is thrown soon to radome fairing |
| CN113218255A (en) * | 2021-04-28 | 2021-08-06 | 北京星途探索科技有限公司 | Separation mechanism with adjustable radome separation power |
| CN113340159A (en) * | 2021-06-10 | 2021-09-03 | 北京星途探索科技有限公司 | Self-adjusting type rotating throwing fairing separating mechanism |
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