CN115610670A - Air-drop multistage time-delay split mechanism tail section - Google Patents
Air-drop multistage time-delay split mechanism tail section Download PDFInfo
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- CN115610670A CN115610670A CN202211346927.1A CN202211346927A CN115610670A CN 115610670 A CN115610670 A CN 115610670A CN 202211346927 A CN202211346927 A CN 202211346927A CN 115610670 A CN115610670 A CN 115610670A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 82
- 239000003381 stabilizer Substances 0.000 claims abstract description 13
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000002955 isolation Methods 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 241000008225 Pogonichthys macrolepidotus Species 0.000 claims 5
- 238000004880 explosion Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 230000000977 initiatory effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/40—Packs
- B64D17/52—Opening, e.g. manual
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention discloses a tail section of an airdrop multistage delay split mechanism, wherein a tail cabin stabilizer sequentially comprises a cylindrical bearing cabin section for containing a bearing object, a conical control cabin section for containing a primary delay control mechanism and a secondary delay control mechanism, and an umbrella cabin section which is cylindrical and smaller than the diameter of the bearing cabin section from front to back, fins are distributed on the excircle of the umbrella cabin section, a ring sheet is annularly sleeved on the rear part of each fin, and the front part of each fin extends to the conical surface of the control cabin section; the front end of the bearing cabin section is connected with a target through a front clamp, the rear end of the parachute cabin section is connected with a parachute cabin cover through a rear clamp and sealed, a spring used for popping out a parachute system is arranged in the parachute cabin section, a front pin pulling mechanism and a rear pin pulling mechanism which respectively lock the front clamp and the rear clamp through a pin pulling are arranged outside the tail cabin stabilizer, and the front pin pulling mechanism and the rear pin pulling mechanism are respectively and independently controlled by a second-stage delay control mechanism and a first-stage delay control mechanism. The invention has low complexity, can realize multi-stage split control, and has good pneumatic stability while reducing the size.
Description
Technical Field
The invention belongs to the field of air-drop, and particularly relates to a tail section of an air-drop multi-stage delay split mechanism.
Background
In order to realize the rapid and accurate air drop of small-batch multipoint mode, the latest method is to fill related materials into a hanging-flying type low-resistance air drop container, and the position of a drop point is accurately controlled by utilizing a parachute technology and ballistic simulation calculation. At present, the scheme has the following problems:
1) Because the airdrop container is required to have good pneumatic stability while meeting the low resistance characteristic so as to ensure the departure safety and the parachute opening posture, the X-shaped symmetrical tail wings are generally used at present and are usually large in diameter, so that the space utilization rate is reduced;
2) In order to reduce the system idle time to realize accurate drop point, the parachute opening working time needs to be strictly controlled, at present, the on-off of a circuit is generally controlled by an electronic delay mechanism, an explosion bolt which is fixed in advance is detonated after the circuit is connected, the thrust generated by the explosion bolt pushes the parachute system out of a wake flow area, then the parachute system fully works until stably falls and lands, the impact force generated by the explosion bolt can provide higher requirements for the local structure of a cabin body, and the system is complex and has higher reliability requirements;
3) At present, the method is one-level delay control, multi-level control is not carried out, and complex actions cannot be realized.
Disclosure of Invention
The invention aims to provide an air-drop multi-stage delay split mechanism tail section, which has low system complexity, high product reliability, capability of multi-stage split control, capability of meeting various air-drop task requirements, and good pneumatic stability while reducing the size.
The technical scheme adopted by the invention is as follows:
a main body of an air-drop multistage delay split mechanism is a tail cabin stabilizer, the tail cabin stabilizer sequentially comprises a cylindrical bearing cabin section for containing a bearing object, a conical control cabin section for containing a primary delay control mechanism and a secondary delay control mechanism, and an umbrella cabin section which is cylindrical and smaller than the diameter of the bearing cabin section and is used for containing an umbrella system from front to back, fins are distributed on the excircle of the umbrella cabin section, a ring piece is sleeved on the rear portion of each fin in a ring mode, and the front portion of each fin extends to the conical surface of the control cabin section; the front end of the bearing cabin section is connected with a target through a front clamp, the rear end of the parachute cabin section is connected with a parachute cabin cover through a rear clamp and sealed, a spring used for popping out a parachute system is arranged in the parachute cabin section, a front pin pulling mechanism and a rear pin pulling mechanism which respectively lock the front clamp and the rear clamp through a pin pulling are arranged outside the tail cabin stabilizer, and the front pin pulling mechanism and the rear pin pulling mechanism are independently controlled by a second-stage delay control mechanism and a first-stage delay control mechanism respectively to complete unlocking.
Furthermore, the inner rings of the front clamp and the rear clamp are uniformly distributed with protruding or concave clamping grooves, when the umbrella is installed, the front clamp simultaneously surrounds the interfaces of the bearing cabin section and the target and clamps the interfaces of the bearing cabin section and the target through the clamping grooves, and the rear clamp simultaneously surrounds the interfaces of the umbrella cabin section and the umbrella cabin cover and clamps the interfaces of the umbrella cabin section and the umbrella cabin cover through the clamping grooves.
Furthermore, the front clamp and the rear clamp are surrounded by two sections; two sections of the front hoop are locked at one end through a pull pin of the front pull pin mechanism and connected at the other end through a pre-tightening component with adjustable tightness; two sections of the rear hoop are locked at one end through a pulling pin of the rear pulling pin mechanism and connected at the other end through a pre-tightening component with adjustable tightness.
Furthermore, the pre-tightening assembly comprises threaded seats respectively arranged on the two sections and a screw rod which is in threaded fit with the threaded seats on the two sections in the opposite directions.
Furthermore, the main bodies of the front clamp and the rear clamp are made of elastic steel belts.
Furthermore, a breaking rope is arranged on the pulling pin to serve as a safety.
Furthermore, a window for installing and observing the first-stage delay control mechanism and the second-stage delay control mechanism is arranged on the control cabin section.
Furthermore, a first-stage delay control mechanism and a second-stage delay control mechanism are arranged on two sides of the positioning installation plate in the control cabin section.
Furthermore, the bearing cabin section, the control cabin section and the umbrella cabin section are isolated by an isolation cabin plate.
Furthermore, eight fins are uniformly distributed on the excircle of the umbrella cabin section.
The beneficial effects of the invention are:
after air drop, the first-stage delay control mechanism is started after reaching delay time, the rear pin pulling mechanism is controlled to finish unlocking, the rear clamp is opened, the umbrella cabin cover is unsealed on the umbrella cabin section, the spring pops out the umbrella system, the umbrella system is opened to decelerate, then the second-stage delay control mechanism is started after reaching delay time, the front pin pulling mechanism is controlled to finish unlocking, and the target is separated; according to the invention, the unlocking clamp is transmitted by using machinery, the umbrella system is popped out by using the spring, the bolt does not need to be exploded, a complex circuit and initiating explosive devices are not introduced, the complexity of the system is effectively reduced, and the reliability of the product is higher; according to the invention, multi-level split control is realized through the primary and secondary delay control mechanisms, so that the requirements of various air-drop tasks are met; the whole tail cabin stabilizer is funnel-shaped, the wing piece is used as a main stable structure, the wing piece has good pneumatic stability, the stability can be further improved by increasing the ring piece, and the pneumatic stability is maintained while the diameter is reduced.
Drawings
Fig. 1 is a first schematic perspective view of a tail section of an air-drop multi-stage time-delay division mechanism in an embodiment of the present invention.
Fig. 2 is a schematic perspective view two of the tail section of the air-drop multi-stage delay time division mechanism in the embodiment of the invention.
Fig. 3 is a perspective view of a tail tank stabilizer in an embodiment of the invention.
Figure 4 is a side view of a stern ballast in an embodiment of the invention.
Fig. 5 is a first schematic diagram of a transmission structure according to an embodiment of the present invention.
Fig. 6 is a second schematic diagram of a transmission structure in an embodiment of the invention.
In the figure: 1, front lathedog; 2-front pin pulling mechanism; 3-a fin; 4-ring piece; 5-parachute bay section; 6-a rear pin pulling mechanism; 7-controlling the cabin section; 8-a load bearing cabin section; 9-rear clamping hoop; 10-a window; 11-a first-stage delay control mechanism; 12-a secondary delay control mechanism; 13-canopy; 14-a spring; 15-positioning the mounting plate; 16-a card slot; 17-pretensioning assembly.
Detailed Description
The invention is further illustrated in the following figures and examples.
As shown in fig. 1 to 6, a tail section of an airdrop multistage delay split mechanism, the main body of which is a tail cabin stabilizer, the tail cabin stabilizer sequentially comprises a cylindrical bearing cabin section 8 for accommodating a bearing object, a conical control cabin section 7 for accommodating first-stage and second-stage delay control mechanisms (11, 12), and a cylindrical umbrella cabin section 5 for accommodating an umbrella system and having a diameter smaller than that of the bearing cabin section 8 from front to back, fins 3 are distributed on the outer circle of the umbrella cabin section 5, a ring sheet 4 is sleeved on the rear portion of each fin 3, and the front portion of each fin extends to a conical surface of the control cabin section 7; the front end of the bearing cabin section 8 is connected with a target through a front hoop 1, the rear end of the umbrella cabin section 5 is connected with an umbrella cabin cover 13 through a rear hoop 9 and sealed, a spring 14 used for popping an umbrella system is arranged in the umbrella cabin section 5, the outer part of the tail cabin stabilizer is provided with a front pin pulling mechanism 2 and a rear pin pulling mechanism 6 which respectively lock the front hoop 1 and the rear hoop 9 through a pin pulling, and the front pin pulling mechanism 2 and the rear pin pulling mechanism 6 are respectively controlled by a second-stage delay control mechanism 12 and a first-stage delay control mechanism 11 independently to complete unlocking.
After air drop, the first-stage delay control mechanism 11 is started after reaching delay time, the rear pin pulling mechanism 6 is controlled to unlock, the rear hoop is opened 9, the opening of the umbrella cabin cover 13 to the umbrella cabin section 5 is released, the spring 14 pops out the umbrella system, the umbrella system is opened to decelerate, then the second-stage delay control mechanism 12 is started after reaching delay time, the front pin pulling mechanism 2 is controlled to unlock, and the target is separated; according to the invention, the mechanical transmission is utilized to unlock the clamp, the spring 14 is utilized to pop out the umbrella system, the explosion bolt is not needed, no complex circuit and initiating explosive are introduced, the complexity of the system is effectively reduced, and the reliability of the product is higher; the invention realizes multi-level split control through the first-level and second-level delay control mechanisms (11, 12) and meets the requirements of various air-drop tasks; the whole tail cabin stabilizer is funnel-shaped, the wing pieces 3 serve as main stable structures and have good pneumatic stability, the stability can be further improved by adding the ring pieces 4, and the pneumatic stability is maintained while the diameter is reduced.
As shown in fig. 1 to 4, in the present embodiment, the control cabin 7 is provided with a window 10 for installing and observing the primary and secondary delay control mechanisms (11, 12).
As shown in fig. 1 to 4, in the present embodiment, eight fins 3 are uniformly distributed on the outer circumference of the umbrella cabin section 5.
As shown in fig. 5 and fig. 6, in this embodiment, protruding or recessed slots 16 are distributed on the inner rings of the front clamp 1 and the rear clamp 9, when the umbrella is installed, the front clamp 1 simultaneously surrounds the joints of the bearing cabin section 8 and the target and blocks the joints of the bearing cabin section and the target through the slots 16, and the rear clamp 9 simultaneously surrounds the joints of the umbrella cabin section 5 and the umbrella cabin cover 13 and blocks the joints of the umbrella cabin cover and the umbrella cabin cover through the slots 16, so that the connection is firm and stable, and the umbrella is prevented from falling off.
As shown in fig. 5 and 6, in the present embodiment, the front clamp 1 and the rear clamp 9 are surrounded by two sections; two sections of the front hoop 1 are locked at one end through a pull pin of the front pull pin mechanism 2 and connected at the other end in an adjustable manner through a pre-tightening component 17; two sections of the rear hoop 9 are locked at one end through a pull pin of the rear pull pin mechanism 6 and connected at the other end in an adjustable manner through a pre-tightening component 17; the tightness is adjusted according to actual conditions, and the connection is guaranteed to be firm and stable.
As shown in fig. 5 and 6, in the present embodiment, the pre-tightening assembly 17 includes threaded seats respectively provided on the two segments, and screws that are threaded in opposite directions to each other on the two segments, so that the adjustment is simple.
As shown in fig. 5 and 6, in the present embodiment, the primary delay control mechanism 11 and the secondary delay control mechanism 12 are installed on both sides of the positioning installation plate 15 in the control cabin section 7.
In this embodiment, the main bodies of the front and rear clips 1 and 9 are made of an elastic steel band.
In this embodiment, the pull pin is provided with a breaking cord as a safety.
In the embodiment, the bearing cabin section 8, the control cabin section 7 and the umbrella cabin section 5 are isolated by isolation cabin plates.
In this embodiment, the front pin-pulling mechanism 2 and the rear pin-pulling mechanism 6 may have the simplest structure, that is, only pin-pulling and rope-pulling, the first-stage and second-stage delay control mechanisms (11, 12) may be electronically controlled or mechanically controlled, both the first-stage and second-stage delay control mechanisms (11, 12) are started by pulling off the soft lock needle, the soft lock needle is connected to the airplane, in order to prevent the soft lock needle from colliding with and winding around other internal structures during pulling out, a soft lock needle pipe may be designed, after the whole tail section is air-dropped, the soft lock needle is pulled straight and pulled off, the delay control mechanism is started, and the delay control mechanism realizes unlocking by pulling out the pin-pulling through the rope-pulling.
It will be understood that modifications and variations can be made by persons skilled in the art in light of the above teachings and all such modifications and variations are intended to be included within the scope of the invention as defined in the appended claims.
Claims (10)
1. The utility model provides an air-drop multistage time delay components of a whole that can function independently mechanism tail section which characterized in that: the main body is a tail cabin stabilizer which sequentially comprises a cylindrical bearing cabin section for containing a bearing object, a conical control cabin section for containing a primary delay control mechanism and a secondary delay control mechanism, and a cylindrical umbrella cabin section smaller than the diameter of the bearing cabin section from front to back, wherein fins are distributed on the excircle of the umbrella cabin section, and the rear parts of the fins are annularly sleeved with ring pieces; the front end of the bearing cabin section is connected with a target through a front clamp, the rear end of the parachute cabin section is connected with a parachute cabin cover through a rear clamp and sealed, a spring used for popping out a parachute system is arranged in the parachute cabin section, a front pin pulling mechanism and a rear pin pulling mechanism which respectively lock the front clamp and the rear clamp through a pulling pin are arranged outside the tail cabin stabilizer, and the front pin pulling mechanism and the rear pin pulling mechanism are independently controlled by a second-stage delay control mechanism and a first-stage delay control mechanism respectively to complete unlocking.
2. The airdrop multistage delay split tail section of claim 1, wherein: the inner rings of the front clamp and the rear clamp are uniformly distributed with protruding or concave clamping grooves, when the umbrella is installed, the front clamp simultaneously surrounds the interfaces of the bearing cabin section and the target and clamps the interfaces of the bearing cabin section and the target through the clamping grooves, and the rear clamp simultaneously surrounds the interfaces of the umbrella cabin section and the umbrella cabin cover and clamps the interfaces of the umbrella cabin section and the umbrella cabin cover through the clamping grooves.
3. The air-drop multi-stage delay split mechanism tail section of claim 1, wherein: the front clamp and the rear clamp are both formed by encircling two sections; two sections of the front hoop are locked at one end through a pull pin of the front pull pin mechanism and connected at the other end through a pre-tightening component with adjustable tightness; two sections of the rear hoop are locked at one end through a pulling pin of the rear pulling pin mechanism and connected at the other end through a pre-tightening component with adjustable tightness.
4. The airdrop multistage delay split tail section of claim 3, wherein: the pre-tightening component comprises thread seats respectively arranged on the two sections and a screw rod which is in mutual reverse thread fit with the thread seats on the two sections.
5. The air-drop multi-stage delay split mechanism tail section of claim 1, wherein: the main bodies of the front clamp and the rear clamp are both made of steel belts with elasticity.
6. The airdrop multistage delay split tail section of claim 1, wherein: the pull pin is provided with a breaking rope as a safety.
7. The airdrop multistage delay split tail section of claim 1, wherein: and a window for installing and observing the primary and secondary delay control mechanisms is arranged on the control cabin section.
8. The air-drop multi-stage delay split mechanism tail section of claim 1, wherein: the first-stage delay control mechanism and the second-stage delay control mechanism are arranged on two sides of the positioning mounting plate in the control cabin section.
9. The air-drop multi-stage delay split mechanism tail section of claim 1, wherein: the bearing cabin section, the control cabin section and the umbrella cabin section are isolated by isolation cabin plates.
10. The airdrop multistage delay split tail section of claim 1, wherein: eight fins are uniformly distributed on the excircle of the umbrella cabin section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211346927.1A CN115610670A (en) | 2022-10-31 | 2022-10-31 | Air-drop multistage time-delay split mechanism tail section |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211346927.1A CN115610670A (en) | 2022-10-31 | 2022-10-31 | Air-drop multistage time-delay split mechanism tail section |
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| Publication Number | Publication Date |
|---|---|
| CN115610670A true CN115610670A (en) | 2023-01-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211346927.1A Pending CN115610670A (en) | 2022-10-31 | 2022-10-31 | Air-drop multistage time-delay split mechanism tail section |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117739752A (en) * | 2024-02-20 | 2024-03-22 | 四川凌空天行科技有限公司 | Rocket cabin capable of being separated with low impact and separation method |
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2022
- 2022-10-31 CN CN202211346927.1A patent/CN115610670A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117739752A (en) * | 2024-02-20 | 2024-03-22 | 四川凌空天行科技有限公司 | Rocket cabin capable of being separated with low impact and separation method |
| CN117739752B (en) * | 2024-02-20 | 2024-05-07 | 四川凌空天行科技有限公司 | Rocket cabin capable of being separated with low impact and separation method |
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