Tail section of an airdropped multi-stage time-delay split mechanism

Abstract

The present invention discloses a tail section for an airdrop multi-stage delay split mechanism. The tail compartment stabilizer comprises, from front to back, a cylindrical load compartment section for accommodating a load, a conical control compartment section for accommodating the primary and secondary delay control mechanisms, and a cylindrical parachute compartment section for accommodating the parachute system, which is smaller in diameter than the load compartment section. The parachute compartment section has fins distributed around its outer circumference, with the rear ends of the fins encircled by rings and extending forward to the conical surface of the control compartment section. The front end of the load compartment section is connected to a target via a front clamp, while the rear end of the parachute compartment section is connected to the parachute cover and sealed via a rear clamp. A spring for ejecting the parachute system is provided within the parachute compartment section. A front and rear pinning mechanism are mounted on the exterior of the tail compartment stabilizer, locking the front and rear pinning mechanisms via pins. The front and rear pinning mechanisms are independently controlled by the secondary and primary delay control mechanisms, respectively. The present invention is low in complexity, capable of multi-stage split control, and offers excellent aerodynamic stability while being compact.

Description

Technical Field

[0001] The invention belongs to the field of airdrop, and in particular relates to a tail section of an airdrop multi-stage time-delay split mechanism. Background Art

[0002] To achieve rapid and precise airdrops at multiple locations in small batches, the latest approach is to load the relevant materials into hanging, low-drag airdrop containers and use parachute technology and ballistic simulation calculations to precisely control the landing point. Currently, this approach has the following problems:

[0003] 1) Since airdrop containers must have both low drag characteristics and good aerodynamic stability to ensure safe departure and parachute deployment, X-shaped symmetrical tails are currently commonly used. These tails often have a large diameter, resulting in reduced space utilization.

[0004] 2) To reduce the system's time in the air and achieve a precise landing point, the parachute opening time must be strictly controlled. Currently, this is typically controlled by an electronic delay mechanism, which detonates pre-fixed explosive bolts after the circuit is connected. The thrust generated by the explosive bolts pushes the parachute system out of the wake area, where it then fully inflates until a stable landing. The impact force generated by the explosive bolts places higher demands on the local structure of the cabin, making the system complex and requiring higher reliability.

[0005] 3) Currently, only one-level delay control is used, and there is no multi-level control, so complex actions cannot be achieved. Summary of the Invention

[0006] The purpose of the present invention is to provide a tail section of an airdrop multi-stage delayed split mechanism with low system complexity and high product reliability. It can be controlled at multiple levels to meet the needs of various airdrop missions, and has good aerodynamic stability while reducing its size.

[0007] The technical solution adopted in the present invention is:

[0008] The invention discloses a tail section of an airdrop multi-stage delay split mechanism, the main body of which is a tail cabin stabilizer. The tail cabin stabilizer comprises, from front to back, a cylindrical load-bearing cabin section for accommodating a load, a conical control cabin section for accommodating a first-stage and second-stage delay control mechanism, and a cylindrical parachute cabin section for accommodating a parachute system, which is smaller in diameter than the load-bearing cabin section. Wings are distributed on the outer circumference of the parachute cabin section, the rear part of the wing is surrounded by a ring, and the front part extends to the conical surface of the control cabin section. The front end of the load-bearing cabin section is connected to a target via a front clamp, and the rear end of the parachute cabin section is connected to a parachute cabin cover via a rear clamp and sealed. A spring for ejecting the parachute system is provided in the parachute cabin section. A front pinning mechanism and a rear pinning mechanism are installed on the outside of the tail cabin stabilizer, which lock the front clamp and the rear clamp respectively by pinning. The front pinning mechanism and the rear pinning mechanism are independently controlled to complete unlocking by the second-stage delay control mechanism and the first-stage delay control mechanism respectively.

[0009] Furthermore, the inner rings of the front clamp and the rear clamp are both provided with protruding or concave slots. During installation, the front clamp simultaneously surrounds the interface between the load-bearing compartment section and the target target and clamps the interface between the two through the slots, and the rear clamp simultaneously surrounds the interface between the parachute compartment section and the parachute compartment cover and clamps the interface between the two through the slots.

[0010] Furthermore, the front clamp and the rear clamp are both composed of two sections; the two sections of the front clamp are locked by the pin of the front pin pulling mechanism at one end and are connected at the other end with adjustable tightness through a pre-tightening component; the two sections of the rear clamp are locked by the pin of the rear pin pulling mechanism at one end and are connected at the other end with adjustable tightness through a pre-tightening component.

[0011] Furthermore, the pre-tightening assembly includes threaded seats respectively provided on the two sections, and a screw rod which is threadably matched with the threaded seats on the two sections in opposite directions.

[0012] Furthermore, the main bodies of the front clamp and the rear clamp are both made of elastic steel strips.

[0013] Furthermore, a breaking rope is provided on the pull pin as insurance.

[0014] Furthermore, the control compartment is provided with windows for installing and observing the first and second level delay control mechanisms.

[0015] Furthermore, the first-level delay control mechanism and the second-level delay control mechanism are installed on both sides of the positioning installation plate in the control cabin section.

[0016] Furthermore, the load-bearing compartment section, the control compartment section and the parachute compartment section are isolated by isolation panels.

[0017] Furthermore, eight wing blades are evenly distributed on the outer circle of the parachute cabin section.

[0018] The beneficial effects of the present invention are:

[0019] After the airdrop, the first-level delay control mechanism is activated when the delay time is reached, and the rear pin-pulling mechanism is controlled to complete unlocking, the rear clamp is opened, the parachute cover releases the seal on the parachute compartment section, the spring pops out the parachute system, and the parachute system opens to decelerate. Then the second-level delay control mechanism is activated when the delay time is reached, and the front pin-pulling mechanism is controlled to complete unlocking, and the target is separated. The present invention utilizes mechanical transmission to unlock the clamp and utilizes springs to pop out the parachute system. It does not require explosive bolts, does not introduce complex circuits and pyrotechnics, effectively reduces the complexity of the system, and has high product reliability. The present invention realizes multi-level split control through the first-level and second-level delay control mechanisms to meet the needs of various airdrop tasks. The tail cabin stabilizer is funnel-shaped as a whole, and the wing as the main stabilizing structure has good aerodynamic stability. Adding ring pieces can further improve stability and maintain aerodynamic stability while reducing the diameter. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a three-dimensional diagram of the tail section of the airdrop multi-stage delay split mechanism in the embodiment of the present invention. Figure 1 .

[0021] Figure 2 This is a three-dimensional diagram of the tail section of the airdrop multi-stage delay split mechanism in the embodiment of the present invention. Figure 2 .

[0022] Figure 3 It is a three-dimensional schematic diagram of the tail cabin stabilizer in an embodiment of the present invention.

[0023] Figure 4 2 is a side view of a tail compartment stabilizer according to an embodiment of the present invention.

[0024] Figure 5 This is a schematic diagram of the transmission structure in an embodiment of the present invention. Figure 1 .

[0025] Figure 6 This is a schematic diagram of the transmission structure in an embodiment of the present invention. Figure 2 .

[0026] In the figure: 1-front clamp; 2-front pin removal mechanism; 3-wing; 4-ring; 5-parachute compartment; 6-rear pin removal mechanism; 7-control compartment; 8-load-bearing compartment; 9-rear clamp; 10-window; 11-first-stage delay control mechanism; 12-second-stage delay control mechanism; 13-parachute compartment cover; 14-spring; 15-positioning mounting plate; 16-slot; 17-preload assembly. DETAILED DESCRIPTION

[0027] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0028] like Figures 1 to 6 As shown, a tail section of an airdrop multi-stage delay split mechanism, the main body of which is a tail cabin stabilizer, the tail cabin stabilizer is composed of a cylindrical load cabin section 8 for accommodating the load, a conical control cabin section 7 for accommodating the first and second level delay control mechanisms (11, 12), a cylindrical parachute cabin section 5 for accommodating the parachute system and having a diameter smaller than the load cabin section 8, the outer circle of the parachute cabin section 5 is distributed with fins 3, the rear of the fins 3 is surrounded by a ring 4, and the front extends to the control cabin section 7. conical surface; the front end of the load-bearing cabin section 8 is connected to the target through the front clamp 1, and the rear end of the parachute cabin section 5 is connected to the parachute cabin cover 13 and sealed through the rear clamp 9. A spring 14 for popping up the parachute system is provided in the parachute cabin section 5. The outside of the tail cabin stabilizer is equipped with a front pinning mechanism 2 and a rear pinning mechanism 6 that lock the front clamp 1 and the rear clamp 9 respectively by pinning. The front pinning mechanism 2 and the rear pinning mechanism 6 are independently controlled by the secondary delay control mechanism 12 and the primary delay control mechanism 11 to complete the unlocking.

[0029] After airdrop, the first-level delay control mechanism 11 starts when the delay time is reached, controls the rear pin-pulling mechanism 6 to complete unlocking, the rear clamp is opened 9, the parachute cover 13 releases the seal on the parachute compartment section 5, and the spring 14 pops out the parachute system, which opens to decelerate. Then, the second-level delay control mechanism 12 starts when the delay time is reached, controls the front pin-pulling mechanism 2 to complete unlocking, and the target is separated. The present invention uses mechanical transmission to unlock the clamp and uses the spring 14 to pop out the parachute system, does not require explosive bolts, does not introduce complex circuits and pyrotechnics, effectively reduces the complexity of the system, and has high product reliability. The present invention realizes multi-level split control through the first-level and second-level delay control mechanisms (11, 12) to meet the needs of various airdrop tasks. The tail cabin stabilizer is funnel-shaped as a whole, and the wing 3 is the main stabilizing structure, which itself has good aerodynamic stability. Adding the ring piece 4 can further improve the stability, and maintain aerodynamic stability while reducing the diameter.

[0030] like Figures 1 to 4 As shown, in this embodiment, a window 10 is provided on the control compartment 7 for installing and observing the first and second delay control mechanisms (11, 12).

[0031] like Figures 1 to 4 As shown, in this embodiment, eight fins 3 are evenly distributed on the outer circle of the parachute compartment section 5 .

[0032] like Figure 5 and Figure 6 As shown, in this embodiment, the inner circles of the front clamp 1 and the rear clamp 9 are both distributed with protruding or concave grooves 16. During installation, the front clamp 1 simultaneously surrounds the interface between the load-bearing compartment section 8 and the target target and clamps the interface between the two through the grooves 16. The rear clamp 9 simultaneously surrounds the interface between the parachute compartment section 5 and the parachute compartment cover 13 and clamps the interface between the two through the grooves 16. The connection is firm and stable to prevent it from falling out.

[0033] like Figure 5 and Figure 6 As shown, in this embodiment, the front clamp 1 and the rear clamp 9 are both composed of two sections; the two sections of the front clamp 1 are locked by the pin of the front pin pulling mechanism 2 at one end and are connected at the other end with adjustable tightness through the pre-tightening component 17; the two sections of the rear clamp 9 are locked by the pin of the rear pin pulling mechanism 6 at one end and are connected at the other end with adjustable tightness through the pre-tightening component 17; the tightness is adjusted according to actual conditions to ensure a firm and stable connection.

[0034] like Figure 5 and Figure 6 As shown, in this embodiment, the pre-tightening assembly 17 includes threaded seats respectively provided on two sections, and screw rods that are threadedly matched with the threaded seats on the two sections in opposite directions, which makes adjustment simple.

[0035] Such as Figure 5 and Figure 6As shown, in this embodiment, the first-level delay control mechanism 11 and the second-level delay control mechanism 12 are installed on both sides of the positioning installation plate 15 in the control compartment 7.

[0036] In this embodiment, the main bodies of the front clamp 1 and the rear clamp 9 are both made of elastic steel strips.

[0037] In this embodiment, a breaking rope is provided on the pull pin as a safety.

[0038] In this embodiment, the load-bearing cabin section 8, the control cabin section 7 and the parachute cabin section 5 are isolated by isolation panels.

[0039] In this embodiment, the front pin pulling mechanism 2 and the rear pin pulling mechanism 6 can adopt the simplest structure, that is, only the pin pulling and the pull rope, and the first and second delay control mechanisms (11, 12) can adopt electronic control or mechanical control. The first and second delay control mechanisms (11, 12) are both activated by pulling off the soft locking pin, and the soft locking pin is connected to the aircraft. In order to prevent the soft locking pin from colliding with or getting entangled with other internal structures during the extraction process, a soft locking pin pipeline can be designed. After the entire tail section is airdropped, the soft locking pin is straightened and pulled off, and the delay control mechanism is activated. The delay control mechanism is unlocked by pulling out the pin by pulling the rope.

[0040] It should be understood that those skilled in the art can make improvements or changes based on the above description, and all such improvements and changes should fall within the scope of protection of the appended claims of the present invention.

Claims

1. A tail section of an airdrop multi-stage delay split mechanism, characterized by: The main body is the tail cabin stabilizer, which consists of a cylindrical load-bearing cabin section for accommodating the load, a conical control cabin section for accommodating the first and second level delay control mechanisms, and a cylindrical parachute cabin section for accommodating the parachute system which is smaller than the diameter of the load-bearing cabin section. Wings are distributed on the outer circle of the parachute cabin section, and the rear part of the wing is ringed with a ring, and the front part of the wing extends to the conical surface of the control cabin section. The front end of the load-bearing cabin section is connected to the target through a front clamp, and the rear end of the parachute cabin section is connected to the parachute cabin cover and sealed through a rear clamp. A spring for popping out the parachute system is provided in the parachute cabin section. A front pinning mechanism and a rear pinning mechanism are installed on the outside of the tail cabin stabilizer to lock the front clamp and the rear clamp respectively through pinning. The front pinning mechanism and the rear pinning mechanism are independently controlled by the second level delay control mechanism and the first level delay control mechanism to complete unlocking respectively.

2. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: The inner circles of the front clamp and the rear clamp are both distributed with protruding or concave slots. During installation, the front clamp simultaneously surrounds the interface between the load-bearing cabin section and the target target and clamps the interface between the two through the slots. The rear clamp simultaneously surrounds the interface between the parachute cabin section and the parachute cabin cover and clamps the interface between the two through the slots.

3. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: The front clamp and the rear clamp are both composed of two sections; the two sections of the front clamp are locked by the pin of the front pin pulling mechanism at one end and are connected at the other end through an adjustable tightness pre-tightening component; the two sections of the rear clamp are locked by the pin of the rear pin pulling mechanism at one end and are connected at the other end through an adjustable tightness pre-tightening component.

4. The tail section of the airdrop multi-stage delay split mechanism according to claim 3, characterized in that: The pre-tightening component comprises threaded seats respectively arranged on two sections and a screw rod which is threadably matched with the threaded seats on the two sections in opposite directions.

5. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: The main bodies of the front clamp and the rear clamp are both made of elastic steel strips.

6. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: A breaking rope is provided on the pull pin as insurance.

7. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: The control compartment is equipped with windows for installing and observing the first and second level delay control mechanisms.

8. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: The first-level delay control mechanism and the second-level delay control mechanism are installed on both sides of the positioning installation plate in the control cabin section.

9. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: The load-bearing compartment section, control compartment section and parachute compartment section are separated by isolation panels.

10. The tail section of the airdrop multi-stage delay split mechanism according to claim 1, characterized in that: There are eight wing blades evenly distributed on the outer circle of the parachute cabin section.

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