A parachute deceleration device providing good parachute opening conditions

Abstract

This invention discloses a parachute deceleration device that provides favorable parachute opening conditions, comprising a parachute compartment with a receiving cavity; a parachute disposed within the receiving cavity; a suspended object disposed within the parachute compartment; a detection mechanism disposed within the parachute compartment for collecting the attitude angle and descent speed of the suspended object; multiple winglets arranged around the periphery of the parachute compartment; and an adjustment mechanism disposed within the parachute compartment, with a fixed end connected to the parachute compartment and a movable end connected to the winglets. The detection mechanism and the adjustment mechanism are electrically connected, and the adjustment mechanism is used to release and adjust the angle of the winglets. The beneficial effects of this invention are: by sensing attitude deviations in real time through the detection mechanism and dynamically controlling the winglet angles through the adjustment mechanism, the interaction between the winglets and the airflow generates a precise attitude adjustment torque, which can actively correct the axial deviation of the suspended object to a state that is consistent with the descent direction, reducing the deflection angle at the moment of parachute opening and providing stable parachute opening conditions.

Description

Technical Field

[0001] This invention relates to the field of parachutes, and more specifically to a parachute deceleration device that provides favorable parachute opening conditions. Background Technology

[0002] In parachute applications, the quality of the parachute deployment conditions directly determines the stability and safety of the parachute system. Ideally, the parachute deploys in the direction of descent, and this descent direction aligns with the axis of the suspended object. Under these ideal conditions, the parachute system can deploy smoothly and operate effectively, effectively avoiding various safety risks.

[0003] In actual airdrop and deployment scenarios, various factors such as airflow disturbances, initial deployment attitude deviations of the suspended object, and fluctuations in the carrier's motion state can easily lead to a misalignment between the axis of the suspended object and its descent direction. When this occurs, the parachute will form a certain angle with the axis of the suspended object at the moment of deployment. If this angle is large, it will directly cause the parachute system to enter an unstable working state. Specifically, this manifests as an abnormally large increase in the swing amplitude of the suspended object, and the system's instantaneous overload reaching extreme values. This can lead to collisions and friction between the parachute lines and the suspended object, and even the serious risk of the parachute lines being cut. This not only affects the deceleration effect of the parachute but may also cause the parachute system to fail, resulting in damage to the suspended object or failure of the deployment mission.

[0004] To reduce the risks caused by the aforementioned adverse operating conditions and to ensure the stable operation of the parachute system and the successful completion of the deployment mission, this application proposes a parachute deceleration device that provides favorable parachute opening conditions. Summary of the Invention

[0005] The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose a parachute deceleration device that provides good parachute opening conditions, thereby solving the technical problem in the prior art that the axial direction of the suspended object is inconsistent with the descent direction.

[0006] To achieve the above-mentioned technical objectives, the technical solution of the present invention provides a parachute deceleration device that provides good parachute opening conditions, including a parachute compartment and a storage cavity;

[0007] A parachute is located inside the storage cavity; A suspended object is located in the umbrella compartment; The detection mechanism, located in the parachute compartment, is used to collect the attitude angle and falling speed of the suspended object; Wings, a plurality of said winglets being arranged around the periphery of said parachute compartment; and, An adjustment mechanism is provided in the parachute compartment, with a fixed end connected to the parachute compartment and a movable end connected to the winglet. The detection mechanism is electrically connected to the adjustment mechanism, and the adjustment mechanism is used to release and adjust the angle of the winglet.

[0008] In some embodiments, the detection mechanism includes a gyroscope, an accelerometer, and a controller. The gyroscope, accelerometer, controller, and adjustment mechanism are electrically connected. The gyroscope is used to acquire the attitude angle of the suspended object in real time. The accelerometer is used to acquire the falling speed of the suspended object in real time. The controller is used to compare the real-time attitude angle, the real-time falling speed, and a threshold value to control the action of the adjustment mechanism.

[0009] In some embodiments, the adjustment mechanism includes an electric push rod, a drive rack, and a driven gear. The electric push rod is disposed inside the cabin. The drive rack is connected to the output shaft of the electric push rod and is slidably connected to the cabin along the axial direction of the cabin. The driven gear is connected to the winglet and is rotatably connected to the cabin. The drive rack meshes with multiple driven gears simultaneously.

[0010] In some embodiments, the deceleration device further includes a cover plate and an opening and closing mechanism. The parachute compartment is provided with a receiving cavity for accommodating the winglets. The cover plate is slidably connected to the opening of the receiving cavity. The fixed end of the opening and closing mechanism is connected to the parachute compartment, and the movable end of the opening and closing mechanism is connected to the cover plate. The opening and closing mechanism is used to control the opening and closing of the cover plate.

[0011] In some embodiments, the opening and closing mechanism includes a push rod, one end of which is hinged to the wing and the other end of which is hinged to the cover plate.

[0012] In some embodiments, the deceleration device further includes a sealing assembly, which includes a convex sealing strip and a concave sealing strip. The convex sealing strip is connected to the cover plate, and the concave sealing strip is connected to the receiving cavity. The convex sealing strip and the concave sealing strip are adapted to each other.

[0013] In some embodiments, the deceleration device further includes a duct ring and an electric fan. The duct ring is connected to one end of the winglet away from the cabin, and the electric fan is installed inside the duct ring. The air inlet of the electric fan faces the parachute side, and the air outlet of the electric fan faces the suspended object side.

[0014] In some embodiments, the deceleration device further includes a filter screen connected to the end of the duct ring.

[0015] In some embodiments, the duct ring is radially arranged on the side of the electric fan's outlet.

[0016] In some embodiments, the reduction device further includes a motor, a driving gear, a driven gear ring, a support ring, a main support head, and a secondary support head. The duct ring is integrally hinged to the vane. The motor is disposed on the vane. The driving gear is connected to the output shaft of the motor. The support ring is rotatably connected to the vane. The driven gear ring is connected to the support ring. The driving gear meshes with the driven gear ring. The main support head and the secondary support head are both connected to the support ring. The main support head and the secondary support head abut against the end of the duct ring to make the duct ring in an inclined state. The end of the duct ring is provided with a sliding groove for the main support head and the secondary support head to slide.

[0017] Compared with the prior art, the beneficial effects of the present invention include: by sensing attitude deviation in real time through the detection mechanism and dynamically adjusting the wing angle through the adjustment mechanism, the interaction between the wing and the airflow generates a precise attitude adjustment torque, which can actively correct the axial deviation of the suspended object to a state that is consistent with the falling direction, reduce the deflection angle at the moment of parachute opening, and provide stable parachute opening conditions. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of the deceleration device provided by the present invention; Figure 2 This is a cross-sectional view of the overall structure of the parachute compartment in its first state provided by the present invention; Figure 3 This is a cross-sectional view of the second state of the parachute compartment provided by the present invention; Figure 4 This is a cross-sectional view of the overall structure of the wing provided by the present invention.

[0019] Explanation of reference numerals in the attached figures: 1. Parachute; 2. Parachute compartment; 21. Storage cavity; 3. Suspension; 4. Detection mechanism; 41. Gyroscope; 42. Accelerometer; 43. Controller; 5. Wing; 51. Cover plate; 52. Opening and closing mechanism; 521. Push rod; 53. Receiving cavity; 6. Adjustment mechanism; 61. Electric push rod; 62. Driving rack; 63. Driven gear; 7. Sealing assembly; 71. Convex sealing strip; 72. Concave sealing strip; 8. Duct ring; 81. Electric fan; 82. Filter screen; 83. Motor; 84. Driving gear; 85. Driven gear ring; 86. Support ring; 87. Main support head; 88. Secondary support head; 89. Slide groove. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0021] This invention provides a parachute deceleration device that provides good parachute opening conditions, the structure of which is as follows: Figure 1 - Figure 4 As shown, it includes a parachute compartment 2 and a storage cavity 21; Parachute 1 is disposed within the receiving cavity 21; Suspension 3 is provided in the umbrella compartment 2; The detection mechanism 4, located in the umbrella chamber 2, is used to collect the attitude angle and falling speed of the suspended object 3; Wings 5, a plurality of said wings 5 ​​are arranged around the periphery of said parachute compartment 2; and, An adjustment mechanism 6 is provided in the parachute compartment 2, with its fixed end connected to the parachute compartment 2 and its movable end connected to the wing 5. The detection mechanism 4 is electrically connected to the adjustment mechanism 6, and the adjustment mechanism 6 is used to release and adjust the angle of the wing 5.

[0022] In use, the parachute 1 is first stored in the storage cavity 21 of the parachute compartment 2, and the suspended object 3 is assembled into the parachute compartment 2, completing the main assembly of the device. In the initial state, the movable end of the adjusting mechanism 6 constrains the winglets 5, so that the multiple winglets 5 are in a state of being folded and attached to the periphery of the parachute compartment 2. When the device is released into the air along with the suspended object 3, the detection mechanism 4 is activated to collect the attitude angle and descent speed of the suspended object 3 in real time, and transmits the collected real-time data to the adjusting mechanism 6. After receiving the real-time data from the detection mechanism 4, the adjusting mechanism 6 first releases the constraint on the winglets 5, completing the release of the winglets 5; then, based on the attitude angle data, it judges the degree of deviation between the axial direction of the suspended object 3 and the descent direction, and drives the movable end to adjust the deployment angle of the multiple circumferential winglets 5. After unfolding and adjusting their angles, the multiple blades 5 interact with the airflow during the descent of the suspended object 3, generating a uniform circumferential attitude adjustment torque. This torque drives the suspended object 3 to rotate around its own axis, gradually correcting its attitude and bringing it axially closer to the downward direction of descent until the attitude angle data collected by the detection mechanism 4 meets the preset good parachute opening conditions. Once the attitude of the suspended object 3 stabilizes under good parachute opening conditions, the parachute 1 inside the parachute compartment 2 can be deployed normally.

[0023] In this invention, the detection mechanism 4 senses the attitude deviation in real time, and the adjustment mechanism 6 dynamically controls the angle of the wing 5 so that the wing 5 interacts with the airflow to generate a precise attitude adjustment torque. This can actively correct the axial deviation of the suspended object 3 to a state that is consistent with the falling direction, reduce the deflection angle at the moment of parachute opening, and provide stable opening conditions for the parachute 1.

[0024] To achieve accurate determination of attitude deviation, please refer to... Figure 2In a preferred embodiment, the detection mechanism 4 includes a gyroscope 41, an accelerometer 42, and a controller 43. The gyroscope 41, the accelerometer 42, the controller 43, and the adjustment mechanism 6 are electrically connected. The gyroscope 41 is used to collect the attitude angle of the suspended object 3 in real time. The accelerometer 42 is used to collect the falling speed of the suspended object 3 in real time. The controller 43 is used to compare the real-time attitude angle, the real-time falling speed, and a threshold value to control the action of the adjustment mechanism 6.

[0025] When in use, the gyroscope 41 can collect attitude angle parameters such as heading angle, pitch angle, and roll angle of the suspended object 3 in real time and with high precision, and accurately quantify the degree of deviation between the axis of the suspended object 3 and the falling direction; the accelerometer 42 simultaneously collects the falling speed of the suspended object 3, providing key basis for the controller 43 to judge the parachute opening condition.

[0026] To adjust the angle of winglet 5, please refer to... Figure 2 In a preferred embodiment, the adjustment mechanism 6 includes an electric push rod 61, a drive rack 62, and a driven gear 63. The electric push rod 61 is disposed in the cabin, the drive rack 62 is connected to the output shaft of the electric push rod 61, the drive rack 62 is slidably connected to the cabin along the axial direction of the cabin, the driven gear 63 is connected to the winglet 5, the driven gear 63 is rotatably connected to the cabin, and the drive rack 62 meshes with multiple driven gears 63 simultaneously.

[0027] In operation, the electric push rod 61 starts upon receiving a command, and its output shaft extends axially along the parachute compartment 2, driving the fixed active rack 62 to slide precisely axially along the guide rail. During the sliding process, the guide rail constantly restricts the movement trajectory of the active rack 62, ensuring stable meshing with all driven gears 63. Since the active rack 62 meshes with multiple driven gears 63 simultaneously, the axial linear motion of the active rack 62 is converted into synchronous rotational motion of all driven gears 63 through tooth surface meshing transmission. Because the driven gears 63 are fixedly connected to the winglets 5, their rotation directly drives the winglets 5 to rotate synchronously around the axis, realizing the deployment or angle fine-tuning of the winglets 5. The controller 43 precisely controls the sliding distance of the active rack 62 by adjusting the extension or retraction stroke of the output shaft of the electric push rod 61 according to the degree of attitude deviation. Combined with the gear transmission ratio, the rotation angle of the driven gears 63 can be accurately calculated, thereby achieving quantitative control of the deployment angle of the winglets 5.

[0028] To reduce the possibility of damage to winglet 5, please refer to Figure 3In a preferred embodiment, the deceleration device further includes a cover plate 51 and an opening and closing mechanism 52. The parachute compartment 2 is provided with a receiving cavity 53 for accommodating the wing 5. The cover plate 51 is slidably connected to the opening of the receiving cavity 53. The fixed end of the opening and closing mechanism 52 is connected to the parachute compartment 2, and the movable end of the opening and closing mechanism 52 is connected to the cover plate 51. The opening and closing mechanism 52 is used to control the opening and closing of the cover plate 51.

[0029] In use, initially, the winglets 5 are retracted into the receiving cavity 53 of the parachute compartment 2. The opening and closing mechanism 52 drives the cover plate 51 to slide and close the opening of the receiving cavity 53, completely enclosing and protecting the winglets 5. This prevents deformation or wear of the winglets 5 during transportation and storage. Simultaneously, during the initial deployment phase, the closed cover plate 51 prevents the winglets 5 from bending and being damaged by high-speed airflow, ensuring the structural integrity and functional effectiveness of the winglets 5 during attitude correction. After the cover plate 51 closes the receiving cavity 53, the parachute compartment 2 presents a streamlined aerodynamic shape, significantly reducing air resistance and airflow disturbance during the initial deployment phase, preventing trajectory deviation caused by exposed winglets 5, and ensuring the initial stability of the suspended object 3's descent attitude.

[0030] To open and close cover 51, please refer to... Figure 3 In a preferred embodiment, the opening and closing mechanism 52 includes a push rod 521, one end of which is hinged to the wing 5, and the other end of which is hinged to the cover plate 51.

[0031] When the device is deployed into the air, the detection mechanism 4 determines that the attitude deviation of the suspended object 3 exceeds the threshold and issues a command to the adjustment mechanism 6: the electric push rod 61 drives the active rack 62 to slide axially, and through tooth surface meshing, drives all driven gears 63 to rotate synchronously. The driven gears 63 drive the fixed wing 5 to rotate around the axis, and the wing 5 begins to unfold from inside the receiving cavity 53 to the outside. During this process, the rotational motion of the wing 5 is transmitted to the push rod 521 through the hinge point: when the wing 5 rotates, its hinge point with the push rod 521 undergoes radial displacement, pushing the push rod 521 to perform a linear pushing motion; since the other end of the push rod 521 is hinged to the inside of the cover plate 51, and the cover plate 51 is constrained by the slide rail of the receiving cavity 53 opening and can only slide axially, the pushing force of the push rod 521 is converted into the power to drive the cover plate 51 to slide, causing the cover plate 51 to move along the slide rail away from the receiving cavity 53, gradually opening the opening of the receiving cavity 53.

[0032] To improve the sealing of parachute compartment 2, please refer to... Figure 3In a preferred embodiment, the deceleration device further includes a sealing component 7, which includes a convex sealing strip 71 and a concave sealing strip 72. The convex sealing strip 71 is connected to the cover plate 51, and the concave sealing strip 72 is connected to the receiving cavity 53. The convex sealing strip 71 and the concave sealing strip 72 are adapted to each other.

[0033] In use, the fitting structure of the convex sealing strip 71 and the concave sealing strip 72 creates a labyrinthine sealing effect with multiple contact sealing surfaces, compared to a single flat sealing strip. When the cover plate 51 closes the opening of the receiving cavity 53, the convex sealing strip 71 will precisely embed into the groove of the concave sealing strip 72, sealing the gap between the cover plate 51 and the receiving cavity 53, effectively preventing foreign objects such as dust, sand, and rainwater from entering the receiving cavity 53.

[0034] To further enhance the regulatory effect, please refer to Figure 4 In a preferred embodiment, the deceleration device further includes a duct ring 8 and an electric fan 81. The duct ring 8 is connected to the end of the wing 5 away from the cabin. The electric fan 81 is installed inside the duct ring 8. The air inlet of the electric fan 81 faces the parachute 1 and the air outlet of the electric fan 81 faces the suspended object 3.

[0035] In use, the controller 43 uses a graded control method based on the attitude deviation collected by the detection mechanism 4. If the attitude deviation of the suspended object 3 is small, attitude correction can be achieved solely by the attitude adjustment torque generated by the interaction between the winglets 5 and the airflow. If the attitude deviation of the suspended object 3 is large, the controller 43 immediately sends a start command to the electric fan 81 at the end of the corresponding winglet 5. After the electric fan 81 starts, the air inlet draws in the airflow above the parachute compartment 2, which is rectified by the duct ring 8 to form a stable directional airflow that blows towards one side of the suspended object 3 from the outlet. The airflow jet generates a reverse thrust, which, combined with the flow convergence effect of the duct ring 8, can be converted into an auxiliary attitude adjustment torque. Since multiple winglets 5 are evenly distributed around the circumference of the parachute compartment 2, the controller 43 can achieve precise fine-tuning of the attitude of the suspended object 3 by adjusting the speed of the electric fan 81 at the ends of different winglets 5.

[0036] To improve the operational stability of electric fan 81, please refer to... Figure 4 In a preferred embodiment, the deceleration device further includes a filter screen 82, which is connected to the end of the duct ring 8.

[0037] During use, in the airdrop process, the high-altitude environment contains foreign objects such as sand and dust particles. If these particles directly enter the duct ring 8, they can easily impact the impeller of the high-speed rotating electric fan 81, causing impeller deformation, dynamic imbalance, and resulting in fan vibration, increased noise, or even shutdown. The filter screen 82 can accurately intercept foreign objects, preventing them from entering the duct ring 8 and contacting the impeller and motor shaft 83, thus ensuring the thrust stability and operational reliability of the fan during attitude correction.

[0038] To improve thrust utilization, please refer to Figure 4 In a preferred embodiment, the duct ring 8 is radially arranged on the side of the air outlet of the electric fan 81.

[0039] When in use, the radial structure of the duct ring 8 outlet can constrain and guide the airflow blown out by the electric fan 81, preventing the airflow from spreading disorderly at the outlet and forcing the airflow to concentrate along the extension direction of the radial ribs, thereby improving the axial concentration and spray distance of the airflow.

[0040] To adjust the angle of the electric fan 81, please refer to... Figure 4 In a preferred embodiment, the reduction device further includes a motor 83, a driving gear 84, a driven gear ring 85, a support ring 86, a main support head 87, and a secondary support head 88. The duct ring 8 is integrally hinged to the vane 5. The motor 83 is disposed on the vane 5. The driving gear 84 is connected to the output shaft of the motor 83. The support ring 86 is rotatably connected to the vane 5. The driven gear ring 85 is connected to the support ring 86. The driving gear 84 meshes with the driven gear ring 85. The main support head 87 and the secondary support head 88 are both connected to the support ring 86. The main support head 87 and the secondary support head 88 abut against the end of the duct ring 8 so that the duct ring 8 is in an inclined state. The end of the duct ring 8 is provided with a sliding groove 89 for the main support head 87 and the secondary support head 88 to slide.

[0041] In use, the duct ring 8 is connected to the end of the vane 5, the motor 83 is fixedly installed inside the vane 5, and its output shaft is rigidly connected to the drive gear 84; the support ring 86 is rotatably connected to the vane 5 through the bearing, the outer ring of the support ring 86 is fixedly connected to the driven gear ring 85, and the drive gear 84 and the driven gear ring 85 mesh precisely to form a gear transmission link; the main support head 87 and the auxiliary support head 88 are symmetrically fixed on the side of the support ring 86 facing the duct ring 8, and the ends of the two are embedded in the pre-set sliding groove 89 at the end of the duct ring 8. In the initial state, the controller 43 keeps the motor 83 stationary, the support ring 86 is in the preset initial position, the main support head 87 and the auxiliary support head 88 are fixed in the position of the slide 89, the main support head 87 and the auxiliary support head 88 have different lengths, pushing the duct ring 8 to form an initial tilt angle of fifteen degrees. After the device is deployed, the gyroscope 41 and the acceleration sensor 42 of the detection mechanism 4 collect the attitude angle and falling speed of the suspended object 3 in real time. When the controller 43 determines that the attitude deviation of the suspended object 3 exceeds the threshold and cannot be quickly corrected by relying solely on the aerodynamics of the wing 5 and the differential speed regulation of the electric fan 81, it immediately sends an angle adjustment command to the motor 83 of the corresponding wing 5. The command includes the tilt direction and angle value that the duct ring 8 needs to be adjusted. After receiving a command, motor 83 starts, and its output shaft drives the drive gear 84 to rotate. The drive gear 84 drives the driven gear ring 85 to rotate synchronously through tooth surface meshing. Since the driven gear ring 85 is fixedly connected to the support ring 86, the rotation of the driven gear ring 85 directly drives the support ring 86 to rotate around its own axis. The main support head 87 and the auxiliary support head 88 on the support ring 86 move in a circular motion synchronously with the support ring 86. During the circular motion with the support ring 86, the ends of the main support head 87 and the auxiliary support head 88 are always embedded in the groove 89 of the duct ring 8 and slide along the groove 89. Using the guiding constraint of the groove 89 and the thrust of the support head, the duct ring 8 is tilted. After the tilt angle of the duct ring 8 is adjusted, the airflow jet direction of the electric fan 81 changes accordingly, and the direction of the generated reverse thrust torque also changes synchronously. Combined with the differential speed regulation and angle adjustment of different blades 5, a multi-dimensional attitude correction torque can be formed.

[0042] To better understand this invention, the following is combined with... Figure 1 - Figure 4The working principle of a parachute 1 deceleration device that provides good parachute opening conditions according to the technical solution of the present invention is described in detail as follows: First, the parachute 1 is stored in the storage cavity 21 of the parachute compartment 2, and the suspended object 3 is assembled into the parachute compartment 2, completing the main assembly of the device. In the initial state, the movable end of the adjusting mechanism 6 constrains the winglets 5, so that multiple winglets 5 are in a state of being folded and attached to the periphery of the parachute compartment 2. When the device is released into the air along with the suspended object 3, the detection mechanism 4 is activated to collect the attitude angle and falling speed of the suspended object 3 in real time, and transmits the collected real-time data to the adjusting mechanism 6. After receiving the real-time data from the detection mechanism 4, the adjusting mechanism 6 first releases the constraint on the winglets 5, completing the release of the winglets 5; then, based on the attitude angle data, it judges the degree of deviation between the axial direction of the suspended object 3 and the falling direction, and drives the movable end to adjust the deployment angle of the multiple circumferential winglets 5. After unfolding and adjusting their angles, the multiple blades 5 interact with the airflow during the descent of the suspended object 3, generating a uniform circumferential attitude adjustment torque. This torque drives the suspended object 3 to rotate around its own axis, gradually correcting its attitude and bringing it axially closer to the downward direction of descent until the attitude angle data collected by the detection mechanism 4 meets the preset good parachute opening conditions. Once the attitude of the suspended object 3 stabilizes under good parachute opening conditions, the parachute 1 inside the parachute compartment 2 can be deployed normally.

[0043] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A parachute deceleration device providing good parachute opening conditions, characterized in that The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity.

2. The parachute deceleration device providing good conditions for opening of the parachute according to claim 1, characterized in that, The parachute cabin is provided with a receiving cavity.

3. The parachute deceleration device providing good parachute opening conditions according to claim 1, characterized in that The parachute cabin is provided with a receiving cavity.

4. The parachute deceleration device providing good parachute opening conditions according to claim 1, characterized in that The parachute cabin is provided with a receiving cavity.

5. The parachute deceleration device providing good conditions for opening of the parachute according to claim 4, characterized in that The parachute cabin is provided with a receiving cavity.

6. The parachute deceleration device providing good canopy opening conditions according to claim 4, characterized in that The parachute cabin is provided with a receiving cavity.

7. The parachute deceleration device providing good canopy opening conditions according to claim 1, characterized in that The parachute cabin is provided with a receiving cavity.

8. The parachute deceleration device providing good canopy opening conditions according to claim 7, characterized in that The parachute cabin is provided with a receiving cavity.

9. The parachute deceleration device providing good canopy opening conditions according to claim 7, characterized in that The parachute cabin is provided with a receiving cavity.

10. The parachute deceleration device providing good parachute opening conditions according to claim 7, characterized in that The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cabinet is provided with a receiving cavity. The parachute cabinet is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute case is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute housing is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute casing is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute cavity is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute chamber is provided with a receiving cavity. The parachute house is provided with a receiving cavity. The parachute cabin is provided with a receiving cavity. The parachute hous

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