A continuously variable drag characteristic test device and method for life-saving parachute airdrop

Abstract

A device and method for testing the continuously variable drag characteristics of a life-saving parachute airdrop relates to the field of parachutes. The device and method comprise a test projectile, a plurality of canopy inner supports arranged circumferentially along the test projectile, a plurality of canopy outer supports arranged circumferentially along the test projectile, an annular drag parachute canopy sleeved over the middle of the test projectile, at least one restraint sleeve, and a cutter connected to the test projectile. Each canopy inner support has two ends connected to the test projectile and the inner wall of the drag parachute canopy, respectively. Each canopy outer support has one end hinged to the test projectile so as to be rotatable toward or away from the test projectile, and the other end connected to the outer wall of the drag parachute canopy. The restraint sleeve is used to sleeve the drag parachute canopy over the middle outer wall of the test projectile, and the cutter is used to periodically cut the restraint sleeve. The device and method for testing the continuously variable drag characteristics of a life-saving parachute airdrop can continuously adjust the drag characteristics of the test projectile to meet the requirements of a life-saving parachute airdrop test.

Description

Technical Field

[0001] The present application relates to the field of parachutes, and in particular to a device and method for testing continuously variable resistance characteristics of a life-saving parachute airdrop. Background Art

[0002] In order to verify the performance of parachutes such as lifesaving parachutes, such as parachute opening overload, parachute opening force, parachute opening procedure, speed and strength when opening, a parachute that can meet the resistance characteristics of 0.2m is required. 2 ~0.4m 2 The test device has a weight of 100kg to 130kg, a parachute opening speed (true speed) of 150km / h to 650km / h, and an airdrop height of 400m to 4000m to meet the needs of life-saving parachute airdrop tests.

[0003] Currently, traditional rigid dummies and projectiles are often used as the front body of airdrop tests, which can lead to problems such as poor parachute opening procedures and excessive parachute opening force. There are also cases where the 250-4 test projectile with good stability is used as the front body, but the drag characteristic of the front body is only 0.011m 2 , which leads to problems such as poor deceleration effect, excessive parachute opening speed and force, and the formal performance of the life-saving parachute cannot be assessed. In addition, the test state is single, the test cost is high, and the single assessment item has limitations. Summary of the Invention

[0004] The purpose of the present application is to provide a continuously variable resistance characteristic test device and method for life-saving parachute airdrop, which can continuously adjust the resistance characteristics of the test projectile to meet the use requirements of the life-saving parachute airdrop test.

[0005] This application is implemented as follows:

[0006] The present application provides a continuously variable drag characteristic test device for airdropping a life-saving parachute, which includes a test projectile, a plurality of canopy inner supports arranged at intervals along the circumference of the test projectile, a plurality of canopy outer supports arranged at intervals along the circumference of the test projectile, an annular drag parachute canopy sleeved on the middle part of the test projectile, at least one restraint sleeve and a cutter connected to the test projectile, wherein the two ends of each canopy inner support are respectively connected to the test projectile and the inner side wall of the drag parachute canopy; one end of each canopy outer support can be hinged to the test projectile so as to be rotatable toward or away from the test projectile, and the other end is connected to the outer side wall of the drag parachute canopy; the restraint sleeve is used to sleeve the drag parachute canopy on the outer wall of the middle part of the test projectile, and the cutter is used to regularly cut off the restraint sleeve.

[0007] In some optional embodiments, the test bomb is further provided with a driving mechanism for driving each canopy outer support to rotate synchronously toward or away from the test bomb.

[0008] In some optional embodiments, the driving mechanism includes a rotating motor corresponding one-to-one to the canopy outer bracket, the canopy outer bracket is hinged to the outer wall of the test bomb through a rotating shaft, and the output shaft of the rotating motor is connected to the rotating shaft.

[0009] In some optional embodiments, the test projectile includes a warhead, a middle part of the projectile, a tail connecting sleeve and a tail of the projectile connected in sequence, and the tail of the projectile is connected to a plurality of tail fins.

[0010] In some optional embodiments, at least one counterweight is connected to the tail connecting sleeve.

[0011] In some optional embodiments, the outer surface profile of the test projectile is formed by rotating the projectile curve around the X-axis of a plane rectangular coordinate system, and the projectile curve includes a first curve segment, a second curve segment, a third curve segment, a fourth curve segment, a fifth curve segment, a sixth curve segment, a seventh curve segment, an eighth curve segment, a ninth curve segment, a tenth curve segment, an eleventh curve segment, a twelfth curve segment, and a thirteenth curve segment connected in sequence along the positive direction of the X-axis;

[0012] The first curve segment is defined by the following formula: x=0, 0≤y≤49.3618;

[0013] The second curve segment is defined by the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92;

[0014] The third curve segment is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045;

[0015] The fourth curve segment is defined by the following formula: x=355.0472, 204.4878≤y≤274.4795;

[0016] The fifth curve segment is defined by the following formula: 354.0472≤x≤364.8727, y=274.4795;

[0017] The sixth curve segment is defined by the following formula: 364.8727≤x≤414.0627, (x-356.17) 2 +(y-(-16.00)) 2 =87731.30;

[0018] The seventh curve segment is defined by the following formula: 414.06272≤x≤485.365, (x-473.15) 2 +(y-(829.74)) 2 =311806.32;

[0019] The eighth curve segment is defined by the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854;

[0020] The ninth curve segment is defined by the following formula: 988.3318≤x≤1101.0523, (x-985.11) 2 +(y-(94.15)) 2 =31563.18;

[0021] The tenth curve segment is defined by the following formula: 1101.0523≤x≤1209.1176, (x-1360.70) 2 +(y-(594.47)) 2 =201158.89;

[0022] The eleventh curve is defined by the following formula: 1209.1176≤x≤1380.7778, (x-1383.77) 2 +(y-(966.85)) 2 =661721.08;

[0023] The twelfth curve is defined by the following formula: 1380.7778≤x≤2148.9854, y=-0.0493x+221.4867;

[0024] The thirteenth curve segment is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

[0025] The present application also provides a method for testing continuously variable drag characteristics for airdropping of a lifesaving parachute, which comprises the following steps:

[0026] Step 1: Connect the life-saving parachute to the above-mentioned continuously variable resistance characteristic test device for life-saving parachute airdrop and perform airdrop;

[0027] Step 2: Control the cutter to cut off the restraint sleeve at the preset time, so that the drag parachute canopy is inflated and opened, driving each canopy outer support to rotate away from the test missile body.

[0028] In some optional embodiments, the method further includes step three: using a driving mechanism to drive each canopy outer support to synchronously rotate toward or away from the test missile to adjust the deployment area of ​​the drag parachute canopy.

[0029] The beneficial effects of the present application are as follows: the continuously variable drag characteristic test device for life-saving parachute airdrop provided by the present application includes a test projectile, a plurality of canopy inner supports spaced apart along the circumference of the test projectile, a plurality of canopy outer supports spaced apart along the circumference of the test projectile, an annular drag parachute canopy sleeved on the middle portion of the test projectile, at least one restraint sleeve, and a cutter connected to the test projectile, wherein the two ends of each canopy inner support are respectively connected to the test projectile and the inner side wall of the drag parachute canopy; one end of each canopy outer support is hinged to the test projectile so as to be rotatable toward or away from the test projectile, and the other end is connected to the outer side wall of the drag parachute canopy; the restraint sleeve is used to sleeve the drag parachute canopy onto the middle outer wall of the test projectile, and the cutter is used to periodically cut the restraint sleeve. The continuously variable drag characteristic test device and method for life-saving parachute airdrop provided by the present application can continuously adjust the drag characteristic of the test projectile and ensure stability during airdrop to meet the use requirements of life-saving parachute airdrop tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0031] Figure 1 A schematic structural diagram of a first use state of a continuously variable resistance characteristic testing device for airdropping of a lifesaving parachute provided in an embodiment of the present application;

[0032] Figure 2 A schematic diagram of the structure of the second use state of the continuously variable resistance characteristic testing device for parachute airdrop provided by an embodiment of the present application;

[0033] Figure 3 A schematic diagram of a partial cross-sectional structure of a continuously variable drag characteristic test device for airdropping of a lifesaving parachute provided in an embodiment of the present application;

[0034] Figure 4 A schematic structural diagram of a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute provided in another embodiment of the present application;

[0035] Figure 5 This is a schematic diagram of a projectile curve of the outer surface profile of a test projectile in a continuous variable resistance characteristic test device for airdrop of a life-saving parachute provided in another embodiment of the present application, in a plane rectangular coordinate system.

[0036] In the figure: 100, test projectile; 101, warhead; 102, middle part of projectile; 103, tail connecting sleeve; 104, tail of projectile; 105, tail wing; 110, inner bracket of canopy; 120, outer bracket of canopy; 130, drag parachute canopy; 140, restraint sleeve; 150, cutter; 160, rotating shaft; 170, rotating motor; 180, counterweight; 201, first section of curve; 202, second section of curve; 203, third section of curve; 204, fourth section of curve; 205, fifth section of curve; 206, sixth section of curve; 207, seventh section of curve; 208, eighth section of curve; 209, ninth section of curve; 210, tenth section of curve; 211, eleventh section of curve; 212, twelfth section of curve; 213, thirteenth section of curve. DETAILED DESCRIPTION

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Generally, the components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for protection, but merely represents selected embodiments of the present application. All other embodiments obtained by persons of ordinary skill in the art based on the embodiments in the present application without creative work are within the scope of protection of the present application.

[0039] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0040] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the product of this application is typically placed when in use. These terms are intended only to facilitate the description of this application and simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," "third," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0041] Furthermore, terms such as "horizontal," "vertical," and "overhanging" do not necessarily imply that a component must be absolutely horizontal or overhanging, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0042] It should also be noted that, in the description of this application, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0043] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0044] The features and performance of the continuously variable resistance characteristic test device and method for airdropping of a lifesaving parachute of the present application are further described in detail below in conjunction with the embodiments.

[0045] like Figure 1 、 Figure 2 and Figure 3As shown, the embodiment of the present application provides a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute, which includes a test projectile 100, six canopy inner brackets 110 arranged at intervals along the circumference of the test projectile 100, six canopy outer brackets 120 arranged at intervals along the circumference of the test projectile 100, an annular drag parachute canopy 130 sleeved on the middle part of the test projectile 100, a restraining sleeve 140 and a cutter 150 connected to the test projectile 100, the canopy inner bracket 110 and the canopy outer bracket 120 both extend along the length direction of the test projectile 100, and the test projectile 100 includes a warhead 101, a projectile middle part 102, a tail connecting sleeve 103 and a tail connecting sleeve 104 connected in sequence. 03 and the tail of the projectile 104, the tail of the projectile 104 is connected with four tail wings 105 arranged in an X shape; the two ends of each canopy inner bracket 110 are respectively connected to the test projectile 100 and the inner wall of the drag parachute canopy 130; the end of each canopy outer bracket 120 close to the warhead 101 is respectively hinged to the test projectile 100 through the rotating shaft 160, which can be rotated towards or away from the test projectile 100, and the other end of each canopy outer bracket 120 away from the warhead 101 is connected to the outer wall of the drag parachute canopy 130; the restraint sleeve 140 is used to sleeve the drag parachute canopy 130 on the middle outer wall of the test projectile 100, and the cutter 150 is used to cut off the restraint sleeve 140 at a time. The test body 100 is provided with a driving mechanism for driving each canopy outer bracket 120 to rotate synchronously toward or away from the test body 100. The driving mechanism includes a rotating motor 170 corresponding one to one with the canopy outer bracket 120. The canopy outer bracket 120 is hinged to the rotating shaft 160. The rotating motor 170 is fixed to the outer wall of the test body 100 and the output shaft is connected to the corresponding rotating shaft 160.

[0046] The present application also provides a method for testing continuously variable drag characteristics for airdropping of a lifesaving parachute, which comprises the following steps:

[0047] Step 1: Pack the life-saving parachute in a parachute bag, connect the life-saving parachute control belt of the life-saving parachute to the above-mentioned continuous variable resistance characteristic test device for life-saving parachute airdrop, fix the detection equipment on the test body 100 of the continuous variable resistance characteristic test device for life-saving parachute airdrop, and airdrop;

[0048] Step 2: After the airdrop, the life-saving parachute opens and drives the continuously variable resistance characteristic test device for life-saving parachute airdrop to descend to a preset height within a preset time. The cutter 150 is controlled to cut off the restraint sleeve 140, so that the drag parachute canopy 130 is inflated and opened, driving each canopy outer frame 120 to rotate away from the test projectile 100, so that the deployed drag parachute canopy 130 adjusts the resistance characteristics of the test projectile 100 and then continues to descend for testing.

[0049] Step 3: Use the driving mechanism to drive each canopy outer bracket 120 to rotate synchronously toward or away from the test projectile 100 to adjust the deployment area of ​​the drag parachute canopy 130. Specifically, control each rotating motor 170 to start and synchronously drive each rotating shaft 160 to rotate through the output shaft to drive each canopy outer bracket 120 to rotate toward or away from the test projectile 100, thereby adjusting the deployment area of ​​the drag parachute canopy 130 to adjust the resistance characteristics of the test projectile 100 to the preset value for testing.

[0050] The continuously variable resistance characteristic test device and method for airdropping of a life-saving parachute provided in the embodiment of the present application is achieved by arranging an annular drag parachute canopy 130 on the outer wall of the test projectile 100, and using multiple canopy inner brackets 110 to connect and confine the inner side wall of the drag parachute canopy 130 to the outer wall of the test projectile 100, and using multiple canopy outer brackets 120 that can rotate toward or away from the test projectile 100 to connect and adjust the outer side wall position of the drag parachute canopy 130. When the test projectile 100 is airdropped, the canopy inner brackets 110 are pushed by air to rotate to change the deployment area of ​​the drag parachute canopy 130, thereby adjusting the resistance characteristics of the test projectile 100 to test different technical conditions. At the same time, the driving mechanism can also be used to drive each canopy outer bracket 120 to rotate synchronously toward or away from the test projectile 100 to adjust the deployment area of ​​the drag parachute canopy 130 to test the required technical conditions. This not only can obtain test data with more comparative significance, but also can greatly save test costs.

[0051] The test projectile 100 includes a warhead 101, a middle part 102, a tail connecting sleeve 103 and a tail part 104 connected in sequence. The tail part 104 is connected to four tail fins 105 arranged in an X shape. The tail fins 105 can be used to improve the stability of the test projectile 100 during airdrop, thereby preventing the test projectile 100 from rolling during the airdrop process and affecting the test progress.

[0052] In other optional embodiments, the tail connecting sleeve 103 can also be connected to one, two, three, four or more counterweights; when the number of the counterweight is one, it can be annular and fixedly sleeved on the tail connecting sleeve 103; when the number of the counterweight is two or more, each counterweight is connected to the tail connecting sleeve 103 at intervals along the axial direction; by arranging one or more counterweights on the tail connecting sleeve 103, the weight of the test body 100 can be adjusted to adapt to different test requirements; Figure 4 The figure shows a schematic structural diagram of a tail connecting sleeve 103 of a continuously variable resistance characteristic test device for parachute airdrop in another embodiment of the present application when it is connected to two counterweights 180 .

[0053] In other optional embodiments, such as Figure 5As shown, the outer surface profile of the test projectile 100 can also be formed by rotating the projectile curve around the X-axis of the plane rectangular coordinate system, and the projectile curve includes a first curve 201, a second curve 202, a third curve 203, a fourth curve 204, a fifth curve 205, a sixth curve 206, a seventh curve 207, an eighth curve 208, a ninth curve 209, a tenth curve 210, an eleventh curve 211, a twelfth curve 212 and a thirteenth curve 213 connected in sequence along the positive direction of the X-axis;

[0054] The first curve 201 is defined by the following formula: x=0, 0≤y≤49.3618;

[0055] The second curve 202 is defined using the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92;

[0056] The third curve 203 is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045;

[0057] The fourth curve 204 is defined using the following formula: x=355.0472, 204.4878≤y≤274.4795;

[0058] The fifth curve 205 is defined using the following formula: 354.0472≤x≤364.8727, y=274.4795;

[0059] The sixth curve 206 is defined by the following formula: 364.8727≤x≤414.0627, (x-356.17) 2 +(y-(-16.00)) 2 =87731.30;

[0060] The seventh curve 207 is defined by the following formula: 414.06272≤x≤485.365, (x-473.15) 2 +(y-(829.74)) 2 =311806.32;

[0061] The eighth curve 208 is defined using the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854;

[0062] The ninth curve 209 is defined by the following formula: 988.3318≤x≤1101.0523, (x-985.11) 2+(y-(94.15)) 2 =31563.18;

[0063] The tenth curve 210 is defined by the following formula: 1101.0523≤x≤1209.1176, (x-1360.70) 2 +(y-(594.47)) 2 =201158.89;

[0064] The eleventh curve 211 is defined by the following formula: 1209.1176≤x≤1380.7778, (x-1383.77) 2 +(y-(966.85)) 2 =661721.08;

[0065] The twelfth curve 212 is defined by the following formula: 1380.7778≤x≤2148.9854, y=-0.0493x+221.4867;

[0066] The thirteenth curve 213 is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

[0067] By limiting the outer surface profile of the test projectile 100 to be formed by rotating the pre-calculated projectile curve around the X-axis of the plane rectangular coordinate system, the stability of the test projectile 100 during airdrop can be improved to avoid the test projectile 100 from rolling during airdrop and affecting the test process. At the same time, it can also ensure that the test projectile 100 has a 0.2m 2 ~0.4m 2 The resistance characteristics of the aircraft are adjusted to meet the specific resistance characteristic requirements of the airdrop test.

[0068] In other optional embodiments, the output shaft of the rotating motor 170 may also be connected to the corresponding rotating shaft 160 via a gear transmission mechanism.

[0069] The embodiments described above are part of the embodiments of the present application, rather than all of the embodiments. The detailed description of the embodiments of the present application is not intended to limit the scope of the present application for protection, but merely represents selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

Claims

1. A continuously variable resistance characteristic test device for life-saving parachute airdrop, comprising a test projectile, characterized in that: It also includes a plurality of canopy inner supports arranged at intervals along the circumference of the test projectile, a plurality of canopy outer supports arranged at intervals along the circumference of the test projectile, an annular drag parachute canopy sleeved on the middle part of the test projectile, at least one restraint sleeve and a cutter connected to the test projectile, the two ends of each canopy inner support being respectively connected to the test projectile and the inner side wall of the drag parachute canopy; one end of each canopy outer support being rotatably hinged to the test projectile in a direction close to or away from the test projectile, and the other end being connected to the outer side wall of the drag parachute canopy; the restraint sleeve being used to sleeve the drag parachute canopy on the middle outer wall of the test projectile, and the cutter being used to cut off the restraint sleeve at regular intervals.

2. The continuously variable resistance characteristic test device for life-saving parachute airdrop according to claim 1, characterized in that: The test bomb is also provided with a driving mechanism for driving each of the canopy outer supports to rotate synchronously toward or away from the test bomb.

3. The continuously variable resistance characteristic test device for life-saving parachute airdrop according to claim 2, characterized in that: The driving mechanism includes a rotating motor corresponding to the canopy outer bracket one by one. The canopy outer bracket is hinged to the outer wall of the test shell through a rotating shaft, and the output shaft of the rotating motor is connected to the rotating shaft.

4. The continuously variable resistance characteristic test device for life-saving parachute airdrop according to claim 1, characterized in that: The test projectile comprises a warhead, a projectile middle part, a tail connecting sleeve and a projectile tail part which are connected in sequence, and the projectile tail part is connected with a plurality of tail fins.

5. The continuously variable resistance characteristic test device for life-saving parachute airdrop according to claim 4, characterized in that: The tail connecting sleeve is connected to at least one counterweight.

6. The continuously variable resistance characteristic test device for life-saving parachute airdrop according to claim 1, characterized in that: The outer surface profile of the test projectile is formed by rotating the projectile curve around the X-axis of a plane rectangular coordinate system, and the projectile curve includes a first curve segment, a second curve segment, a third curve segment, a fourth curve segment, a fifth curve segment, a sixth curve segment, a seventh curve segment, an eighth curve segment, a ninth curve segment, a tenth curve segment, an eleventh curve segment, a twelfth curve segment, and a thirteenth curve segment connected in sequence along the positive direction of the X-axis; The first curve segment is defined by the following formula: x=0, 0≤y≤49.3618; The second curve segment is defined by the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92; The third curve segment is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045; The fourth curve segment is defined by the following formula: x=355.0472, 204.4878≤y≤274.4795; The fifth curve segment is defined by the following formula: 354.0472≤x≤364.8727, y=274.4795; The sixth curve segment is defined by the following formula: 364.8727≤x≤414.0627, (x-356.17) 2 +(y-(-16.00)) 2 =87731.30; The seventh curve segment is defined by the following formula: 414.06272≤x≤485.365, (x-473.15) 2 +(y-(829.74)) 2 =311806.32; The eighth curve segment is defined by the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854; The ninth curve segment is defined by the following formula: 988.3318≤x≤1101.0523, (x-985.11) 2 +(y-(94.15)) 2 =31563.18; The tenth curve segment is defined by the following formula: 1101.0523≤x≤1209.1176, (x-1360.70) 2 +(y-(594.47)) 2 =201158.89; The eleventh curve is defined by the following formula: 1209.1176≤x≤1380.7778, (x-1383.77) 2 +(y-(966.85)) 2 =661721.08; The twelfth curve is defined by the following formula: 1380.7778≤x≤2148.9854, y=-0.0493x+221.4867; The thirteenth curve segment is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

7. A method for testing continuously variable drag characteristics for parachute airdrop, characterized in that: It includes the following steps: Step 1: Connect the life-saving parachute to the continuously variable resistance characteristic test device for airdropping of a life-saving parachute according to any one of claims 1 to 6 for airdropping; Step 2: Control the cutter to cut off the restraint sleeve at a preset time, so that the drag parachute canopy is inflated and opened, driving each of the canopy outer supports to rotate away from the test missile body.

8. The continuously variable drag characteristic test method for parachute airdrop according to claim 7, characterized in that: The method further includes step three: using a driving mechanism to drive each of the canopy outer supports to synchronously rotate toward or away from the test missile to adjust the deployment area of ​​the drag parachute canopy.

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