Continuous variable resistance characteristic test device and method for lifesaving parachute air drop

Abstract

The invention discloses a continuous variable resistance characteristic test device and method for lifesaving parachute air drop, and relates to the field of parachutes. The continuous variable resistance characteristic test device for lifesaving parachute air drop comprises a test projectile body, a plurality of canopy inner supports arranged in the circumferential direction of the test projectile body, a plurality of canopy outer supports arranged in the circumferential direction of the test projectile body, an annular drag parachute canopy arranged in the middle of the test projectile body in a sleeving mode, at least one restraining sleeve and a cutter connected to the test projectile body. Two ends of each canopy inner support are respectively connected with the test projectile body and the inner side wall of the drag parachute canopy; one end of each canopy outer support can be rotatably hinged to the test projectile body in the direction close to or away from the test projectile body, and the other end is connected with the outer side wall of the drag parachute canopy; the restraining sleeve is used for sleeving the parachute canopy of the drag parachute on the outer wall of the middle of a test projectile body, and the cutter is used for cutting off the restraining sleeve regularly. The continuous variable resistance characteristic test device and method for lifesaving parachute air drop can continuously adjust the resistance characteristics of the experimental projectile body to meet the use requirements of lifesaving parachute air drop tests.

Description

Technical Field

[0001] The present application relates to the field of parachutes, and in particular to a continuously variable resistance characteristic test device and method for airdropping a lifesaving parachute. Background Art

[0002] In order to verify the performance of lifesaving parachutes, such as parachute overload, parachute force, parachute procedure, speed and strength during parachute opening, a parachute with a resistance characteristic of 0.2m is required. 2 ~0.4m 2 , a test device with a weight of 100kg to 130kg, a parachute opening speed (true speed) of 150km / h to 650km / h, and an airdrop altitude of 400m to 4000m to meet the needs of lifesaving parachute airdrop tests.

[0003] At present, traditional rigid dummies and projectiles are often used as the front body of airdrop tests, which will lead to problems such as poor parachute opening procedures and excessive parachute opening force. There are also 250-4 test projectiles with good stability as the front body, but the elastic resistance 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 lifesaving 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: The present application provides a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute, which comprises a test projectile, and also comprises a plurality of canopy inner brackets arranged at intervals along the circumference of the test projectile, a plurality of canopy outer brackets 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 restraining sleeve and a cutter connected to the test projectile, wherein the two ends of each canopy inner bracket are respectively connected to the test projectile and the inner side wall of the drag parachute canopy; one end of each canopy outer bracket can be rotatably hinged to the test projectile in a direction approaching or moving away from the test projectile, and the other end is connected to the outer side wall of the drag parachute canopy; the restraining 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 cut off the restraining sleeve at a fixed time.

[0006] In some optional embodiments, the test bomb is further provided with a driving mechanism for driving each canopy outer support to synchronously rotate toward or away from the test bomb.

[0007] In some optional embodiments, 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.

[0008] 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 which are connected in sequence, and the tail of the projectile is connected to a plurality of tail fins.

[0009] In some optional embodiments, at least one counterweight is connected to the tail connecting sleeve.

[0010] In some optional embodiments, the outer surface profile of the test projectile is formed by rotating the projectile curve around the X-axis of the 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 is defined by the following formula: x=0, 0≤y≤49.3618; The second curve is defined by the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92; The third curve is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045; The fourth curve is defined by the following formula: x=355.0472, 204.4878≤y≤274.4795; The fifth curve is defined by the following formula: 354.0472≤x≤364.8727, y=274.4795; The sixth curve is defined by the following formula: 364.8727≤x≤414.0627, (x-356.17) 2 +(y-(-16.00)) 2 =87731.30; The seventh curve is defined by the following formula: 414.06272≤x≤485.365, (x-473.15) 2 +(y-(829.74)) 2 =311806.32; The eighth curve is defined by the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854; The ninth curve is defined by the following formula: 988.3318≤x≤1101.0523, (x-985.11) 2 +(y-(94.15)) 2 =31563.18; The tenth curve 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 is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

[0011] The present application also provides a method for testing the continuously variable resistance characteristics of a lifesaving parachute airdrop, which comprises the following steps: Step 1: connect the lifesaving parachute to the above-mentioned continuous variable resistance characteristic test device for airdropping of lifesaving parachutes for airdropping; 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 bracket to rotate away from the test missile body.

[0012] In some optional implementation schemes, 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 body to adjust the deployment area of ​​the drag parachute canopy.

[0013] The beneficial effects of the present application are as follows: the continuously variable resistance characteristic test device for airdropping of a lifesaving parachute provided by the present application includes a test projectile, and also includes a plurality of canopy inner brackets arranged at intervals along the circumference of the test projectile, a plurality of canopy outer brackets 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 bracket are respectively connected to the test projectile and the inner side wall of the drag parachute canopy; one end of each canopy outer bracket can be hinged to the test projectile in a rotatable manner 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 middle outer wall of the test projectile, and the cutter is used to cut off the restraint sleeve at a fixed time. The continuously variable resistance characteristic test device and method for airdropping of a lifesaving parachute provided by the present application can continuously adjust the resistance characteristics of the test projectile, and ensure the stability during airdrop to meet the use requirements of the lifesaving parachute airdrop test. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. 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 related drawings can be obtained based on these drawings without paying creative work.

[0015] Figure 1 A schematic diagram of the structure of a first use state of a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute provided in an embodiment of the present application; Figure 2 A schematic diagram of the structure of the second use state of the continuously variable resistance characteristic test device for airdropping of a lifesaving parachute provided in an embodiment of the present application; Figure 3 A schematic diagram of a partial cross-sectional structure of a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute provided in an embodiment of the present application; Figure 4 A schematic diagram of the structure of a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute provided in another embodiment of the present application; Figure 5 It is a schematic diagram of a projectile curve of the outer surface contour of a test projectile in a continuous variable resistance characteristic test device for airdropping of a lifesaving parachute provided in another embodiment of the present application in a plane rectangular coordinate system.

[0016] 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

[0017] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0018] 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 which protection is sought, 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 the field without creative work are within the scope of protection of the present application.

[0019] 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, further definition and explanation thereof is not required in subsequent drawings.

[0020] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the application is usually placed when in use. They are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0021] In addition, the terms "horizontal", "vertical", "overhanging" and the like do not mean that the components are required to be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0022] In the description of this application, it should also be noted that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0023] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0024] 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.

[0025] 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 resistance 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 connecting sleeve 114 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 and can be rotatably moved toward 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 fixed time. The test bomb body 100 is provided with a driving mechanism for driving each canopy outer bracket 120 to rotate synchronously toward or away from the test bomb body 100, the driving mechanism includes a rotating motor 170 corresponding to the canopy outer bracket 120 one by one, the canopy outer bracket 120 is hinged to the outer wall of the test bomb body 100 through a rotating shaft 160, the rotating motor 170 is fixed to the outer wall of the test bomb body 100 and the output shaft is connected to the corresponding rotating shaft 160.

[0026] The present application also provides a method for testing the continuously variable resistance characteristics of a lifesaving parachute airdrop, which comprises the following steps: 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 airdropping of the life-saving parachute, and fix the detection equipment on the test bomb 100 of the continuous variable resistance characteristic test device for airdropping of the life-saving parachute for airdropping; Step 2: After the airdrop, the life-saving parachute opens and drives the continuously variable resistance characteristic test device for the life-saving parachute airdrop to descend to the preset height within the preset time, and the cutter 150 is controlled to cut off the restraining sleeve 140, so that the drag parachute canopy 130 is inflated and opened, driving each canopy outer bracket 120 to rotate away from the test missile 100, so that the unfolded drag parachute canopy 130 adjusts the resistance characteristics of the test missile 100 and then continues to descend for testing.

[0027] Step three, use the driving mechanism to drive each canopy outer bracket 120 to synchronously rotate 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.

[0028] The continuously variable resistance characteristic test device and method for airdropping of a lifesaving parachute provided in the embodiment of the present application is implemented by arranging an annular drag parachute canopy 130 on the outer wall of the test missile 100, and using a plurality of canopy inner brackets 110 to connect and limit the inner side wall of the drag parachute canopy 130 to the outer wall of the test missile 100, and using a plurality of canopy outer brackets 120 that can rotate toward or away from the test missile 100 to connect and adjust the outer side wall position of the drag parachute canopy 130. When the test missile 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 missile 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 missile 100 to adjust the deployment area of ​​the drag parachute canopy 130 to test the required technical conditions. This can not only obtain test data with more comparative significance, but also greatly save test costs.

[0029] 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 wings 105 arranged in an X shape. The tail wings 105 can be used to improve the stability of the test projectile 100 during airdrop, so as to prevent the test projectile 100 from rolling during the airdrop process and affecting the test.

[0030] 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 more than two, 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 bomb 100 can be adjusted to meet different test requirements; Figure 4 It is a schematic structural diagram of a tail connecting sleeve 103 of a continuously variable resistance characteristic test device for airdropping of a lifesaving parachute in another embodiment of the present application when two counterweights 180 are connected.

[0031] 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; The first curve 201 is defined by the following formula: x=0, 0≤y≤49.3618; The second curve 202 is defined by the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92; The third curve 203 is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045; The fourth curve 204 is defined by the following formula: x=355.0472, 204.4878≤y≤274.4795; The fifth curve 205 is defined by the following formula: 354.0472≤x≤364.8727, y=274.4795; 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; 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; The eighth curve 208 is defined by the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854; 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; 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; 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; The twelfth curve 212 is defined by the following formula: 1380.7778≤x≤2148.9854, y=-0.0493x+221.4867; The thirteenth curve 213 is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

[0032] By limiting the outer surface contour of the test projectile 100 to be formed by rotating the projectile curve obtained in advance 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. At the same time, it can also ensure that the test projectile 100 has a 0.2m 2 ~0.4m 2 The drag characteristics are adjusted to meet the specific drag characteristic requirements of the airdrop test.

[0033] In other optional embodiments, the output shaft of the rotary motor 170 may also be connected to the corresponding rotating shaft 160 via a gear transmission mechanism.

[0034] 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 the 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 creative work are within the scope of protection of the present application.

Claims

1. A continuously variable resistance characteristic test device for airdrop of a lifesaving parachute, comprising a test bomb, 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 approaching or moving 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 for sleeveing ​​the drag parachute canopy on the middle outer wall of the test projectile, and the cutter being used for regularly cutting off the restraint sleeve.

2. The continuously variable resistance characteristic test device for airdrop of a lifesaving parachute 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 airdrop of a lifesaving parachute 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 body 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 airdrop of a lifesaving parachute 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 airdrop of a lifesaving parachute according to claim 4, characterized in that: The tail connecting sleeve is connected with at least one counterweight.

6. The continuously variable resistance characteristic test device for lifesaving 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 the 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 is defined by the following formula: x=0, 0≤y≤49.3618; The second curve is defined by the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92; The third curve is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045; The fourth curve is defined by the following formula: x=355.0472, 204.4878≤y≤274.4795; The fifth curve is defined by the following formula: 354.0472≤x≤364.8727, y=274.4795; The sixth curve is defined by the following formula: 364.8727≤x≤414.0627, (x-356.17) 2 +(y-(-16.00)) 2 =87731.30; The seventh curve is defined by the following formula: 414.06272≤x≤485.365, (x-473.15) 2 +(y-(829.74)) 2 =311806.32; The eighth curve is defined by the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854; The ninth curve is defined by the following formula: 988.3318≤x≤1101.0523, (x-985.11) 2 +(y-(94.15)) 2 =31563.18; The tenth curve 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 is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

7. A method for testing the continuously variable drag characteristics of a lifesaving parachute airdrop, characterized in that: It includes the following steps: Step 1, connecting the lifesaving parachute to the continuously variable resistance characteristic test device for airdropping of a lifesaving parachute as described in 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 also 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 body to adjust the deployment area of ​​the drag parachute canopy.

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