Lifesaving parachute airdrop variable resistance test device and method

Abstract

A life-saving parachute airdrop variable resistance test device and method relates to the field of life-saving parachute testing. The life-saving parachute airdrop variable resistance test device includes a test projectile, a plurality of resistance fins arranged at intervals along the circumference of the test projectile, a compression spring corresponding to each resistance fin, at least one clamp and a cutter connected to the test projectile. Each resistance fin extends along the length of the test projectile and is hinged to the test projectile at one end. The resistance fin can rotate toward or away from the test projectile; the two ends of the compression spring are respectively connected to the test projectile and the corresponding resistance fin, and the compression spring is used to push the corresponding resistance fin to rotate to a preset angle with the test projectile; the clamp is used to overcome the elastic force of each compression spring to fix each resistance fin that is attached to the middle outer wall of the test projectile; and the cutter is used to cut the clamp at a time. The life-saving parachute airdrop variable resistance test device and method can adjust the resistance characteristics of the test projectile at a time to meet the use requirements of the life-saving parachute airdrop test.

Description

Technical Field

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

[0002] In order to verify the performance of the life-saving parachute, it is necessary to connect the life-saving parachute to the test device for airdrop. The test device needs to meet the resistance characteristics of 0.2m 2 ~0.4m 2 , weight 100kg ~ 130kg, parachute opening speed (true speed): 150km / h ~ 650km / h, parachute opening height 400m ~ 4000m to meet the needs of life-saving parachute airdrop test.

[0003] Currently, traditional rigid dummies and test projectiles are often used as front bodies for airdrop tests. The use of rigid dummies often results in severe rolling and poor parachute opening procedures during the airdrop process. The drag characteristic of using test projectiles as front bodies is only 0.011m2, which leads to poor deceleration effect, excessive parachute opening speed and force, and is unable to assess the formal performance of the lifesaving parachute. Summary of the Invention

[0004] The purpose of this application is to provide a life-saving parachute airdrop variable resistance test device and method, which can regularly adjust the resistance characteristics of the test projectile to meet the use requirements of the life-saving parachute airdrop test and ensure the stability of the test projectile during airdrop.

[0005] This application is implemented as follows:

[0006] The present application provides a life-saving parachute airdrop variable resistance test device, which includes a test projectile, and also includes a plurality of resistance wings arranged at intervals along the circumference of the test projectile, a pressure leaf spring corresponding to the resistance wings one by one, at least one clamp and a cutter connected to the test projectile, one end of each resistance wing is hinged to the test projectile and is configured to be able to rotate toward or away from the test projectile; the two ends of the pressure leaf spring are respectively connected to the test projectile and the corresponding resistance wing, the pressure leaf spring is used to push the corresponding resistance wing to rotate to a preset angle with the test projectile; the clamp is used to overcome the elastic force of each pressure leaf spring to fix each resistance wing attached to the outer wall of the middle part of the test projectile; the cutter is used to cut off the clamp at a regular time.

[0007] In some optional embodiments, the test projectile body includes a test projectile head, a test projectile middle, a body adapter and a test projectile tail connected in sequence, and the test projectile tail is connected to a plurality of tail fins arranged at intervals along its circumference.

[0008] In some optional embodiments, the drag wing is arc-shaped and one end away from the test warhead is hinged to the outer wall of the middle part of the test warhead.

[0009] In some optional embodiments, the central fixed sleeve of the test projectile is provided with an annular equipment plate, and the equipment plate is connected to at least one counterweight.

[0010] In some optional embodiments, the outer wall of the test projectile is provided with a receiving groove corresponding to the resistance wing, and the resistance wing is received in the corresponding receiving groove when it rotates to fit the outer wall of the middle part of the test projectile.

[0011] In some optional embodiments, the drag fins extend along the length of the test airframe.

[0012] 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;

[0013] The first curve segment is defined by the following formula: x=0, 0≤y≤49.3618;

[0014] The second curve segment is defined by the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92;

[0015] The third curve segment is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045;

[0016] The fourth curve segment is defined by the following formula: x=355.0472, 204.4878≤y≤274.4795;

[0017] The fifth curve segment is defined by the following formula: 354.0472≤x≤364.8727, y=274.4795;

[0018] 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;

[0019] 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;

[0020] The eighth curve segment is defined by the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854;

[0021] 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;

[0022] 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;

[0023] The eleventh curve is defined by the following formula: 1209.1176≤x≤1380.7778, (x-1383.77) 2 +(y-(966.85)) 2 =661721.08;

[0024] The twelfth curve is defined by the following formula: 1380.7778≤x≤2148.9854, y=-0.0493x+221.4867;

[0025] The thirteenth curve segment is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

[0026] The present application also provides a life-saving parachute airdrop variable resistance test method, which includes the following steps:

[0027] Use a life-saving parachute to connect to the above-mentioned life-saving parachute airdrop variable resistance test device and perform airdrop;

[0028] At a preset time, the cutter is controlled to cut off the clamp, so that each compression spring pushes the corresponding resistance wing to rotate to a preset angle with the test projectile.

[0029] The beneficial effects of the present application are as follows: the life-saving parachute airdrop variable resistance test device provided by the present application includes a test projectile, and also includes a plurality of resistance fins arranged at intervals along the circumference of the test projectile, a compression spring corresponding to the resistance fins, at least one clamp and a cutter connected to the test projectile, each resistance fin extends along the length direction of the test projectile and is configured to be rotatable toward or away from the test projectile; the two ends of the compression spring are respectively connected to the test projectile and the corresponding resistance fin, and the compression spring is used to push the corresponding resistance fin to rotate to a preset angle with the test projectile; the clamp is used to overcome the elastic force of each compression spring to fix each resistance fin attached to the middle outer wall of the test projectile; the cutter is used to cut off the clamp at regular intervals. The life-saving parachute airdrop variable resistance test device and method provided by the present application can regularly adjust the resistance characteristics of the test projectile to meet the use requirements of the life-saving parachute airdrop test, and ensure the stability of the test projectile during airdrop. 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 lifesaving parachute airdrop variable resistance test device provided in an embodiment of the present application;

[0032] Figure 2 A schematic structural diagram of the second use state of the lifesaving parachute airdrop variable resistance test device provided in an embodiment of the present application;

[0033] Figure 3 A schematic structural diagram of a lifesaving parachute airdrop variable resistance test device provided in another embodiment of the present application;

[0034] Figure 4 This is a schematic diagram of a projectile curve of the outer surface contour of a test projectile of a life-saving parachute airdrop variable resistance test device provided by another embodiment of the present application in a plane rectangular coordinate system.

[0035] In the figure: 100, drag wing; 110, pressure spring; 120, clamp; 130, cutter; 200, test projectile; 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; 211, tenth section of curve; 212, eleventh section of curve; 213, twelfth section of curve; 214, thirteenth section of curve; 210, test projectile head; 220, test projectile middle; 230, body socket; 240, test projectile tail; 250, tail fin; 260, equipment plate; 270, counterweight; 280, receiving slot. DETAILED DESCRIPTION

[0036] 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.

[0037] 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 making any creative efforts shall fall within the scope of protection of the present application.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] 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.

[0042] 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.

[0043] The features and performance of the life-saving parachute airdrop variable resistance test device and method of the present application are further described in detail below in conjunction with the embodiments.

[0044] like Figure 1 and Figure 2As shown, an embodiment of the present application provides a life-saving parachute airdrop variable resistance test device, which includes a test projectile 200, four arc-shaped resistance wings 100 arranged at intervals along the circumference of the test projectile 200, a pressure spring 110 corresponding to the resistance wings 100, an annular clamp 120 and a cutter 130 connected to the test projectile 200; wherein, the test projectile 200 includes a test projectile head 210, a test projectile middle part 220, a body sleeve 230 and a test projectile tail part 240 connected in sequence, the test projectile tail part 240 is connected to four tail wings 250 arranged at intervals along its circumference, and the four tail wings 250 are arranged in an X shape, and the test projectile middle part 220 is provided with four accommodating grooves 280 corresponding to the resistance wings 100. Each resistance wing 100 extends along the length direction of the test projectile 200 and is hinged to the middle part 220 of the test projectile at one end away from the test projectile head 210. The resistance wing 100 can rotate toward or away from the test projectile 200; the two ends of the pressure spring 110 are respectively connected to the test projectile 200 and the corresponding resistance wing 100, and the pressure spring 110 is used to push the corresponding resistance wing 100 to rotate to be arranged at a preset angle with the test projectile 200; when the resistance wing 100 is rotated to fit the middle outer wall of the test projectile 200, it is accommodated in the corresponding accommodating groove 280; the clamp 120 is used to overcome the elastic force of each pressure spring 110 to fix each resistance wing 100 accommodated in the accommodating groove 280 on the middle outer wall of the test projectile 200; the cutter 130 is used to cut off the clamp 120 at regular intervals; the middle part 220 of the test projectile is fixedly sleeved with a ring-shaped equipment plate 260.

[0045] The present application also provides a method for testing a lifesaving parachute airdrop variable resistance, which includes the following steps:

[0046] 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 life-saving parachute airdrop variable resistance test device, fix the detection equipment on the equipment plate 260 of the life-saving parachute airdrop variable resistance test device, and airdrop;

[0047] Step 2: After airdrop, the life-saving parachute opens to drive the test projectile 200 of the life-saving parachute airdrop variable resistance test device to descend to a preset height within a preset time, and the cutter 130 is controlled to cut the clamp 120, so that each compression spring 110 pushes the corresponding resistance wing 100 to rotate to a preset angle with the test projectile 200, so that the deployed resistance wing 100 adjusts the resistance characteristics of the test projectile 200 and then continues to descend for testing.

[0048] The lifesaving parachute airdrop variable resistance test device and method provided in the embodiment of the present application is to hinge a plurality of arc-shaped resistance wings 100 on the outer wall of the test projectile 200, and use the pressure spring 110 to push each resistance wing 100 to rotate to form a preset angle with the outer wall of the test projectile 200, and then use the clamp 120 to overcome the elastic force of each pressure spring 110 to fit each resistance wing 100 of the middle outer wall of the test projectile 200 and fix it. When the test projectile 200 is airdropped, the clamp 120 is cut off at a time by the cutter 130 to stop the collection of the limited resistance wings 100. 00 position, so that the pressure spring 110 pushes each resistance wing 100 to rotate to a preset angle with the outer wall of the test body 200, thereby adjusting the resistance characteristics of the test body 200 to test different technical conditions, which not only can obtain more comparative test data, but also can greatly save the test cost. At the same time, by replacing the pressure spring 110 with different elastic force to adjust the resistance wing 100 to rotate to a preset angle with the outer wall of the test body 200, the deployment area of ​​the resistance wing 100 can be adjusted to test the required technical conditions.

[0049] The test projectile 200 includes a test projectile head 210, a test projectile middle 220, a body sleeve 230 and a test projectile tail 240 connected in sequence. The test projectile tail 240 is connected to four tail fins 250 arranged at intervals along its circumference. The four tail fins 250 are arranged in an X shape. The tail fins 250 can be used to improve the stability of the test projectile 200 during airdrop, thereby preventing the test projectile 200 from rolling during the airdrop process and affecting the test progress.

[0050] The middle part 220 of the test projectile is provided with four accommodating grooves 280 corresponding one to one with the resistance wing 100. When the resistance wing 100 is rotated to fit against the outer wall of the middle part of the test projectile 200, it is accommodated in the corresponding accommodating groove 280, which can reduce the influence of the resistance wing 100 on the resistance characteristics of the test projectile 200 when it fits against the outer wall of the test projectile 200, thereby ensuring the test accuracy.

[0051] In other optional embodiments, the device plate 260 may be connected to one, two, three, four or more counterweights; when there is one counterweight, it may be annular and fixedly mounted on the device plate 260; when there are two or more counterweights, each counterweight is connected to the device plate 260 at intervals along the circumference; by providing one or more counterweights on the device plate 260, the weight of the test bomb 200 can be adjusted to meet different test requirements; Figure 3 FIG2 is a schematic structural diagram of a device plate 260 connected to two counterweights 270 in a life-saving parachute airdrop variable resistance test device provided by another embodiment.

[0052] In other optional embodiments, such as Figure 4As shown, the outer surface profile of the test projectile 200 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 211, an eleventh curve 212, a twelfth curve 213 and a thirteenth curve 214 connected in sequence along the positive direction of the X-axis;

[0053] The first curve 201 is defined by the following formula: x=0, 0≤y≤49.3618;

[0054] The second curve 202 is defined using the following formula: 0≤x≤323.0641, (x-522.16) 2 +(y-(-665.35)) 2 =783468.92;

[0055] The third curve 203 is defined by the following formula: 323.0641≤x≤355.0472, y=0.0208x+197.1045;

[0056] The fourth curve 204 is defined using the following formula: x=355.0472, 204.4878≤y≤274.4795;

[0057] The fifth curve 205 is defined using the following formula: 354.0472≤x≤364.8727, y=274.4795;

[0058] 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;

[0059] 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;

[0060] The eighth curve 208 is defined using the following formula: 485.365≤x≤988.3318, y=0.0006x+271.1854;

[0061] 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;

[0062] The tenth curve 211 is defined by the following formula: 1101.0523≤x≤1209.1176, (x-1360.70) 2 +(y-(594.47)) 2 =201158.89;

[0063] The eleventh curve 212 is defined by the following formula: 1209.1176≤x≤1380.7778, (x-1383.77) 2 +(y-(966.85)) 2 =661721.08;

[0064] The twelfth curve 213 is defined by the following formula: 1380.7778≤x≤2148.9854, y=-0.0493x+221.4867;

[0065] The thirteenth curve 214 is defined by the following formula: x=2148.9854, 0≤y≤115.5417.

[0066] By limiting the outer surface profile of the test projectile 200 to be formed by rotating a specific projectile curve around the X-axis of the plane rectangular coordinate system, it is possible to ensure that the test projectile 200 has a 0.2m 2 ~0.4m 2 On the one hand, the resistance characteristics can meet the requirements of the airdrop test, and on the other hand, the stability of the test projectile 200 in the airdrop can be improved to avoid the test projectile 200 rolling during the airdrop and affecting the progress of the test.

[0067] 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 life-saving parachute airdrop variable resistance test device, comprising a test projectile, characterized in that: It also includes a plurality of resistance wings arranged at intervals along the circumference of the test body, a pressure spring corresponding to the resistance wings one by one, at least one clamp and a cutter connected to the test body, one end of each resistance wing is hinged to the test body and is configured to be able to rotate toward or away from the test body; the two ends of the pressure spring are respectively connected to the test body and the corresponding resistance wing, the pressure spring is used to push the corresponding resistance wing to rotate to a preset angle with the test body; the clamp is used to overcome the elastic force of each pressure spring to fix each resistance wing attached to the middle outer wall of the test body; the cutter is used to cut off the clamp at regular intervals.

2. The lifesaving parachute airdrop variable resistance test device according to claim 1, characterized in that: The test projectile body comprises a test projectile head, a test projectile middle, a body sleeve and a test projectile tail which are connected in sequence. The test projectile tail is connected to a plurality of tail fins which are arranged at intervals along its circumference.

3. The lifesaving parachute airdrop variable resistance test device according to claim 2, characterized in that: The resistance wing is arc-shaped and one end away from the test bullet head is hinged to the outer wall of the middle part of the test bullet.

4. The lifesaving parachute airdrop variable resistance test device according to claim 2, characterized in that: The central fixed sleeve of the test projectile is provided with an annular equipment plate, and the equipment plate is connected to at least one counterweight.

5. The lifesaving parachute airdrop variable resistance test device according to claim 1, characterized in that: The outer wall of the test body is provided with a receiving groove corresponding to the resistance wing one by one, and the resistance wing is received in the corresponding receiving groove when it rotates to fit the outer wall of the middle part of the test body.

6. The lifesaving parachute airdrop variable resistance test device according to claim 1, characterized in that: The drag fin extends along the length direction of the test bomb.

7. The lifesaving parachute airdrop variable resistance test device 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.

8. A lifesaving parachute airdrop variable resistance test method, characterized in that: It includes the following steps: Use a life-saving parachute to connect to the life-saving parachute airdrop variable resistance test device according to any one of claims 1 to 7 and perform airdrop; The cutter is controlled to cut off the clamp at a preset time, so that each of the compression springs pushes the corresponding resistance wing to rotate to form a preset angle with the test projectile.

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