A high-speed impact simulation test device for spacecraft landing tests

Abstract

This invention relates to a high-speed impact simulation test device for spacecraft landing tests, belonging to the technical field of extraterrestrial landing and takeoff tests. A rotating speed-up mechanism is horizontally positioned axially on top of a support frame. A lifting motor is coaxially connected to the rotating speed-up mechanism via a clutch. A counterweight is placed on the top platform of the support frame. One end of a first rope is connected to the counterweight, and the other end is wound around the small-diameter end of the rotating speed-up mechanism. One end of a second rope is wound around the large-diameter end of the rotating speed-up mechanism, and the other end hangs down naturally. A release device is installed on the second rope. The bottom end of the release device hooks the top end of a third rope. The third rope is connected to a parachute system. The parachute system and a buffer pad are placed on the bottom surface of the support frame, with the buffer pad located directly below the counterweight. This invention can pull out the parachute pack at a maximum speed of 40 m / s, enabling parachute pull-out performance tests of different specifications of parachute systems. Simultaneously, it can meet other high-speed impact test requirements.

Description

Technical Field

[0001] This invention belongs to the field of extraterrestrial landing and takeoff test technology, and relates to a high-speed impact simulation test device for spacecraft landing tests. Background Technology

[0002] Parachutes are widely used deceleration devices during spacecraft landing. The operation of a parachute involves multiple actions, including deployment, straightening, and inflation. During the design of a parachute system, potential problems at each stage must be considered, and thorough testing must be conducted to prevent malfunctions and ensure reliable system operation. How to simulate the real-world operating conditions of a parachute through testing is a key issue in parachute performance analysis and reliability assessment.

[0003] Parachute system testing methods are divided into ground testing and airdrop testing. Airdrop testing has a long cycle, high cost, poor repeatability, and difficulty in obtaining sufficient test data. It is generally used for system performance verification. Ground testing is cheaper, more repeatable, and easier to measure test data, making it suitable for early performance evaluation of the system. However, meeting the performance requirements of parachute testing is a design challenge for ground testing equipment.

[0004] During spacecraft landing, upon receiving the ejection command, the parachute system activates the ejector to deploy the parachute canopy and pull out the parachute pack. The parachute canopy then continues to deploy based on the relative motion between the spacecraft and the parachute pack. As the first step in system activation, the successful deployment of the parachute pack plays a crucial role in the system's normal operation. Therefore, thorough ground-based parachute deployment tests are necessary during the system's design and evaluation. The key to ground testing lies in simulating the high-speed deployment process of the parachute pack. The deployment speed can reach up to 40 m / s, and the parachute pack and lines are subjected to impact loads during deployment, with instantaneous loads reaching up to 200 kN. Currently, there is no low-cost ground testing device capable of simulating such high-speed impact conditions. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a high-speed impact simulation test device for spacecraft landing tests, which can pull out the parachute pack at a maximum speed of 40 m / s, and can realize parachute pull-out performance tests of parachute systems of different specifications; at the same time, it can also meet other high-speed impact test requirements.

[0006] The solution of the present invention is:

[0007] A high-speed impact simulation test device for spacecraft landing tests includes a support frame, a counterweight, a first rope, a rotary lifting mechanism, a second rope, a parachute system, a release device, a third rope, a lifting motor, a clutch, and a buffer pad.

[0008] The support frame is a vertical frame structure; the rotary lifting mechanism is horizontally placed on top of the support frame; the output end of the lifting motor is coaxially connected to the rotary lifting mechanism via a clutch; the counterweight is placed on the top platform of the support frame; one end of the first rope is connected to the counterweight, and the other end of the first rope is wrapped around the small-diameter end of the rotary lifting mechanism; one end of the second rope is wrapped around the large-diameter end of the rotary lifting mechanism, and the other end of the second rope hangs down naturally; a release device is installed on the hanging end of the second rope; the bottom end of the release device hooks the top end of the third rope; the bottom end of the third rope is connected to the parachute system; the parachute system is placed on the bottom surface of the support frame; and a buffer pad is placed on the bottom surface of the support frame, directly below the counterweight.

[0009] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, the working process of the impact simulation test device is as follows:

[0010] The counterweight undergoes free fall; the first rope drives the rotary lifting mechanism to rotate, which in turn drives the second rope to rotate until the second rope is taut; the second rope pulls up the third rope via a release device, and the third rope pulls the parachute out of the parachute system. When the parachute is pulled out to a preset height, the release device automatically disengages from the third rope; the counterweight falls onto the buffer pad, completing the impact simulation test.

[0011] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, the clutch disconnects from the output end of the lifting motor during the free fall motion of the counterweight.

[0012] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, when the counterweight is lifted to the top of the support frame and the impact simulation test is repeated, the clutch is connected to the output end of the lifting motor. The lifting motor drives the clutch and the rotation speed-up mechanism to rotate, and the counterweight is lifted to the top of the support frame through the first rope.

[0013] In the aforementioned high-speed impact simulation test device for spacecraft landing test, when the rotating lifting mechanism tightens the second rope, the falling speed of the counterweight reaches the preset speed, which is 40m / s.

[0014] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, the preset height is 2m.

[0015] In the aforementioned high-speed impact simulation test device for spacecraft landing test, the impact simulation test device also includes a laser velocity sensor, a force sensor, and a brake.

[0016] The laser speed sensor is located at the large-diameter end of the rotary lifting mechanism; the force sensor is located at the bottom of the parachute system; and the brake is located at the shaft end of the rotary lifting mechanism.

[0017] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, a laser velocity sensor measures the ascent speed of the second rope; a force sensor measures the impact load on the parachute system; and after the impact simulation test is completed, a brake is used to brake the rotating lifting mechanism.

[0018] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, the rotary speed-up mechanism includes an input drum and an output drum; wherein, the input drum and the output drum are both coaxially connected main structures; a brake is installed at the axial outer end of the output drum; and the axial outer end of the input drum is connected to a clutch.

[0019] In the aforementioned high-speed impact simulation test device for spacecraft landing tests, the diameter of the input drum is smaller than the diameter of the output drum; that is, the input drum is the small-diameter end of the rotary lifting mechanism, and the output drum is the large-diameter end of the rotary lifting mechanism.

[0020] The advantages of this invention compared to the prior art are:

[0021] (1) This invention can realize high-speed impact simulation, and the speed is controllable, and high-speed impact simulation tests under different working conditions can be carried out.

[0022] (2) The test device of the present invention realizes the amplification of input speed through the rotation speed-up mechanism, which greatly reduces the space occupation of the test device and saves the construction cost of the test device;

[0023] (3) The test device of the present invention accelerates energy storage through gravity, which consumes less energy, has a short test cycle, good repeatability, and further reduces the test cost. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the high-speed impact simulation test device of the present invention;

[0025] Figure 2 This is a schematic diagram of the rotary speed-up mechanism of the present invention;

[0026] Figure 3 This is a schematic diagram of the operation of the unhooking device of the present invention. Detailed Implementation

[0027] The present invention will be further described below with reference to the embodiments.

[0028] This invention provides a high-speed impact simulation test device for spacecraft landing tests. This device can deploy the parachute pack at a maximum speed of 40 m / s, enabling performance testing of parachute systems of different specifications. Furthermore, a similar mechanism can be used to meet other high-speed impact test requirements.

[0029] High-speed impact simulation test apparatus for spacecraft landing tests, such as Figure 1 As shown, it specifically includes a support frame 1, a counterweight 2, a first rope 3, a rotary lifting mechanism 4, a second rope 5, a parachute system 6, a release device 7, a third rope 8, a lifting motor 11, a clutch 12, a buffer pad 14, a laser speed sensor 9, a force sensor 10, and a holding brake 13.

[0030] The support frame 1 is a vertical frame structure; the rotary lifting mechanism 4 is placed horizontally on top of the support frame 1; the output end of the lifting motor 11 is coaxially connected to the rotary lifting mechanism 4 through the clutch 12; the counterweight 2 is placed on the top platform of the support frame 1; one end of the first rope 3 is connected to the counterweight 2, and the other end of the first rope 3 is wrapped around the small diameter end of the rotary lifting mechanism 4; one end of the second rope 5 is wrapped around the large diameter end of the rotary lifting mechanism 4, and the other end of the second rope 5 hangs down naturally; the release device 7 is installed on the hanging end of the second rope 5; the bottom end of the release device 7 hooks the top end of the third rope 8; the bottom end of the third rope 8 is connected to the parachute system 6; the parachute system 6 is placed on the bottom surface of the support frame 1; the buffer pad 14 is placed on the bottom surface of the support frame 1 and is located directly below the counterweight 2.

[0031] The laser speed sensor 9 is located at the large-diameter end of the rotary lifting mechanism 4; the force sensor 10 is located at the bottom of the parachute system 6; and the brake 13 is located at the shaft end of the rotary lifting mechanism 4.

[0032] The laser velocity sensor 9 measures the ascent speed of the second rope 5; the force sensor 10 measures the impact load on the parachute system 6; and after the impact simulation test is completed, the rotating lifting mechanism 4 is braked by the brake 13.

[0033] The working process of the impact simulation test device is as follows:

[0034] The counterweight 2 undergoes free fall; the first rope 3 drives the rotary lifting mechanism 4 to rotate, which in turn drives the second rope 5 to rotate until the second rope 5 is taut; when the rotary lifting mechanism 4 tauts the second rope 5, the falling speed of the counterweight 2 reaches a preset speed, which is 40 m / s. The second rope 5 pulls up the third rope 8 through the release device 7, and the third rope 8 pulls out the parachute from the parachute system 6. When the parachute is pulled out to a preset height, which is 2 m, the release device 7 automatically disengages from the third rope 8; the counterweight 2 lands on the buffer pad 14, completing the impact simulation test.

[0035] When the counterweight 2 is in free fall, the clutch 12 is disconnected from the output of the lifting motor 11.

[0036] When the counterweight 2 is lifted to the top of the support frame 1 and the impact simulation experiment is repeated, the clutch 12 is connected to the output end of the lifting motor 11. The lifting motor 11 drives the clutch 12 and the rotation speed mechanism 4 to rotate, and the counterweight 2 is lifted to the top of the support frame 1 through the first rope 3.

[0037] like Figure 2 As shown, the rotary speed-lifting mechanism 4 includes an input drum 41 and an output drum 42; both the input drum 41 and the output drum 42 are coaxially connected main structures; a brake 13 is installed at the axial outer end of the output drum 42; the axial outer end of the input drum 41 is connected to a clutch 12. The diameter of the input drum 41 is smaller than the diameter of the output drum 42; that is, the input drum 41 is the small-diameter end of the rotary speed-lifting mechanism 4; and the output drum 42 is the large-diameter end of the rotary speed-lifting mechanism 4.

[0038] Figure 3 The diagram shows the operation of the release device. The release device 7 consists of an upper plate 71, a lower plate 72, and a spring buckle 73. The upper plate 71 and the lower plate 72 are connected to the second rope 5 and the third rope 8, respectively. After the parachute is pulled out to the specified position, the spring buckle 73 of the release device is pushed inward by the limiting pulley, and the upper plate 71 and the lower plate 72 are separated.

[0039] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A high-speed impact simulation test device for spacecraft landing tests, characterized in that: It includes a support frame (1), a counterweight (2), a first rope (3), a rotary lifting mechanism (4), a second rope (5), a parachute system (6), a release device (7), a third rope (8), a lifting motor (11), a clutch (12), and a buffer pad (14). Among them, the support frame (1) is a vertical frame structure; the rotary lifting mechanism (4) is placed horizontally on the top of the support frame (1); the output end of the lifting motor (11) is coaxially connected to the rotary lifting mechanism (4) through the clutch (12); the counterweight (2) is placed on the top platform of the support frame (1); one end of the first rope (3) is connected to the counterweight (2), and the other end of the first rope (3) is wrapped around the small diameter end of the rotary lifting mechanism (4); one end of the second rope (5) is wrapped around the large diameter end of the rotary lifting mechanism (4), and the other end of the second rope (5) hangs down naturally; the unhooking device (7) is installed on the hanging end of the second rope (5); the bottom end of the unhooking device (7) hooks the top end of the third rope (8); the bottom end of the third rope (8) is connected to the parachute system (6); the parachute system (6) is placed on the bottom surface of the support frame (1); the buffer pad (14) is placed on the bottom surface of the support frame (1) and is located directly below the counterweight (2); The working process of the impact simulation test device is as follows: The counterweight (2) undergoes free fall; the first rope (3) drives the rotational lifting mechanism (4) to rotate, and the rotational lifting mechanism (4) drives the second rope (5) to rotate until the second rope (5) is tightened; the second rope (5) pulls up the third rope (8) through the release device (7), and the third rope (8) pulls out the parachute in the parachute system (6). When the parachute is pulled out to the preset height, the release device (7) and the third rope (8) automatically disengage; the counterweight (2) falls on the buffer pad (14) to complete the impact simulation test; The impact simulation test device also includes a laser velocity sensor (9), a force sensor (10), and a holding brake (13). The laser speed sensor (9) is located at the large-diameter end of the rotary lifting mechanism (4); the force sensor (10) is located at the bottom of the parachute system (6); and the brake (13) is located at the shaft end of the rotary lifting mechanism (4). The laser speed sensor (9) measures the ascent speed of the second rope (5); the force sensor (10) measures the impact load of the parachute system (6); and after the impact simulation test is completed, the rotating lifting mechanism (4) is braked by the holding brake (13).

2. The high-speed impact simulation test device for spacecraft landing tests according to claim 1, characterized in that: When the counterweight (2) is in free fall, the clutch (12) is disconnected from the output end of the lifting motor (11).

3. The high-speed impact simulation test device for spacecraft landing tests according to claim 2, characterized in that: When the counterweight (2) is lifted to the top of the support frame (1) and the impact simulation experiment is repeated, the clutch (12) is connected to the output end of the lifting motor (11). The lifting motor (11) drives the clutch (12) and the rotation speed mechanism (4) to rotate. The counterweight (2) is lifted to the top of the support frame (1) through the first rope (3) wrapped around it.

4. The high-speed impact simulation test device for spacecraft landing test according to claim 1, characterized in that: When the rotating lifting mechanism (4) tightens the second rope (5), the counterweight (2) falls at a preset speed of 40 m / s.

5. The high-speed impact simulation test device for spacecraft landing tests according to claim 1, characterized in that: The preset height is 2m.

6. The high-speed impact simulation test device for spacecraft landing test according to claim 1, characterized in that: The rotary speed-up mechanism (4) includes an input drum (41) and an output drum (42); wherein the input drum (41) and the output drum (42) are both coaxially connected main structures; a brake (13) is installed at the outer axial end of the output drum (42); and the outer axial end of the input drum (41) is connected to the clutch (12).

7. A high-speed impact simulation test device for spacecraft landing tests according to claim 6, characterized in that: The diameter of the input drum (41) is smaller than the diameter of the output drum (42); that is, the input drum (41) is the small diameter end of the rotary speed-up mechanism (4); the output drum (42) is the large diameter end of the rotary speed-up mechanism (4).

Images