Test device and system thereof

Abstract

The invention relates to the technical field of spaceflight, particularly provides a test device and a system thereof, and aims to solve the problems of resource waste, extremely high cost and difficulty in repeated test of a firework separation and recovery device in the prior art. The test device comprises a fairing body, a rocket simulation assembly, a separation assembly, a recovery assembly and a pneumatic connection assembly. The fairing body is connected with the tail end of the rocket simulation assembly; the separation assembly is arranged at the geometric center where the fairing body is in contact with the tail end of the rocket simulation assembly; the recovery assembly is fixed on the rocket body of the rocket simulation assembly and is close to the two sides of the fairing body; the pneumatic connection assembly is used for connecting the fairing body and the rocket simulation assembly. The pneumatic connecting assembly comprises a first pneumatic connecting piece and a second pneumatic connecting piece which are used for connecting the two sides of the fairing body and the rocket simulation assembly. The test system comprises a controller and a test device. The testing device and the system thereof provided by the invention are used for the fairing separation and recovery test.

Description

Technical Field

[0001] The present disclosure relates to the field of aerospace technology, and in particular to a test device and a system thereof. Background Art

[0002] As an important structure to protect the payload, the launch vehicle fairing is mainly used to prevent the influence of atmospheric resistance, thermal barriers, acoustic barriers, etc. Therefore, it can be jettisoned outside the atmosphere. Jetting off the excess mass can increase the rocket's carrying capacity. Ensuring that the fairing can be jettisoned reliably is a key link in the development process. Most launch vehicles must conduct fairing separation tests before their first flight to verify the feasibility and reliability of the fairing separation plan.

[0003] In the prior art, the connection and unlocking devices used on the fairing separation surface are mostly pyrotechnic separation devices. Each set of pyrotechnic separation devices can only be used once and are expensive. If multiple tests are to be conducted, multiple sets of pyrotechnic separation devices must be prepared, which wastes resources and is extremely costly. At the same time, the safe and reliable recovery of the fairing after separation is also a crucial part of the ground separation test, on the one hand for the next test, and on the other hand for the subsequent flight use. Therefore, a set of reusable fairing separation test devices can provide great help to the development of launch vehicles. Summary of the invention

[0004] The present disclosure is proposed in view of the above problems. The present disclosure provides a test device and a system thereof.

[0005] According to one aspect of the present disclosure, there is provided a test device, comprising: A fairing body, a rocket simulation component, a separation component, a recovery component and a pneumatic connection component; the fairing body is connected to the end of the rocket simulation component, the separation component is arranged at the geometric center of the contact between the fairing body and the end of the rocket simulation component, and is used to throw the fairing body away from the end of the rocket simulation component; the recovery component is fixed on the arrow body of the rocket simulation component and close to the two sides of the fairing body, and is used to recover the ejected fairing body; the pneumatic connection component is used to connect the fairing body and the rocket simulation component; the pneumatic connection component includes a first pneumatic connection piece and a second pneumatic connection piece, the first pneumatic connection piece is arranged around the left side of the fairing body and is connected to the end of the rocket simulation component, and is used to connect the left side of the fairing body and the rocket simulation component, the second pneumatic connection piece is arranged around the right side of the fairing body and is connected to the end of the rocket simulation component, and is used to connect the right side of the fairing body and the rocket simulation component.

[0006] Compared with the prior art, the test device in the present application includes a fairing body, a rocket simulation component, a separation component, a recovery component and a pneumatic connection component. Among them, the fairing body is connected to the end of the rocket simulation component. At the same time, the separation component is arranged at the geometric center where the fairing body contacts the end of the rocket simulation component, and is used to throw the fairing body away from the end of the rocket simulation component. In addition, the pneumatic connection component is used to connect the fairing body and the rocket simulation component. Therefore, when the pneumatic connection component is in a locked state, gas can be introduced into the test device to change the first pneumatic connection member and the second pneumatic connection member in the pneumatic connection component from a locked state to an unlocked state. Then, under the action of the elastic force of the separation component, the fairing body can be thrown away from the end of the rocket simulation component. In this process, the recovery components fixed on the arrow body of the rocket simulation component and close to the two sides of the fairing body can recover the ejected fairing body, reducing the probability of the fairing being damaged by impact after being ejected, so that the fairing body can be safely and reliably recovered and repeated tests at a lower maintenance cost, which is conducive to verifying the feasibility and reliability of the fairing separation plan. In addition, in the process of separating and recovering the fairing body, the air source is used as the separation energy, which has the characteristics of high resource utilization and low cost compared to the use of pyrotechnics and other energy sources, which is conducive to repeating the fairing separation test.

[0007] According to another aspect of the present disclosure, there is provided a test system, comprising: A controller and the above-mentioned test device; the controller is electrically connected to the pneumatic connection component included in the test device.

[0008] Compared with the prior art, the beneficial effects of the test system provided in the present application are the same as those of the above-mentioned test device, which will not be described in detail here.

[0009] It is to be understood that both the foregoing general description and the following detailed description are exemplary, and are intended to provide further explanation of the technology as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0011] Figure 1 is a schematic diagram of one structure of a test device according to an embodiment of the present disclosure; Figure 2 is another structural schematic diagram illustrating a test device according to an embodiment of the present disclosure; Figure 3 It is a partially enlarged view illustrating the rotation limiting mechanism of an embodiment of the present disclosure.

[0012] Reference numerals: 1- fairing body; 101- left half fairing; 102- right half fairing; 2- rocket simulation assembly; 3- separation assembly; 301- push rod; 302- separation elastic member; 303- elastic member bracket; 4- recovery assembly; 401- support seat; 402- telescopic mechanism; 4021- cylinder; 4022- adjustment connector; 4023- sliding member; 403- cushion; 501- first pneumatic connector; 502- second pneumatic connector; 503- third pneumatic connector; 504- first gas cylinder; 505- second gas cylinder; 506- first pneumatic switch; 507- second pneumatic switch; 6- rotation limit mechanism; 601- connection seat; 602- connection member; 603- limit member and 604- rotating member. DETAILED DESCRIPTION

[0013] In order to make the purpose, technical solution and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described here.

[0014] In view of the characteristics of the pyrotechnic separation and recovery devices in the prior art that they waste resources, are extremely costly, and are difficult to conduct repeated tests, the present application provides a test device that can safely and reliably recover and repeatedly test the fairing body with higher resource utilization and lower maintenance costs, which is conducive to verifying the feasibility and reliability of the fairing separation scheme. Figure 1 FIG. 1 is a schematic diagram of a structure of a test device according to an embodiment of the present disclosure. Figure 1 As shown, the test device in the present application includes: a fairing body 1, a rocket simulation component 2, a separation component 3, a recovery component 4 and a pneumatic connection component. The fairing body 1 is connected to the end of the rocket simulation component 2; the separation component 3 is arranged at the geometric center where the fairing body 1 and the end of the rocket simulation component 2 contact, and is used to throw the fairing body 1 away from the end of the rocket simulation component 2; the recovery component 4 is fixed on the arrow body of the rocket simulation component 2 and close to both sides of the fairing body 1, and is used to recover the thrown fairing body 1; the pneumatic connection component is used to connect the fairing body 1 and the rocket simulation component 2.

[0015] The pneumatic connection assembly includes a first pneumatic connection member 501 and a second pneumatic connection member 502. The first pneumatic connection member 501 is disposed on the left side of the fairing body 1 and is connected to the end of the rocket simulation assembly 2, and is used to connect the left side of the fairing body 1 and the rocket simulation assembly 2. The second pneumatic connection member 502 is disposed on the right side of the fairing body 1 and is connected to the end of the rocket simulation assembly 2, and is used to connect the right side of the fairing body 1 and the rocket simulation assembly 2.

[0016] During specific implementation, the fairing body 1 is connected to the end of the rocket simulation component 2, the separation component 3 is located at the geometric center where the fairing body 1 contacts the end of the rocket simulation component 2, and the pneumatic connection component is used to connect the fairing body 1 and the rocket simulation component 2. Therefore, when the pneumatic connection component is in a locked state, gas can be introduced into the test device to change the first pneumatic connection member 501 and the second pneumatic connection member 502 of the pneumatic connection component 5 from a locked state to an unlocked state. Then, under the action of the elastic force of the separation component, the fairing body 1 can be thrown away from the end of the rocket simulation component. In this process, the recovery component 4 fixed on the arrow body of the rocket simulation component 2 and close to the two sides of the fairing body 1 can recover the fairing body 1 thrown away, reducing the probability of the fairing body 1 being damaged by impact after being thrown away, so that the fairing body 1 can be safely and reliably recovered and repeated tests at a lower maintenance cost, which is conducive to verifying the feasibility and reliability of the fairing separation scheme. Moreover, in the process of separating and recovering the fairing body 1, the gas source is used as the separation energy source, which has the characteristics of high resource utilization and low cost compared with the use of pyrotechnics and other energy sources, thus facilitating repeated fairing separation tests.

[0017] Figure 2 is another schematic diagram of the structure of the test device of the embodiment of the present disclosure. Figure 1 and Figure 2 As shown, the fairing body 1 includes a left half-cover 101 and a right half-cover 102 which are spliced ​​together. The pneumatic connection assembly also includes a third pneumatic connection member 503, which is ring-arranged on the left half-cover 101 and connected to the right half-cover 102, for connecting the left half-cover 101 and the right half-cover 102.

[0018] For example, Figure 1 and Figure 2 As shown, the gas source in the present application includes a gas cylinder and a pneumatic switch, and the gas cylinder is connected to various pneumatic connectors through the pneumatic switch.

[0019] When there are multiple gas cylinders, the test device in the present application may include a first gas cylinder 504 and a second gas cylinder 505; when there are multiple pneumatic switches, the test device in the present application may include a first pneumatic switch 506 and a second pneumatic switch 507. The first gas cylinder 504 is connected to the first pneumatic connector 501 and the second pneumatic connector 502 respectively through the first pneumatic switch 506. The second gas cylinder 505 is connected to the third pneumatic connector 503 through the second pneumatic switch 507. Therefore, when the first gas cylinder 504 and the second gas cylinder 505 are filled with gas, the first pneumatic connector 501, the second pneumatic connector 502 and the third pneumatic connector 503 can be driven to open or close by controlling the opening and closing states of the first pneumatic switch 506 and the second pneumatic switch 507, thereby realizing the connection or separation between the end of the rocket simulation component 2 and the fairing body 1.

[0020] It can be understood that the number of the first pneumatic connector 501 , the second pneumatic connector 502 and the third pneumatic connector 503 in the present application are all multiple.

[0021] Taking the left half-cover 101 having nine pneumatic connectors as an example: a first gas cylinder 504 and a first pneumatic switch 506 can be provided in the left half-cover 101, and six third pneumatic connectors 503 can be provided on the docking surface between the left half-cover 101 and the right half-cover 102. At the same time, three first pneumatic connectors 501 can be provided on the docking surface between the left half-cover 101 and the end of the rocket simulation component 2.

[0022] Taking the case where the right half-cover 102 has three pneumatic connectors as an example: a second gas cylinder 505 and a second pneumatic switch 507 can be provided in the right half-cover 102, and three second pneumatic connectors 502 can be provided on the docking surface between the right half-cover 102 and the end of the rocket simulation component 2.

[0023] It can be seen that the present application realizes the connection between the two sides of the fairing body 1 and the end of the rocket simulation component 2 through the first pneumatic connector 501 and the second pneumatic connector 502, and realizes the connection inside the fairing body 1 through the third pneumatic connector 503. That is to say, under their joint action, the separation state and connection state between the fairing body 1 and the rocket simulation component 2 can be adjusted.

[0024] Exemplarily, each pneumatic connector in the present application includes a housing, a pneumatic piston, a support, an elastic member and a locking connection assembly, wherein the housing has an air inlet end, the air inlet end is connected to the outlet of the air source, the pneumatic piston, the support, the elastic member and the locking connection assembly are sequentially distributed in the housing along a direction away from the air inlet end, the support has an opening at one end facing the locking connection assembly, the support has a through hole for the pneumatic piston to move, the pneumatic piston is abutted against the locking connection assembly through the elastic member, and the pneumatic connector is connected to the rocket simulation assembly and / or the right half-cover through the locking connection assembly. Therefore, when the gas is passed from the air source into the air inlet end, the gas can push the pneumatic piston to move in a direction away from the air inlet end, thereby causing the elastic member abutting against it to be in a compressed state. Subsequently, under the action of the elastic member, the locking connection assembly is changed from a closed state to an open state, at which time, the fairing body and the rocket simulation assembly are in a separated state; and / or, the right half-cover and the left half-cover are in a separated state.

[0025] In an alternative approach, Figure 1 As shown, the first pneumatic connector 501 and the second pneumatic connector 502 in the present application are linearly distributed or arrayed along the radial direction of the end of the rocket simulation component 2, which can make the end of the rocket simulation component 2 be evenly stressed when separated from the fairing body 1, so that there is a guide constraint during the separation process of the end of the rocket simulation component 2 and the fairing body 1, ensuring the reliability of the separation of the end of the rocket simulation component 2 and the fairing body 1. The third pneumatic connector 503 is linearly distributed or arrayed along the axial direction of the fairing body 1, and its effect is the same as the above effect, which is not limited here.

[0026] In an alternative approach, Figure 1As shown, the separation assembly 3 in the present application comprises a push rod 301, a separation elastic member 302 and an elastic member bracket 303, the elastic member bracket 303 is respectively arranged on the left half cover 101 and the right half cover 102, the separation elastic member 302 is sleeved on the push rod 301, one end of the push rod 301 is connected to the end of the rocket simulation assembly 2, and the other end of the push rod 301 is connected to the elastic member bracket 303. It can be understood that before the separation assembly is arranged at the geometric center where the fairing body 1 contacts the end of the rocket simulation assembly 2, the push rod 301 should be used to squeeze the separation elastic member 302 in the direction close to the elastic member bracket 303 to make it in a pre-compression state. Therefore, when the pneumatic connection assembly changes from a locked state to an unlocked state, the separation elastic member 302 in a pre-compression state can apply a force to the end of the rocket simulation assembly 2, so that the left half cover 101 and the right half cover 102 are separated from the end of the rocket simulation assembly 2. At this time, the recovery assembly 4 fixed on the arrow body of the rocket simulation assembly 2 and close to the two sides of the fairing body 1 can recover the ejected fairing body 1, reducing the probability of the fairing body 1 being damaged by impact after being ejected, so that the entire device can be reused. It is suitable for separation tests that require multiple times and multiple working conditions, or situations where an abnormality occurs in the test and needs to be performed again. While reducing the test cost, it enhances the reliability of the product.

[0027] When the fairing body separation test is completed, the pneumatic connection assembly can be depressurized, and the separation assembly 3 can be removed, and the separation elastic member 302 in the separation assembly 3 can be compressed again, and the installation and docking operations can be repeated. Before testing again, the gas cylinder can be inflated until the unlocking pressure of the pneumatic connection is reached. Then a second test can be carried out to achieve the reuse of the test device.

[0028] In an alternative approach, Figure 1 and Figure 2 As shown, the recovery assembly 4 in the present application includes a support seat 401, a telescopic mechanism 402 and a buffer pad 403, wherein the support seat 401 is fixed on the arrow body of the rocket simulation assembly 2, the telescopic mechanism 402 is arranged on the support seat 401, and the buffer pad 403 is installed on the telescopic mechanism 402. Therefore, when the left half cover 101 and the right half cover 102 are thrown away under the action of elastic force, they can fall on the buffer pad 403, thereby reducing the probability of damage due to impact and improving the utilization rate of the fairing body. Specifically, in the recovery assembly 4, the support seat 401 can provide support force for the telescopic mechanism 402 and the buffer pad 403 arranged thereon, reducing the probability of damage to the recovery assembly. In addition, since the buffer pad 403 is installed on the telescopic mechanism 402, under the action of the telescopic mechanism 402, the buffer position of the fairing body 1 can be adjusted more flexibly.

[0029] For example, Figure 1 and Figure 2As shown, the telescopic mechanism 402 in the present application includes a cylinder 4021, an adjusting connector 4022 and a sliding member 4023. The cylinder 4021 is arranged on the support seat 401, the sliding member 4023 is threadedly connected to the cylinder 4021, the adjusting connector 4022 is sleeved on the outside of the sliding member 4023, and is used to adjust the extension length of the sliding member 4023 relative to the cylinder, and the buffer pad is installed on the sliding member. When the falling position of the left half cover 101 and the right half cover 102 deviates due to problems with the internal parts of the test device, the position of the buffer pad 403 can be moved by extending the extension length of the sliding member 4023 in the telescopic mechanism 402 relative to the cylinder, so that the left half cover 101 and the right half cover 102 fall safely.

[0030] Figure 3 FIG. 2 is a partial enlarged view of the rotation limiting mechanism of the embodiment of the present disclosure. Figure 3 As shown, the test device in the present application also includes a plurality of rotation limiting mechanisms 6 , one end of each rotation limiting mechanism 6 is connected to the fairing body 1 , and the other end of each rotation limiting mechanism 6 is connected to the arrow body of the rocket simulation assembly 2 .

[0031] Exemplarily, each rotation limiting mechanism 6 includes: a connection seat 601, a connection piece 602, a limiting piece 603 and a rotating piece 604. The connection seat 601 is arranged at the end of the rocket simulation component 2. One end of the connection piece 602 is connected to the outer side wall of the fairing body 1. The connection seat 601 and the connection piece 602 are provided with a limiting groove for the limiting piece 603 to pass through. The rotating piece 604 is used to connect the connection seat 601 and the other end of the connection piece 602. During the assembly process, the connection piece 602 is stuck in the limiting groove, and the connection piece 602 can rotate around the rotating piece 604 at a certain angle. Since the left half cover 101 and the right half cover 102 are constrained by the connection piece 602, they will rotate outward around the rotating piece 604, and after rotating a certain angle, they will escape from the limiting groove, and the left half cover 101 and the right half cover 102 will be separated from the rocket body, completing the separation. It can be seen that by setting up a rotation limit mechanism, not only can the fairing body 1 and the rocket simulation component 2 be connected, but also the ejection angle of the fairing body 1 can be limited, thereby ensuring that it can fall into the buffer range of the recovery component 4.

[0032] The present application also provides a test system to control the test device. The test system includes a controller and a test device; the controller is electrically connected to the test device. At the beginning of the test, the controller can control the opening and closing of the pneumatic switch, so that each pneumatic connector is in a locked state or an unlocked state, and the end of the rocket simulation component and the fairing body are closed or separated.

[0033] The above is only a specific implementation of the present application. Obviously, various modifications and combinations can be made without departing from the spirit and scope of the present application. Accordingly, this specification and the drawings are only exemplary illustrations of the present application as defined by the attached claims, and are deemed to have covered any and all modifications, changes, combinations or equivalents within the scope of the present application. Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include these changes and variations. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be covered within the scope of protection of the present application. Therefore, the scope of protection of the present application shall be based on the scope of protection of the claims.

[0034] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0035] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

[0036] The above description has been given for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, changes, additions and sub-combinations thereof.

Claims

1. A test device, characterized in that: include: A fairing body, a rocket simulation component, a separation component, a recovery component and a pneumatic connection component; the fairing body is connected to the end of the rocket simulation component, the separation component is arranged at the geometric center of the contact between the fairing body and the end of the rocket simulation component, and is used to throw the fairing body away from the end of the rocket simulation component; the recovery component is fixed on the arrow body of the rocket simulation component and close to the two sides of the fairing body, and is used to recover the ejected fairing body; the pneumatic connection component is used to connect the fairing body and the rocket simulation component; the pneumatic connection component includes a first pneumatic connection piece and a second pneumatic connection piece, the first pneumatic connection piece is arranged around the left side of the fairing body and is connected to the end of the rocket simulation component, and is used to connect the left side of the fairing body and the rocket simulation component, the second pneumatic connection piece is arranged around the right side of the fairing body and is connected to the end of the rocket simulation component, and is used to connect the right side of the fairing body and the rocket simulation component.

2. The test device according to claim 1, characterized in that The fairing body includes a left half-cover and a right half-cover which are spliced ​​together. The pneumatic connection assembly also includes a third pneumatic connection piece, which is arranged on the left half-cover and connected to the right half-cover for connecting the left half-cover and the right half-cover.

3. The test device according to claim 2, characterized in that The third pneumatic connectors are distributed linearly or in an array along the axial direction of the fairing body.

4. The test device according to claim 2, characterized in that Each pneumatic connecting part includes a shell, a pneumatic piston, a support part, an elastic part and a locking connection assembly. The shell has an air inlet end, which is connected to an air source. The pneumatic piston, support part, elastic part and locking connection assembly are distributed in the shell in sequence along a direction away from the air inlet end. The support part has an opening at one end facing the locking connection assembly. The support part has a through hole for the pneumatic piston to move. The pneumatic piston is abutted against the locking connection assembly through the elastic part. The pneumatic connecting part is connected to the rocket simulation assembly and / or the right half cover through the locking connection assembly.

5. The test device according to any one of claims 1 to 4, characterized in that: The first pneumatic connector and the second pneumatic connector are both distributed linearly or in an array along the radial direction of the end of the rocket simulation component.

6. The test device according to claim 5, characterized in that The separation assembly includes a push rod, a separation elastic member and an elastic member bracket, the elastic member bracket is respectively arranged on the left half cover of the fairing body and the right half cover of the fairing body, the separation elastic member is sleeved on the push rod, one end of the push rod is connected to the end of the rocket simulation assembly, and the other end of the push rod is connected to the elastic member bracket.

7. The test device according to claim 1, characterized in that The recovery assembly includes a support seat, a telescopic mechanism and a buffer pad. The support seat is fixed on the arrow body of the rocket simulation assembly, the telescopic mechanism is arranged on the support seat, and the buffer pad is installed on the telescopic mechanism.

8. The test device according to claim 7, characterized in that The telescopic mechanism includes a cylinder, an adjusting connector and a sliding member. The cylinder is arranged on the supporting seat. The sliding member is threadedly connected to the cylinder. The adjusting connector is sleeved on the outside of the sliding member to adjust the extension length of the sliding member relative to the cylinder. The buffer pad is installed on the sliding member.

9. The test device according to claim 1, characterized in that: The test device also includes a plurality of rotation limiting mechanisms, one end of each of the rotation limiting mechanisms is connected to the fairing body, and the other end of each of the rotation limiting mechanisms is connected to the arrow body of the rocket simulation assembly.

10. The test device according to claim 9, characterized in that Each of the rotation limiting mechanisms includes: a connecting seat, a connecting member, a limiting member and a rotating member. The connecting seat is arranged at the end of the rocket simulation assembly, one end of the connecting member is connected to the outer side wall of the fairing body, the connecting seat and the connecting member are provided with limiting grooves for the limiting member to pass through, and the rotating member is used to connect the connecting seat and the other end of the connecting member.

11. A test system, characterized in that: include: A controller and a test device as claimed in any one of claims 1 to 10; The controller is electrically connected to the test device.

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