Gravity unloading device for satellite radar ground testing

Abstract

The present invention discloses a gravity unloading device for ground testing of satellite radars, comprising: a frame, a driving component and a transmission component provided on the frame. The single-degree-of-freedom rotating part of the satellite radar to be tested is connected to the driving component through the transmission component. The driving component acts on the satellite radar to be tested through the transmission component, so as to balance the rotational torque generated by the gravity of the satellite radar to be tested. Compared with the gravity unloading method in the prior art, the gravity unloading device for ground testing of satellite radars of the present invention has a compact structure and a small volume, can meet the ground testing requirements of various scenarios of satellite radars, and has strong flexibility.

Description

Technical Field

[0001] The present invention relates to the technical field of ground test equipment for spacecraft products, and particularly relates to a gravity unloading device for satellite radar ground testing. Background Art

[0002] The radar equipment carried on a satellite usually has a one-dimensional or two-dimensional pointing mechanism for driving a load such as an antenna to point to a target direction. With the improvement of the lightweight design index of satellite radar, the design of the pointing mechanism develops in the direction of selecting a small-torque motor and abandoning the speed reducer. In the weightless situation in space, the pointing mechanism with a small driving force can meet the use requirements of the satellite radar. However, during the ground debugging stage after the satellite radar is manufactured, the influence of gravity cannot be ignored. Therefore, a corresponding gravity unloading device must be used to counteract the gravity of the antenna loaded by the pointing mechanism.

[0003] The prior art usually uses a counterweight to adjust the center of gravity of the load to the rotating shaft of the pointing mechanism, that is, passive gravity unloading, or uses a follow-up hanging device to tow the load of the pointing mechanism so that the traction force is equal to the load gravity, that is, active gravity unloading. The disadvantage of passive gravity unloading is that it will increase the weight and moment of inertia of the load, which is disadvantageous to the pointing mechanism; the disadvantage of active gravity unloading is that the equipment is huge in volume and can only be deployed in a fixed site, making it difficult to meet the flexible ground debugging requirements of satellite radar. Summary of the Invention

[0004] The purpose of the present invention is to overcome the defects of the prior art and propose a gravity unloading device for satellite radar ground testing, which is used to eliminate the influence of gravity on the pointing mechanism during the ground debugging stage of the satellite radar.

[0005] To achieve the above purpose, the present invention is realized through the following technical solutions:

[0006] A gravity unloading device for satellite radar ground testing, comprising: a frame, and a driving component and a transmission component arranged on the frame, the single-degree-of-freedom rotating part of the satellite radar to be measured is connected to the driving component through the transmission component, and the driving component acts on the satellite radar to be measured through the transmission component, so as to balance the rotational torque generated by the satellite radar to be measured due to gravity.

[0007] Preferably, the transmission component includes: an output shaft connected to the single-degree-of-freedom rotating part of the satellite radar to be measured; an input shaft connected to the driving component; and a flat spiral spring, the output shaft and the input shaft are coaxially connected through the flat spiral spring.

[0008] Furthermore, the planar scroll spring includes an external mounting plate and an internal mounting plate; the output shaft includes a hollow section, the planar scroll spring is placed in the hollow section, the inner wall of the hollow section is provided with a first rectangular notch, and the external mounting plate can be embedded in the first rectangular notch; a second rectangular notch is provided on the outer wall of one end of the input shaft, and the internal mounting plate can be embedded in the second rectangular notch.

[0009] Furthermore, the gravity unloading equipment for ground testing of satellite radar also includes: an angle sensor, arranged on the frame, for detecting the rotation angle of the output shaft; a torque sensor, arranged on the frame, for detecting the rotational torque of the input shaft; a controller, connected to the angle sensor, the torque sensor and the driving component, for calculating the angle change rate according to the rotation angle, thereby controlling the driving component to provide corresponding rotational torque to balance the rotational torque generated by gravity of the satellite radar under test.

[0010] Furthermore, the gravity unloading equipment for ground testing of satellite radar also includes: a gyroscope sensor, which is arranged on the frame and connected to the controller; the controller measures the angle of the pointed direction of the tested satellite radar to the ground through the gyroscope sensor and the angle sensor, thereby controlling the driving component to provide corresponding torque to balance the torque generated by gravity of the tested satellite radar.

[0011] Furthermore, the driving component includes a driving motor, and the driving motor is connected to the input shaft through a worm gear reducer arranged on the frame.

[0012] Furthermore, the output shaft is coaxially connected to the single-degree-of-freedom rotating part of the satellite radar under test through a switching fixture.

[0013] The present invention has the following advantages during use:

[0014] The gravity unloading device for ground testing of satellite radar of the present invention is provided with a driving component and a transmission component on a frame, and then the single-degree-of-freedom rotating part of the satellite radar under test is connected to the driving component through the transmission component, and the driving component acts on the satellite radar under test through the transmission component to balance the rotational torque generated by gravity of the satellite radar under test, thereby eliminating the influence of gravity on the pointing mechanism. The gravity unloading device for ground testing of satellite radar of the present invention can directly act on the single-degree-of-freedom rotating part of the satellite radar under test, balance the rotational torque generated by gravity, thereby eliminating the influence of gravity on the pointing mechanism. Compared with the active gravity unloading method in the prior art, the present invention does not need to add an additional follow-up hanging device to pull the load of the pointing mechanism, so that the traction force is equal to the load gravity. Therefore, the whole device has a compact structure and a small volume, can adapt to the ground testing requirements of various scenarios of satellite radar, and has strong flexibility. Brief Description of the Drawings

[0015] To more clearly illustrate the technical solutions of the present invention, the drawings required for description will be briefly introduced below. Obviously, the drawings in the following description are an embodiment of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts:

[0016] Figure 1 It is a schematic structural diagram of a gravity unloading device for satellite radar ground testing in an embodiment of the present invention from a certain perspective;

[0017] Figure 2 It is a schematic structural diagram of a gravity unloading device for satellite radar ground testing in an embodiment of the present invention from another perspective;

[0018] Figure 3 It is a schematic cross-sectional structure diagram of a transmission component in an embodiment of the present invention;

[0019] Figure 4 It is an exploded structural diagram of a transmission component in an embodiment of the present invention;

[0020] Figure 5 It is a schematic diagram of the working state of a gravity unloading device for satellite radar ground testing in an embodiment of the present invention.

[0021] Description of the Reference Numerals:

[0022] 1: Frame;

[0023] 2: Transmission component;

[0024] 210: Output shaft;

[0025] 211: Hollow section;

[0026] 212: First rectangular notch;

[0027] 220: Input shaft;

[0028] 221: Second rectangular notch;

[0029] 222: Thin nut;

[0030] 223: Round washer;

[0031] 230: Flat spiral spring;

[0032] 231: External mounting piece;

[0033] 232: Internal mounting piece;

[0034] 240: First bearing group;

[0035] 241: The first bushing;

[0036] 250: The first-stage housing;

[0037] 251: The first end cap;

[0038] 260: The second bearing set;

[0039] 261: The second bushing;

[0040] 270: The second-stage housing;

[0041] 271: The second end cap;

[0042] 3: The radar of the satellite to be measured;

[0043] 4: The angle sensor;

[0044] 5: The torque sensor;

[0045] 510: The coupling;

[0046] 6: The controller;

[0047] 7: The gyroscope sensor;

[0048] 8: The drive motor;

[0049] 9: The worm and worm gear reducer;

[0050] 10: The adapter tooling. Specific implementation manners

[0051] The following further details the solution proposed by the present invention in conjunction with the accompanying drawings and specific implementation manners. According to the following description, the advantages and features of the present invention will be clearer. It should be noted that the accompanying drawings are in a very simplified form and all use non-precise scales, only for conveniently and clearly assisting in explaining the purpose of the implementation manners of the present invention. In order to make the purpose, features, and advantages of the present invention more obvious and understandable, please refer to the accompanying drawings. It should be known that the structures, scales, sizes, etc. shown in the drawings of this specification are only used to cooperate with the content disclosed in the specification for those skilled in this technology to understand and read, and are not used to limit the limiting conditions for the implementation of the present invention. Therefore, they do not have a technical essence. Any modification of the structure, change of the proportional relationship, or adjustment of the size, without affecting the effects that the present invention can produce and the purposes that can be achieved, should still fall within the scope that the technical content disclosed by the present invention can cover.

[0052] This embodiment provides a gravity unloading device for ground testing of satellite radars, including: a frame 1, a driving component and a transmission component 2 provided on the frame 1. The single-degree-of-freedom rotating part of the satellite radar 3 to be measured is connected to the driving component through the transmission component 2. The driving component acts on the satellite radar 3 to be measured through the transmission component 2, so as to balance the rotational torque generated by the satellite radar 3 to be measured due to gravity.

[0053] In the gravity unloading device for ground testing of satellite radars in this embodiment, by setting a driving component and a transmission component 2 on the frame 1, and then connecting the single-degree-of-freedom rotating part of the satellite radar 3 to be measured to the driving component through the transmission component 2, the driving component acts on the satellite radar 3 to be measured through the transmission component 2 to balance the rotational torque generated by the satellite radar 3 to be measured due to gravity, thereby eliminating the influence of gravity on the pointing mechanism. Compared with the gravity unloading methods in the prior art, the gravity unloading device for ground testing of satellite radars of the present invention has a compact structure and a small volume, can meet the ground testing requirements of various scenarios of satellite radars, and has strong flexibility.

[0054] As a preferred embodiment, the transmission component 2 in this embodiment includes: an output shaft 210, which is connected to the single-degree-of-freedom rotating part of the satellite radar 3 to be measured; an input shaft 220, which is connected to the driving component; a flat spiral spring 230, and the output shaft 210 and the input shaft 220 are coaxially connected through the flat spiral spring 230. In this embodiment, the input shaft 220 and the output shaft 210 are flexibly connected through the flat spiral spring 230. When the driving component drives the input shaft 220 to rotate, the flat spiral spring 230 will undergo a certain degree of elastic deformation and then transmit the rotational torque to the output shaft 210. In this way, the driving component and the satellite radar 3 to be measured can be isolated, allowing the satellite radar 3 to be measured to move first, and then the driving component to increase or decrease the balancing torque, which can reduce the impact of the balancing torque on the satellite radar 3 to be measured and make the satellite radar 3 to be measured move more smoothly.

[0055] Specifically, the flat spiral spring 230 in this embodiment includes an external mounting piece 231 and an internal mounting piece 232; the output shaft 210 includes a hollow section 211, the flat spiral spring 230 is placed inside the hollow section 211, and a first rectangular notch 212 is provided on the inner wall of the hollow section 211. The external mounting piece 231 can be embedded into the first rectangular notch 212, so as to realize the connection between the flat spiral spring 230 and the output shaft 210; a second rectangular notch 221 is provided on the outer wall of one end of the input shaft 220, and the internal mounting piece 232 can be embedded into the second rectangular notch 221, so as to realize the connection between the flat spiral spring 230 and the input shaft 220. The input shaft 220, the flat spiral spring 230 and the output shaft 210 in this embodiment are integrally detachable, with a compact structure and simple assembly.

[0056] In this embodiment, the hollow section 211 is installed in the primary housing 250 through the first bearing set 240. One shaft section of the input shaft 220 is installed in the secondary housing 270 through the second bearing set 260, and the secondary housing 270 is fixedly connected to the primary housing 250. A first bushing 241 is clamped between the inner rings of the first bearing set 240, and a second bushing 261 is clamped between the inner rings of the second bearing set 260.

[0057] A first end cap 251 is provided on the end face of the output shaft 210. After the first end cap 251 is installed, it presses against the inner ring of the first bearing set 240 to fix the first bearing set 240 on the output shaft 210. The secondary housing 270 contacts the outer ring of the first bearing set 240 to fix the first bearing set 240 in the primary housing 250.

[0058] A thread is provided on one shaft section of the input shaft 220, and a thin nut 222 is installed on this shaft section. At the same time, a round washer 223 is sleeved on this shaft section and clamped between the thin nut 222 and the inner ring of the second bearing set 260. Tightening the thin nut 222 fixes the input shaft 220 and the second bearing set 260. A second end cap 271 is provided on the end face of the secondary housing 270. After the second end cap 271 is installed, it presses against the outer ring of the second bearing set 260 to fix the second bearing set 260 in the secondary housing 270.

[0059] Specifically, the gravity unloading device for satellite radar ground testing in this embodiment further includes: an angle sensor 4, provided on the frame 1, for detecting the rotation angle of the output shaft 210; a torque sensor 5, provided on the frame 1, for detecting the torque of the input shaft 220; a controller 6, connected to the angle sensor 4, the torque sensor 5, and the driving component, for calculating the angle change rate based on the rotation angle, so as to control the driving component to provide a corresponding torque to balance the torque generated by the gravity of the satellite radar 3 to be measured.

[0060] In this embodiment, the design method of measuring the angle first and then the torque is adopted, which allows the device to calculate the angle change rate first and then determine the torque adjustment strategy, ensuring the smoothness of the torque balance process.

[0061] More specifically, the gravity unloading device for satellite radar ground testing in this embodiment further includes: a gyroscope sensor 7, provided on the frame 1 and connected to the controller 6; the controller 6 measures the ground angle of the pointing direction of the satellite radar 3 to be measured through the gyroscope sensor 7 and the angle sensor 4, so as to control the driving component to provide a corresponding torque to balance the torque generated by the gravity of the satellite radar 3 to be measured.

[0062] In this embodiment, a gyroscope sensor 7 and an angle sensor 4 are combined to accurately measure the ground angle of the satellite radar's pointing direction, provide a dynamic balance torque value, and ensure that the satellite radar with a small self-driving force will not bear excessive resistance caused by system errors.

[0063] Specifically, the driving component in this embodiment includes a driving motor 8, and the driving motor 8 is connected to the input shaft 220 through a worm and worm gear reducer 9 provided on the frame 1. In this embodiment, the worm and worm gear reducer 9 is used. Due to its self-locking property, it can ensure that the measured satellite radar 3 will not lose the balance force in the event of a sudden power failure, which is beneficial to improving the safety of the test experiment.

[0064] In this embodiment, the central hole of the angle sensor 4 is connected to the output shaft 210, the output shaft of the torque sensor 5 is connected to the input shaft 220 through a coupling 510, the output shaft of the worm and worm gear reducer 9 is connected to the input shaft of the torque sensor 5, and the output shaft of the driving motor 8 is connected to the input shaft of the worm and worm gear reducer 9.

[0065] Specifically, the output shaft 210 in this embodiment is coaxially connected to the single-degree-of-freedom rotating part of the measured satellite radar 3 through an adapter tool 10. The overall shape of the adapter tool 10 is a frame, which plays a role in stabilizing the measured satellite radar 3 and facilitating the balancing of the rotational torque.

[0066] In summary, the present invention provides a gravity unloading device for ground testing of satellite radars, which can balance the rotational torque generated by the gravity of the measured satellite radar, eliminate the influence of gravity on the pointing mechanism, and play a role in gravity unloading.

[0067] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be recognized that the above description should not be considered as a limitation of the present invention. After those skilled in the art have read the above content, various modifications and substitutions to the present invention will be obvious. Therefore, the protection scope of the present invention should be defined by the appended claims.

Claims

1. A gravity unloading device for satellite radar ground testing, characterized in that Comprising: A frame, a driving component and a transmission component provided on the frame, a single-degree-of-freedom rotating part of the satellite radar to be measured is connected to the driving component through the transmission component, and the driving component acts on the satellite radar to be measured through the transmission component, so as to balance the rotational torque generated by the gravity of the satellite radar to be measured; The transmission component includes: an output shaft connected to the single-degree-of-freedom rotating part of the satellite radar to be measured; An input shaft connected to the driving component; a flat spiral spring, the output shaft and the input shaft are coaxially connected through the flat spiral spring. The flat spiral spring includes an external mounting piece and an internal mounting piece; the output shaft includes a hollow section, the flat spiral spring is placed in the hollow section, a first rectangular notch is provided on the inner wall of the hollow section, and the external mounting piece can be embedded in the first rectangular notch; a second rectangular notch is provided on the outer wall of one end of the input shaft, and the internal mounting piece can be embedded in the second rectangular notch.

2. The gravity unloading device for satellite radar ground testing according to claim 1, characterized in that, Further comprising: An angle sensor provided on the frame for detecting the rotation angle of the output shaft; A torque sensor provided on the frame for detecting the rotational torque of the input shaft; A controller connected to the angle sensor, the torque sensor and the driving component, for calculating the angle change rate according to the rotation angle, so as to control the driving component to provide a corresponding rotational torque to balance the rotational torque generated by the gravity of the satellite radar to be measured.

3. The gravity unloading device for satellite radar ground testing according to claim 2, wherein, Further comprising: A gyroscope sensor provided on the frame and connected to the controller; The controller measures the ground angle of the pointing direction of the satellite radar to be measured through the gyroscope sensor and the angle sensor, so as to control the driving component to provide a corresponding rotational torque to balance the rotational torque generated by the gravity of the satellite radar to be measured.

4. The gravity unloading device for satellite radar ground testing according to claim 1, wherein The driving component includes a driving motor, and the driving motor is connected to the input shaft through a worm and worm gear reducer provided on the frame.

5. The gravity unloading device for satellite radar ground testing according to claim 1, characterized in that, The output shaft is coaxially connected to the single-degree-of-freedom rotating part of the satellite radar to be measured through an adapter tooling.

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