A wide range thruster thrust test device and test method

Abstract

The present invention belongs to the field of thrust test of thrusters, and specifically relates to a wide range thrust test device and a test method of thrusters, wherein the wide range thrust test device comprises a fixed bracket, a rotating bracket and a damping mechanism; the rotating bracket comprises a horizontal mounting member and a vertical rotating rod connected to each other, the horizontal mounting member is used to mount the thruster to be tested, and the thrust direction of the thruster to be tested is skewed and perpendicular to the axis of the vertical rotating rod; the vertical rotating rod is arranged on the fixed bracket for vertical rotation; the damping mechanism comprises a damping member connector and n damping members, and the damping member comprises a rotating ring and a damper; the damping member connector comprises a mounting member arranged on the vertical rotating rod, and n connecting and separating members are arranged on the mounting member along the radial direction of the vertical rotating rod, and the n connecting and separating members correspond to the n rotating rings one by one, and the connecting and separating members are used to connect or separate the rotating rings. The present invention is suitable for testing thrusters with ultra-wide thrust range.

Description

Technical Field

[0001] The invention belongs to the field of thrust test of a propeller, and in particular relates to a wide range thrust test device and a test method of the thrust test of a propeller. Background Art

[0002] As space missions continue to expand, the demand for the development of various types of thrusters has grown rapidly. Not only are there many types of thrusters, but the thrust levels also span a very significant range.

[0003] The thrust level of micro-thrusters ranges from micro-newtons to Newtons. Pulsed plasma thrusters and Hall thrusters play a key role in tasks such as micro-satellite attitude adjustment and precise orbit correction of tiny space probes. Chemical thrusters cover a thrust range from Newtons to tens of kilonewtons. Taking dual-principal chemical thrusters as an example, their thrust range is relatively wide to meet the needs of different space propulsion missions. In the application scenarios of orbit control and attitude adjustment of small satellites, their thrust is usually in the Newton level. For example, some dual-principal chemical thrusters used for micro-orbit corrections have a minimum thrust of about 3 to 5 Newtons, which can fine-tune the orbital parameters of small satellites. In deep space exploration missions, the thrust of dual-principal chemical thrusters in the mid-course orbit correction phase is in the range of hundreds of Newtons to thousands of Newtons; and in the orbit transfer phase from the Earth orbit to the deep space target orbit, in order to overcome the Earth's gravity and accelerate the spacecraft, its thrust is generally at a higher level of thousands of Newtons to tens of kilonewtons.

[0004] In the production and development process of the thruster, accurately testing its thrust is a key test link before the thruster is put into use. However, the current situation is that thrusters of different thrust scales need to be specially designed with thrust test devices that are compatible with them. For corporate R&D departments, scientific research institutions or colleges and universities that have a variety of different models and thrust level spans, this requires a lot of manpower, material and time resources to develop, produce and design these specific test devices. This kind of complex and hugely different R&D work will greatly slow down the overall R&D cycle of the thruster, resulting in a serious reduction in R&D efficiency. Therefore, there is an urgent need for a thrust test device for thrusters that can be widely used in a wide range of thrusts. The device should have a high degree of versatility and flexibility, and can accurately, stably and efficiently complete the thrust test tasks of various thrusters in a wide thrust range from Newtons to kilonewtons, laying a solid foundation for testing technology for the rapid development of aerospace thruster technology. Summary of the invention

[0005] The object of the present invention is to provide a wide range thruster thrust test device and test method.

[0006] The present invention provides a wide range thruster thrust test device, comprising a fixed bracket, a rotating bracket and a damping mechanism;

[0007] The rotating bracket comprises a horizontal mounting piece and a vertical rotating rod connected to each other, the horizontal mounting piece is used to mount the thruster to be measured, and the thrust direction of the thruster to be measured is skewed and perpendicular to the axis of the vertical rotating rod;

[0008] The vertical rotation rod is vertically rotatably arranged on the fixed bracket;

[0009] The damping mechanism comprises a damping member connecting member and n damping members, the damping member comprises a rotating ring and a damper, the damper connecting end is connected to the rotating ring through a synchronous belt; the rotating ring is rotatably arranged on a fixed bracket, the n rotating rings are arranged concentrically from large to small in diameter, and the innermost rotating ring is concentric with the axis of the vertical rotating rod and arranged outside the vertical rotating rod;

[0010] The damping member connecting member includes a mounting member arranged on the vertical rotating rod, and n connecting and separating members are arranged on the mounting member along the radial direction of the vertical rotating rod. The n connecting and separating members correspond one-to-one to the n rotating rings, and the connecting and separating members are used to connect or separate the rotating rings.

[0011] Furthermore, the rotating ring includes a planar circular ring and a three-dimensional circular ring arranged outside the planar circular ring;

[0012] The planar circular rings of the n rotating rings are located in the same plane, and the connecting and separating members are used to connect or separate the planar circular rings;

[0013] Among the n three-dimensional circular rings, the distance between the outer end of the three-dimensional circular ring and the plane circular ring is closer than the distance between the inner end of the three-dimensional circular ring and the plane circular ring. A driving wheel for connecting a synchronous belt is arranged on the outer side of one end of the three-dimensional circular ring away from the plane circular ring.

[0014] Furthermore, the fixed bracket includes a bottom plate and n support plates fixed to the bottom plate and arranged at intervals in the upper and lower parts, and a support plate is correspondingly arranged at the lower end of each of the three-dimensional circular rings;

[0015] The support plate is provided with a through hole with a diameter larger than the outer diameter of the inner three-dimensional circular ring, and a supporting vertical ring with a diameter smaller than the inner diameter of the corresponding three-dimensional circular ring is provided outside the through hole;

[0016] The top of the supporting vertical ring is rotatably connected to the bottom of the corresponding planar circular ring, and the outer wall of the supporting vertical ring is rotatably connected to the inner wall of the corresponding three-dimensional circular ring.

[0017] Furthermore, n dampers are fixedly arranged on the bottom plate;

[0018] A driven wheel is arranged at the connecting end of each damper, and the driving wheel and the driven wheel are connected through the synchronous belt.

[0019] Furthermore, the transmission ratio of the corresponding driving wheel to the driven wheel is 1:1.

[0020] Furthermore, the damping of the n dampers is adjustable, and the damping adjustable intervals are connected end to end.

[0021] Furthermore, an engaging hole is provided on the upper end surface of the rotating ring;

[0022] The connecting and separating member is a telescopic column extending into and away from the fitting hole.

[0023] Furthermore, the fixed bracket is fixedly provided with a conductive slip ring, the rotating part of the conductive slip ring is fixedly connected to the bottom of the vertical rotating rod, and the n telescopic columns are electrically connected to the conductive slip ring.

[0024] Furthermore, more than two connecting and separating members are arranged in a circular array around the axis of the vertical rotating rod, and more than two engaging holes are arranged in a circular array around the axis of the rotating ring.

[0025] The present invention also provides a wide range thruster thrust test method, using the wide range thruster thrust test device, comprising the following steps:

[0026] S1, install the thruster to be tested on the horizontal mounting piece;

[0027] S2, igniting the thruster under test, so that the thruster under test drives the rotating bracket to rotate;

[0028] Before the thruster under test is ignited or during the rotation of the rotating bracket, at least one connecting and separating member is controlled to be connected with the damping member as required to perform a load driving capacity test of the thruster under test.

[0029] The beneficial effect of the present invention is that the wide-range thrust test device for a thruster provided by the present invention can control the vertical rotation rod to be connected to one of the damping members through a damping member connector. When the damping of multiple damping members is adjustable and the damping adjustable ranges are connected end to end, damping members with different damping forces can be selected to perform corresponding thrust tests. Moreover, when the damping member connector controls the vertical rotation rod to be connected to multiple damping members at the same time, the damping of multiple dampers can be added together to further widen the damping range, thereby providing a wide-range thrust test device for a thruster. Specifically, when the damping of the damper is adjustable within a certain range, the damping intervals of multiple dampers can be connected end to end. At this time, an ultra-large range damping test can be achieved, which is suitable for testing thrusters with an ultra-wide thrust range, and solves the problem that thrusters with different thrust scales currently need to specially develop a corresponding thrust test device. It is particularly suitable for corporate R&D departments, scientific research institutions or universities that specialize in various thrusters. In addition, by connecting or separating damping parts during the test process, different scales of damping increase, decrease, sudden increase and sudden decrease tests can be achieved, and the response of the thruster under load changes can be tested. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Attached Figure 1 This is a schematic diagram of the first angle structure of the wide range thruster thrust test device;

[0031] Attached Figure 2 It is a second angle structural schematic diagram of the wide range thruster thrust test device;

[0032] Attached Figure 3 This is the front view of the wide range thruster thrust test device;

[0033] Attached Figure 4 For attachment Figure 3 Middle AA section view;

[0034] Attached Figure 5 For attachment Figure 3 Middle BB section view;

[0035] Attached Figure 6 For attachment Figure 3 Middle CC section view;

[0036] Attached Figure 7 is a side elevational sectional view of the wide range thruster thrust test device;

[0037] Attached Figure 8 For attachment Figure 7 A partial enlarged view of point D in the middle;

[0038] Attached Fig. 9 For attachment Figure 7 A partial enlarged view of point E in the middle;

[0039] Attached Fig.10 It is a schematic diagram of the structure of three rotating rings in the wide range thruster thrust test device;

[0040] Attached Fig.11 Schematic diagram of the explosion of three support plates in this wide-range thruster thrust test device.

[0041] In the figure, 1-fixed bracket; 11-bottom plate; 12-upper panel; 13-connecting column I; 14-support plate; 141-through hole; 142-support vertical ring; 15-connecting column II; 2-rotating bracket; 21-horizontal mounting member; 22-vertical rotating rod; 221-load-bearing support plate; 3-damping mechanism; 31-damping member connecting member; 311-mounting member; 312-connecting and separating member; 32-damping member; 321-rotating ring; 3211-plane circular ring; 32111-embedded hole; 3212-three-dimensional circular ring; 3213-driving wheel; 322-damper; 3221-driven wheel; 323-synchronous belt; 33-tensioning wheel; 4-conductive slip ring; 5-plane thrust bearing; 6-deep groove ball bearing; 7-tested thruster. DETAILED DESCRIPTION

[0042] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0043] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0044] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0045] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0046] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0047] As attached Figure 1 -Attached Fig.11 As shown, the present invention provides a wide range thruster thrust test device, comprising a fixed bracket 1, a rotating bracket 2 and a damping mechanism 3;

[0048] The rotating bracket 2 includes a horizontal mounting member 21 and a vertical rotating rod 22 connected to each other. The horizontal mounting member 21 is used to mount the measured propeller 7. The thrust direction of the measured propeller 7 is eccentric and perpendicular to the axis of the vertical rotating rod 22. After the measured propeller 7 is ignited, the measured propeller 7 will push the horizontal mounting member 21 to rotate around the axis of the vertical rotating rod 22, and the measured propeller 7 performs a circular motion on the horizontal plane. At this time, the thrust direction of the measured propeller 7 is tangent to the circumference of the circle.

[0049] The vertical rotation rod 22 is vertically rotatably arranged on the fixed bracket 1;

[0050] The damping mechanism 3 includes a damping member connector 31 and n damping members 32, wherein n is greater than or equal to 2, and the damping member 32 includes a rotating ring 321 and a damper 322, wherein the connecting end of the damper 322 is connected to the rotating ring 321 via a synchronous belt 323; the rotating ring 321 is rotatably arranged on the fixed bracket 1, and the n rotating rings 321 are arranged concentrically from large to small in diameter, and the innermost rotating ring 321 is concentric with the axis of the vertical rotating rod 22 and is arranged outside the vertical rotating rod 22, preferably, the n rotating rings 321 are spaced apart from each other, and the innermost rotating ring 321 is also spaced apart from the vertical rotating rod 22 to avoid contact with each other to generate friction;

[0051] The damping member connecting member 31 includes a mounting member 311 disposed on the vertical rotating rod 22 , and n connecting and separating members 312 are arranged on the mounting member 311 along the radial direction of the vertical rotating rod 22 , and the n connecting and separating members 312 correspond one-to-one to the n rotating rings 321 , and the connecting and separating members 312 are used to connect or separate the rotating rings 321 .

[0052] The wide-range thrust test device for a thruster provided by the present invention can control the vertical rotation rod 22 to be connected to one of the damping members 32 through the damping member connector 31. When the damping of multiple damping members 32 is adjustable and the damping adjustable ranges are connected end to end, damping members 32 with different damping forces can be selected to perform corresponding thrust tests. Moreover, when the damping member connector 31 controls the vertical rotation rod 22 to be connected to multiple damping members 32 at the same time, the damping of multiple dampers 322 can be added together to further widen the damping range, thereby providing a wide-range thrust test device for a thruster. Specifically, when the damping of the damper 322 is adjustable within a certain range, the damping intervals of the multiple dampers 322 can be connected end to end. Taking the case where there are three damping members 32 as an example, for example, the adjustable damping interval of the first damper 322 is AB, the adjustable damping interval of the second damper 322 is BC, and the adjustable damping interval of the third damper 322 is CD. When there are more than three damping members 32, and so on, the damping force represented by AD increases from small to large. At this time, an ultra-large range damping test from A to B+C+D can be achieved, which is suitable for testing thrusters with ultra-wide thrust ranges, solving the problem that thrusters with different thrust scales currently need to specially develop a corresponding thrust testing device, and is particularly suitable for corporate R&D departments, scientific research institutions or universities that specialize in studying various thrusters. In addition, by connecting or separating the damping members 32 during the test process, different scales of damping increase, decrease, sudden increase and sudden decrease tests can be achieved, and the response of the thruster under load changes can be tested.

[0053] In one embodiment, referring to FIG. 9 and FIG. Fig.10 The rotating ring 321 includes a planar ring 3211 and a three-dimensional ring 3212 arranged outside the planar ring 3211;

[0054] The planar circular rings 3211 of the n rotating rings 321 are located in the same plane, and the connecting and separating member 312 is used to connect or separate the planar circular rings 3211, so that the connecting and separating member 312 can be easily connected or separated from the n rotating rings 321;

[0055] Among the n three-dimensional circular rings 3212, the distance between the end of the outer three-dimensional circular ring 3212 and the plane circular ring 3211 is closer than the distance between the end face of the inner three-dimensional circular ring 3212 and the plane circular ring 3211. The outer side of the end of the three-dimensional circular ring 3212 away from the plane circular ring 3211 is provided with a driving wheel 3213 for connecting the synchronous belt 323, that is, the height of the outermost three-dimensional circular ring 3212 is the lowest, and then the height of the inner three-dimensional circular ring 3212 gradually increases, so as to facilitate the arrangement of the inner driving wheel 3213. At this time, refer to the attached Figure 1 , Attachment Figure 3 -Attached Figure 6 The outermost driving wheel 3213 has the largest diameter and the highest position, and then the diameter of the inner driving wheel 3213 gradually decreases and the position gradually moves downward.

[0056] In one embodiment, referring to FIG. 9 and FIG. Fig.11 The fixed bracket 1 includes a bottom plate 11 and n support plates 14 fixed to the bottom plate 11 and arranged at intervals in the upper and lower directions. A support plate 14 is correspondingly provided at the lower end of each three-dimensional circular ring 3212. Preferably, the n support plates 14 are connected to each other and fixed to the bottom plate 11 through connecting columns II 15 at four corners. The support plates 14 are used to rotate and fix the rotating ring 321;

[0057] The support plate 14 is provided with a through hole 141 whose diameter is larger than the outer diameter of the inner three-dimensional circular ring 3212, and the through hole 141 is used to provide installation and rotation space for the inner three-dimensional circular ring 3212. A support stand ring 142 whose diameter is smaller than the inner diameter of the corresponding three-dimensional circular ring 3212 is provided outside the through hole 141, and the support stand ring 142 is used to rotatably support and fix the rotating ring 321. The through hole 141 of the lowest support plate 14 has a diameter larger than the vertical rotating rod 22, and the through hole 141 is used to provide installation and rotation space for the vertical rotating rod 22.

[0058] The top of the support ring 142 is rotatably connected to the bottom of the corresponding plane ring 3211. Preferably, a plane thrust bearing 5 is arranged between the top of the support ring 142 and the bottom of the corresponding plane ring 3211. The outer wall of the support ring 142 is rotatably connected to the inner wall of the corresponding three-dimensional ring 3212. Preferably, a deep groove ball bearing 6 is arranged between the outer wall of the support ring 142 and the inner wall of the corresponding three-dimensional ring 3212.

[0059] In this embodiment, the n rotating rings 321 are rotationally supported and fixed by n supporting plates 14 , thereby ensuring that the n supporting plates 14 are independent of each other and that their planar circular rings 3211 are located in the same plane, facilitating cooperation with the connecting and separating parts 312 .

[0060] In one embodiment, referring to the attached Figure 2 -Attached Figure 3 , n dampers 322 are fixedly arranged on the bottom plate 11;

[0061] The connection end of each damper 322 passes through the bottom plate 11 and is provided with a driven wheel 3221, and the driving wheel 3213 and the driven wheel 3221 are connected by the synchronous belt 323. Preferably, the n dampers 322 are arranged in a circular array around the axis of the vertical rotation rod 22, so that the distance between the connection ends of the n dampers 322 and the vertical rotation rod 22 can be ensured. Preferably, a tensioning wheel 33 is provided on the support plate 14, and the tensioning wheel 33 can adjust the tension of the synchronous belt 323 to ensure smooth and reliable transmission.

[0062] In one embodiment, the transmission ratio of the driven wheel 3221 to the corresponding driving wheel 3213 is 1:1, so that the damping of the damper 322 can be intuitively fed back.

[0063] In one of the embodiments, the damping of n dampers 322 is adjustable, and the adjustable damping intervals are connected end to end. In this embodiment, when the damping of the damper 322 is adjustable within a certain range, the damping intervals of multiple dampers 322 can be connected end to end. Taking three damping members 32 as an example, for example, the adjustable damping interval of the first damper 322 is AB, the adjustable damping interval of the second damper 322 is BC, and the adjustable damping interval of the third damper 322 is CD, and so on. The damping represented by AD is from small to large. At this time, an ultra-wide range damping test from A to B+C+D can be achieved, which is suitable for testing thrusters with ultra-wide thrust range.

[0064] In one embodiment, the upper end surface of the rotating ring 321 is provided with an embedding hole 32111, that is, the embedding hole 32111 is provided on the upper end surface of the plane ring 3211;

[0065] The connecting and separating member 312 is a telescopic column that extends into and out of the fitting hole 32111. The telescopic column is preferably an electric telescopic rod or an electromagnetic telescopic rod. When the output shaft of the electric telescopic rod or the electromagnetic telescopic rod extends into the fitting hole 32111, the connection between the vertical rotating rod 22 and the corresponding rotating ring 321 is completed, thereby facilitating the control of the connection and separation of the connecting and separating member 312 and the rotating ring 321.

[0066] In one of the embodiments, the fixed bracket 1 is fixedly provided with a conductive slip ring 4, and the rotating portion of the conductive slip ring 4 is fixedly connected to the bottom of the vertical rotating rod 22. Preferably, the conductive slip ring 4 is arranged on the lowest support plate 14, and the n telescopic columns are electrically connected to the conductive slip ring 4. In this way, the power supply and control components of the telescopic columns can be arranged on the fixed bracket 1 instead of the rotating bracket 2, which simplifies the line connection and realizes the continuous rotation of the rotating bracket 2.

[0067] In one embodiment, referring to FIG. 2, the connecting and separating members 312 are arranged in a circular array around the axis of the vertical rotating rod 22, and the fitting holes 32111 are arranged in a circular array around the axis of the rotating ring 321. By setting more than two connecting and separating members 312 and arranging them in a circular array, on the one hand, the connection strength between the connecting and separating members 312 and the damping member 32 can be improved, and on the other hand, the central symmetry of the rotating bracket 2 as a whole can be ensured, the center of gravity of the rotating shaft can be ensured to be uniform, and no additional lateral torque or vibration will be introduced, thereby ensuring the test accuracy of the device. When only two connecting and separating members 312 are provided, the mounting member 311 is a rod structure, and the two mounting members 311 are in a straight line.

[0068] In one embodiment, referring to FIG. 2, at least two propellers 7 to be tested are arranged in a circular array on the horizontal mounting member 21. By setting more than two and arranging them in a circular array, on the one hand, the thrust of the propeller 7 to be tested can be increased, on the other hand, the joint action of multiple propellers 7 to be tested can be simulated, and on the other hand, the central symmetry of the rotating bracket 2 as a whole can be ensured, the center of gravity of the rotating shaft can be ensured to be uniform, and no additional lateral torque or vibration will be introduced, thereby ensuring the test accuracy of the device. When only two propellers 7 to be tested are provided, the horizontal mounting member 21 is a rod structure, and the middle of the horizontal mounting member 21 is provided at the upper end of the vertical rotating rod 22. In other embodiments, when only one propeller 7 to be tested is provided, a counterweight block having the same mass as the propeller 7 to be tested is provided on the other side of the horizontal mounting member 21, so as to ensure the central symmetry of the rotating bracket 2 as a whole.

[0069] In one embodiment, the fixing bracket 1 includes a bottom plate 11, an upper panel 12, and a connecting column Ⅰ 13 connecting the bottom plate 11 and the upper panel 12;

[0070] The vertical rotating rod 22 is rotatably arranged on the lowest support plate 14 and the upper panel 12 via a deep groove ball bearing 6. Such an arrangement can ensure the rotation stability of the vertical rotating rod 22 and the fixed bracket 1 and prevent the vertical rotating rod 22 from deflecting.

[0071] In one of the embodiments, the vertical rotating rod 22 is provided with a load-bearing support plate 221 above the upper panel 12, and the load-bearing support plate 221 and the upper panel 12 are rotationally matched through the planar thrust bearing 5. At this time, the weight of the vertical rotating rod 22 is transferred to the upper panel 12 by the planar thrust bearing 5, thereby reducing the downward pressure burden of the vertical rotating rod 22 on the base plate 11 and the conductive slip ring 4.

[0072] The present invention also provides a wide range thruster thrust test method, using the wide range thruster thrust test device, comprising the following steps:

[0073] S1, installing the thruster 7 to be tested on the horizontal mounting member 21;

[0074] S2, igniting the thruster 7 under test, so that the thruster 7 under test drives the rotating bracket 2 to rotate;

[0075] Before the thruster 7 under test is ignited or during the rotation of the rotating bracket 2, at least one connecting and separating member 312 is controlled to be connected with the damping member 32 as required to test the load driving capability of the thruster 7 under test. When the damping force of the thruster 7 under test and one or more damping members 32 are balanced, the rotating bracket 2 stops rotating, and at this time, the damping force of one or more damping members 32 can feed back the thrust of the thruster 7 under test.

[0076] Taking three damping members 32 as an example, the adjustable damping range of the first damper 322 is 1N-100N, the adjustable damping range of the second damper 322 is 100N-500N, and the adjustable damping range of the third damper 322 is 500N-1000N. At this time, the wide range thruster thrust test device can realize the damping test between 1N and 1600N, which is suitable for testing thrusters with thrusts ranging from 1N to 1600N.

[0077] When the connecting separation member 312 is connected to the first damping member 32 and other damping members 32 are not involved in the test, the thrust of the thruster 7 under test can be tested between 1N-100N; for example, a thrust test is performed on a small dual-principal chemical thruster (such as hydrogen peroxide-kerosene).

[0078] When the connecting separation member 312 is connected to the second damping member 32 and other damping members 32 are not involved in the test, the thrust of the thruster 7 under test can be tested between 100N-500N; for example, a thrust test is performed on a medium-sized two-component liquid thruster (such as unsymmetrical dimethylhydrazine-nitrogen tetroxide).

[0079] When the connecting separation member 312 is connected to the third damping member 32 and other damping members 32 are not involved in the test, the thrust of the thruster 7 under test can be tested between 500N-1000N; for example, a thrust test is performed on a medium-sized two-component liquid thruster (such as unsymmetrical dimethylhydrazine-nitrogen tetroxide).

[0080] When the connecting and separating member 312 is connected to the first damping member 32 and the second damping member 32, and the third damping member 32 is not involved in the test, the thrust of the thruster 7 under test can be tested to be between 101N and 600N;

[0081] When the connecting and separating member 312 is connected to the first damping member 32 and the third damping member 32, and the second damping member 32 is not involved in the test, the thrust of the thruster 7 under test can be tested to be between 501N and 1100N;

[0082] When the connecting and separating member 312 is connected to the second damping member 32 and the third damping member 32, and the first damping member 32 is not involved in the test, the thrust of the thruster 7 under test can be tested to be between 600N and 1500N;

[0083] When the connection separation member 312 is connected to the three damping members 32, the thrust of the thruster 7 under test can be tested to be between 601N and 1600N; for example, a thrust test is performed on a small thrust unit group liquid rocket engine;

[0084] By analogy, the damping test can be achieved from 1N to 1600N.

[0085] In the specific test process, the damping of the connected damper 322 is adjusted until the vertical rotation rod 22 stops rotating. At this time, the thrust of the tested propeller 7 is equal to the damping force of the connected damper 322, thereby testing the thrust of the tested propeller 7.

[0086] The above is only an embodiment and does not limit the present invention in any way. Any person skilled in the art can use the above disclosed technical contents to make many possible changes, modifications or modifications to the technical solutions of the present invention into equivalent embodiments of equivalent changes without departing from the scope of the technical solutions of the present invention. Therefore, any simple modification, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A wide range thrust test device, characterized in that: It comprises a fixed bracket (1), a rotating bracket (2) and a damping mechanism (3); The rotating bracket (2) comprises a horizontal mounting member (21) and a vertical rotating rod (22) connected to each other, the horizontal mounting member (21) being used to mount a thruster (7) to be measured, the thrust direction of the thruster (7) to be measured being skewed and perpendicular to the axis of the vertical rotating rod (22); The vertical rotation rod (22) is vertically rotatably arranged on the fixed bracket (1); The damping mechanism (3) comprises a damping member connecting member (31) and n damping members (32); the damping member (32) comprises a rotating ring (321) and a damper (322); a connecting end of the damper (322) is connected to the rotating ring (321) via a synchronous belt (323); the rotating ring (321) is rotatably arranged on a fixed bracket (1); the n rotating rings (321) have diameters from large to small and are arranged concentrically; the innermost rotating ring (321) is concentric with the axis of the vertical rotating rod (22) and is arranged outside the vertical rotating rod (22); The damping member connecting member (31) comprises a mounting member (311) arranged on the vertical rotating rod (22), n connecting and separating members (312) being arranged on the mounting member (311) along the radial direction of the vertical rotating rod (22), the n connecting and separating members (312) corresponding one-to-one to the n rotating rings (321), and the connecting and separating members (312) being used to connect or separate the rotating rings (321); The rotating ring (321) comprises a planar circular ring (3211) and a three-dimensional circular ring (3212) arranged outside the planar circular ring (3211); The planar circular rings (3211) of the n rotating rings (321) are located on the same plane, and the connecting and separating members (312) are used to connect or separate the planar circular rings (3211); Among the n three-dimensional circular rings (3212), the distance between the end of the outer three-dimensional circular ring (3212) and the plane circular ring (3211) is closer than the distance between the end face of the inner three-dimensional circular ring (3212) and the plane circular ring (3211), and a driving wheel (3213) for connecting to a synchronous belt (323) is provided on the outer side of one end of the three-dimensional circular ring (3212) away from the plane circular ring (3211).

2. The wide range thruster thrust test device according to claim 1, characterized in that: The fixed bracket (1) comprises a bottom plate (11) and n support plates (14) fixed to the bottom plate (11) and arranged at intervals in the upper and lower parts, wherein a support plate (14) is correspondingly arranged at the lower end of each three-dimensional circular ring (3212); The support plate (14) is provided with a through hole (141) having a diameter greater than the outer diameter of the inner three-dimensional circular ring (3212), and a supporting vertical ring (142) having a diameter smaller than the inner diameter of the corresponding three-dimensional circular ring (3212) is provided outside the through hole (141); The top of the supporting stand ring (142) is rotatably connected to the bottom of the corresponding planar circular ring (3211), and the outer wall of the supporting stand ring (142) is rotatably connected to the inner wall of the corresponding three-dimensional circular ring (3212).

3. The wide range propeller thrust test device according to claim 2, characterized in that: The n dampers (322) are fixedly arranged on the bottom plate (11); A driven wheel (3221) is provided at the connection end of each damper (322), and the driving wheel (3213) and the driven wheel (3221) are connected via the synchronous belt (323).

4. The wide range propeller thrust test device according to claim 3, characterized in that: The transmission ratio of the corresponding driving wheel (3213) to the driven wheel (3221) is 1:

1.

5. The wide range propeller thrust test device according to claim 1, characterized in that: The damping of the n dampers (322) is adjustable, and the damping adjustable intervals of the n dampers (322) are connected end to end.

6. The wide range thrust test device for a propeller according to any one of claims 1 to 5, characterized in that: An engaging hole (32111) is provided on the upper end surface of the rotating ring (321); The connecting and separating member (312) is a telescopic column that extends into and out of the fitting hole (32111).

7. The wide range propeller thrust test device according to claim 6, characterized in that: The fixed bracket (1) is fixedly provided with a conductive slip ring (4), the rotating portion of the conductive slip ring (4) is fixedly connected to the bottom of the vertical rotating rod (22), and the n telescopic columns are electrically connected to the conductive slip ring (4).

8. The wide range propeller thrust test device according to claim 7, characterized in that: There are more than two connecting and separating members (312) arranged in a ring array around the axis of the vertical rotating rod (22), and there are more than two engaging holes (32111) arranged in a ring array around the axis of the rotating ring (321).

9. A wide range propeller thrust test method, characterized in that: Using the wide range thruster thrust test device as described in any one of claims 1 to 8 comprises the following steps: S1, installing the thruster (7) to be tested on the horizontal mounting member (21); S2, igniting the thruster (7) under test, so that the thruster (7) under test drives the rotating bracket (2) to rotate; Before the thruster (7) under test is ignited or during the rotation of the rotating bracket (2), at least one connecting and separating member (312) is controlled to be connected to the damping member (32) as required, so as to perform a load driving capacity test on the thruster (7) under test.

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