Startup response time detection system and method for cold air thruster

Abstract

This application discloses a system and method for detecting the start-up response time of a cold gas thruster. The system includes: a thrust reaction device for providing a thrust reaction surface; a motion limiting device for limiting the motion trajectory of the thrust reaction device when it is driven by the thrust of the cold gas thruster; a position detection device for generating and / or outputting a detectable detection electrical signal when the thrust reaction device is driven to a preset position by the cold gas thruster; and a signal processing device for calculating and / or outputting the start-up response time of the cold gas thruster based on the time difference between the detection electrical signal and the command electrical signal for starting the cold gas thruster. The advantage of this application is that it provides a system and method for detecting the start-up response time of a cold gas thruster by directly propelling the reactant and efficiently detecting the position of the reactant to indirectly detect the thrust response time.

Description

Technical Field

[0001] This application relates to the field of measurement technology, and more specifically, to a system and method for detecting the start-up response time of a cold gas thruster. Background Technology

[0002] With the continuous advancement of microelectromechanical systems (MEMS) technology and the development of microsatellite technology, the scientific mission capabilities of small and microsatellites have been greatly enhanced. This has placed higher demands on the propulsion systems of microsatellites to meet the demands of these more demanding scientific missions. Employing small-sized and simple-to-control cold gas propulsion technology on microsatellites to meet the needs of attitude adjustment, orbit maintenance, and deorbiting at the end of their lifespan is a viable solution. However, due to the small mass of microsatellites, the thrust response time of the cold gas thruster has a significant impact on the real-time control of satellite attitude adjustment. Measuring the response time of the cold gas thruster is the delay between the thruster receiving a control command and the cold gas being ejected from the thruster nozzle. In conventional cold gas propulsion systems, the propellant is typically ammonia or nitrogen; however, the thrust of cold gas thrusters used on microsatellites is only in the micronewton range, and the cold gas flow rate is extremely weak, making the measurement of the cold gas thruster response time very difficult. Summary of the Invention

[0003] The summary section of this application is intended to provide a brief overview of the concepts, which will be described in detail in the detailed description section below. This summary section is not intended to identify key or essential features of the claimed technical solutions, nor is it intended to limit the scope of the claimed technical solutions.

[0004] Some embodiments of this application propose a start-up response time detection system and method suitable for cold gas thrusters to solve the technical problems mentioned in the background section above.

[0005] As a first aspect of this application, some embodiments of this application provide a start-up response time detection system suitable for a cold gas thruster, comprising: a thrust reaction device for providing a thrust reaction surface disposed on the thrust output path of the cold gas thruster; a motion limiting device for limiting the motion trajectory of the thrust reaction device when it is driven by the thrust of the cold gas thruster; a position detection device for generating and / or outputting a detectable detection electrical signal when the thrust reaction device is driven to a preset position by the cold gas thruster; and a signal processing device for calculating and / or outputting the start-up response time of the cold gas thruster based on the time difference between the detection electrical signal and the command electrical signal for starting the cold gas thruster; wherein the thrust reaction device and the motion limiting device are physically connected; and the position detection device and the signal processing device are electrically connected.

[0006] Furthermore, the thrust response device includes: a oscillating member configured to have a plane as a thrust response surface; the motion limiting device includes: a suspension line for freely suspending the oscillating member under the action of gravity; wherein one end of the suspension line is connected to the oscillating member so that the thrust response surface of the oscillating member is perpendicular to the thrust output path.

[0007] Furthermore, the motion limiting device also includes: a suspension frame comprising a horizontally extending suspension arm; wherein the other end of the suspension line is connected to the middle section of the suspension arm.

[0008] Furthermore, the oscillating member is constructed to have: a force-receiving part for forming a thrust reaction surface; and a triggering part for forming a triggering structure for a triggering position detection device; wherein the center of gravity of the oscillating member is located between the force-receiving part and the triggering part.

[0009] Furthermore, when the oscillating component is in a free suspension state, the extension of the suspension line passes through the center of gravity of the oscillating component.

[0010] Furthermore, the force-bearing part is constructed as a plate-like structure parallel to the first plane, and the triggering part is constructed as a plate-like structure parallel to the second plane.

[0011] Furthermore, when the oscillating element is in free suspension, the projected shape of the oscillating element on the horizontal plane includes a "T"-shaped profile.

[0012] Furthermore, the oscillating element is constructed with a polyhedral structure, with one plane of the polyhedron serving as the thrust response surface and the portion of the polyhedron away from that plane serving as the triggering structure.

[0013] Furthermore, the position detection device includes: at least two detection probes spaced a certain distance apart so that at least a portion of the thrust response device can move between them; a field source device for creating an energy field between the detection probes that is different from other spaces; wherein the field source device is electrically connected to the detection probes so that at least a portion of the thrust response device can move between them. When the field source device creates an energy field through at least one of the detection probes, the position detection device can generate a detection electrical signal according to the change of the energy field.

[0014] Furthermore, the energy field generated by the field source device can be an electric field, a magnetic field, or a light energy field.

[0015] As a second aspect of this application, some embodiments of this application provide a method for detecting the start-up response time of a cold gas thruster, employing a start-up response time detection system for a cold gas thruster as described in any of the foregoing claims.

[0016] The beneficial effects of this application are: it provides a start-up response time detection system and method suitable for cold gas thrusters, which utilizes a cold gas thruster to directly drive the reaction material and efficiently detect the position of the reaction material to indirectly detect the thrust response time. Attached Figure Description

[0017] The accompanying drawings, which form part of this application, are used to provide a further understanding of the application and to make other features, objects, and advantages of the application more apparent. The illustrative embodiments and descriptions of this application are used to explain the application and do not constitute an undue limitation of the application.

[0018] Furthermore, throughout the accompanying drawings, the same or similar reference numerals denote the same or similar elements. It should be understood that the drawings are schematic, and the elements are not necessarily drawn to scale.

[0019] In the attached diagram:

[0020] Figure 1 This is a schematic diagram of a start-up response time detection system for a cold gas thruster according to an embodiment of this application.

[0021] Figure 2 This is a schematic diagram of signal processing for a start-up response time detection system for a cold gas thruster according to an embodiment of this application;

[0022] Figure 3 This is a schematic diagram of the overall structure of the start-up response time detection system for a cold gas thruster according to the first embodiment of this application;

[0023] Figure 4 This is a schematic diagram of the overall structure of a start-up response time detection system for a cold gas thruster according to a second embodiment of this application;

[0024] Figure 5 This is a schematic diagram of the overall structure of a start-up response time detection system for a cold gas thruster according to a third embodiment of this application;

[0025] Figure 6 This is a schematic diagram of the main steps of a start-up response time detection method for a cold gas thruster according to an embodiment of this application;

[0026] The meanings of the reference numerals in the attached figures are as follows:

[0027] 100. Start the response time detection system;

[0028] 110. Thrust reaction device; 111. Oscillating component; 1111. Force-receiving part; 111a. Thrust reaction surface; 1112. Triggering part; 1113. Triggering structure;

[0029] 120. Motion limiting device; 121. Suspension line; 122. Suspension frame; 1221. Suspension arm; 123. Auxiliary line;

[0030] 130. Position detection device; 131. Detection probe; 131a. Infrared transmitter; 131b. Infrared receiver;

[0031] 140. Signal processing device; 141. Digital oscilloscope; 142. Signal conditioning device;

[0032] 150. Air conditioning thruster;

[0033] 160. Reset device; 161. Electrostatic chuck; 162. Pushing device. Detailed Implementation

[0034] Embodiments of this disclosure will now be described in more detail with reference to the accompanying drawings. While some embodiments of this disclosure are shown in the drawings, it should be understood that this disclosure can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of this disclosure. It should be understood that the accompanying drawings and embodiments of this disclosure are for illustrative purposes only and are not intended to limit the scope of protection of this disclosure.

[0035] It should also be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings. Unless otherwise specified, the embodiments and features described in this disclosure can be combined with each other.

[0036] It should be noted that the concepts of "first" and "second" mentioned in this disclosure are used only to distinguish different devices, modules or units, and are not used to limit the order of functions performed by these devices, modules or units or their interdependencies.

[0037] It should be noted that the terms "a" and "a plurality of" used in this disclosure are illustrative rather than restrictive, and those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0038] The names of messages or information exchanged between multiple devices in the embodiments of this disclosure are for illustrative purposes only and are not intended to limit the scope of such messages or information.

[0039] This disclosure will now be described in detail with reference to the accompanying drawings and embodiments.

[0040] like Figures 1 to 2 As shown, the start-up response time detection system 100 for cold gas thrusters of this application includes: a thrust response device 110, a motion limiting device 120, a position detection device 130, and a signal processing device 140.

[0041] Specifically, the thrust response device 110 is used to provide a thrust response surface 111a disposed on the thrust output path of the cold gas thruster 150; the motion limiting device 120 is physically connected to the thrust response device 110 and is used to limit the motion trajectory of the thrust response device 110 when it is driven by the thrust of the cold gas thruster 150; the position detection device 130 is used to generate or / and output a detectable detection electrical signal when the thrust response device 110 is driven to a preset position by the cold gas thruster 150; the signal processing device 140 is electrically connected to the position detection device 130 and is used to calculate or / and output the start-up response time of the cold gas thruster 150 based on the time difference between the detection electrical signal and the command electrical signal for starting the cold gas thruster 150.

[0042] With this approach, the thrust response device 110 changes position under the thrust drive of the cold gas thruster 150 so that the position detection device 130 can generate and / or output a detection electrical signal. In the start-up response time detection system 100 of this application, the cold gas thruster 150 is only used to change the position of the thrust response device 110 and does not directly act on the position detection device 130, thus avoiding coupling with the cold gas thruster 150. The mass of the cold gas thruster 150 and the working fluid supply pipeline and cable connection of the cold gas thruster 150 will not introduce error factors to the measuring device, thereby greatly improving the measurement accuracy and being able to reflect the dynamic changes of the thruster in the time domain, realizing continuous measurement of the response time of the cold gas thruster 150.

[0043] like Figure 6 As shown, the detection method performed by the start-up response time detection system 100 for cold gas thrusters of this application includes the following main steps:

[0044] S1: Start the cold air thruster 150, and the thrust it generates acts on the thrust reaction surface 111a on the thrust output path;

[0045] S2: When the thrust reaction device 110 is driven to a preset position by the cold gas thruster 150, the position detection device 130 generates or / and outputs a detectable detection electrical signal.

[0046] S3: Calculate and / or output the start-up response time of the cold air thruster 150 based on the time difference between the detection electrical signal and the command electrical signal for starting the cold air thruster 150.

[0047] like Figures 1 to 2As shown, as a specific solution, the thrust response device 110 includes a swing member 111. The swing member 111 is constructed to have a plane as a thrust response surface 111a. The thrust response surface is perpendicular to the thrust output path, and the area of ​​the thrust response surface is larger than the area of ​​the cold air ejected by the thruster, so that the cold air ejected by the thruster can fully act on the swing member and realize the rapid response of the swing member. The motion limiting device 120 includes a suspension line 121 and a suspension frame 122. The suspension line 121 is used to suspend the swing member 111 freely under the action of gravity. Specifically, the suspension line 121 can be made of nylon thread, and one end of it is connected to the swing member 111 so that the thrust reaction surface 111a of the swing member 111 is perpendicular to the thrust output path. The suspension frame 122 is used to support the whole formed by the swing member 111 and the suspension line 121 and to provide a stable suspension point for the suspension line 121. Specifically, the suspension frame 122 includes a horizontally extending suspension arm 1221, and the other end of the suspension line 121 is connected to the middle section of the suspension arm 1221.

[0048] By adopting this scheme, the swing process of the swinging component 111 is approximately the free pendulum motion, which converts the weak thrust of the cold air into the pendulum motion of the swinging component 111 and indirectly obtains the detection electrical signal, making it easy to obtain the response time of the cold air thruster 150.

[0049] Of course, as an alternative, the oscillating component can be placed on an air-floating motion platform, converting the weak thrust of the cold air into the sliding of the oscillating component 111 to indirectly obtain a detection electrical signal; or the oscillating component can be suspended using magnetic levitation technology, thereby reacting to the thrust of the cold air to obtain a detection electrical signal. Although the above alternative solutions can all achieve the detection purpose, the oscillating component in these solutions has a relatively high response delay to the action of the cold air, and compared with the free pendulum method of this application, its detection accuracy of the response time of the cold air thruster is lower.

[0050] like Figures 1 to 2 As shown, in a specific embodiment, the swing member 111 is constructed to include a force-receiving part 1111 and a triggering part 1112; the force-receiving part 1111 forms a thrust reaction surface 111a; the triggering part 1112 forms a triggering structure 1113 of the triggering position detection device 130; preferably, the center of gravity of the swing member 111 is located between the force-receiving part 1111 and the triggering part 1112. Preferably, when the swing member 111 is in free suspension, the extension line of the suspension line 121 passes through the center of gravity of the swing member 111. This is to ensure the attitude of the swing member 111 so that it can quickly respond to the received thrust.

[0051] More specifically, this method ensures the stability of the swing member 111 when it is in a free suspension position, so that the thrust reaction surface 111a is perpendicular to the thrust output path of the cold air thruster 150, which makes it easier for the weak thrust of the cold air ejected by the cold air thruster 150 to push the swing member 111 to a preset position, thereby causing the position detection device 130 to generate a detection electrical signal.

[0052] like Figure 3 As shown, the motion limiting device 120 further includes auxiliary lines 123, of which multiple auxiliary lines 123 are provided. One end of each auxiliary line 123 is connected to the suspension line, and the other end is connected to different positions of the swing member. Each auxiliary line 123 forms an angle with the suspension line. This method improves the stability of the swing member during suspension, maintains the thrust reaction surface perpendicular to the thrust output path, and prevents the swing member from rotating around the center of the suspension line during movement, thus avoiding the generation of a detection signal by the position detection device.

[0053] Specifically, the oscillating component 111 uses a lightweight mica sheet, which offers significant air resistance, especially under vacuum conditions. Since the error introduced by air resistance is negligible, this ensures accurate response time measurement. As an optional solution, to further reduce this error, the oscillating component can be designed as... Figure 4 and Figure 5 The design shown has a wedge-shaped or pointed structure on the part of it that is away from the cold gas thruster.

[0054] To achieve better detection results, the mass M of the swing component 111, its distance L1 from the preset position, its distance L2 from the cold air thruster nozzle, and the length L3 of the suspension line will all affect the actual reaction speed, especially for different thrusts F.

[0055] As a preferred embodiment, to ensure that the cold air ejected from the cold air thruster does not easily diffuse and lose some thrust, and that the cold air can quickly move to the oscillating component, while also ensuring easy control of the oscillating component's motion, the ratio of the distance L1 between the oscillating component and the preset position to the distance L2 between the oscillating component and the nozzle of the cold air thruster ranges from 0.25 to 0.75, preferably from 0.4 to 0.6, and ideally is 0.5. By adopting the above parameters, the oscillating component can quickly move to the preset position under the thrust of the cold air, and the response time of the cold air thruster is much longer than the time it takes for the oscillating component to move to the preset position under the thrust.

[0056] Under the constraint of the suspension line, the movement trajectory of the oscillating component approximates an arc. For the same horizontal distance traveled, the shorter the suspension line, the longer the actual path the oscillating component takes to reach the preset position. To reduce the actual path length of the oscillating component to the preset position, and simultaneously reduce the impulse of the external force required to change the initial state, the ratio of the suspension line length L3 to the distance L1 between the oscillating component and the preset position ranges from 2.5 to 7.5, preferably from 4 to 6, and ideally is 5.

[0057] According to the momentum theorem, the impulse of the net external force acting on an object is equal to the change in its momentum. The larger the mass of the oscillating component, the greater the external force required to change its state, and the air-cooled thruster can only output a weak thrust. If the mass of the oscillating component is too small or the suspension line is too long, the oscillating component needs a larger oscillation angular velocity to maintain its arc trajectory due to centrifugal force, but the weak air-cooled thrust cannot meet the oscillation angular velocity requirement. If the mass of the oscillating component is too large, it will not be able to be propelled by the air-cooled force or its movement speed will be slow. If the suspension line is shorter, the actual path of the oscillating component to the preset position will be longer.

[0058] To enable the oscillating component to react quickly to the cold air and maintain its trajectory under the thrust of the cold air, the ratio of the mass M of the oscillating component 111 to the length L3 of the suspension line is between 0.001 g / mm and 0.003 g / mm. To further improve measurement accuracy, the preferred ratio range is between 0.0015 g / mm and 0.0025 g / mm. After further verification and optimization, the preferred ratio is 0.002 g / mm.

[0059] Based on multiple comparative experiments, the ratio of the mass M of the oscillating component 111 to the length L3 of the suspension line is between 0.005 g / mm and 0.015 g / mm. Under this parameter setting, the oscillating component can achieve a faster response speed and move quickly to the preset position, thus achieving higher measurement accuracy of the thruster response time. To further improve the measurement accuracy, the preferred ratio of the mass M of the oscillating component 111 to the length L1 of the suspension line is between 0.008 g / mm and 0.012 g / mm. After further optimization, the preferred value is 0.01 g / mm.

[0060] As a preferred solution, in order to enable the swinging component to move quickly to the preset position under the thrust of the cold air, the distance L1 between the swinging component and the preset position is in the range of 0.5mm to 2mm; in order to further shorten the trigger time, the preferred value is in the range of 0.8mm to 1.5mm; after further verification, the preferred value is 1mm.

[0061] As a preferred embodiment, in order to enable the oscillating component to respond quickly to the cold air output by the cold air thruster, while ensuring that the motion trajectory is not difficult to control due to the oscillating component being too light (the oscillating component floats rather than oscillates under the push of the cold air); the mass M of the oscillating component 111 ranges from 0.005g to 0.02g; to further improve the motion characteristics of the oscillating component (rapid response and stable motion trajectory), the preferred value range is 0.008g to 0.015g; after further verification, the preferred value is 0.01g.

[0062] By using the above parameters in combination, the oscillating component can respond quickly to different thrusts F, and the response time of the cold air thruster is much longer than the time it takes for the oscillating component 111 to move to the preset position, thus improving the detection accuracy.

[0063] Optimal values ​​are: M = 0.01g, L1 = 1mm, L2 = 2mm, and L3 = 5mm.

[0064] As a more specific solution, such as Figures 1 to 2 As shown, in the first embodiment of the swing member 111, the force-receiving part 1111 is constructed as a plate-shaped structure parallel to the first plane, and the triggering part 1112 is constructed as a plate-shaped structure parallel to the second plane, wherein the first plane and the second plane are perpendicular to each other.

[0065] Preferably, when the swing member 111 is in free suspension, the projected shape of the swing member 111 on the horizontal plane includes a "T" shaped profile.

[0066] like Figure 4 As shown, in a second embodiment of the oscillating member, the oscillating member 211 is constructed to have a polyhedral structure. One plane of the polyhedron serves as a thrust response surface 211a, and the portion of the polyhedron away from the thrust response surface 211a serves as a trigger structure 2113, which is arranged parallel to the thrust response surface 211a. Preferably, the polyhedral structure can be a hollow structure.

[0067] like Figure 5 As shown, in the third embodiment of the oscillating member, the oscillating member 311 is constructed to have a polyhedral structure, one plane of the polyhedron serving as the thrust reaction surface 311a, and the portion of the polyhedron away from the thrust reaction surface 311a serving as the trigger structure 3113, which is inclined relative to the thrust reaction surface 311a.

[0068] like Figures 1 to 2As shown, as a specific embodiment, the position detection device 130 includes: a detection probe 131 and a field source device (not shown); at least two detection probes 131 are provided, which are spaced a certain distance apart so that the trigger structure 1113 can move between them; the field source device is used to form an energy field between the detection probes 131 that is different from other spaces; specifically, the field source device and the detection probes 131 are electrically connected so that the trigger structure 1113 can move to the point where the field source device forms an energy field through at least one of the detection probes 131, and the position detection device 130 can generate a detection electrical signal according to the change of the energy field.

[0069] like Figures 1 to 2 As shown, more specifically, one detection probe 131 is an infrared emitter 131a, and the other detection probe 131 is an infrared receiver 131b. These two are arranged opposite each other. Under unobstructed conditions, the infrared light emitted by the infrared emitter 131a can be received by the infrared receiver 131b, and the infrared emitter 131a, the infrared receiver 131b, and the swing member 111 are on the same horizontal plane. The thrust reaction surface 111a of the swing member 111 is close to the nozzle of the cold air thruster 150, and the distance between the two is 5 to 20 mm. The other side is close to the propagation path of the infrared light emitted by the infrared emitter 131a. The airflow ejected by the cold air thruster 150 can immediately push the swing member 111 between the infrared emitter 131a and the infrared receiver 131b, blocking the infrared light from being emitted to the infrared receiver 131b.

[0070] like Figures 1 to 2 As shown, in a specific embodiment, the signal processing device 140 includes a digital oscilloscope 141. The digital oscilloscope 141 captures the detection electrical signal and the command electrical signal, and measures the time difference between the command electrical signal and the detection electrical signal used to activate the gas thruster 150 via the time cursor line of the digital oscilloscope 141. This avoids processing analog signals; only high and low level state quantities need to be processed to determine the response time of the gas thruster 150. Changes in signal state are easily extracted, and the measured response time is highly accurate, simple, and easy to implement. The time it takes for the airflow ejected from the gas thruster 150 to reach the thrust reaction surface 111a of the oscillating member 111 can be ignored.

[0071] like Figures 1 to 2As shown, in a preferred embodiment, the signal processing device 140 further includes a signal conditioning device 142. The signal conditioning device 142 provides a compliant electrical signal to the infrared transmitter 131a, and after processing the electrical signal received from the infrared receiver 131b through filtering, noise reduction, and comparison circuits, outputs a detection signal indicating a change in state. The moving oscillating member 111 blocks the infrared light emitted by the infrared transmitter 131a, causing a change in the state of the detection signal output by the signal conditioning device 142, thereby directly reflecting the response time of the air-cooled thruster 150. The signal conditioning device 142 is also connected to a digital oscilloscope 141, and the oscilloscope displays the state-flipping electrical signal output by the signal conditioning device 142. The energy field of the position detection device 130 is a light energy field.

[0072] In the initial detection state, the infrared receiver 131b can normally receive the infrared rays emitted by the infrared transmitter 131a. The infrared receiver 131b converts the received light signal into an electrical signal and outputs a state of 0 through the signal conditioning circuit. When the propellant of the cold gas thruster 150 is ejected, the gas pushes the swing member 111 to move, blocking the infrared rays from entering the infrared receiver 131b. The state of the electrical signal output by the infrared receiver 131b is reversed, and after processing by the signal conditioning device 142, the output state becomes 1. Of course, the way the electrical signal is output can be varied accordingly and is not necessarily limited to the above form.

[0073] like Figure 3 As shown, t1 is the moment when the start command for the cold air thruster 150 is issued, t r For the actual response time of the cold gas thruster, t s t1 is the time when the cold air ejected from the cold air thruster reaches the thrust reaction surface, t2 is the time when the signal conditioning device outputs the detection electrical signal, Δt1 is the time when the airflow ejected from the cold air thruster 150 moves to the swing member 111, and Δt2 is the time when the swing member starts to move to the preset position.

[0074] By measuring the time difference t2-t1 between the activation command of the air-cooled thruster 150 and the state reversal of the signal conditioning device 142, and then subtracting Δt1 and Δt2, the response time of the air-cooled thruster 150 can be obtained, i.e., t2-t1-Δt1-Δt2. Since the airflow velocity emitted by the air-cooled thruster 150 is extremely high, Δt1 is much smaller than t2-t1. Furthermore, because the oscillating component has a small enough mass to move quickly to block infrared light, Δt2 is also much smaller than t2-t1. Therefore, the time difference t2-t1 between the activation command of the air-cooled thruster 150 and the state reversal of the signal conditioning circuit can be used as the response time of the air-cooled thruster 150. Of course, if needed, Δt1 and Δt2 can still be calculated to make the detected response time more accurate.

[0075] As an alternative, the energy field generated by the source device can be an electric field, a magnetic field, or a light field. For example, a Hall element can be installed at the probe, where the energy field is an electric field. Then, the oscillating element can be a magnetic component or partially made of magnetic material, thus triggering the Hall effect and causing the Hall element to generate a corresponding electrical signal. Alternatively, a magnet can be placed at the probe to create a magnetic field, and then a Hall element can be installed at the oscillating element to detect the electrical signal at that point.

[0076] Because the oscillating component 111 needs to operate in a vacuum or highly stable, undisturbed environment, after each test, the oscillating component 111 will still undergo approximately undamped pendulum motion. For example... Figure 3 As shown, as a preferred embodiment, the start-up response time detection system 100 for cold air thrusters in this application also includes a reset device 160. The reset device 160 is used to quickly stop the movement of the swinging component and reset it to its initial position (i.e., the position of the swinging component when the suspension line is in a vertical state) after one detection is completed, so as to facilitate the continuity of the next measurement.

[0077] like Figure 3 As shown, in a specific embodiment, the reset device 160 includes an electrostatic chuck 161, an electrostatic controller (not shown), and a pushing device 162. The electrostatic chuck 161 is connected to the output shaft of the pushing device 162 to operate under the drive of the pushing device 162. Specifically, the pushing device is an electric push rod. The electrostatic controller converts DC voltage into high-voltage static electricity through voltage boosting and multiplication, thereby forming an electrostatic magnetic field on the surface of the electrostatic chuck 161. Specifically, there are two sets of electrostatic chuck 161 and pushing device 162, which are respectively arranged on both sides of the air compressor.

[0078] With this approach, after the swinging component completes one test, the control push device 162 pushes the electrostatic chuck 161 to a position close to the initial position of the swinging component. When the swinging component swings back to the initial position, the electrostatic chuck 161 can attract the swinging component, thus quickly braking the swinging component. After the swinging component stabilizes, the electrostatic chuck is de-energized and moves away from the swinging component. At this time, the swinging component is stationary at the initial position, thus quickly preparing for the next measurement.

[0079] All of the above solutions can be applied to the detection methods performed by the detection system.

[0080] In summary, after practical testing with various micro-Newton level cold gas thrusters, the above scheme can test whether cold gas thrusters with a response time design range of 25ms to 500ms can meet the design requirements.

[0081] The above description is merely a selection of preferred embodiments of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in the embodiments of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described inventive concept. For example, technical solutions formed by substituting the above-described features with (but not limited to) technical features with similar functions disclosed in the embodiments of this disclosure.

Claims

1. A start-up response time detection system suitable for cold gas thrusters, characterized in that: The start-up response time detection system for cold gas thrusters includes: A thrust reaction device is used to provide a thrust reaction surface located in the thrust output path of a cold gas thruster; A motion limiting device for limiting the trajectory of the thrust response device when it is driven by the thrust of the cold gas thruster; A position detection device is used to generate and / or output a detectable electrical signal when the thrust reaction device is driven to a preset position by the cold gas thruster. The signal processing device is used to calculate and / or output the start-up response time of the cold gas thruster based on the time difference between the detection electrical signal and the command electrical signal for starting the cold gas thruster; The thrust response device and the motion limiting device are physically connected; the position detection device and the signal processing device are electrically connected. The thrust reaction device includes: The oscillating element is configured to have a plane as the thrust response surface; The motion limiting device includes: The suspension line is used to suspend the swinging component freely under the action of gravity; Wherein, one end of the suspension line is connected to the oscillating member so that the thrust reaction surface of the oscillating member is perpendicular to the thrust output path; The motion restriction device also includes: The suspension bracket includes a horizontally extending suspension arm; The other end of the suspension line is connected to the middle section of the suspension arm.

2. The start-up response time detection system for cold gas thrusters according to claim 1, characterized in that: The oscillating element is configured to have: The force-bearing part is used to form the thrust reaction surface; The triggering part is used to form a triggering structure for triggering the position detection device; The center of gravity of the swinging member is located between the force-receiving part and the triggering part.

3. The start-up response time detection system for cold gas thrusters according to claim 2, characterized in that: When the swinging member is in a free suspension state, the extension of the suspension line passes through the center of gravity of the swinging member.

4. The start-up response time detection system for cold gas thrusters according to claim 3, characterized in that: The force-bearing part is constructed as a plate-like structure parallel to the first plane, and the triggering part is constructed as a plate-like structure parallel to the second plane.

5. The start-up response time detection system for cold gas thrusters according to claim 4, characterized in that: When the swinging member is in a free suspension, the projected shape of the swinging member on the horizontal plane includes a "T" shaped outline.

6. The start-up response time detection system for cold gas thrusters according to claim 3, characterized in that: The oscillating element is constructed to have a polyhedral structure, with one plane of the polyhedron serving as the thrust response surface, and the portion of the polyhedron away from the plane serving as the triggering structure.

7. The start-up response time detection system for cold gas thrusters according to claim 1, characterized in that: The position detection device includes: At least two detection probes are spaced apart so that at least a portion of the thrust response device can move between them; A field source device is used to create an energy field between the detection probes that is different from other spaces; The field source device and the detection probe are electrically connected so that at least a part of the thrust response device can move to a position where the position detection device can generate the detection electrical signal according to the change of the energy field when the field source device forms an energy field through at least one of the detection probes.

8. The start-up response time detection system for cold gas thrusters according to claim 7, characterized in that: The energy fields generated by the field source device are electric fields, magnetic fields, and light energy fields.

9. A method for detecting the start-up response time of a cold gas thruster, characterized in that, The start-up response time detection system for cold gas thrusters as described in any one of claims 1 to 8 is adopted.

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