Quick-release mounting bracket for GNSS occultation sounding payload of micro-nano satellite

Abstract

The application relates to a GNSS occultation detection payload quick detachable mounting bracket for micro-nano satellites, and belongs to the technical field of spacecraft structures and mechanisms, which comprises a base provided with a V-shaped groove and a limiting boss, the rear end of the base is provided with an elastic compression arm, the two sides and the front end of the base are provided with self-locking buckles, the V-shaped groove is used for bidirectional positioning of a load in Y and Z directions, the limiting boss and the self-locking buckle located at the front end of the base are used for X direction positioning of the load, the self-locking buckles on the two sides of the base compress the elastic compression arm, and Z direction positioning of the load is realized, and the self-locking buckles adopt a pressing type structure, and locking and unlocking switching is provided for the load. The application is a tool-free quick detachable bracket of a pure mechanical structure, through tool-free quick detachable mounting, the problems of low assembly efficiency, easy damage of the structure, thermal stress concentration, and excess risk in the prior art are solved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of spacecraft structure and mechanism, and particularly relates to a mechanical support device for rapid installation, positioning and locking of a GNSS occultation detection payload of a micro-nano satellite. BACKGROUND

[0002] The miniaturized GNSS occultation detection payload has the characteristics of light weight (about 1-3 kg) and small size, but traditional satellite payload installation adopts threaded fastener connection, and the following problems exist:

[0003] 1. Special tools are required for installation and disassembly, and the operation is cumbersome, affecting the satellite assembly efficiency;

[0004] 2. Frequent disassembly and assembly can cause damage to the threads, and is not suitable for rapid iteration of commercial satellite mass production;

[0005] 3. Thermal stress is concentrated, which is not conducive to the dimensional stability of the payload in the on-orbit temperature environment;

[0006] 4. Excess material is easily generated during disassembly and assembly, affecting the reliability of the satellite.

[0007] A tool-free quick disassembly support of a purely mechanical structure is urgently needed. SUMMARY

[0008] To solve the problems in the background art, the application provides a quick disassembly installation support for a GNSS occultation detection payload of a micro-nano satellite, which solves the problems of low assembly efficiency, easy damage to the structure, thermal stress concentration and excess material risk in the prior art through tool-free quick disassembly.

[0009] To solve the above technical problems, the application adopts the following technical scheme: a base, an elastic compression arm, a positioning pin and a self-locking buckle,

[0010] The base includes a V-shaped groove and a limiting boss, the V-shaped groove is arranged on the top surface of the base along the X-axis in parallel, and is used for providing Y and Z direction positioning for the payload, the base is fixed on the satellite cabin plate and is used for bearing the payload, and the limiting boss is arranged at the rear end of the base and is used for X direction positioning of the payload;

[0011] The elastic compression arm is integrally formed with the base and is arranged at the rear end of the base, is aligned with the center of the V-shaped groove, and is stretched out along the X-axis in the arm length direction to provide Z direction elastic compression force, and the end is provided with a compression head;

[0012] The self-locking buckles are arranged on the side surface and the front end of the base respectively, the side surface self-locking buckle is located on the side of the elastic pressing arm, and the side surface self-locking buckle is used for positioning the load in the Z direction; the locking tongue center of the front end self-locking buckle is aligned with the end slot of the elastic pressing arm, and the front end self-locking buckle is used for providing locking and unlocking switching; the front end self-locking buckle is used for positioning the load in the X direction, and the front end self-locking buckle is used for providing locking and unlocking switching.

[0013] The positioning pin is arranged on the bottom surface of the load and is in contact with the inclined surface of the V-shaped groove, so that automatic centering is realized, and the load is positioned in the Y direction.

[0014] The load is embedded in the V-shaped groove through the positioning pin to realize automatic centering, the elastic pressing arm elastically presses the top surface of the load downward, the locking tongue of the self-locking buckle located on the side surface of the base is clamped into the end slot of the elastic pressing arm to form locking, and the locking tongue of the self-locking buckle located on the front end of the base is clamped on the end surface of the load to form locking, so that the load is quickly disassembled without tools.

[0015] Further, the V-shaped groove is two grooves that are parallel to each other and have an included angle of 90°, and the groove bottom is provided with a chip removal chamfer, and the surface roughness of the groove is Ra≤0.8 μm.

[0016] Further, the elastic pressing arm is a cantilever beam structure and is integrally milled and formed with the base, and the pressing head is bonded with a silica rubber pad at the contact position of the pressing head and the load.

[0017] Further, the self-locking buckle adopts a pressing structure, the locking tongue stroke is 3-5 mm, the pressing force is 15-20 N, and the self-locking buckle is fixed on the side surface and the front end of the base through a T-shaped nut or a screw.

[0018] Further, the positioning pin is a cylindrical pin, protrudes from the bottom surface of the load, and is in double-line contact with the V-shaped groove, and the cooperation gap is 0.02-0.05 mm.

[0019] Further, a suspension gap of 1.0±0.2 mm is reserved between the bottom surface of the load and the top surface of the base, and the positioning pin bears the suspension gap.

[0020] Further, the base is a hollow aluminum alloy frame structure, and the overall weight of the base is not more than 100 g, and the base accounts for 3%-5% of the total weight of the load.

[0021] Further, the elastic pressing force provided by the elastic pressing arm is 5-10 N, and the elastic pressing force can compensate for thermal deformation of 0.1-0.3 mm in a temperature range of-40°C to +80°C.

[0022] Further, the bottom surface of the base is provided with a threaded hole or a flange interface connected with a satellite platform, and the base is suitable for a 1-5 kg micro-nano satellite GNSS occultation detection load.

[0023] Further, the base includes the following steps:

[0024] 1) Align the locating pin of the load bottom surface and slide into the V-shaped groove of the base, the self-locking buckle on the front end of the base is pressed during sliding;

[0025] 2) When the front end surface of the load is in contact with the limiting boss on the base, the locking tongue of the self-locking buckle on the front end of the base automatically pops out and clamps the rear end surface of the load, realizing X-axis positioning;

[0026] 3) Manually press the elastic compression arm so that the end head contacts the top surface of the load;

[0027] 4) Continue to press until the clamping groove at the end of the elastic compression arm is aligned with the locking tongue of the self-locking buckle on the side of the base, and the locking tongue automatically pops out to lock, completing the installation;

[0028] 5) When disassembling, first press the self-locking buckle button on the side of the base, the locking tongue retracts, and the elastic compression arm automatically pops open, then press the self-locking buckle button on the front end of the base, the locking tongue retracts, and slide out of the load along the V-shaped groove.

[0029] Compared with the prior art, the application has the advantages and beneficial effects as follows.

[0030] 1. The present application adopts "sliding-in, pressing-down and self-locking" three-step tool-free operation, the installation time is less than 2 minutes, the disassembly time is less than 30 seconds, and according to the calculation of 50 satellites per year and 4 loads per satellite, more than 1000 hours of assembly time is saved per year, the labor cost is directly reduced by more than 800,000 yuan, and it perfectly matches the production mode of "small satellites, fast response and batch production" of commercial aerospace.

[0031] 2. The present application adopts cantilever beam elastic compression arm and base integrated design, utilizes material elastic deformation energy storage, cooperates with pressing type self-locking buckle to realize locking, and verifies 3000 times of vibration cycles and 100 times of thermal shock, the fatigue life is more than 100 times of disassembly and assembly, the locking force attenuation is less than 5%, which fundamentally solves the industry pain point of easy damage of screw thread, and is especially suitable for the demand of repeated testing and verification on the ground.

[0032] 3. The present application allows the load to slightly slide along the V-shaped groove (Δ≈0.1mm) when thermal expansion through 1mm suspension gap+V-shaped groove inclined surface sliding+elastic arm compensation three mechanisms, the elastic arm automatically absorbs the deformation amount, the thermal stress is reduced by 90% (<5MPa), and the phase center stability and measurement accuracy of GNSS detection load under extreme temperature are ensured.

[0033] 4. The present application integrates functions in the one-piece hollow base+standard self-locking buckle, reduces the number of parts, the weight is less than 100g, the weight is reduced by 40%, the weight ratio to the load is reduced from 10% to 3%, which is of great significance to the precious kilogram-level budget of micro-nano satellites, at the same time, the simplified structure reduces the cost of single set of machining, meets the low-cost batch production demand of commercial aerospace.

[0034] 5. The non-rotating friction pair of the application completely avoids the generation of debris, and the locking tongue of the press self-locking buckle and the pressure arm clamping groove are in surface contact and self-locking, which is verified by 8.8g random vibration test to be free of micron-level looseness, meets the reliability requirements of "zero maintenance" during the 10-year life of the spacecraft, and passes the vibration and impact test certification of the national military standard GJB1027A-2012. BRIEF DESCRIPTION OF DRAWINGS

[0035] The accompanying drawings, which form a part of the present application, are intended to provide further understanding of the present application, and are used to explain the illustrative embodiments of the present application and their descriptions, and do not constitute improper limitations on the present application. In the drawings:

[0036] Figure 1 The connection schematic diagram of the quick-release mounting bracket for the GNSS occultation detection payload of the micro-nano satellite according to the present application;

[0037] Figure 2 The M view of the present application; Figure 1

[0038] Figure 3 The structure schematic diagram of the base and the elastic compression arm of the present application;

[0039] Figure 4 The local enlarged view of the V-shaped groove of the present application;

[0040] Figure 5 The enlarged view of part A of the present application; Figure 3

[0041] Explanation of reference signs:

[0042] 1, base; 11, V-shaped groove; 12, threaded hole; 13, limiting boss; 2, elastic compression arm; 21, pressure head; 22, silicone rubber pad; 23, first clamping groove; 24, second clamping groove; 3, first self-locking buckle; 31, first locking tongue; 32, first button; 6, second self-locking buckle; 61, second locking tongue; 62, second button; 63, first bracket; 7, third self-locking buckle; 71, third locking tongue; 72, third button; 73, second bracket; 4, positioning pin; 5, payload. DETAILED DESCRIPTION

[0043] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0044] ​​In the description of the present application, it should be understood that the orientation or positional relationship indicated by the technical terms "parallel", "top surface", "thickness", "front end", "rear end", "center", "side surface", "below", "end", "bottom surface", "two sides", "bevel", "downward" and the like is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. The terms "include" or "contain" and the like mean that the elements appearing before the word mean to cover the elements listed after the word and their equivalents, without excluding other elements.

[0045] The accompanying drawings are referred to in the following description of the present application. Figure 1 The specific embodiments of the present application are described in detail.

[0046] The present application is a GNSS occultation detection payload quick-release mounting bracket for micro-nano satellites, which comprises a base 1, a V-shaped groove 11, a threaded hole 12, a limiting boss 13, an elastic compression arm 2, a pressure head 21, a silicone rubber pad 22, a first clamping groove 23, a second clamping groove 24, a first self-locking buckle 3, a first locking tongue 31, a first button 32, a second self-locking buckle 6, a second locking tongue 61, a second button 62, a first bracket 63, a third self-locking buckle 7, a third locking tongue 71, a third button 72, a second bracket 73, a positioning pin 4 and a payload 5.

[0047] The base 1 is mounted on the satellite platform, the payload 5 is slid into the V-shaped groove 11 for Y-direction and Z-direction positioning, the limiting boss 13 and the first self-locking buckle 3 are used for X-direction positioning of the payload 5, and the second self-locking buckle 6 and the third self-locking buckle 7 are used for locking the elastic compression arm 2 to position the payload 5 in the Z-direction.

[0048] Preferably, the V-shaped groove 11 is two grooves parallel to each other at an angle of 90°, the groove bottom is provided with a chip removal chamfer, and the groove surface roughness Ra is ≤0.8 μm, which realizes automatic centering, eliminates over-constraint, homogenizes errors, and has strong universality.

[0049] The chip removal chamfer prevents interference, making the assembly smooth, and the groove surface roughness Ra≤0.8 μm reduces the friction coefficient and improves the positioning stability.

[0050] Preferably, the elastic compression arm 2 is a cantilever beam structure and is integrally milled and formed with the base 1, the pressure head 21 is bonded with the silicone rubber pad 22 at the contact position of the payload 5, no additional spring parts are needed, the compression force is stable and controllable, assembly errors are eliminated, the structural rigidity is doubled, and the silicone rubber pad 22 bonded at the contact position of the pressure head 21 protects the surface of the payload 5.

[0051] Preferably, the self-locking buckle adopts a press type structure, the locking tongue stroke is 3-5 mm, the pressing force is 15-20 N, and the T-shaped nut or screw is fixed to the side surface and the front end of the base 1.

[0052] The lock tongue stroke of 3-5 mm is the optimal interval for the aerospace quick connection mechanism. A stroke that is too short (<2 mm) can easily lead to insufficient locking, and under 14.1 grms random vibration, it can easily be loosened. A stroke that is too long (>8 mm) increases the operation time.

[0053] After being enlarged by the lever mechanism, the 15-20 N pressing force generates a 30-40 N locking force at the end of the lock tongue, which perfectly matches the 30 N springback force of the elastic compression arm 2. At this time, the lock is in a "self-locking critical state" - the static friction force (μ=0.15) can resist 4-6 N dynamic shear force under vibration, and only the spring force needs to be overcome to unlock under manual pressing, realizing the ideal characteristics of "self-locking during work and easy disassembly during maintenance".

[0054] Preferably, the positioning pin 4 is a cylindrical pin, the bottom surface of the convex load 5 forms a double-line contact with the V-shaped groove 11, the matching gap is 0.02-0.05 mm, the lower limit of the gap is 0.02 mm, which ensures that it can be easily slid in under a 15 N pushing force (friction force is about 3 N), avoiding jamming, while limiting the inclination angle of the load 5 to be <0.05°, ensuring the normal accuracy of the GNSS antenna, and the upper limit of the gap is 0.05 mm, under 14.1 grms random vibration, the maximum sliding amount of the load 5 is less than the gap value, and it will not collide with the groove wall of the V-shaped groove 11, avoiding micro-discharge or abrasive contamination.

[0055] Preferably, a suspension gap of 1.0±0.2 mm is reserved between the bottom surface of the load 5 and the top surface of the base 1, which is borne by the positioning pin 4, eliminating the mismatch stress of thermal expansion, and the positioning pin 4 becomes the only heat conduction path. The slender ratio of the pin causes it to produce a slight bending under thermal deformation rather than rigid shearing, further reducing the thermal stress by 70%. This design is similar to the hinge of a satellite solar cell panel, realizing "rigid positioning and flexible thermal decoupling".

[0056] 1.0±0.2 mm gap allows the following errors without affecting the function:

[0057] Positioning pin 4 height tolerance ±0.05 mm

[0058] Elastic compression arm 2 height tolerance ±0.1 mm

[0059] Silicone rubber pad 22 compression amount variation ±0.3 mm

[0060] The total assembly tolerance is ±0.45 mm, the assembly qualification rate is improved from 90% to 99.5%, avoiding expensive repair costs.

[0061] Preferably, the base 1 is a hollow aluminum alloy frame structure, the overall weight is not more than 100g, accounting for 3%-5% of the total weight of the load 5, reducing the transportation cost, the hollow design can accurately adjust the mass distribution, so that the centroid of the support deviates from the center of the V-shaped groove 11 by <0.5mm, when the satellite attitude is maneuvered (0.5° / s), the inertia moment is <0.01N·m, which does not affect the satellite attitude control accuracy.

[0062] Preferably, the elastic compression arm 2 provides an elastic compression force of 5-10N, which can compensate for thermal deformation of 0.1-0.3mm in the temperature range of -40°C to +80°C;

[0063] The shell of the GNSS occultation load 5 is mostly magnesium alloy (MB8) or carbon fiber composite material, with a wall thickness of only 2.0-2.5mm, and a traditional compression force of 30-50N will cause stress concentration σ=150-250MPa on the contact surface, close to the yield strength of magnesium alloy (83MPa) or the interlaminar shear strength of carbon fiber (50MPa), which is easy to cause micro-cracks, and the 5-10N stress is only 25-50MPa, the shell deformation is <0.01mm, ensuring that the internal GNSS receiver antenna, crystal oscillator and other precision components are not affected by external force;

[0064] Excessive compression force will change the dynamic characteristics of the PCB board of the load 5, causing frequency deviation and phase noise deterioration of the crystal oscillator, and the additional stiffness of 5-10N to the PCB board is <5%, the actual measured GNSS L1 frequency band phase noise deterioration is <0.1dB, and the occultation data signal-to-noise ratio (SNR) remains above 42dB, meeting the EUMETSAT standard;

[0065] The 0.1-0.3mm compensation range covers 99.7% of the working conditions, and the design redundancy is sufficient, which can not only compensate for the expansion at high temperature (the gap increases from 1.0mm to 1.14mm), but also compensate for the contraction at low temperature (to 0.86mm), and the elastic stroke of the cantilever beam is 5-8mm, of which 0.1-0.3mm is used for thermal compensation, and the remaining is used for assembly tolerance, the function is reasonably divided, and overdesign is avoided;

[0066] In the range of -40°C~+80°C, the compression force is stable at 6.2-9.8N, ensuring constant connection stiffness.

[0067] Preferably, the base 1 bottom surface is provided with a threaded hole or flange interface connected with the satellite platform, suitable for 1-5 kg level micro-nano satellite GNSS occultation detection payload, the threaded hole has universality, more preferably M5 or M4 standard threaded hole (4-6, evenly distributed on the four corners of the base), hole distance conforms to CubeSat standard (such as P-POD 3U / 6U deployer) or domestic micro-nano satellite platform general specification (such as Q / W 1065-2018), can be directly installed on the satellite adapter of Blue Origin Zhuque-2, Xinghe Power Valley Shenxing-1 rocket, without repeated design of adapter plate, single satellite development cycle is shortened by 2-3 weeks.

[0068] The flange interface can be quickly switched for the ultra-small load 5 of 1-1.5 kg, and the base 1 bottom surface can be pre-installed with an ISO 9409-1 flange interface (Φ31.5mm or Φ50mm), which can be mechanically / electrically integrated with the satellite platform within 10 seconds. Compared with the traditional distributed interface (mechanical+electrical connector independent), the assembly time is compressed from 4 hours to 15 minutes.

[0069] The GNSS occultation detection payload quick-release mounting bracket for micro-nano satellites includes the following contents:

[0070] The load weighs 2.3 kg, the outer dimensions are 180mm×120mm×80mm, and the satellite platform is a micro-nano satellite with an installation surface size of 200mm×150mm.

[0071] 1) Structure of the base 1:

[0072] Material: 6061-T6 aluminum alloy, size 300mm×150mm×25mm (length×width×height);

[0073] Processing technology: overall milling, V-shaped groove 11 surface roughness Ra≤1.6μm;

[0074] V-shaped groove 11 (2): included angle 90°, groove depth 4mm, length 180mm, center distance of two grooves 100mm;

[0075] Hollow structure: 6×8 array of φ10mm weight reduction holes, with 5mm wide edge reinforcing ribs;

[0076] Four M5 threaded holes 12 on each corner, the M5 threaded hole 12 is a through hole for connecting with the satellite platform;

[0077] Limiting boss 13: a 3mm×3mm×3mm (length×width×height) limiting boss 13 is arranged at the center position of the two grooves on the upper surface of the base 1, and the inner side surface of the limiting boss 13 is 90mm away from the front end surface of the base 1.

[0078] 2) Structure of the elastic compression arm 2:

[0079] Located at the rear end of the base 1, it is integrally milled with the base 1, and the material is 6061-T6 aluminum alloy;

[0080] Size: pressure head 21 long 105mm, arm width 130mm, arm thickness 3.0mm (key control size);

[0081] The pressure head 21 is arranged at the end of the elastic pressing arm 2, and a 0.5mm thick silicone rubber pad 22 is bonded at the contact load;

[0082] The first clamping groove 23 and the second clamping groove 24 are respectively located on both sides of the elastic pressing arm 2, and are respectively a rectangular groove with a depth of 1.8mm and a width of 4mm milled downward from the top surface of the elastic pressing arm 2, located directly above the center of the load 5, and the gap between the locking tongue is 0.1mm;

[0083] 3) Structure of self-locking buckle:

[0084] The first self-locking buckle 3, the second self-locking buckle 6 and the third self-locking buckle 7 are all selected from EVAN-Yiwen, model EV0602-0006295;

[0085] Installation: the second self-locking buckle 6 is fixed on the first bracket 63 on the side of the base 1 by M3 screws, and the first bracket 63 is fixed on the side of the base 1 by M5 screws, and the center of the second locking tongue 61 is 82mm away from the top surface of the base 1;

[0086] The third self-locking buckle 7 is fixed on the second bracket 73 on the side of the base 1 by M3 screws, and the second bracket 73 is fixed on the side of the base 1 by M5 screws, and the center of the third locking tongue 71 is 82mm away from the top surface of the base 1;

[0087] The first self-locking buckle 3 is fixed on the front end face of the base 1 by M3 screws, and the first locking tongue 31 is flush with the rear end face of the load 5.

[0088] Service life: nominal 30,000 times of pressing, actual test >5000 times without failure.

[0089] 4) Structure of positioning pin 4:

[0090] Specification: GB / T 119.1 standard cylindrical pin, φ5m6, length 8mm, quantity 4;

[0091] Installation: interference fit into the bottom surface of the load 5, distributed at the four corners of the load 5, matched with the center of the V-shaped groove of the base 1, and the protruding height is 3mm (strictly controlled);

[0092] Material: stainless steel 9Cr18, surface DLC coating (hardness >2000HV).

[0093] 5) Installation steps:

[0094] Step 1: Pre-positioning (15 seconds)

[0095] Align the load 5 bottom surface locating pin 4 with the base 1 V-shaped groove 11 entrance, press the first locking tongue 31 under the load 5 bottom surface, slide horizontally in the +X direction until the load 5 front end surface touches the base 1 limiting boss 13, while the first locking tongue 31 automatically pops out and stops against the load 5 rear end surface, limiting the load 5 movement in the X-axis direction;

[0096] Verification: The load 5 should slide smoothly without jamming, and the gap between the V-shaped groove 11 and the locating pin 4 should be 0.03-0.05mm checked with a feeler gauge.

[0097] Step 2: Elastic compression (30 seconds)

[0098] Press the elastic compression arm 2 end head 21 with the thumb, apply about 15N downward pressure, and the compression arm will deform elastically by 3.2mm;

[0099] Key control: Compress to the first card slot 23 flush with the second self-locking buckle 6 second locking tongue 61 on the side of the base 1, and the second card slot 24 flush with the third self-locking buckle 7 third locking tongue 71 on the side of the base 1.

[0100] Step 3: Automatic locking (5 seconds)

[0101] Continue to press down 2mm, the second locking tongue 61 pops out under the action of the spring and is clamped into the first card slot 23, and the third locking tongue 71 pops out under the action of the spring and is clamped into the second card slot 24;

[0102] Release the thumb, the elastic compression arm 2 remains deformed due to the combined constraint of the second locking tongue 61 and the third locking tongue 71, and continues to apply 7N elastic pressure to the top surface of the load 5;

[0103] Verification: Gently push the load 5 with your hand, there is no looseness, and the horizontal anti-slip force measured by the push-pull force gauge is >50N.

[0104] Step 4: State check (10 seconds)

[0105] Visual inspection: The gap between the load 5 bottom surface and the base 1 top surface is 1.0±0.1mm (pass with a 1mm feeler gauge);

[0106] Light transmission inspection: The locating pin 4 and the V-shaped groove 11 slope are seamlessly transparent (proving good contact);

[0107] Mark: Apply yellow marking paint to the side of the elastic compression arm 2 to indicate that it has been installed in place;

[0108] Total time: 60 seconds (excluding load electrical measurement), 97% shorter than traditional threaded connection.

[0109] Step 5: Disassembly (20 seconds)

[0110] When disassembling, press the second button 62 of the second self-locking buckle 6 and the third button 72 of the third self-locking buckle 7 on the side of the base 1 first, the second locking tongue 61 and the third locking tongue 71 retract, the elastic compression arm 2 automatically pops open, and then press the first button 32 of the first self-locking buckle 3 on the front end of the base 1, the first locking tongue 31 retracts, and slides out the load 5 along the V-shaped groove 11.

[0111] The above only describes one embodiment of the present application in detail, but the content is only the preferred embodiment of the present application, and cannot be considered as limiting the scope of the present application. Any equivalent changes and improvements made according to the scope of the present application should still belong to the patent scope of the present application.

Claims

1. A quick-release mounting bracket for GNSS occultation payload on micro-nano satellites, characterized in that: The base, the elastic compression arm, the positioning pin and the self-locking buckle, The base includes a V-shaped groove and a limiting boss, the V-shaped groove is arranged on the top surface of the base along the X-axis in parallel, and is used for providing Y and Z direction positioning for the load, the base is fixed on the satellite cabin plate and is used for bearing the load, and the limiting boss is arranged on the rear end of the base and is used for X direction positioning of the load. The elastic compression arm is integrally formed with the base, is arranged at the rear end of the base, is aligned with the center of the V-shaped groove, and is extended along the X-axis in the arm length direction to provide Z direction elastic compression force, and the end is provided with a pressing head. The self-locking buckle is arranged on the side surface and the front end of the base respectively, the side surface self-locking buckle is located on the side of the elastic compression arm, provides Z direction positioning for the load, the center of the lock tongue is aligned with the end slot of the elastic compression arm, and locking and unlocking switching is provided, and the front end self-locking buckle provides X axis direction positioning for the load and provides locking and unlocking switching. The positioning pin is arranged on the bottom surface of the load and is in contact with the inclined surface of the V-shaped groove to realize automatic centering and Y direction positioning of the load. The load is embedded in the V-shaped groove through the positioning pin to realize automatic centering, the elastic compression arm elastically compresses the top surface of the load downwards, the lock tongue of the self-locking buckle located on the side surface of the base is clamped into the end slot of the elastic compression arm to form locking, the lock tongue of the self-locking buckle located on the front end of the base is clamped on the end surface of the load to form locking, and tool-free quick disassembly and assembly of the load are realized.

2. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The V-shaped groove is two grooves with an included angle of 90 degrees, the groove bottom is provided with a chip removal chamfer, and the groove surface roughness is Ra≤0.8 μm.

3. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The elastic compression arm is a cantilever beam structure and is integrally milled with the base, and the pressing head is bonded with a silicone rubber pad at the contact position of the load.

4. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The self-locking buckle adopts a pressing structure, the lock tongue stroke is 3-5 mm, the pressing force is 15-20 N, and the T-shaped nut or screw is fixed on the side surface and the front end of the base.

5. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The positioning pin is a cylindrical pin, protrudes from the bottom surface of the load, and forms a double-line contact with the V-shaped groove, and the cooperation gap is 0.02-0.05 mm.

6. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The suspension gap between the bottom surface of the load and the top surface of the base is 1.0±0.2 mm, and is borne by the positioning pin.

7. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The base is a hollow aluminum alloy frame structure, the overall weight is not more than 100 g, and the weight accounts for 3%-5% of the total weight of the load.

8. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The elastic compression force provided by the elastic compression arm is 5-10 N, and the thermal deformation in the temperature range of-40°C to +80°C is compensated by 0.1-0.3 mm.

9. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The bottom surface of the base is provided with a threaded hole or a flange interface connected with the satellite platform, and is suitable for 1-5 kg level micro-nano satellite GNSS occultation detection load.

10. The quick-release mounting bracket for GNSS occultation payload of micro-nano satellites according to claim 1, characterized in that: The installation steps include: 1) The positioning pin on the bottom surface of the load is aligned and slid into the V-shaped groove of the base, and the self-locking buckle on the front end of the base is pressed on the bottom surface of the load during the sliding process; 2) When the front end surface of the load is attached to the limiting boss on the base, the lock tongue of the self-locking buckle on the front end of the base automatically pops out and clamps the rear end surface of the load to realize X axis direction positioning; 3) The elastic compression arm is manually pressed so that the end pressing head contacts the top surface of the load; 4) Continue to press until the end slot of the elastic compression arm is aligned with the lock tongue of the self-locking buckle on the side surface of the base, the lock tongue automatically pops out to lock, and the installation is completed. 5) When disassembling, first press the self-locking button on the side of the base, the lock tongue retracts, the elastic compression arm automatically opens, then press the self-locking button on the front end of the base, the lock tongue retracts, and slide out the load along the V-shaped groove.

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