A flat-plate satellite based on high-stiffness constant-torque spring hinge

Abstract

The present invention provides a flat-plate satellite based on a high-rigidity constant-torque spring hinge, comprising a satellite body, a solar cell body-mounted subarray connected to the sky side of the satellite body, constant-torque spring hinges respectively connected to both sides of the solar cell body-mounted subarray, and solar cell deployment subarrays respectively connected to the other end of the constant-torque spring hinge, the number of solar cell deployment subarrays is at least two, and both the solar cell body-mounted subarray and the solar cell deployment subarray are plate-shaped structures. In the present invention, the solar wing and the antenna use constant-torque springs to provide the required energy, and under the condition that the static moment margin of the deployment remains unchanged, the energy required for deployment is lower, the speed at the end of the deployment is smaller, and the impact force at the end of the deployment is lower. At the same time, the hinge is locked with a stainless steel leaf spring after deployment, and the hinge locking stiffness can be increased by increasing the number of leaf springs. The deployment angle of the hinge can be accurately adjusted by a positioning bolt to ensure the hinge deployment accuracy requirements and reduce the impact.

Description

Technical Field

[0001] The invention relates to the technical field of satellites, and in particular to a flat-plate satellite based on a high-rigidity constant-torque spring hinge. Background Art

[0002] A hinge mechanism is usually used to unfold, lock or maintain the shape of the satellite's solar panels and antennas. The unfolding accuracy and driving force release of the hinge mechanism determine whether the satellite can ultimately reach the required working state or working position.

[0003] The most commonly used is the passive deployment hinge. The hinge designed for cubic satellites uses screws and mounting flanges to directly connect with the satellite and solar wing. The mechanical interface is simple, and the hinge has the functions of deployment locking and deployment indication. For solar wings with a large installation size span, lock hook and wedge hinges are often used. The hinge uses a joint bearing to compensate for the coaxiality error. For hinges for phased array antennas, each antenna forms a complete surface after deployment, and the surface accuracy requirements are high. The hinge bears heavy loads and has a large size span. The coaxiality, axis direction accuracy, and hinge assembly accuracy are all high, and it needs to have high strength and rigidity.

[0004] The hinge drive is usually driven by a torsion spring / volute spring. In order to ensure sufficient static margin, the design generally has a large driving force in the folded state. The driving force is released during the deployment process, driving the deployment components to accelerate the deployment. The deployment end will have an impact on the fixed components. Excessive impact may even cause structural parts to break. In order to prevent excessive impact at the end of deployment, additional dampers are usually added to slowly release the driving force during the entire deployment process, but this will increase the weight of the mechanism and the development cost.

[0005] Therefore, there is a need for a hinge that can ensure the deployment accuracy of satellite solar wings and antennas and reduce impact. Summary of the invention

[0006] The present invention aims to solve the problems of satellite solar wing and antenna deployment accuracy and impact, and provides a flat-plate satellite based on high-rigidity constant torque spring hinges. The solar wing and the antenna use constant torque springs to provide the required energy. Under the condition that the deployment static moment margin remains unchanged, the energy required for deployment is lower, the deployment end speed is smaller, and the deployment end impact force is lower. At the same time, the hinge is locked with a stainless steel leaf spring after deployment. The hinge locking stiffness can be increased by increasing the number of leaf springs. The deployment angle of the hinge can be accurately adjusted by positioning bolts to ensure the hinge deployment accuracy requirements and reduce impact.

[0007] The present invention provides a flat-plate satellite based on a high-rigidity constant-torque spring hinge, comprising a satellite body, a solar cell body-mounted sub-array connected to the sky side of the satellite body, constant-torque spring hinges respectively connected to both sides of the solar cell body-mounted sub-array, and solar cell deployment sub-arrays respectively connected to the other ends of the constant-torque spring hinges, the number of solar cell deployment sub-arrays is at least two, and both the solar cell body-mounted sub-array and the solar cell deployment sub-array are plate-shaped structures;

[0008] In the emission state, the unfolded sub-arrays of the solar cells are respectively folded up and pressed tightly on the sub-arrays of the solar cell body at the same side;

[0009] When in orbit, the solar cell deployment sub-array is driven by the constant torque spring hinge to be deployed around both sides of the solar cell body sub-array and to form a coplanar surface with the solar cell deployment sub-array;

[0010] The constant torque spring hinge comprises a fixed hinge connected to the edge of one side of the solar cell body sub-array, a movable hinge connected to the edge of one side of the solar cell unfolded sub-array, an axis system component that movably connects the fixed hinge and the movable hinge, a driving component that is partially fixedly connected to the movable hinge and partially extends into the fixed hinge and can drive the movable hinge to rotate along the axis system component, and an unfolding locking leaf spring connected to both sides of the fixed hinge;

[0011] The driving assembly includes a constant force spring with one end extending into the fixed hinge and the other end fixedly connected to the movable hinge, a limiting shaft sleeve connected to the fixed hinge and one end of the constant force spring, and a limiting shaft with a clearance fit in the limiting shaft sleeve. One end of the constant force spring fixedly connected to the movable hinge is a plane, and the side connected to the limiting shaft sleeve is bent downward, and the middle is an arc surface. The limiting shaft sleeve and the limiting shaft are both located at the corner where the constant force spring is bent.

[0012] When in the launching state, the constant force spring is compressed and fixed; when in the on-orbit state, the constant force spring is released, and is unfolded along the limit axis with constant force, driving the movable hinge and the solar cell unfolding subarray to rotate and unfold along the axis system assembly with constant force, until the locking boss of the movable hinge is inserted into the notch of the unfolding locking leaf spring and locked.

[0013] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention, as a preferred embodiment, the constant-torque spring hinge further comprises an unfolding precision adjustment component, the unfolding precision adjustment component comprises an adjustment screw threadedly connected to the fixed hinge and an adjustment nut fixing the adjustment screw;

[0014] The adjusting screw is located in the middle of the two unfolded locking leaf springs. The end face of the adjusting screw is an external hexagon and a slightly curved surface. In the firing state, the end face of the adjusting screw contacts the end of the adjusting boss of the movable hinge. During debugging, the depth of the adjusting screw on the fixed hinge is adjusted by rotating to limit the adjusting boss of the movable hinge to continue to rotate so as to accurately adjust the matching angle between the fixed hinge and the movable hinge. After adjustment, tighten the adjusting nut;

[0015] In the firing state, the locking boss of the movable hinge is completely inserted into the notch of the unfolded locking leaf spring and locked under the restriction of the end face of the adjusting screw, and the unfolded locking leaf spring returns to the initial state to prevent the movable hinge from rebounding.

[0016] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention, as a preferred embodiment, the constant-torque spring hinge further includes an unfolding-in-place feedback signal component connected to the rear end of the movable hinge locking boss;

[0017] The deployed in-position feedback signal assembly includes a micro switch connected to the side of the movable hinge and an insulating gasket connected between the micro switch and the movable hinge. The micro switch includes a switch body and a reed having one end connected to the bottom of the switch body and the other end extending toward the locking boss. The reed is located at the rear side of the locking boss.

[0018] In the firing state, the reed is not triggered by the locking boss and is in an open circuit state and is not conducting;

[0019] When the movable hinge is unfolded and in place in the on-track state, the reed is triggered by the locking leaf spring to make the micro switch conductive and feedback the unfolded in place signal.

[0020] The flat-plate satellite based on the high-rigidity constant-torque spring hinge of the present invention, as a preferred embodiment, the constant-torque spring hinge further comprises a mounting screw sleeve;

[0021] The fixed hinge includes a fixed hinge body with a flat bottom and a front end extending forward, a body-mounted sub-array mounting hole and a grounding threaded hole connected to the fixed hinge body, a limit shaft mounting hole and a leaf spring fixing hole connected to the side wall of the fixed hinge body, a rotating shaft mounting hole connected to the forward extending end of the fixed hinge body and an adjustment screw mounting hole installed at the front end connecting plate of the fixed hinge body, the number of the limit shaft mounting holes and the rotating shaft mounting holes are both two and are arranged oppositely, and the number of the leaf spring fixing holes is four and two are in a group;

[0022] The fixed hinge body comprises a body-mounted sub-array connecting piece, a movable hinge spring connecting piece connected to the front end of the body-mounted sub-array connecting piece, and an adjustment screw connecting piece connected between the movable hinge spring connecting pieces;

[0023] The body-mounted sub-array connector is an I-shaped plate structure with body-mounted sub-array mounting holes arranged on the upper and lower surfaces. The body-mounted sub-array connector is fixedly connected to the solar cell body-mounted sub-array through a mounting screw sleeve and is connected to a grounding mounting bolt through a grounding threaded hole.

[0024] The movable hinge spring connector is a two-plate structure whose ends are vertically connected to the vertical plate of the body-mounted sub-array connector and whose front ends extend obliquely forward. The lower part of the movable hinge spring connector is connected to the limit shaft mounting hole and the leaf spring fixing hole, and the front end of the movable hinge spring connector is connected to the rotating shaft mounting hole.

[0025] The movable hinge spring connector is connected to the limit shaft through the limit shaft mounting hole, connected to the expansion locking leaf spring through the leaf spring fixing hole, and movably connected to the shaft system assembly and the movable hinge through the rotating shaft mounting hole;

[0026] The screw connector is vertically connected between the two plate-like structures of the movable hinge spring connector and is connected to the adjusting screw through the adjusting screw mounting hole.

[0027] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention is preferably configured such that the two fixed hinge bodies connected to the two sides of the solar cell sub-array have different heights.

[0028] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention, as a preferred embodiment, the movable hinge includes a movable hinge body and a second body-mounted sub-array mounting hole connected to the movable hinge body, a second grounding threaded hole, locking bosses respectively connected to both sides of the movable hinge body, a precision adjustment boss connected between the two locking bosses and a constant-force spring mounting hole and a retaining spring bearing mounting hole connected to the movable hinge body;

[0029] The movable hinge body comprises a second body-mounted sub-array connecting member, a locking boss connecting plate vertically connected to the front end of the second body-mounted sub-array connecting member, and a spring mounting member connected to the locking boss connecting plate and extending downward;

[0030] The second body-mounted sub-array connector is an I-shaped plate structure with second body-mounted sub-array mounting holes arranged on the upper and lower surfaces. The second body-mounted sub-array connector is fixedly connected to the solar cell deployment sub-array through a mounting screw sleeve and is connected to a grounding mounting bolt through a second grounding threaded hole.

[0031] The locking boss connecting plate is a hollow frame structure with a front end connected, and insulating gaskets are connected to both sides of the locking boss connecting plate;

[0032] The spring mounting part is a hollow cylindrical structure, and the cylindrical surface has the same arc shape as the constant force spring. The limiting retaining spring and deep groove ball bearing of the shaft system assembly are installed on both sides of the spring mounting part and are movably connected with the movable hinge spring connector through the shaft system assembly.

[0033] The locking boss is a block structure including an inclined surface, the precision adjustment boss is a micro-curved surface and matches with the end surface of the adjustment screw, and the constant force spring mounting hole is fixedly connected with the constant force spring;

[0034] The straight part of the constant force spring is fixedly connected with the constant force spring installation hole, and the bent part extends out of the movable hinge body and extends into the fixed hinge body to be movably connected with the limiting shaft sleeve.

[0035] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention is preferably configured such that the two movable hinge bodies connected to the two sides of the solar cell sub-array have different heights.

[0036] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention, as a preferred embodiment, the shaft system assembly includes a rotating shaft passing through the movable hinge spring connector, two shaft sleeves connected to both ends of the rotating shaft, two limit retaining springs, two deep groove ball bearings and a tightening nut connected to the end of the rotating shaft, and the limit retaining spring and the deep groove ball bearing are movably connected in the spring mounting member;

[0037] The shaft sleeve, limit retaining spring and deep groove ball bearing are symmetrically distributed;

[0038] The rotating shaft is in the form of a stepped shaft, which is convenient for installation at one end of the driven hinge, and the end of the rotating shaft is in the shape of an external hexagon;

[0039] There are two unfolding locking leaf springs, which are respectively connected to the two sides of the movable hinge spring connector. The unfolding locking leaf spring is a sheet structure with a square notch at one end.

[0040] When in the on-track state, the locking boss squeezes and expands the locking leaf spring to produce deformation. After being fully expanded, the locking boss is completely inserted into the square notch and locked.

[0041] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention, as a preferred embodiment, has at least two constant-force springs stacked, and the torque of the constant-torque spring hinge is adjusted by adjusting the number of constant-force springs.

[0042] The flat-plate satellite based on the high-rigidity constant-torque spring hinge described in the present invention, as a preferred embodiment, further comprises an antenna body-mounted sub-array connected to the ground side of the satellite body and an antenna deployment sub-array respectively connected by constant-torque spring hinges, two constant-torque spring hinges form a group, and a total of at least 4 groups, the antenna body-mounted sub-array and the antenna deployment sub-array are both plate-type antennas, and the number of antenna deployment sub-arrays is at least two;

[0043] The fixed hinges are respectively connected to the edges of the antenna body mounted sub-arrays on both sides, and the movable hinges are respectively connected to the edges of the antenna deployed sub-arrays. The driving assembly drives the movable hinge to rotate along the shaft assembly, and after rotating into place, it is locked by deploying a locking leaf spring.

[0044] In the transmitting state, the antenna unfolds its sub-arrays and folds them together at the same side, high and low, and is pressed against the antenna body mounted sub-array;

[0045] When in orbit, the antenna deployment subarray is driven by the constant torque spring hinge to be deployed around both sides of the antenna body subarray and to be coplanar with the antenna deployment subarray.

[0046] The present invention has the following advantages:

[0047] (1) The solar wing and antenna of the present invention use a constant torque spring to provide the required energy. When the static torque margin of the deployment remains unchanged, the energy required for deployment is lower, the speed at the end of deployment is lower, and the impact force at the end of deployment is lower;

[0048] (2) Changing the number of constant force springs can change the driving torque;

[0049] (3) After the hinge is unfolded, it is locked with a stainless steel leaf spring. The hinge locking stiffness can be increased by increasing the number of leaf springs.

[0050] (4) The unfolding angle of the hinge can be precisely adjusted by positioning bolts to ensure the unfolding accuracy requirements of the hinge. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 It is a schematic diagram of the launch state of a flat-plate satellite based on a high-stiffness constant-torque spring hinge;

[0052] Figure 2 It is a schematic diagram of the unfolding state of the solar cell sub-array of a flat-plate satellite based on a high-stiffness constant-torque spring hinge when it is in orbit;

[0053] Figure 3 It is a schematic diagram of a flat-plate satellite constant torque spring hinge structure based on a high-rigidity constant torque spring hinge;

[0054] Figure 4 The exploded diagram of a flat-plate satellite constant torque spring hinge based on a high-rigidity constant torque spring hinge;

[0055] Figure 5 It is a cross-sectional schematic diagram of a flat-plate satellite constant torque spring hinge based on a high-rigidity constant torque spring hinge;

[0056] Figure 6 It is a schematic diagram of a fixed hinge of a flat-plate satellite constant torque spring hinge based on a high-rigidity constant torque spring hinge;

[0057] Figure 7 It is a schematic diagram of a flat-plate satellite constant torque spring hinge movable hinge based on a high-rigidity constant torque spring hinge;

[0058] Figure 8 A schematic diagram of installing a constant force spring on a moving hinge of a flat-plate satellite constant moment spring hinge based on a high-rigidity constant moment spring hinge;

[0059] Fig. 9 It is a cross-sectional schematic diagram of a flat-plate satellite constant torque spring hinge in a folded state based on a high-rigidity constant torque spring hinge;

[0060] Fig.10 It is a schematic diagram of a flat-plate satellite constant torque spring hinge in a folded state based on a high-rigidity constant torque spring hinge;

[0061] Fig.11 It is a schematic diagram of the unfolded state of a flat-plate satellite constant torque spring hinge based on a high-rigidity constant torque spring hinge;

[0062] Fig.12 It is a cross-sectional schematic diagram of an unfolded state of a flat-plate satellite constant torque spring hinge based on a high-rigidity constant torque spring hinge;

[0063] Fig.13 It is a schematic diagram of the connection state of the constant torque spring hinge on the other side of a flat-plate satellite based on a high-rigidity constant torque spring hinge and the unfolded subarray of solar cells;

[0064] Fig.14 It is a schematic diagram of the superposition state of two constant force springs in a flat-plate satellite constant moment spring hinge based on a high-rigidity constant moment spring hinge;

[0065] Fig.15 The diagram is a schematic diagram of the unfolded state of a flat-plate satellite solar cell unfolding subarray and antenna unfolding pointer based on a high-rigidity constant-torque spring hinge when both are connected by constant-torque spring hinges.

[0066] Reference numerals:

[0067] 1. Satellite body; 2. Solar cell body-mounted sub-array; 3. Constant torque spring hinge; 31. Fixed hinge; 311. Fixed hinge body; 3111. Body-mounted sub-array connector; 3112. Moving hinge spring connector; 3113. Adjustment screw connector; 312. Body-mounted sub-array mounting hole; 313. Grounding threaded hole; 314. Limiting shaft mounting hole; 315. Leaf spring fixing hole; 316. Rotating shaft mounting hole; 317. Adjustment screw mounting hole; 32. Moving hinge; 321. Moving hinge body; 3211. Second body-mounted sub-array connector; 3212. Locking boss connecting plate; 3213. Spring mounting piece; 322. Second body-mounted sub-array mounting hole; 323. Second grounding threaded hole; 324. Locking boss; 325. Precision Degree adjustment boss; 326, constant force spring mounting hole; 327, retaining spring bearing mounting hole; 33, shaft system assembly; 331, rotating shaft; 332, bushing; 333, limiting retaining spring; 334, deep groove ball bearing; 335, tightening nut; 34, driving assembly; 341, constant force spring; 342, limiting bushing; 343, limiting shaft; 35, unfolding locking leaf spring; 36, unfolding precision adjustment assembly; 361, adjustment screw; 362, adjustment nut; 37, unfolding in place feedback signal assembly; 371, micro switch; 3711, switch body; 3712, spring leaf; 372, insulating gasket; 38, mounting screw sleeve; 4, solar cell unfolding subarray; 5, antenna body mounting subarray; 6, antenna unfolding subarray. DETAILED DESCRIPTION

[0068] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0069] Example 1

[0070] like Figures 1 to 13 As shown, a flat-plate satellite based on a high-rigidity constant-torque spring hinge comprises a satellite body 1, a solar cell body-mounted sub-array 2 connected to the sky side of the satellite body 1, constant-torque spring hinges 3 respectively connected to both sides of the solar cell body-mounted sub-array 2, and solar cell deployment sub-arrays 4 respectively connected to the other ends of the constant-torque spring hinges 3, the number of solar cell deployment sub-arrays 4 is at least two, and both the solar cell body-mounted sub-array 2 and the solar cell deployment sub-array 4 are plate-shaped structures;

[0071] like Figure 1 As shown, in the emission state, the solar cell unfolded sub-arrays 4 are respectively folded and pressed against the solar cell body mounted sub-array 2 at the same side in high and low positions;

[0072] like Figure 2 As shown, when in the on-orbit state, the solar cell deployment sub-array 4 is driven by the constant torque spring hinge 3 to be deployed around both sides of the solar cell body sub-array 2 and to form a coplanar surface with the solar cell deployment sub-array 4;

[0073] like Figure 3 As shown, the hinge 3 mainly includes a fixed hinge 31, a movable hinge 32, a shaft assembly 33, a drive assembly 34, an unfolding locking leaf spring 35, an unfolding precision adjustment assembly 36, and an unfolding in place feedback signal assembly 37, and the two hinges 32 on one side form a group.

[0074] Each component is composed of Figure 4 As shown, the fixed hinge 31 and the movable hinge 32 are respectively installed with the solar cell body mounting subarray 2 and the solar cell deployment subarray 4 through two mounting screw sleeves 38;

[0075] The shaft assembly 33 includes a rotating shaft 331, two shaft sleeves 332, two limit springs 333, two deep groove ball bearings 334, and a tightening nut 335. The rotating shaft 331 is in the form of a stepped shaft to facilitate the installation of one end of the driven hinge 32, and the end of the rotating shaft 331 is in an external hexagonal shape, which is convenient for a wrench to fix and apply tightening torque from the nut 335 end.

[0076] The driving assembly 34 includes a constant force spring 341, a limiting shaft sleeve 342, and a limiting shaft 343. The limiting shaft sleeve 342 and the limiting shaft 343 are clearance-matched, so that the constant force spring can roll smoothly along the limiting shaft during the deployment process, reducing the deployment resistance. The driving torque can be changed by changing the number of superimposed constant force springs 341.

[0077] The unfolding locking leaf spring 35 is made of stainless steel, is relatively thin, has a square notch at one end, and is respectively installed on both sides of the fixed hinge 31. During the unfolding process, the locking boss 324 of the movable hinge 32 is squeezed and deformed. After the unfolding is completed, the locking boss 324 of the movable hinge 32 is completely inserted into the square notch, and the unfolding locking leaf spring 35 returns to the initial state, thereby preventing the movable hinge 32 from rebounding. By increasing the number of the unfolding locking leaf springs 35, the unfolding locking stiffness can be increased.

[0078] The unfolding precision adjustment component 36 includes an adjustment screw 361 and an adjustment nut 362. The end face of the adjustment screw 361 is an external hexagon and a slightly curved surface. The depth of the adjustment screw 361 on the fixed hinge 31 is rotated by a universal tool to accurately adjust the matching angle between the fixed hinge 31 and the movable hinge 32. After adjustment, tighten the adjustment nut 362.

[0079] The unfolded position feedback signal assembly 37 includes a micro switch 371 and an insulating gasket 372. The micro switch 371 is installed on the movable hinge 32 through the insulating gasket 372. When the hinge is folded, the reed 3712 on the micro switch 371 is not triggered and is in an open circuit state. When the hinge is folded and unfolded, the reed 3712 on the micro switch 371 will be triggered by the locking leaf spring 35 installed on the fixed hinge 31, and the micro switch 371 is in a conducting state. The change of state indicates that the hinge is unfolded to the position.

[0080] like Figure 5 As shown, the sleeve 332, the limit spring 333, and the deep groove ball bearing 334 are installed on both sides of the fixed hinge 31, and are symmetrically distributed, one on each side, to increase the bending stiffness of the hinge along the axial direction of the rotating shaft 331.

[0081] like Figure 6 As shown, the fixed hinge 31 mainly includes the following features: it is installed on the base plate through the mounting hole 312 and the mounting screw sleeve 38, the threaded hole 313 is a grounding hole for installing the grounding bolt, the hole 314 is used to install the limit shaft 343, the two holes 315 are used to install the expansion locking leaf spring 35, the hole 316 is used to install the rotating shaft 331, and the hole 317 is used to install the adjustment screw 361.

[0082] like Figure 7 , 8 The movable hinge 32 shown mainly includes the following features: it is installed on the base plate through the mounting hole 322 and the mounting screw sleeve 38, the threaded hole 323 is a grounding hole for installing the grounding bolt, the locking boss 324 plays the role of locking in place, the precision adjustment boss 325 is a micro-curved surface, which cooperates with the end face of the adjustment screw 361, the two screw holes 326 are used to install the constant force spring 341, and the hole 327 is used to install the limit spring 333 and the deep groove ball bearing 334.

[0083] Fig. 9 , 10The diagram shows the hinge in a folded state and in cross section. The fixed hinge 31 and the movable hinge 32 are in a parallel state, the locking leaf spring 35 is in a free state, and the constant force spring 341 is deformed along the curved surface of the movable hinge 32 under the restriction of the limit shaft 343 to store energy.

[0084] Fig.11 , 12 The figure shows the unfolded state and cross-section of the hinge. The movable hinge 32 rotates around the rotating shaft 331 under the torque of the constant force spring 341. When it rotates to 180 degrees, the end face of the adjustment screw 361 limits the precision adjustment boss 324 to continue to rotate. At this time, the locking boss 324 of the movable hinge 32 is completely inserted into the square notch of the unfolded locking leaf spring 35, and the unfolded locking leaf spring 35 returns to its initial state, thereby preventing the movable hinge 32 from rebounding. When the unfolded locking leaf spring 35 returns to its initial state, it triggers the reed 3712 on the micro switch 371. The micro switch 371 is in the on state and feeds back the unfolded position signal. The depth of the adjustment screw 361 on the fixed hinge 31 is rotated by a universal tool to accurately adjust the matching angle between the fixed hinge 31 and the movable hinge 32.

[0085] Fig.13 It is a constant moment spring hinge on the other side, and the two fixed hinge bodies 311 and the movable hinge body 321 connected to the two sides of the solar cell body mounting sub-array 2 have different heights / angles.

[0086] Example 2

[0087] A flat-plate satellite based on a high-rigidity constant-torque spring hinge, the structure of which is the same as that of Example 1, except that the number of constant-force springs 341 is two and they are stacked, as shown in FIG. Fig.14 As shown, the torque of the constant moment spring hinge is adjusted by adjusting the number of constant force springs 341 .

[0088] Example 3

[0089] A flat-plate satellite based on a high-rigidity constant-torque spring hinge has the same structure as that of Example 1, and further comprises an antenna body-mounted subarray 5 connected to the ground side of a satellite body 1 and antenna deployment subarrays 6 connected respectively via constant-torque spring hinges 3. Both the antenna body-mounted subarray 5 and the antenna deployment subarray 6 are plate-type antennas, and the number of the antenna deployment subarrays 6 is at least two. Fig.15 As shown;

[0090] The fixed hinges 31 are respectively connected to the edges of both sides of the antenna body mounted sub-array 5, and the movable hinges 32 are respectively connected to the edges of the antenna deployed sub-array 6. The driving assembly 34 drives the movable hinge 32 to rotate along the shaft assembly 33, and after rotating to the right position, it is locked by the deployed locking leaf spring 35;

[0091] In the transmitting state, the antenna unfolded sub-arrays 6 are respectively folded and pressed against the antenna body mounted sub-array 5 at the same side;

[0092] When in the on-orbit state, the antenna deployment sub-array 6 is driven by the constant torque spring hinge 3 to be deployed around both sides of the antenna body sub-array 5 and to be coplanar with the antenna deployment sub-array 6 .

[0093] The specific implementation methods of Examples 1 to 3 are:

[0094] The hinge is closed. Fig. 9 , 10 As shown, after the satellite 1 releases the solar wing 4 / antenna 6, the unfolded solar wing 4 / antenna 6 rotates around the rotating shaft 331 under the torque of the constant force spring 341. When it rotates to 180 degrees, the end face limiting precision adjustment boss 324 of the adjustment screw 361 continues to rotate. At this time, the locking boss 324 of the movable hinge 32 is completely inserted into the square notch of the unfolding locking leaf spring 35, and the unfolding locking leaf spring 35 returns to the initial state, thereby preventing the movable hinge 32 from rebounding. When the unfolding locking leaf spring 35 returns to the initial state, it triggers the reed on the micro switch 371, and the micro switch 371 is in the on state, feeding back the unfolding in place signal.

[0095] When the hinge is adjusted on the ground, the depth of the adjustment screw 361 on the fixed hinge 31 can be rotated by a general tool to accurately adjust the matching angle between the fixed hinge 31 and the movable hinge 32; the driving torque can be changed by changing the number of superimposed constant force springs 341; and the expansion locking stiffness can be increased by increasing the number of expansion locking leaf springs 35.

[0096] In embodiments 1 to 3, the single constant torque spring 341 is: material titanium alloy TB2 plate, thickness 1 mm, constant torque 1.2 Nm;

[0097] The locking boss 324 is made of 7075T6 aluminum alloy, with a width of 3.5 mm and a height of 6 mm, and a bevel angle of 125 degrees;

[0098] The leaf spring 35 is made of 301 stainless steel, with a thickness of 0.5 mm and a square notch size of 4*6.5 mm (slightly larger than the locking boss size);

[0099] In Examples 1 to 3, the hinge 3 takes 10 seconds to unfold, and the unfolding accuracy is 180°±1.5°.

[0100] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A flat-plate satellite based on a high-rigidity constant-torque spring hinge, characterized in that: The invention comprises a satellite body (1), a solar cell body-mounted sub-array (2) connected to the sky side of the satellite body (1), constant moment spring hinges (3) respectively connected to both sides of the solar cell body-mounted sub-array (2), and solar cell deployment sub-arrays (4) respectively connected to the other ends of the constant moment spring hinges (3), wherein the number of the solar cell deployment sub-arrays (4) is at least two, and both the solar cell body-mounted sub-array (2) and the solar cell deployment sub-array (4) are plate-shaped structures; In the emission state, the solar cell unfolded sub-arrays (4) are respectively folded up and pressed tightly on the solar cell body mounted sub-arrays (2) at the same side; When in the on-orbit state, the solar cell deployment sub-array (4) is driven by the constant moment spring hinge (3) to be deployed around both sides of the solar cell body mounted sub-array (2) and to form a coplanar surface with the solar cell deployment sub-array (4); The constant moment spring hinge (3) comprises a fixed hinge (31) connected to the edge of one side of the solar cell body mounting sub-array (2), a movable hinge (32) connected to the edge of one side of the solar cell unfolding sub-array (4), an axis assembly (33) movably connecting the fixed hinge (31) and the movable hinge (32), a driving assembly (34) partially fixedly connected to the movable hinge (32) and partially extending into the fixed hinge (31) and capable of driving the movable hinge (32) to rotate along the axis assembly (33), and an unfolding locking leaf spring (35) connected to both sides of the fixed hinge (31); The driving assembly (34) comprises a constant force spring (341) with one end extending into the fixed hinge (31) and the other end fixedly connected to the movable hinge (32), a limiting shaft sleeve (342) connected to the fixed hinge (31) and one end of the constant force spring (341), and a limiting shaft (343) loosely fitted in the limiting shaft sleeve (342), one end of the constant force spring (341) fixedly connected to the movable hinge (32) is a plane, the other side connected to the limiting shaft sleeve (342) is bent downward, and the middle is an arc surface, and the limiting shaft sleeve (342) and the limiting shaft (343) are both located at the bent corner of the constant force spring (341); In the launching state, the constant force spring (341) is compressed and fixed; in the on-orbit state, the constant force spring (341) is released, unfolded along the limit axis (343) with constant force, and drives the movable hinge (32) and the solar cell unfolding subarray (4) to rotate and unfold along the axis system component (33) with constant force until the locking boss of the movable hinge (32) is inserted into the notch of the unfolding locking leaf spring (35) and locked; The constant torque spring hinge (3) further comprises an unfolding precision adjustment component (36), wherein the unfolding precision adjustment component (36) comprises an adjustment screw (361) threadedly connected to the fixed hinge (31) and an adjustment nut (362) for fixing the adjustment screw (361); The adjusting screw (361) is located between the two unfolding locking leaf springs (35), and the end face of the adjusting screw (361) is an external hexagon and a slightly curved surface. In the firing state, the end face of the adjusting screw (361) contacts the end of the adjusting boss of the movable hinge (32). During debugging, the depth of the adjusting screw (361) on the fixed hinge (31) is adjusted by rotation to limit the adjustment boss of the movable hinge (32) to continue to rotate so as to accurately adjust the matching angle between the fixed hinge (31) and the movable hinge (32). After adjustment, the adjusting nut (362) is tightened; In the launching state, the locking boss of the movable hinge (32) is completely inserted into the notch of the unfolding locking leaf spring (35) and locked under the restriction of the end face of the adjusting screw (361), and the unfolding locking leaf spring (35) returns to the initial state to prevent the movable hinge (32) from rebounding.

2. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 1, characterized in that: The constant torque spring hinge (3) further comprises an unfolded position feedback signal component (37) connected to the rear end of the locking boss of the movable hinge (32); The deployed in-position feedback signal assembly (37) comprises a micro switch (371) connected to the side of the movable hinge (32) and an insulating gasket (372) connected between the micro switch (371) and the movable hinge (32), the micro switch (371) comprising a switch body (3711) and a reed (3712) having one end connected to the bottom of the switch body (3711) and the other end extending toward the locking boss, the reed (3712) being located at the rear side of the locking boss; In the firing state, the reed (3712) is not triggered by the locking boss and is in an open circuit state and is not conducting; When the movable hinge (32) is unfolded and in place in the on-track state, the leaf spring (3712) is triggered by the locking leaf spring (35) to cause the micro switch (371) to be in a conducting state and to feed back an unfolded and in place signal.

3. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 1, characterized in that: The constant torque spring hinge (3) further comprises a mounting screw sleeve (38); The fixed hinge (31) comprises a fixed hinge body (311) with a flat bottom and a front end extending forward, a body-mounted sub-array mounting hole (312) and a grounding threaded hole (313) connected to the fixed hinge body (311), a limit shaft mounting hole (314) and a leaf spring fixing hole (315) connected to the side wall of the fixed hinge body (311), a rotating shaft mounting hole (316) connected to the forward extending end of the fixed hinge body (311) and an adjustment screw mounting hole (317) installed at the front end connecting plate of the fixed hinge body (311), the limit shaft mounting hole (314) and the rotating shaft mounting hole (316) are both two in number and are arranged opposite to each other, and the leaf spring fixing holes (315) are four in number and are arranged in groups of two; The fixed hinge body (311) comprises a body-mounted sub-array connecting piece (3111), a movable hinge spring connecting piece (3112) connected to the front end of the body-mounted sub-array connecting piece (3111), and an adjustment screw connecting piece (3113) connected between the movable hinge spring connecting piece (3112); The body-mounted sub-array connecting piece (3111) is an I-shaped plate structure with the body-mounted sub-array mounting holes (312) arranged on both the upper and lower surfaces; the body-mounted sub-array connecting piece (3111) is fixedly connected to the solar cell body-mounted sub-array (2) via the mounting screw sleeve (38) and is connected to the grounding mounting bolt via the grounding threaded hole (313); The movable hinge spring connector (3112) is a two-plate structure whose ends are vertically connected to the vertical plate of the body-mounted sub-array connector (3111) and whose front ends extend obliquely forward; the lower part of the movable hinge spring connector (3112) is connected to the limit shaft mounting hole (314) and the leaf spring fixing hole (315); and the front end of the movable hinge spring connector (3112) is connected to the rotating shaft mounting hole (316); The movable hinge spring connector (3112) is connected to the limit shaft (343) through the limit shaft mounting hole (314), is connected to the deployment locking leaf spring (35) through the leaf spring fixing hole (315), and is movably connected to the shaft system assembly (33) and the movable hinge (32) through the rotating shaft mounting hole (316); The screw connector (3113) is vertically connected between the two plate-like structures of the movable hinge spring connector (3112) and is connected to the adjustment screw (361) through the adjustment screw mounting hole (317).

4. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 3, characterized in that: The two fixed hinge bodies (311) connected to the two sides of the solar cell body mounting sub-array (2) have different heights.

5. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 3, characterized in that: The movable hinge (32) comprises a movable hinge body (321), a second body-mounted sub-array mounting hole (322) connected to the movable hinge body (321), a second grounding threaded hole (323), locking bosses (324) respectively connected to both sides of the movable hinge body (321), a precision adjustment boss (325) connected between the two locking bosses (324), and a constant force spring mounting hole (326) and a retaining spring bearing mounting hole (327) connected to the movable hinge body (321); The movable hinge body (321) comprises a second body-mounted sub-array connecting member (3211), a locking boss connecting plate (3212) vertically connected to the front end of the second body-mounted sub-array connecting member (3211), and a spring mounting member (3213) connected to the locking boss connecting plate (3212) and extending downward; The second body-mounted sub-array connecting member (3211) is an I-shaped plate structure with the second body-mounted sub-array mounting holes (322) arranged on both the upper and lower surfaces; the second body-mounted sub-array connecting member (3211) is fixedly connected to the solar cell unfolded sub-array (4) via the mounting screw sleeve (38) and is connected to the grounding mounting bolt via the second grounding threaded hole (323); The locking boss connecting plate (3212) is a hollow frame structure with a front end connected, and both sides of the locking boss connecting plate (3212) are connected to insulating gaskets (372); The spring mounting member (3213) is a hollow cylindrical structure, and the cylindrical surface has the same arc shape as the constant force spring (341). The limiting retaining spring and deep groove ball bearing of the shaft system assembly (33) are installed on both sides of the spring mounting member (3213) and are movably connected to the movable hinge spring connector (3112) through the shaft system assembly (33); The locking boss (324) is a block structure including an inclined surface, the precision adjustment boss (325) is a micro-curved surface and matches the end surface of the adjustment screw (361), and the constant force spring mounting hole (326) is fixedly connected to the constant force spring (341); The straight portion of the constant force spring (341) is fixedly connected to the constant force spring mounting hole (326), and the bent portion extends out of the movable hinge body (321) and into the fixed hinge body (311) to be movably connected to the limiting shaft sleeve (342).

6. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 5, characterized in that: The two movable hinge bodies (321) connected to the two sides of the solar cell body mounting sub-array (2) have different heights.

7. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 5, characterized in that: The shaft system assembly (33) comprises a rotating shaft (331) passing through the movable hinge spring connector (3112), two shaft sleeves (332) connected to two ends of the rotating shaft (331), two limiting retaining springs (333), two deep groove ball bearings (334) and a tightening nut (335) connected to the end of the rotating shaft (331), wherein the limiting retaining spring (333) and the deep groove ball bearing (334) are movably connected in the spring mounting member (3213); The shaft sleeve (332), the limiting retaining spring (333), and the deep groove ball bearing (334) are symmetrically distributed; The rotating shaft (331) is in the form of a stepped shaft to facilitate installation from one end of the movable hinge (32), and the end of the rotating shaft (331) is in an external hexagonal shape; The number of the unfolding locking leaf springs (35) is two, which are respectively connected to the two sides of the movable hinge spring connector (3112); the unfolding locking leaf spring (35) is a sheet structure with a square notch at one end; When in the on-rail state, the locking boss (324) squeezes the unfolding locking leaf spring (35) to cause deformation, and after being unfolded into place, the locking boss (324) is completely inserted into the square notch and locked.

8. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 1, characterized in that: The number of the constant force springs (341) is at least two and they are stacked, and the torque of the constant torque spring hinge is adjusted by adjusting the number of the constant force springs (341).

9. A flat-plate satellite based on a high-rigidity constant-torque spring hinge according to claim 1, characterized in that: It also includes an antenna body-mounted sub-array (5) connected to the ground side of the satellite body (1) and an antenna deployment sub-array (6) connected respectively via the constant moment spring hinges (3), two of the constant moment spring hinges (3) form a group, and a total of at least four groups, the antenna body-mounted sub-array (5) and the antenna deployment sub-array (6) are both plate antennas, and the number of the antenna deployment sub-arrays (6) is at least two; The fixed hinges (31) are respectively connected to the edges of both sides of the antenna body sub-array (5), the movable hinges (32) are respectively connected to the edges of the antenna deployment sub-array (6), the driving assembly (34) drives the movable hinge (32) to rotate along the shaft assembly (33), and after rotating to the right position, the movable hinge is locked by the deployment locking leaf spring (35); In the transmitting state, the antenna unfolded subarrays (6) are respectively folded up and pressed tightly on the antenna body mounted subarrays (5) at the same side; When in the on-orbit state, the antenna deployment sub-array (6) is driven by the constant moment spring hinge (3) to be deployed around both sides of the antenna body mounted sub-array (5) and to be coplanar with the antenna deployment sub-array (6).

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