CN217980660U - Unmanned aerial vehicle weight focus measuring device - Google Patents
Unmanned aerial vehicle weight focus measuring device Download PDFInfo
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- CN217980660U CN217980660U CN202222282987.3U CN202222282987U CN217980660U CN 217980660 U CN217980660 U CN 217980660U CN 202222282987 U CN202222282987 U CN 202222282987U CN 217980660 U CN217980660 U CN 217980660U
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Abstract
The utility model discloses an unmanned aerial vehicle weight center of gravity measuring device, which comprises a bracket and three supporting tools, wherein the three supporting tools are distributed along the periphery of the bracket and are respectively matched with three supporting points of an unmanned aerial vehicle; the support tool comprises a support, a lifting assembly and a leveling assembly, the leveling assembly is arranged at the bottom of the support, the lifting assembly is rotatably connected to the top of the support, and a pressure detection piece is fixed to the end of the lifting assembly. The beneficial effects of the utility model are that, through set up three support frock around the bracket to keep the horizontality through the three strong point of lifting unit fast adjustment unmanned aerial vehicle, so that swift realization unmanned aerial vehicle weight and centrobaric allotment.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle ground support equipment technical field, especially an unmanned aerial vehicle weight focus measuring device.
Background
The rocket-assisted launching is an unmanned aerial vehicle take-off mode widely applied, the gravity center matching of the unmanned aerial vehicle is the key for the success or failure of the rocket-assisted launching, and the determination of the position of the gravity center is the basis for the gravity center matching of the unmanned aerial vehicle. In the prior art, the gravity center position of the unmanned aerial vehicle needs to be determined, and then calculation is carried out after multi-point measurement. And the multipoint measurement can not ensure that the multipoint is weighed simultaneously, so that the measurement point of the aircraft is subjected to sideslip extrusion and generates a large friction force, and the measurement precision is seriously influenced.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the above problem, an unmanned aerial vehicle weight focus measuring device has been designed. The unmanned aerial vehicle support device comprises a bracket and three support tools, wherein the three support tools are distributed along the periphery of the bracket, and are respectively matched with three support points of the unmanned aerial vehicle; the support tool comprises a support, a lifting assembly and a leveling assembly, the leveling assembly is arranged at the bottom of the support, the lifting assembly is rotatably connected to the top of the support, and a pressure detection piece is fixed to the end of the lifting assembly.
Furthermore, a guide sleeve penetrates through the top of the support, a flange plate is fixed at the end part of the guide sleeve, and the flange plate is fixedly connected with the support.
Further, the lifting assembly comprises an adjusting wheel and a lifting seat, the lifting seat penetrates through the adjusting wheel, the adjusting wheel is in threaded connection with the lifting seat, and the lifting seat is in threaded connection with the guide sleeve.
Furthermore, a connecting sleeve is fixed on the flange plate, and the adjusting wheel penetrates through the connecting sleeve and is matched with the connecting sleeve.
Furthermore, the end portion, extending out of the guide sleeve, of the lifting seat is fixedly provided with a sliding plate assembly, the sliding plate assembly comprises a sliding plate, steel balls, a supporting seat and a cover body, the surface of the sliding plate is provided with a plurality of round holes, each round hole is internally provided with one steel ball, the supporting seat is in contact with the steel balls, the end portion of the supporting seat is fixedly provided with a pressure detection piece, and the cover body is fixedly connected with the sliding plate.
Further, the leveling assemblies are arranged at least three along the bottom of the bracket.
Furthermore, the leveling assembly comprises leveling support legs and a leveling rod, the leveling support legs penetrate through the support and are in threaded connection with the support, and the leveling rod is fixed on the leveling support legs.
Further, the bracket includes bearing main part and supporting shoe, bearing main part both sides are fixed with the supporting shoe respectively, and two adjacent supporting shoes of one side bearing main part form the support position of supporting the unmanned aerial vehicle main part.
Utilize the technical scheme of the utility model an unmanned aerial vehicle weight focus measuring device of preparation, the beneficial effect who reaches: three supporting tools are arranged around the bracket, and three supporting points of the unmanned aerial vehicle are quickly adjusted by the lifting assembly to keep a horizontal state, so that the weight and the gravity center of the unmanned aerial vehicle can be quickly adjusted; the sliding plate, the steel ball and the supporting seat still have horizontal sliding freedom when being attached to an airplane measuring point, so that the friction force of the aircraft in a sideslip extrusion state can be eliminated.
Drawings
Fig. 1 is a schematic layout view of a device for measuring the weight center of gravity of an unmanned aerial vehicle according to the present invention;
fig. 2 is a top view of the unmanned aerial vehicle weight center of gravity measuring device in the use state;
fig. 3 is a perspective view of the supporting tool of the present invention;
fig. 4 is a front view of the supporting tool of the present invention;
fig. 5 is a cross-sectional view of the present invention in fig. 4 taken along the direction B-B;
FIG. 6 is an enlarged view of a portion of the present invention shown in FIG. 5 at reference A;
fig. 7 is a perspective view of the bracket of the present invention;
FIG. 8 is a schematic diagram of a left projection plane coordinate system in the unmanned aerial vehicle gravity center measurement method;
FIG. 9 is a schematic plane coordinate system in a pitching state in a gravity center measurement method of the unmanned aerial vehicle;
in the figure, 1, a bracket; 11. supporting the main body; 12. a support block; 2. supporting a tool; 21. a support; 22. a lifting assembly; 211. an adjustment wheel; 222. a lifting seat; 23. a leveling assembly; 231. leveling the supporting legs; 232. a leveling rod; 24. a sled assembly; 241. a slide plate; 242. steel balls; 243. a supporting base; 244. a cover body; 25. a pressure detecting member; 26. a guide sleeve; 27. a flange plate; 28. connecting sleeves; 3. a butt joint block; 4. unmanned aerial vehicle.
Detailed Description
The utility model discloses it is next described to combine the figure specifically, as shown in fig. 1 and fig. 2, an unmanned aerial vehicle weight focus measuring device, including bracket 1 and support frock 2, support frock 2 edge it is three to distribute around the bracket 1, three support frock 2 respectively with unmanned aerial vehicle's three strong point looks adaptation. The airplane is hoisted to the bracket 1, and the fuselage assembly parts forming the unmanned aerial vehicle are arranged on a front supporting point and a rear supporting point of the airplane. And then, placing the three support tools 2 below the three support points, and placing a weighing device below each support tool 2. The weighing equipment is used for measuring 2 parts of each supporting tool
As shown in fig. 3-6, the supporting tool 2 includes a support 21, a lifting assembly 22 and a leveling assembly 23, the leveling assembly 23 is disposed at the bottom of the support 21, the lifting assembly 22 is disposed at the top of the support 21, and a pressure detecting member 25 is fixed at an end of the lifting assembly 22. Support 21 plays the supporting role, and lifting unit 22 is used for adjusting different strong points department unmanned aerial vehicle's height makes unmanned aerial vehicle adjust to the horizontality, and leveling unit 23 is used for adjusting support 21 all to be in balanced state in three strong points department.
The top of the support 21 is provided with a guide sleeve 26 in a penetrating way, the end part of the guide sleeve 26 is fixed with a flange 27, and the flange 27 is fixedly connected with the support 21. The lifting assembly 22 comprises an adjusting wheel 211 and a lifting seat 222, the lifting seat 222 penetrates through the adjusting wheel 211, the adjusting wheel 211 is in threaded connection with the lifting seat 222, and the lifting seat 222 is in threaded connection with the guide sleeve 26. Because regulating wheel 211 and lift seat 222 threaded connection, lift seat 222 again with 26 threaded connection of uide bushing, when rotating regulating wheel 211, lift seat 222 just moves in vertical direction along uide bushing 26, and then the height of the unmanned aerial vehicle assembly part that supports 2 supports of frock is changed, regulating wheel 211 and the height that takes the screwed lift seat 222 to mutually support and promote unmanned aerial vehicle, wear to be equipped with uide bushing 26 in the support 21, lift seat 222 and 26 threaded connection of uide bushing and not direct and support 21 threaded connection, eliminate rocking of lift in-process, the lift process is more steady.
The flange 27 is fixed with a connecting sleeve 28, and the adjusting wheel 211 passes through the connecting sleeve 28 and is matched with the connecting sleeve 28. The top of the bracket 21 is fixedly connected with the flange 27, the connecting sleeve 28 is arranged at one side of the flange 27, the section of the connecting sleeve 28 is L-shaped, the bottom of the adjusting wheel 211 is clamped in the connecting sleeve 28, and the adjusting wheel 211 is kept in a stable and stable state in the rotating process.
A sliding plate assembly 24 is fixed at the end of the lifting seat 222 extending out of the guide sleeve 26, the sliding plate assembly 24 includes a sliding plate 241, steel balls 242, a supporting seat 243 and a cover body 244, a plurality of circular holes are formed in the surface of the sliding plate 241, one steel ball 242 is accommodated in each circular hole, the supporting seat 243 and the steel ball 242 are in mutual contact, a pressure detection piece 25 is fixed at the end of the supporting seat 243, and the cover body 244 is fixedly connected with the sliding plate 241. This slide subassembly 24 sets up between pressure measurement 25 and lift subassembly 22, slide 241 subassembly 24 is provided with slide 241 subassembly 24 in order to reduce the friction assurance precision after pressure measurement 25 department receives downward pressure, and pressure measurement 25 transmits power to supporting seat 243, further transmits to the steel ball surface, and the power that acts on lift subassembly 22 and support 21 under the effect of a plurality of steel ball is even, further guarantees the stable removal of lift seat 222 in uide bushing 26. The mechanism still has horizontal sliding freedom when abutting against the measuring point. The horizontal sliding freedom here means the ability to move in a direction parallel or approximately parallel to the aircraft surface. Thereby, the friction force in the aircraft sideslip pressing state can be eliminated.
As shown in fig. 3, the leveling members 23 are arranged at least three along the bottom of the bracket 21. The leveling assembly 23 comprises a leveling leg 231 and a leveling rod 232, the leveling leg 231 penetrates through the support 21 and is in threaded connection with the support 21, and the leveling rod 232 is fixed on the leveling leg 231. Leveling landing leg 231 and support 21 threaded connection, the height that seat 222 adjusted unmanned aerial vehicle is not different in different strong points department, and the height at seat 222 place also is different, and whole support 21's three shank may produce askew, changes the height of adjusting the landing leg screw in support 21 through rotating the regulation pole, makes support 21 more stable.
Bracket 1 includes bearing main part 11 and supporting shoe 12, 11 both sides of bearing main part are fixed with supporting shoe 12 respectively, and two adjacent supporting shoes 12 of one side bearing main part 11 form the support position of supporting the unmanned aerial vehicle main part.
The working process comprises the following steps:
1. and (5) adjusting the airplane to be in a horizontal state by using the supporting tool 2.
(1) As shown in fig. 1, 2 and 7, the airplane is hoisted to the bracket 1, three fuselage assembly parts are assembled on a front supporting point a and a rear two supporting points B and C of the unmanned aerial vehicle 4 through the butt-joint block 3, and the bottom of the butt-joint block 3 is provided with a groove matched with the pressure detection part 25;
(2) Placing three supporting tools 2 below the three supporting points, and placing a weighing device below each supporting tool 2;
(3) The airplane is hoisted, then the front supporting point A tool is adjusted to the height of 800mm, the two rear supporting point tools B and C are adjusted to the height of 941.5mm, the airplane is put down onto the supporting tool 2, and the airplane is completely separated from the bracket 1. The front supporting point and the rear supporting point are not on the same horizontal plane, and the front supporting point and the rear supporting point are high and low, so that the front supporting tool 2 and the rear supporting tool 2 are different in adjusting height;
(4) The aircraft is confirmed to be adjusted to the horizontal state by matching the tape measure with the theodolite, and if the aircraft is not horizontal, the aircraft is adjusted to the horizontal state by rotating the adjusting wheel 211.
(5) And (4) obtaining the weight F1 of the front supporting point through the degree of the weighing equipment, wherein the weight on the left side of the rear supporting point is F2, and the weight on the right side of the rear supporting point is F3.
2. After the horizontal adjustment of the airplane is finished, a front supporting point of the airplane is set to be A, the left side and the right side of a rear supporting point are respectively set to be B and C, D is the gravity center position of the airplane, three points ABC are projected from the left side of the airplane to form a rectangular coordinate system, as shown in FIG. 8, the point A is used as an original point, a square with an X axis is arranged on the right side in parallel, and the calculation is carried out on the square with the Z axis in the direction vertical to the ground.
(1) The horizontal distance AD is L1, the horizontal distance AB is L2, the barycentric coordinate is (X, Z), the distance from the barycentric to the point A on the X axis can be obtained through a moment balance formula, the weight of the airplane is W, the weight of the front supporting point is F1, the left side of the rear supporting point is F2, and the right side of the rear supporting point is F3, so that the airplane can be obtained
W＝F 1 +F 2 -F 3
W*L 1 ＝(F 2 +F 3 )*L 1
(2) When the Y-axis gravity center of the airplane is measured by using the weighing equipment, if the masses of the left side and the right side of the rear fulcrum are unequal, the Y-axis gravity center is located at the longitudinal center of the airplane by adding or reducing the counter weight.
(3) And (3) solving a Z-axis coordinate by using an inclination method, keeping the state of the point A unchanged, lifting the airplane by 50mm by rotating the adjusting wheels at the point B and the point C, and determining that the lifting height is 50mm by using a tape measure matched with a theodolite. Setting the pitch angle of the lifted airplane as alpha and the weighing data of the sensors A, B and C after lifting as F 11 ，F 22 ，F 33 The coordinate system at this time is shown in fig. 9;
and B and C are moved to B ' and C ' points after being lifted, the rotation angle is set as alpha, the gravity center is also rotated by alpha, the horizontal distance between the gravity center and the A point at the moment is set as m, and the horizontal distance between the B ' point and the A point is set as n.
The moment balance is still calculated by taking the point A as a balance point, and the method can be obtained
W*m＝(F 22 +F 33 )*α
W＝F 11 +F 22 +F 33
N is a measurable value, α can be calculated by the change of point B, and m = (L) 1 -Zig α) × cos α, available
(F 11 +F 33 )*α＝W*(L 1 -Zigα)cosα
Simultaneous solution can be obtained
Thus, the coordinate value of the center of gravity D is obtained.
Above-mentioned technical scheme has only embodied the utility model discloses technical scheme's preferred technical scheme, some changes that this technical field's technical staff probably made to some parts wherein have all embodied the utility model discloses a principle belongs to within the protection scope of the utility model.
Claims (8)
1. The unmanned aerial vehicle weight center of gravity measuring device is characterized by comprising a bracket (1) and three supporting tools (2), wherein the three supporting tools (2) are distributed along the periphery of the bracket (1), and the three supporting tools (2) are respectively matched with three supporting points of an unmanned aerial vehicle;
support frock (2) including support (21), lifting unit (22) and leveling subassembly (23), support (21) bottom is equipped with leveling subassembly (23), support (21) top is equipped with lifting unit (22), lifting unit (22) end fixing has pressure measurement spare (25).
2. The unmanned aerial vehicle weight center of gravity measuring device of claim 1, characterized in that, guide sleeve (26) is worn to be equipped with at the support (21) top, guide sleeve (26) end fixing has ring flange (27), ring flange (27) with support (21) fixed connection.
3. The unmanned aerial vehicle weight center of gravity measuring device of claim 2, wherein the lifting assembly (22) comprises an adjusting wheel (211) and a lifting base (222), the lifting base (222) penetrates through the adjusting wheel (211) and the adjusting wheel (211) is in threaded connection with the lifting base (222), and the lifting base (222) is in threaded connection with the guide sleeve (26).
4. The unmanned aerial vehicle weight center of gravity measuring device of claim 3, characterized in that, adapter sleeve (28) is fixed with in ring flange (27), and adjusting wheel (211) passes through adapter sleeve (28) and with adapter sleeve (28) looks adaptation.
5. The unmanned aerial vehicle weight center of gravity measuring device of claim 3, wherein the end of the lifting seat (222) extending out of the guide sleeve (26) is fixed with a sliding plate assembly (24), the sliding plate assembly (24) comprises a sliding plate (241), steel balls (242), a supporting seat (243) and a cover body (244), the surface of the sliding plate (241) is provided with a plurality of round holes, each round hole contains one steel ball (242), the supporting seat (243) and the steel balls (242) are in contact with each other, the end of the supporting seat (243) is fixed with a pressure detecting piece (25), and the cover body (244) is fixedly connected with the sliding plate (241).
6. The unmanned aerial vehicle weight center of gravity measuring device of claim 1, wherein the leveling assembly (23) is arranged at least three along the bottom of the bracket (21).
7. An unmanned aerial vehicle weight center of gravity measuring device of claim 6, characterized in that, the leveling subassembly (23) includes leveling leg (231) and leveling pole (232), leveling leg (231) pass through the support (21) and with support (21) threaded connection, leveling pole (232) is fixed in leveling leg (231).
8. The unmanned aerial vehicle weight center of gravity measuring device of claim 1, characterized in that, the bracket (1) comprises a bearing body (11) and supporting blocks (12), the supporting blocks (12) are respectively fixed on two sides of the bearing body (11), and two adjacent supporting blocks (12) of the bearing body (11) on one side form a supporting position for supporting the unmanned aerial vehicle body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222282987.3U CN217980660U (en) | 2022-08-29 | 2022-08-29 | Unmanned aerial vehicle weight focus measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222282987.3U CN217980660U (en) | 2022-08-29 | 2022-08-29 | Unmanned aerial vehicle weight focus measuring device |
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| Publication Number | Publication Date |
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| CN217980660U true CN217980660U (en) | 2022-12-06 |
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| CN202222282987.3U Active CN217980660U (en) | 2022-08-29 | 2022-08-29 | Unmanned aerial vehicle weight focus measuring device |
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- 2022-08-29 CN CN202222282987.3U patent/CN217980660U/en active Active
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