CN204964218U - Multidimension framework formula satellite antenna deployment mechanism gravity balance arm - Google Patents
Multidimension framework formula satellite antenna deployment mechanism gravity balance arm Download PDFInfo
- Publication number
- CN204964218U CN204964218U CN201520771885.5U CN201520771885U CN204964218U CN 204964218 U CN204964218 U CN 204964218U CN 201520771885 U CN201520771885 U CN 201520771885U CN 204964218 U CN204964218 U CN 204964218U
- Authority
- CN
- China
- Prior art keywords
- axis
- hanging
- antenna
- voussoir
- wire rope
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Landscapes
- Details Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The utility model relates to a weightless analogue means of satellite antenna deployment mechanism ground testing, specifically speaking is a multidimension framework formula satellite antenna deployment mechanism gravity balance arm, which comprises a mounting bas, the antenna expandes to follow the arm, the directional subassembly of following, the encoder, the hooke hinge, driving motor expandes, constant force adjusting device, the frock is hung to the X axle, the frock is hung to three -dimensional adjusting device of hoisting point and antenna, the hooke hinge is installed and is expanded to follow arm and the directional subassembly below of following at the antenna, the hinge department in the hooke hinge is installed to the encoder, constant force adjusting device is through hanging scroll installation hooke hinge below and hang frock and antenna with the X axle respectively through wire rope and hang the frock and be connected, X hangs frock and antenna and hangs the frock and be used for connecting antenna deployment mechanism X axle and antenna respectively. The utility model has the characteristics of the degree of freedom is many, the structure is reliable, the accuracy is followed to the position appearance, the force control is accurate, operation ann congruent, weightless simulation when satisfying multidimension framework formula antenna deployment mechanism and testing on ground.
Description
Technical field
The utility model relates to satellite antenna development mechanism ground test weightless flight device, specifically a kind of multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm.
Background technology
In order to ensure that satellite antenna reliably launches in-orbit, must on ground in the face of its antenna deployment mechanism is tested before satellite launch, this just requires in the state of weightlessness of ground simulation antenna deployment mechanism in space.The domestic research to multidimensional truss antenna development mechanism is at present in mathematical model simulation and three dimensional analysis stage, do not meet the device in its state of weightlessness of ground simulation, in the urgent need to the gravitational equilibrium mechanism corresponding with multidimensional truss antenna development mechanism, meet and additional moment is not introduced to the gravitational equilibrium that development mechanism is real-time, and then provide weightlessness to carry out ground spreading test.For this present situation, research and develop a kind of multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm, to the ground test of antenna deployment mechanism and ensure its in-orbit reliable launch significant.
Utility model content
The purpose of this utility model is to provide a kind of multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm.This gravitational equilibrium mechanical arm can on ground in the face of multidimensional truss antenna development mechanism carries out real-time gravitational equilibrium in expansion and sensing test process.
The purpose of this utility model is achieved through the following technical solutions:
The utility model comprises expansion drive motor, mount pad, antenna expansion follower arm, points to and follow assembly, suspension centre three-dimensional regulating mechanism, constant force regulating device, antenna suspending equipment, X-axis suspending equipment and launch arm suspending equipment, wherein launching drive motor is arranged on described mount pad, and output terminal is connected with sensing by described antenna expansion follower arm and follows assembly; Described antenna suspending equipment and X-axis suspending equipment are connected with respective constant force regulating device respectively by wire rope, each described constant force regulating device respectively be arranged on the Hooke's hinge that described sensing follows on assembly and be connected, described expansion arm suspending equipment by wire rope be arranged on the Hooke's hinge that described antenna launches in follower arm and be connected;
Described sensing is followed assembly and is comprised X-axis mount pad, X-axis swivel base, Y-axis swivel base, X-axis drive motor and Y-axis drive motor, this X-axis mount pad is arranged on described antenna and launches in follower arm, described X-axis swivel base is rotatably installed on this X-axis mount pad, and drive rotation by the X-axis drive motor be arranged on described X-axis mount pad, described Y-axis drive motor is arranged on X-axis swivel base, output terminal is connected with and drives by it described Y-axis swivel base rotated, and this Y-axis swivel base is connected with described suspension centre three-dimensional regulating mechanism by Y-axis follower arm;
Described suspension centre three-dimensional regulating mechanism comprises Z axis adjustment voussoir, Z axis screw rod, Z axis adjusting seat, Y-axis adjustment voussoir, Y-axis screw rod, Y-axis adjusting seat, X-axis adjustment voussoir, X-axis screw rod and X-axis adjusting seat, this Z axis screw rod, Y-axis screw rod and X-axis screw rod are rotatably installed on Z axis adjustment voussoir, Y-axis adjustment voussoir and X-axis adjustment voussoir respectively, be equipped with the adjusting nut be connected with respective screw flight in described Z axis adjusting seat, Y-axis adjusting seat and X-axis adjusting seat, and realize with Z axis adjusts voussoir, Y-axis adjusts voussoir and X-axis adjusts voussoir relative movement by tightening respective screw rod; Described Z axis adjustment voussoir is arranged in described Y-axis follower arm, described Y-axis adjusting seat is arranged in Z axis adjusting seat by vertical mount pad, described X-axis adjustment voussoir is arranged on Y-axis adjustment voussoir, and the Hooke's hinge connecting described X-axis suspending equipment is arranged in described X-axis adjusting seat.
Wherein: the hinge place of described Hooke's hinge is provided with detects wire rope under a stretching force and form the scrambler at inclination angle between pedal line; Described Z axis adjusting seat and Z axis adjust between voussoir, Y-axis adjusting seat and Y-axis adjusts between voussoir and X-axis adjusting seat and X-axis adjust between voussoir and all leave wedge-shaped slot, all be equipped with jam-packed voussoir in each described wedge-shaped slot, each described jam-packed voussoir is all by being arranged on the fastening nut jam-packed in each adjusting seat; The two ends of described Z axis adjustment voussoir, Y-axis adjustment voussoir and X-axis adjustment voussoir are all provided with end plate, and described Z axis screw rod, Y-axis screw rod and X-axis screw rod are rotatably installed on the end plate at each self-adjusting voussoir two ends respectively by bearing;
Described constant force regulating device comprises servo electric jar and force snesor, the upper end of this force snesor is connected with described Hooke's hinge by hanging axis, lower end is connected with described servo electric jar, the push rod of this servo electric jar is connected with described wire rope by hanging joint, this wire rope is regulated tensioning by the pushrod movement of described servo electric jar or is loosened, and then realizes the size adjustment to hanging force;
Described antenna suspending equipment comprises carbon fiber suspension rod, carbon fiber bar, antenna connection leg and hanging Change-over frame, the two ends of this carbon fiber bar are connected with carbon fiber suspension rod respectively by joint spherical hinge lug ring bearing, the other end of the described carbon fiber suspension rod at two ends is connected with the both sides of described hanging Change-over frame by joint spherical hinge lug ring bearing, described carbon fiber bar is provided with the suspension centre spherical hinge lug ring bearing be connected with described wire rope, the upper/lower terminal of described hanging Change-over frame both sides is all provided with described antenna connection leg;
Described X-axis suspending equipment comprises spherical hinge lug ring bearing, bearing seat, X-axis hanging suspension rod, X-axis hanging rotating shaft and X-axis hanging web joint, this X-axis hanging suspension rod is L-shaped, one end is rotatablely equipped with the spherical hinge lug ring bearing be connected with described wire rope by bearing seat, the other end is provided with described X-axis hanging rotating shaft, and described X-axis hanging web joint is rotatably installed in this X-axis hanging rotating shaft;
Described wire rope is provided with the hanging adjusting sleeve of adjustment lineoutofservice signal pull size, this hanging adjusting sleeve comprises hanging joint, hanging adjusting lever and adjusting sleeve, the two ends of described adjusting sleeve have been threaded hanging adjusting lever respectively, and be connected with hanging joint by hanging adjusting lever, described hanging joint comprises and meets block A and meet block B, and this meets block B and is connected with described hanging adjusting lever, described in meet block A and be arranged on and connect on block B, described wire line clamp is meeting block A and is connecing between block B, and is passed by the described block A that connects;
Be connected with pull bar between described mount pad and X-axis swivel base, the two ends of this pull bar are hinged with mount pad and X-axis swivel base respectively; The material that described antenna launches follower arm, Y-axis follower arm and X-axis swivel base is carbon fiber.
Advantage of the present utility model and good effect are:
Weight dynamic balance mechanical arm of the present utility model has the features such as degree of freedom is many, structure reliable, pose is followed accurately, power controls accurately, handling safety, on ground in the face of multidimensional truss antenna development mechanism carries out servo-actuated gravitational equilibrium, multidimensional truss antenna development mechanism carries out being difficult to when launching test real-time high-precision gravitational equilibrium technical barrier on ground can be solved.
Accompanying drawing explanation
Fig. 1 is perspective view of the present utility model;
Fig. 2 is one-piece construction front view of the present utility model;
Fig. 3 is one-piece construction left view of the present utility model;
Fig. 4 A is the perspective view that the utility model connects antenna suspending equipment;
Fig. 4 B is the structural representation hanging adjusting sleeve in Fig. 4 A;
Fig. 5 A is the structural front view of the utility model antenna suspending equipment;
Fig. 5 B is the right view of Fig. 5 A;
Fig. 6 is the structural representation of the utility model suspension centre three-dimensional regulating mechanism;
Fig. 7 A is the structural front view of X-axis suspending equipment in Fig. 4 A;
Fig. 7 B is the left view of Fig. 7 A;
Fig. 8 A is that the utility model points to the perspective view of following assembly;
Fig. 8 B is that the utility model points to the structural front view of following assembly;
Fig. 8 C is the left view of Fig. 8 B;
Wherein: 1 is servo electric jar, 2 is force snesor, 3 is Hooke's hinge, 4 is scrambler, 5 is X-axis adjustment voussoir, 6 is Y-axis adjusting seat, 7 is Y-axis adjustment voussoir, 8 is Z axis adjustment voussoir, 9 is speed reduction unit, 10 is Y-axis drive motor, 11 is X-axis drive motor, 12 follow assembly for sensing, 13 is pull bar, 14 is mount pad, 15 for launching drive motor, 16 is antenna expansion follower arm, 17 is wire rope, 18 is Y-axis follower arm, 19 is suspension centre three-dimensional regulating mechanism, 20 is constant force regulating device, 21 is antenna suspending equipment, 22 is hanging adjusting sleeve, 23 is X-axis suspending equipment, 24 for launching arm suspending equipment, 25 is joint spherical hinge lug ring bearing, 26 is carbon fiber suspension rod, 27 is carbon fiber bar, 28 is suspension centre spherical hinge lug ring bearing, 29 is antenna connection leg, 30 is hanging Change-over frame, 31 is Z axis screw rod, 32 is vertical mount pad, 33 is jam-packed voussoir, 34 is adjusting nut, 35 is spherical hinge lug ring bearing, 36 is bearing seat, 37 is X-axis hanging suspension rod, 38 is deep groove ball bearing, 39 is X-axis hanging rotating shaft, 40 is X-axis hanging web joint, 41 is Y-axis swivel base, 42 is X-axis swivel base, 43 is X-axis mount pad, 44 is Z axis adjusting seat, 45 is end plate, 46 is Y-axis screw rod, 47 is X-axis adjustment voussoir, 48 is X-axis screw rod, 49 is X-axis adjusting seat, 50 is fastening nut, 51 is adjusting sleeve, 52 is hanging adjusting lever, 53 is hanging joint, 54 for meeting block A, 55 for meeting block B.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As shown in Fig. 1 ~ 3 and Fig. 4 A, the utility model comprises expansion drive motor 15, mount pad 14, antenna expansion follower arm 16, points to and follow assembly 12, suspension centre three-dimensional regulating mechanism 19, constant force regulating device 20, antenna suspending equipment 21, X-axis suspending equipment 23 and launch arm suspending equipment 24, wherein launching drive motor 15 is fixed on mount pad 14, one end that output terminal and the antenna of this expansion drive motor 15 launch follower arm 16 is connected, and the other end of antenna expansion follower arm 16 is connected with sensing and follows assembly 12.Antenna suspending equipment 21 and X-axis suspending equipment 23 are connected with respective constant force regulating device 20 respectively by wire rope 17, two constant force regulating devices 20 are pointed to the Hooke's hinge 3 of following below assembly 12 and are connected with being arranged on respectively, launch arm suspending equipment 24 by wire rope 17 be arranged on the Hooke's hinge 3 that antenna launches below follower arm 16 and be connected, X-axis suspending equipment 23 and antenna suspending equipment 21 are respectively in order to be connected X-axis and the antenna of antenna deployment mechanism.The hinge place of Hooke's hinge 3 is provided with scrambler 4, in order to detect wire rope 17 under a stretching force and the inclination angle size formed between pedal line.
As figs. 8 a to 8 c, sensing is followed assembly 12 and is comprised X-axis mount pad 43, X-axis swivel base 42, Y-axis swivel base 41, Y-axis follower arm 18, X-axis drive motor 11 and Y-axis drive motor 10, the other end that this X-axis mount pad 43 and antenna launch follower arm 16 is affixed, the both sides of X-axis swivel base 42 one end are rotatably installed on X-axis mount pad 43 respectively by bearing, X-axis drive motor 11 and speed reduction unit 9 are fixed in X-axis mount pad 43 respectively, and be connected with the either end of X-axis swivel base 42, X-axis drive motor 11 drives X-axis swivel base 42 around X-axis drive motor 11 output shaft rotation by speed reduction unit 9, the other end of X-axis swivel base 42 is provided with Y-axis drive motor 10 and speed reduction unit 9, and output terminal is connected with and drives by it Y-axis swivel base 41 rotated around Y-axis drive motor 10, and Y-axis swivel base 41 also rotates with X-axis swivel base 42.Be connected with suspension centre three-dimensional regulating mechanism 19 by Y-axis follower arm 18 at Y-axis swivel base 41.Be connected with pull bar 13 between mount pad 14 and X-axis swivel base 42, the two ends of this pull bar 13 are hinged with mount pad 14 and X-axis swivel base 42 respectively, to ensure that X-axis swivel base 42 drives security and stability when rotating at X-axis drive motor 11.
As shown in Figure 6, suspension centre three-dimensional regulating mechanism 19 comprises Z axis adjustment voussoir 8, Z axis screw rod 31, Z axis adjusting seat 44, Y-axis adjustment voussoir 7, Y-axis screw rod 46, Y-axis adjusting seat 6, X-axis adjustment voussoir 47, X-axis screw rod 48 and X-axis adjusting seat 49, Z axis adjustment voussoir 8 is fixed in the end of Y-axis follower arm 18, the two ends of Z axis adjustment voussoir 8 are equipped with end plate 45, the two ends of Z axis screw rod 31 are rotatably installed on the end plate 45 at two ends by bearing, the adjusting nut 34 be threaded with Z axis screw rod 31 is installed in Z axis adjusting seat 44, the movement of Z axis adjusting seat 44 on Z axis adjustment voussoir 8 can be realized by turning Z axis screw rod 31, Z axis adjusting seat 44 and Z axis adjust between voussoir 8 and leave wedge-shaped slot, are all equipped with jam-packed voussoir 33 in wedge-shaped slot, and each jam-packed voussoir 33 all by being arranged on fastening nut 50 jam-packed in Z axis adjusting seat 44, and then makes the position of Z axis adjusting seat 44 fix.Y-axis adjusting seat 6 is fixed in Z axis adjusting seat 44 by vertical mount pad 32, is provided with adjusting nut 34 in Y-axis adjusting seat 6; The two ends of Y-axis adjustment voussoir 7 are equipped with end plate 45, the two ends of Y-axis screw rod 46 are rotatably installed on the end plate 45 at two ends by bearing, and be threaded with the adjusting nut 34 in Y-axis adjusting seat 6, by turn Y-axis screw rod 46 can implement Y-axis adjustment voussoir 7 move relative to Y-axis adjusting seat 6; Y-axis adjusting seat 6 and Y-axis adjust between voussoir 7 and leave wedge-shaped slot, are all equipped with jam-packed voussoir 33 in wedge-shaped slot, and each jam-packed voussoir 33 all by being arranged on fastening nut 50 jam-packed in Y-axis adjusting seat 6, and then makes the position of Y-axis adjusting seat 6 fix.X-axis adjustment voussoir 47 is fixed on Y-axis adjustment voussoir 7, the two ends of X-axis adjustment voussoir 47 are equipped with end plate 45, the two ends of X-axis screw rod 48 are rotatably installed on the end plate 45 at two ends by bearing, the adjusting nut 34 be threaded with X-axis screw rod 48 being installed in X-axis adjusting seat 49, the movement of X-axis adjusting seat 49 on X-axis adjustment voussoir 47 can being realized by turning X-axis screw rod 48; X-axis adjusting seat 49 and X-axis adjust between voussoir 47 and leave wedge-shaped slot, are all equipped with jam-packed voussoir 33 in wedge-shaped slot, and each jam-packed voussoir 33 all by being arranged on fastening nut 50 jam-packed in X-axis adjusting seat 49, and then makes the position of X-axis adjusting seat 49 fix.The Hooke's hinge 3 connecting X-axis suspending equipment 23 is arranged in X-axis adjusting seat 49.
As shown in Figure 2, constant force regulating device 20 comprises servo electric jar 1 and force snesor 2, the upper end of this force snesor 2 is connected with Hooke's hinge 3 by hanging axis, lower end is connected with servo electric jar 1, the push rod of this servo electric jar 1 is connected with wire rope 17 by hanging joint, this wire rope 17 is regulated tensioning by the pushrod movement of servo electric jar 1 or is loosened, and then realizes the size adjustment to hanging force.
As Fig. 5 A, shown in Fig. 5 B, antenna suspending equipment 21 comprises joint spherical hinge lug ring bearing 25, carbon fiber suspension rod 26, carbon fiber bar 27, suspension centre spherical hinge lug ring bearing 28, antenna connection leg 29 and hanging Change-over frame 30, the two ends of this carbon fiber bar 27 are connected with carbon fiber suspension rod 26 respectively by joint spherical hinge lug ring bearing 25, the other end of the carbon fiber suspension rod 26 at two ends is connected by the both sides of joint spherical hinge lug ring bearing 25 with hanging Change-over frame 30, the centre of carbon fiber bar 27 is provided with the suspension centre spherical hinge lug ring bearing 28 be connected with wire rope 17, hang the upper of Change-over frame 30 both sides, lower two ends are all provided with antenna connection leg 29.
As shown in Figure 7 A, 7 B, X-axis suspending equipment 23 comprises spherical hinge lug ring bearing 35, bearing seat 36, X-axis hanging suspension rod 37, deep groove ball bearing 38, X-axis hanging rotating shaft 39 and X-axis hanging web joint 40, this X-axis hanging suspension rod 37 is L-shaped, one end is rotatablely equipped with the spherical hinge lug ring bearing 35 be connected with wire rope 17 by bearing seat 36, the other end is provided with X-axis hanging rotating shaft 39, and X-axis hanging web joint 40 is rotatably installed in X-axis hanging rotating shaft 39 by deep groove ball bearing 38.X-axis web joint 40 can be hung rotating shaft 39 around X-axis and rotate, and spherical hinge lug ring bearing 35 can rotate relative to X-axis hanging suspension rod 37.
Wire rope 17 is provided with the hanging adjusting sleeve 22 of adjustment wire rope 17 pulling force size.As shown in Figure 4 B, this hanging adjusting sleeve 22 comprises hanging joint 53, hanging adjusting lever 52 and adjusting sleeve 51, and adjusting sleeve 51 is the rectangular parallelepiped of hollow, and two ends are connected with nut, and the hanging adjusting lever 52 that has been threaded respectively; One end of every root hanging adjusting lever 52 is positioned at adjusting sleeve 51, and the other end is connected with hanging joint 53.Hanging joint 53 comprises and meets block A54 and meet block B55, and this end face meeting block B55 is L-shaped, and one side is affixed with the other end of hanging adjusting lever 52, and another side has screw.Block A54 is square, has screw equally.Wire rope 17 is clipped in and meets block A54 and connect between block B55, and passes by meeting block A54, meets block A54 and is fixed in and connects on block B55, clamping steel wire rope 17.
The material that antenna of the present utility model launches follower arm 16, Y-axis follower arm 18 and X-axis swivel base 42 can be carbon fiber.
Principle of work of the present utility model is:
Before antenna deployment mechanism carries out ground test, be connected with suspending equipment by the suspension centre of the utility model gravitational equilibrium mechanical arm and the interface of suspending equipment and multidimensional truss antenna development mechanism connected, X-axis suspending equipment 23 and antenna suspending equipment 21 were arranged in the vertical plane of each assembly barycenter.When carrying out gravitational equilibrium, regulate suspension centre three-dimensional regulating mechanism 19 (manually turning Z axis screw rod 31, Y-axis screw rod 46 or X-axis screw rod 48) and then make each wire rope 17 be in vertical state; Regulate the length of hanging adjusting sleeve 22 (adjusting distance between hanging joint 53 and adjusting sleeve 51 by turning hanging adjusting lever 52) by the pulling force size adjustment of wire rope 17 to actual demand value.Antenna deployment mechanism drives antenna antenna expansion process in simulation space on simulation wall, and gravitational equilibrium mechanical arm carries out pose to development mechanism and antenna and follows.When there is position deviation in gravitational equilibrium mechanical arm and development mechanism, spherical hinge lug ring bearing 35 is connected respectively and Hooke's hinge 3 has rotational freedom due to wire rope 17 two ends, wire rope 17 can form an inclination angle with pedal line under a stretching force, inclination angle size to be reflected on Hooke's hinge 3 and to be measured by the orthogonal scrambler 4 being arranged on Hooke's hinge 3 rotating shaft place, control system (control system of the present utility model is prior art) controls to launch drive motor 15 according to the dip angle signal measured, X-axis drive motor 11 and Y-axis drive motor 10, each drive motor respectively driven antenna launches follower arm 16, X-axis swivel base 42 and Y-axis swivel base 41 pairs of position tracking errors are revised, simultaneously, the force snesor 2 be arranged on servo electric jar 1 measures size and the change of wire rope 17 pulling force, servo electric jar 1 extends according to the changing value of pulling force or the size of its push rod to wire rope 17 hanging force that bounce back regulates, and the constant force that the fluctuation reducing hanging force realizes in error allowed band is hung.Gravitational equilibrium mechanical arm of the present utility model has three series connection rotational freedoms, namely launch that drive motor 15 driven antenna launches that follower arm 16 is rotated, X-axis drive motor 11 drives that X-axis swivel base 42 rotates, Y-axis drive motor 10 drives Y-axis swivel base 41 to rotate, the expansion campaign of antenna deployment mechanism can be followed well and point to motion, position tracking error is revised.X-axis suspending equipment 23 and antenna suspending equipment 21 can make the extended line of wire rope 17 under vertical state cross development mechanism X-axis and antenna barycenter, so just achieve and in real time the hanging of constant force barycenter is carried out to development mechanism while to development mechanism location following, and then in the weightlessness of space state of ground simulation development mechanism, Mechanics Performance Testing is carried out to it.
Claims (10)
1. a multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm, it is characterized in that: comprise and launch drive motor (15), mount pad (14), antenna launches follower arm (16), assembly (12) is followed in sensing, suspension centre three-dimensional regulating mechanism (19), constant force regulating device (20), antenna suspending equipment (21), X-axis suspending equipment (23) and expansion arm suspending equipment (24), wherein launching drive motor (15) is arranged on described mount pad (14), output terminal is connected with sensing by described antenna expansion follower arm (16) and follows assembly (12), described antenna suspending equipment (21) and X-axis suspending equipment (23) are connected with respective constant force regulating device (20) respectively by wire rope (17), each described constant force regulating device (20) respectively be arranged on the Hooke's hinge (3) that described sensing follows on assembly (12) and be connected, described expansion arm suspending equipment (24) by wire rope (17) be arranged on the Hooke's hinge (3) that described antenna launches in follower arm (16) and be connected,
Described sensing is followed assembly (12) and is comprised X-axis mount pad (43), X-axis swivel base (42), Y-axis swivel base (41), X-axis drive motor (11) and Y-axis drive motor (10), this X-axis mount pad (43) is arranged on described antenna and launches in follower arm (16), described X-axis swivel base (42) is rotatably installed on this X-axis mount pad (43), and drive rotation by the X-axis drive motor (11) be arranged on described X-axis mount pad (43), described Y-axis drive motor (10) is arranged on X-axis swivel base (42), output terminal is connected with and drives by it described Y-axis swivel base (41) rotated, this Y-axis swivel base (41) is connected with described suspension centre three-dimensional regulating mechanism (19) by Y-axis follower arm (18),
Described suspension centre three-dimensional regulating mechanism (19) comprises Z axis adjustment voussoir (8), Z axis screw rod (31), Z axis adjusting seat (44), Y-axis adjustment voussoir (7), Y-axis screw rod (46), Y-axis adjusting seat (6), X-axis adjustment voussoir (47), X-axis screw rod (48) and X-axis adjusting seat (49), this Z axis screw rod (31), Y-axis screw rod (46) and X-axis screw rod (48) are rotatably installed in Z axis adjustment voussoir (8) respectively, Y-axis adjustment voussoir (7) and X-axis adjust on voussoir (47), described Z axis adjusting seat (44), the adjusting nut (34) be connected with respective screw flight is equipped with in Y-axis adjusting seat (6) and X-axis adjusting seat (49), and realize adjusting voussoir (8) with Z axis by tightening respective screw rod, Y-axis adjustment voussoir (7) and X-axis adjustment voussoir (47) relative movement, described Z axis adjustment voussoir (8) is arranged on described Y-axis follower arm (18), described Y-axis adjusting seat (6) is arranged in Z axis adjusting seat (44) by vertical mount pad (32), described X-axis adjustment voussoir (47) is arranged in Y-axis adjustment voussoir (7), and the Hooke's hinge (3) connecting described X-axis suspending equipment (23) is arranged on described X-axis adjusting seat (49).
2. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: the hinge place of described Hooke's hinge (3) is provided with detects wire rope (17) under a stretching force and form the scrambler (4) at inclination angle between pedal line.
3. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: described Z axis adjusting seat (44) and Z axis adjust between voussoir (8), Y-axis adjusting seat (6) and Y-axis adjusts between voussoir (7) and X-axis adjusting seat (49) and X-axis adjust between voussoir (47) and all leave wedge-shaped slot, all be equipped with jam-packed voussoir (33) in each described wedge-shaped slot, each described jam-packed voussoir (33) is all by being arranged on fastening nut (50) jam-packed in each adjusting seat.
4. by the multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm described in claim 1 or 3, it is characterized in that: the two ends that described Z axis adjustment voussoir (8), Y-axis adjustment voussoir (7) and X-axis adjust voussoir (47) are all provided with end plate (45), and described Z axis screw rod (31), Y-axis screw rod (46) and X-axis screw rod (48) are rotatably installed on the end plate (45) at each self-adjusting voussoir two ends respectively by bearing.
5. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: described constant force regulating device (20) comprises servo electric jar (1) and force snesor (2), the upper end of this force snesor (2) is connected with described Hooke's hinge (3) by hanging axis, lower end is connected with described servo electric jar (1), the push rod of this servo electric jar (1) is connected with described wire rope (17) by hanging joint, this wire rope (17) is regulated tensioning by the pushrod movement of described servo electric jar (1) or is loosened, and then the size adjustment realized hanging force.
6. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: described antenna suspending equipment (21) comprises carbon fiber suspension rod (26), carbon fiber bar (27), antenna connection leg (29) and hanging Change-over frame (30), the two ends of this carbon fiber bar (27) are connected with carbon fiber suspension rod (26) respectively by joint spherical hinge lug ring bearing (25), the other end of the described carbon fiber suspension rod (26) at two ends is connected with the both sides of described hanging Change-over frame (30) by joint spherical hinge lug ring bearing (25), described carbon fiber bar (27) is provided with the suspension centre spherical hinge lug ring bearing (28) be connected with described wire rope (17), described hanging Change-over frame (30) both sides upper, lower two ends are all provided with described antenna connection leg (29).
7. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: described X-axis suspending equipment (23) comprises spherical hinge lug ring bearing (35), bearing seat (36), X-axis hanging suspension rod (37), X-axis hanging rotating shaft (39) and X-axis hanging web joint (40), this X-axis hanging suspension rod (37) is L-shaped, one end is rotatablely equipped with by bearing seat (36) the spherical hinge lug ring bearing (35) be connected with described wire rope (17), the other end is provided with described X-axis hanging rotating shaft (39), described X-axis hanging web joint (40) is rotatably installed in this X-axis hanging rotating shaft (39).
8. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: the hanging adjusting sleeve (22) described wire rope (17) being provided with adjustment wire rope (17) pulling force size, this hanging adjusting sleeve (22) comprises hanging joint (53), hanging adjusting lever (52) and adjusting sleeve (51), the two ends of described adjusting sleeve (51) have been threaded hanging adjusting lever (52) respectively, and be connected with hanging joint (53) by hanging adjusting lever (52), described hanging joint (53) comprises and meets block A (54) and meet block B (55), this meets block B (55) and is connected with described hanging adjusting lever (52), the described block A (54) that connects is arranged on and connects on block B (55), described wire rope (17) is clipped in and meets block A (54) and connect between block B (55), and passed by the described block A (54) that connects.
9. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: be connected with pull bar (13) between described mount pad (14) and X-axis swivel base (42), the two ends of this pull bar (13) are hinged with mount pad (14) and X-axis swivel base (42) respectively.
10. by multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm according to claim 1, it is characterized in that: the material that described antenna launches follower arm (16), Y-axis follower arm (18) and X-axis swivel base (42) is carbon fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520771885.5U CN204964218U (en) | 2015-09-30 | 2015-09-30 | Multidimension framework formula satellite antenna deployment mechanism gravity balance arm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520771885.5U CN204964218U (en) | 2015-09-30 | 2015-09-30 | Multidimension framework formula satellite antenna deployment mechanism gravity balance arm |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204964218U true CN204964218U (en) | 2016-01-13 |
Family
ID=55059274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520771885.5U Withdrawn - After Issue CN204964218U (en) | 2015-09-30 | 2015-09-30 | Multidimension framework formula satellite antenna deployment mechanism gravity balance arm |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204964218U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181373A (en) * | 2015-09-30 | 2015-12-23 | 中国科学院沈阳自动化研究所 | Gravity balancing mechanical arm of satellite antenna expanding mechanism of multi-dimensional structure |
| CN106324574A (en) * | 2016-11-30 | 2017-01-11 | 上海卫星工程研究所 | Ground test method for RF compatibility of synthetic aperture radar satellite |
| CN106330359A (en) * | 2016-11-30 | 2017-01-11 | 上海卫星工程研究所 | Method for compatibility test fully-unfolded RF |
| CN109118931A (en) * | 2018-08-03 | 2019-01-01 | 上海宇航系统工程研究所 | A kind of zero-g for big displacement multidimensional deployed configuration is without friction expanding unit |
-
2015
- 2015-09-30 CN CN201520771885.5U patent/CN204964218U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181373A (en) * | 2015-09-30 | 2015-12-23 | 中国科学院沈阳自动化研究所 | Gravity balancing mechanical arm of satellite antenna expanding mechanism of multi-dimensional structure |
| CN105181373B (en) * | 2015-09-30 | 2017-06-30 | 中国科学院沈阳自动化研究所 | A kind of multidimensional framework type satellite antenna development mechanism gravitational equilibrium mechanical arm |
| CN106324574A (en) * | 2016-11-30 | 2017-01-11 | 上海卫星工程研究所 | Ground test method for RF compatibility of synthetic aperture radar satellite |
| CN106330359A (en) * | 2016-11-30 | 2017-01-11 | 上海卫星工程研究所 | Method for compatibility test fully-unfolded RF |
| CN106330359B (en) * | 2016-11-30 | 2019-03-29 | 上海卫星工程研究所 | Full-expasion Radio Frequency Compatibility test method |
| CN109118931A (en) * | 2018-08-03 | 2019-01-01 | 上海宇航系统工程研究所 | A kind of zero-g for big displacement multidimensional deployed configuration is without friction expanding unit |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204964218U (en) | Multidimension framework formula satellite antenna deployment mechanism gravity balance arm | |
| CN107830324B (en) | Arm supporting structure | |
| CN109018430B (en) | Rotorcraft blade performance test bench | |
| CN107499533A (en) | A kind of full machine drop test device and full machine drop-test method | |
| CN104326368A (en) | Gravity compensation device for solar wing low temperature unfolding experiment | |
| CN102862688B (en) | Sling-type low-gravity simulation tension control buffer mechanism and adjustment method | |
| CN113460338B (en) | Multifunctional antenna gravity unloading device | |
| CN108760220B (en) | External balance tailstock supporting device for measuring six-degree-of-freedom mechanism interference | |
| CN105599922A (en) | A 1/6g low gravity balance hoisting device | |
| CN114414181A (en) | A modularization experimental apparatus for civil engineering structure dynamic and static test | |
| CN203579153U (en) | Balance arm mechanism for vertical assembly | |
| CN110395415B (en) | Universal zero-gravity unloading device | |
| CN105067456A (en) | Impact test device for building board | |
| CN202494560U (en) | Portable driving mechanism for testing high-speed elevator speed governor | |
| CN105181373A (en) | Gravity balancing mechanical arm of satellite antenna expanding mechanism of multi-dimensional structure | |
| CN203011579U (en) | Air spring detection device | |
| CN209910943U (en) | Wind tunnel balance terminal attitude measuring device | |
| CN111044221A (en) | Three-dimensional inertia testboard adjusting device of unmanned aerial vehicle | |
| CN214520057U (en) | Three-axis turntable with self-stabilizing function | |
| CN107246993A (en) | A kind of mechanical property test device | |
| CN114216688A (en) | Thrust measuring device of miniature turbine engine | |
| CN207964062U (en) | A kind of in-orbit mass measurer ground calibrating installation | |
| CN209764167U (en) | Air duct clamping mechanism and air duct air quantity sensor using same | |
| CN209117256U (en) | Small drone weight center of gravity measuring device | |
| CN113252315B (en) | Follow-up gravity unloading suspension device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160113 Effective date of abandoning: 20170630 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20160113 Effective date of abandoning: 20170630 |