CN114180213B - Helicopter rotor folding and fixing system - Google Patents

Abstract

The invention provides a helicopter rotor folding and fixing system, comprising: a saddle bracket (1), a support truss (2) and a blade locking chuck (3); the saddle bracket (1) is clamped above the tail beam of the helicopter, The supporting truss (2) is fixedly arranged above the saddle-shaped support (1), and a plurality of paddle locking chucks (3) are fixedly arranged on the supporting truss (2), respectively clamping a helicopter blade; the saddle-shaped support ( 1) It includes two bent front joint brackets (102), transverse tie rods (106) and two bent rear joint brackets (108). Both the front joint brackets (102) and the rear joint brackets (108) use The adjustable transverse tie rod (106) is connected, and the bottom of the front joint support (102) and the rear joint support (108) are connected with the tail beam joint (4) on the tail beam using a single and double lug structure, and the single and double lug structures in the single and double lug structure are connected. An eccentric shaft sleeve (103) is arranged on the ear. Easy to adjust, anti-rotation, high strength, less parts.

Description

A Helicopter Rotor Folding Fixing System

technical field

The invention belongs to the design field of a helicopter rotor folding device, in particular to a helicopter rotor folding and fixing system.

Background technique

Helicopters are widely used in complex environments such as mountains, oceans, and deserts because of their unique rotor configuration, which can perform various actions such as hovering, vertical take-off and landing, level flight, and side flight. However, after the helicopter is installed with rotors, the vertical projected area of the entire body will be significantly increased, and it will take up a large space when the whole machine is transported and stored, and it is difficult to meet the loading requirements of ships, large transport aircraft and other carrier platforms. Therefore, by redesigning the hinge structure at the hub, the engineers realized the folding of multiple blades, effectively reducing the transportation and storage space of the helicopter.

However, after the blades are folded, they still cannot meet the shipping requirements. During the shipping process, due to the limitations of sea conditions, road conditions and transportation methods, the helicopter will inevitably experience bumps and vibrations. The shimmy motion can easily damage the blade itself and the body structure.

Therefore, there is an urgent need for a device or system capable of fixing the helicopter rotor after being folded, so as to avoid the damage caused by the inability to limit the movement during transportation, and ensure the integrity of the helicopter's technical and tactical effectiveness.

Contents of the invention

The invention provides a helicopter rotor folding and fixing system, which solves the problem that the helicopter will inevitably bump and vibrate due to the limitations of sea conditions, road conditions and carrying methods during the shipment of existing blades, resulting in damage to the blades.

The invention provides a helicopter rotor folding and fixing system, comprising: a saddle bracket 1, a supporting truss 2 and a blade locking chuck 3;

The saddle bracket 1 is clamped above the tail boom of the helicopter, the support truss 2 is fixedly arranged above the saddle bracket 1, and a plurality of blade locking chucks are fixedly arranged on the support truss 2 3. Each blade locking chuck 3 is used to respectively clamp a helicopter blade;

The saddle bracket 1 includes two bent front joint supports 102, a transverse tie rod 106 and two bent rear joint supports 108, and the two bent front joint supports 102 and two bent rear joint supports The brackets 108 are respectively connected by transverse tie rods 106. The transverse tie rods 106 are length-adjustable tie rods positioned above the tail beam of the helicopter, and the front joint support 102 and the rear joint support 108 on the same side of the tail beam of the helicopter are connected by cross beams;

The bottoms of the front joint support 102 and the rear joint support 108 are connected with the tail beam joint 4 on the tail beam by a single and double ear structure, and an eccentric bushing 103 is arranged on the single ear in the single and double ear structure.

Optionally, the supporting truss 2 includes: a portal frame, 4 diagonal stay rods 201, two-way screw sleeves 205, and three-phase joints 207;

Two diagonal stay rods 201 are respectively arranged on the inside and one side of the door-shaped frame, and a three-phase joint 207 is arranged on the bottom of the door-shaped frame;

The bottom of the door-shaped frame, the bottom of the two diagonal stay rods 201 arranged inside the door-shaped frame and the top of the saddle-shaped bracket 1 are fixedly connected by a three-phase joint 207 using a single and double-ear structure;

The bottoms of the two diagonal stay rods 201 arranged on the side of the door frame are fixedly connected to the top of the saddle bracket 1 with a single and double ear structure;

The top beam of the portal frame is provided with a two-way screw sleeve 205 for adjusting the width of the top beam.

Optionally, the saddle bracket 1 further includes: a pedal 105;

A pedal 105 is also arranged between the front joint support 102 and the rear joint support 108 on the same side of the tail boom of the helicopter.

Optionally, there are multiple beams connected to the pedal 105 .

Optionally, the saddle bracket 1 and the support truss 2 are composed of square tubes.

Optionally, the number of the blade locking chucks 3 is determined according to the number of helicopter blades, and each blade locking chuck 3 is symmetrically distributed on the support truss 2 with the helicopter heading as the axis of symmetry.

Optionally, the blade locking chuck 3 is fixedly connected to the support truss 2 through a triangular structure bracket.

Optionally, the two longitudinal beams 206 of the portal frame are made of titanium alloy or stainless steel.

The invention provides a helicopter rotor folding and fixing system, comprising: a saddle bracket 1, a support truss 2 and a blade locking chuck 3; the saddle bracket 1 is clamped above the helicopter tail beam, and the support truss 2 is fixedly arranged Above the bracket 1, a plurality of blade locking chucks 3 are fixedly arranged on the supporting truss 2, and each blade locking chuck 3 is used to respectively clamp a helicopter blade; the saddle bracket 1 includes two bent The front joint support 102, the transverse tie rod 106 and the two bent rear joint supports 108, the two bent front joint supports 102 and the two bent rear joint supports 108 are respectively connected by the transverse tie rod 106, and the transverse tie rod 106 is The length-adjustable pull rod is positioned at the top of the tail beam of the helicopter, and the front joint support 102 and the rear joint support 108 on the same side of the helicopter tail beam are connected by a beam; The beam joint 4 is connected by a single and double lug structure, and an eccentric shaft sleeve 103 is arranged on the single lug in the single and double lug structure. The helicopter rotor folding and fixing system provided by the invention integrates easy adjustment, anti-turnover, high strength, few parts and quick clamping, high integration, outstanding performance, reliable connection between structures, and can be used under the condition of relatively small manual operation force. It can realize fast clamping, which is very suitable for the restraint after the helicopter rotor is folded, and can be extended to various needs of helicopter blade folding. It has good innovation, practicability and economy.

Description of drawings

Fig. 1 is the structural representation of the helicopter rotor folding and fixing system provided by the present invention;

Fig. 2 is the structural representation of the saddle-shaped support provided by the present invention;

Fig. 3 is the structural representation of the support truss provided by the present invention;

Explanation of reference signs:

1—saddle bracket; 2—support truss; 3—blade locking chuck;

4—Tail beam joint; 101—First quick release pin; 102—Front joint bracket;

103—eccentric shaft sleeve; 104—the first beam; 105—pedal;

106—horizontal tie rod; 107—second beam; 108—rear joint bracket;

201—diagonal tie rod; 202—the third beam; 203—strengthening beam;

204—Chuck support rod; 205—Two-way screw sleeve; 206—Longitudinal beam;

207—three-phase joint; 208—second quick release pin; 2051—screw sleeve;

2052—long screw; 2053—square shaft; 2054—short screw.

Detailed ways

The helicopter rotor folding and fixing system provided by the present invention will be explained below in conjunction with the accompanying drawings.

As shown in Figures 1-3, the present invention proposes a helicopter rotor folding and fixing system, which is mainly composed of a saddle bracket 1, a supporting truss 2 and a blade locking chuck 3.

After the helicopter rotor is folded, the saddle bracket 1, the support truss 2 and the blade locking chuck 3 are erected on the tail boom joint 4 in sequence. Put the blades into the blade locking chuck 3 in turn and lock them, so that the helicopter blades and the tail boom form an integral structure, and the inertial load received by the folded helicopter rotor is transmitted to the body.

As shown in Figure 2, the saddle support 1 is made up of the first quick-release pin 101, the front joint support 102, the eccentric bushing 103, the first beam 104, the pedal 105, the lateral pull rod 106, the second cross beam 107 and the rear joint support 108 compositions.

The front connector bracket 102 is mainly composed of three parts including a bracket, 5 three-hole binaural connectors and 2 single-hole binaural connectors. The passed three-hole double ear joint is respectively connected with the first beam 104 , the pedal 105 and the second beam 107 from bottom to top. The two single-hole lug joints passed through are respectively connected to the transverse tie rod 106 and the support truss 2 .

The front joint bracket 102 is connected to the eccentric bushing 103 through the double lug structure at the lower end of the bracket arranged on it, and is connected to the tail beam joint 4 through the first quick release pin 101 . The fine adjustment requirement when the first quick release pin 101 is inserted is realized by the eccentric bushing 103 .

The transverse tie rod 106 is a pull rod with adjustable length, which can be provided with two parts, one part is composed of a single-ear joint and a short rod with external threads, and the other part is composed of a single-ear joint and a long rod with internal threads. Cooperate to realize the requirement of length adjustment within a certain range, so as to adapt to different batches of helicopter tail beams, avoid the problem that the equipment cannot be installed due to the shape and position error of the tail beam joint 4 during installation, and improve the interchangeability of the rotor folding and fixing system sex and versatility.

The pedal 105 is provided with 2 to 3 hollow beams in the horizontal direction for the operator to step on.

The rear connector bracket 108 is similar in structure to the front connector bracket 102, and also includes three parts: a bracket, a three-hole binaural joint and a single-hole binaural joint. The main difference between the front joint support 102 and the rear joint support 108 is that the quantity and joint direction of the three-hole double ear joints are different.

As shown in Figure 3, the supporting truss 2 includes a portal frame, the portal frame includes a top beam and two longitudinal beams 206, and the supporting truss 2 also includes: 4 diagonal stay rods 201, a third beam 202, a reinforcing beam 203, Chuck support rod 204 , two-way screw sleeve 205 , three-phase connector 207 and second quick release pin 208 .

Diagonal tie rods 201 have the same structure as transverse tie rods 106 but different lengths. The tilting torque of support truss 2 is transmitted to saddle bracket 1 through diagonal stay rods 201 , ensuring the strength and stability of the overall structure. In addition, since the lug joints at the ends of the four diagonal stay rods 201 can be adjusted to a certain length through internal threads, the length adjustment of the support truss 2 in multiple directions is realized, installation errors are compensated, and the overall adaptability of the system is improved.

The support truss 2 is provided with five third crossbeams 202 and five chuck support rods 204, and each chuck support rod 204 is equipped with a paddle locking chuck 1 to fit the blade with 5 paddles. helicopter.

Two-way screw sleeve 205 is made of screw sleeve 2051 , long screw rod 2052 , square shaft 2053 and short screw rod 2054 . Wherein, both the long screw 2052 and the short screw 2054 have square grooves for inserting the square shaft 2053, and the long screw 2052 and the short screw 2054 have opposite thread directions and the same pitch. The screw sleeve 2051 is provided with internal threads respectively matched with the long screw 2052 and the short screw 2054 . In use, the long screw 2052 and the short screw 2054 can be approached or separated by rotating the screw sleeve 2051 . In addition, due to the existence of the square shaft 2053, the long screw 2052 and the short screw 2054 can only move in the axial direction without relative rotation, which ensures the assembly relationship of other parts and can effectively improve the The strength and rigidity of the two-way threaded sleeve 205.

The three-phase connector 207 has two single-hole double-ear joints and one three-hole double-ear joint, and the two single-hole double-ear joints are respectively connected with the upper ends of the diagonal stay rod 201 and the rear joint bracket 108 .

Among the various components of the support truss 2 , the parts connected by the single-hole lug joint are all locked by the second quick release pin 208 .

The blade locking chuck 3 is used to clamp the blade, and any existing clamping device can be selected according to the specific shape of the blade. Wherein, the blade locking chuck 3 is connected with the chuck support rod 204 of the supporting truss 2 through a quick release pin, and the blade locking chuck 3 and the supporting truss 2 form an integral structure.

The helicopter rotor folding and fixing system provided by the invention has few parts, high modularization degree and good maintainability. It is convenient and quick to use, and has high practicability, which can meet the needs of helicopter rotors for fast folding and fixing and rapid deployment to restore combat effectiveness.

The invention adopts the saddle-shaped bracket, the support truss and the paddle locking chuck to respectively realize the functions of connecting the body structure, load transmission and structure fine-tuning, and paddle clamping and fixing. Its main advantages are:

The eccentric bushing is designed on the saddle bracket to fine-tune and compensate the shape and position error when installing the tail beam joint of different sorties of helicopters;

The saddle-shaped bracket organically combines the whole frame beam through the bracket of multiple double-ear joints, which reduces the number of connecting parts and improves interchangeability and versatility;

The saddle-shaped bracket can meet the length adjustment requirements within a certain range by setting the horizontal pull rod;

The support truss is used with two-way screw sleeves through diagonal stays, which effectively increases the flexibility of the system and increases the anti-turning ability;

The support truss effectively transmits the load on the blade locking chuck to the body through the transverse and longitudinal beams, which effectively increases the rigidity of the system.

The helicopter rotor folding and fixing system provided by the present invention also uses quick-release pins to connect multiple connecting parts, which can greatly improve the efficiency of disassembly and assembly, and increase the practicability of the system.

The helicopter rotor folding and fixing system provided by the invention integrates easy adjustment, anti-turnover, high strength, few parts and fast clamping, high integration, outstanding performance, reliable connection between structures, and can be used under the condition of relatively small manual operation force. It can realize fast clamping, which is very suitable for the restraint after the helicopter rotor is folded, and can be extended to various needs of helicopter blade folding. It has good innovation, practicability and economy.

Claims (7)

1. A helicopter rotor folding and fixing system is characterized in that, comprising: a saddle support (1), a support truss (2) and a blade locking chuck (3); The saddle bracket (1) is clamped above the tail beam of the helicopter, the support truss (2) is fixedly arranged above the saddle bracket (1), and the support truss (2) is fixedly arranged with multiple The blade locking chucks (3), each of the blade locking chucks (3) is used to respectively clamp a helicopter blade; The saddle-shaped support (1) includes two bent front joint supports (102), a transverse tie rod (106) and two bent rear joint supports (108), and the two bent front joint supports ( 102) and the two bent rear joint brackets (108) are respectively connected by transverse tie rods (106). The front joint support (102) and the rear joint support (108) of the side are connected by a crossbeam; The bottoms of the front joint bracket (102) and the rear joint bracket (108) are connected with the tail beam joint (4) on the tail boom by a single and double lug structure, and an eccentric bushing (103) is arranged on the single lug in the single and double lug structure ; The supporting truss (2) includes: a portal frame, 4 diagonal stay rods (201), two-way screw sleeves (205), and three-phase joints (207); Two diagonal stay rods (201) are respectively arranged on the inside and one side of the door-shaped frame, and a three-phase joint (207) is arranged on the bottom of the door-shaped frame; The bottom of the door-shaped frame, the bottom of the two diagonal stay rods (201) arranged inside the door-shaped frame and the top of the saddle-shaped bracket (1) are fixedly connected by a three-phase joint (207) using a single and double-ear structure; The bottoms of the two diagonal stay rods (201) arranged on the side of the door frame are fixedly connected to the top of the saddle bracket (1) by a single and double ear structure; A two-way threaded sleeve (205) is provided on the top beam of the portal frame for adjusting the width of the top beam. 2. The system according to claim 1, characterized in that, the saddle bracket (1) further comprises: a foot pedal (105); A pedal (105) is also arranged between the front joint support (102) and the rear joint support (108) on the same side of the tail beam of the helicopter. 3. The system according to claim 2, characterized in that, there are multiple beams connected in the footboard (105). 4. The system according to claim 1, characterized in that, the saddle bracket (1) and the support truss (2) are composed of square tubes. 5. The system according to claim 1, characterized in that, the number of the blade locking chucks (3) is determined according to the number of helicopter blades, and each of the blade locking chucks (3) follows the heading of the helicopter. is the axis of symmetry, symmetrically distributed on the support truss (2). 6. The system according to claim 1, characterized in that the blade locking chuck (3) is fixedly connected to the support truss (2) through a triangular structure bracket. 7. The system according to claim 1, characterized in that the two longitudinal beams (206) of the portal frame are made of titanium alloy or stainless steel.

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