CN-224211262-U - Aviation seat energy absorber

Abstract

The invention belongs to the technical field of aviation seat safety, and particularly relates to an aviation seat energy absorbing device which comprises seat legs, wherein a first side surface of the upper part of each seat leg is provided with a chute in the vertical direction, a sliding block which can be fixedly connected with a basin framework is arranged on each chute in a sliding manner, a second side surface adjacent to the first side surface of each seat leg is fixedly provided with two bolt shafts, annular steel belts are sleeved on the two bolt shafts, pin mounting holes are formed in the steel belts, mounting lugs extend to the steel belt side of each sliding block, and shear pins with frangible grooves are connected to the second side surface of each seat leg in a threaded manner through the pin mounting holes and through holes in the mounting lugs.

Inventors

• CHEN YUN
• ZHOU QINGHUA
• SUN CHUAN
• LUO LIQIONG
• LIU JUNLIANG
• ZHOU ENMING
• YANG JUNLIN
• LI GUOMIN

Assignees

• 浙江天成航空科技有限公司

Dates

Publication Date

20260508

Application Date

20250806

Claims (10)

1. 1. The aviation seat energy absorbing device is characterized in that a sliding groove in the vertical direction is formed in a first side face of the upper portion of the seat leg, a sliding block which can be fixedly connected with a basin framework is arranged on the sliding groove in a sliding mode, two bolt shafts are fixed on a second side face adjacent to the first side face of the seat leg, annular steel belts are sleeved on the two bolt shafts, pin mounting holes are formed in the steel belts, mounting lugs extend to the steel belt side of the sliding block, and a shear pin with a frangible groove penetrates through the pin mounting holes and through holes in the mounting lugs and is in threaded connection with the second side face of the seat leg.
2. 2. The aviation seat energy-absorbing device of claim 1, wherein a bearing is sleeved in the middle of the bolt shaft, check rings are sleeved on two sides of the outer surface of the bearing respectively, gaskets are sleeved on the bolt shaft on the outer side of each check ring respectively, and a mounting groove of the steel belt is formed between the two check rings and the outer surface of the bearing.
3. 3. The aero seat energy absorbing device of claim 2, wherein a bushing is disposed between the bearing and the bolt shaft.
4. 4. The aviation seat energy absorber of claim 1, wherein a stepped hole is formed in the second side face of the chair leg between the two bolt shafts, the outer end portion of the breaking groove formed in the shear pin is reduced in diameter to form a threaded portion, an annular table is formed between the breaking groove and the threaded portion, the threaded portion is screwed on threads on the inner side of the stepped hole, and the annular table is located on a large-diameter portion outside the stepped hole.
5. 5. The airline seat energy absorber of claim 4, wherein the frangible groove is located outside of and adjacent to the second side and the side of the frangible groove is flush with the second side.
6. 6. The energy absorber of the aero seat according to claim 1, wherein the sliding groove is a trapezoid groove or a T-shaped groove, and the sliding block is provided with a sliding rail part which extends into and is matched with the trapezoid groove or the T-shaped groove, and the sliding rail part can slide in the trapezoid groove or the T-shaped groove.
7. 7. The aviation seat energy absorber of claim 1, wherein the mounting lug of the slider extending to the steel belt side comprises an extending plate arranged on the slider, two convex plates perpendicular to the extending plate are arranged on the extending plate, the two convex plates are oppositely provided with concentric through holes, and the pin mounting hole on the steel belt is positioned between the two convex plates.
8. 8. The aviation seat energy absorber of claim 1, wherein the pin mounting holes in the steel belt are annular steel belts formed by integrally forming opposite side surfaces of a cylinder with a center hole with two ends of the strip steel belt.
9. 9. The aviation seat energy absorber of claim 8, wherein the joint of the two side surfaces of the cylinder and the two ends of the strip-shaped steel belt is provided with an arc-shaped transition surface so as to strengthen the strength of the joint of the cylinder and the strip-shaped steel belt.
10. 10. The aero seat energy absorbing device of claim 1, wherein more than two mounting protrusions are arranged on the side surface, away from the sliding groove, of the sliding block at intervals, and thread grooves are formed in the mounting protrusions.

Description

Aviation seat energy absorber Technical Field The invention belongs to the technical field of aviation seat safety, and particularly relates to an aviation seat energy absorption device. Background In recent years, with the development of low-altitude economy, various electric vertical take-off and landing aircrafts (eVTOL) and traditional civil helicopter products are continuously developed and put on the market. Such aircraft seats are required to meet the requirements of anti-collision in civil aviation regulations such as CTSO-C127 and the like to protect passengers. Since a great acceleration impact (30 g) is transmitted to a human body in the vertical direction during the emergency landing or crash of the aircraft, the lumbar load cannot exceed 6670N in the civil aviation regulations in consideration of the tolerance limit of the human body. The special energy absorbing device is arranged on the seat, so that the impact of the seat system on the lumbar vertebra of the human body can be effectively reduced, the injury of the lumbar vertebra of the human body is avoided, and a certain safety protection is provided for passengers in accidents. The traditional aero seat energy absorbing device or mechanism has certain defects in energy absorbing efficiency, manufacturability, reliability, applicability and the like. Disclosure of Invention The invention aims to provide an energy absorption mechanism scheme meeting the requirements of an aviation seat, which has the advantages of high energy absorption efficiency, light weight, simple structure, good manufacturability, good reliability and good applicability, well solves the defects of the traditional energy absorption mechanism, and can meet the related requirements of civil aviation regulations. The invention aims to solve the following problems: The utility model provides an aviation seat energy-absorbing device, includes the chair leg of seat, be provided with the spout of upper and lower direction on the first side on chair leg upper portion, slide on the spout be provided with can with seat basin skeleton fixed connection's slider, with be fixed with two bolt shafts on the second side adjacent of first side of chair leg, the epaxial cover of two bolts is equipped with annular steel band, be provided with the pin mounting hole on the steel band, the slider is to the extension of steel band side have the installation to connect the ear, and the shear pin that has the breakable groove passes through the through-hole spiro union on pin mounting hole and the installation to connect the ear is in on the second side of chair leg. As a further optimization of the technical scheme, the middle part of the bolt shaft is sleeved with the bearing, two sides of the outer surface of the bearing are respectively sleeved with the check rings, the bolt shaft at the outer side of each check ring is respectively sleeved with the gasket, and the installation groove of the steel belt is formed between the two check rings and the outer surface of the bearing. As a further optimization of the above technical solution, a bushing is arranged between the bearing and the bolt shaft. As a further optimization of the technical scheme, a step hole is formed in the second side face of the chair leg between the two bolt shafts, the outer end part of the breakable groove arranged on the shear pin is contracted to form a threaded part, an annular table is formed between the breakable groove and the threaded part, the threaded part is screwed on the thread on the inner side of the step hole, and the annular table is located on the large-diameter part outside the step hole. As a further optimization of the above technical solution, the side surface of the frangible groove located outside the second side surface and adjacent to the second side surface is flush with the second side surface. As a further optimization of the technical scheme, the sliding groove is a trapezoid groove or a T-shaped groove, the sliding block is provided with a sliding rail part which extends into and is matched with the trapezoid groove or the T-shaped groove, and the sliding rail part can slide in the trapezoid groove or the T-shaped groove. As a further optimization of the technical scheme, the installation lug of the sliding block extending towards the steel belt side comprises an extension plate arranged on the sliding block, two convex plates perpendicular to the extension plate are arranged on the extension plate, the two convex plates are oppositely provided with concentric through holes, and the pin installation hole on the steel belt is positioned between the two convex plates. As a further optimization of the technical scheme, the pin mounting holes on the steel belt are circular steel belts formed by integrally forming opposite side surfaces of the cylinder with the central hole with two ends of the strip steel belt. As a further optimization of the technical scheme, the joint of the two side surfac