CN107776887B - Flight experience/primary training glider - Google Patents
Flight experience/primary training glider Download PDFInfo
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- CN107776887B CN107776887B CN201711183069.2A CN201711183069A CN107776887B CN 107776887 B CN107776887 B CN 107776887B CN 201711183069 A CN201711183069 A CN 201711183069A CN 107776887 B CN107776887 B CN 107776887B
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- 230000008093 supporting effect Effects 0.000 claims abstract description 123
- 230000005540 biological transmission Effects 0.000 claims abstract description 6
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000011084 recovery Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
- B64C31/02—Gliders, e.g. sailplanes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
- B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
- B66D1/60—Rope, cable, or chain winding mechanisms; Capstans adapted for special purposes
- B66D1/74—Capstans
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
- B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
- B66D1/60—Rope, cable, or chain winding mechanisms; Capstans adapted for special purposes
- B66D1/74—Capstans
- B66D1/7463—Accessories
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lift-Guide Devices, And Elevator Ropes And Cables (AREA)
- Bridges Or Land Bridges (AREA)
Abstract
The invention relates to a flight experience/primary training glider, which comprises a fuselage, wings and tail wings; the main structure of the machine body comprises a top beam, a bottom beam and a first supporting beam; the bottom beam comprises a machine head bottom beam and a machine body bottom beam, and the rear end of the machine head bottom beam is fixedly connected with the front end of the machine body bottom beam and forms an obtuse angle; the front end of the top beam is bent downwards and fixedly connected with the front end of the machine head bottom beam, and the rear end of the top beam is fixedly connected with the rear end of the machine body bottom beam; the top end of the first supporting beam is fixedly connected with the top beam, and the bottom end of the first supporting beam is fixedly connected with the rear end of the machine head bottom beam; the machine head bottom beam is sequentially provided with pedals, an operating rod and a seat from the front end to the rear end of the machine head bottom beam; the operating rod is connected with an aileron of the wing, an elevator of the tail wing and a rudder through a transmission mechanism; the aircraft nose floorpan is provided with the aircraft nose skid, the fuselage floorpan is provided with the take-off and landing wheel. The invention has the advantages of simple structure, light weight and the like, improves the stability and flexibility of the flight of the glider, and is beneficial to the flight experience of a driver.
Description
Technical Field
The invention belongs to the technical field of gliders, and particularly relates to a flight experience/primary training glider.
Background
The glider is a fixed wing aircraft without a power device and needs external assistance for taking off; the lift force is generated by the camber shape of the section of the wing. When the air flows through the wing, the distance of the air molecules above the wing is longer in the same time, so that the air molecules flow faster than the air molecules below the wing, the air pressure above the wing is lower than the air pressure below the wing, and the lower higher air pressure supports the glider, so that the glider can fly or soaring.
However, the existing glider has the problems of complex structure, heavy weight and the like, so that the stability and flexibility of the glider in flight are affected, and the flight experience of a driver is reduced.
In addition, because the glider has higher requirements on the flight airspace and the flight field, the pilot is required to be trained systematically; thus, the safety and usability of the glider and the flight experience for beginners are affected.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a flight experience/primary training glider, which has the advantages of simple structure, light weight and the like, improves the stability and flexibility of the flight of the glider, and is beneficial to the flight experience of a driver.
The technical scheme adopted by the invention is as follows:
a flight experience/primary training glider comprising a fuselage and wings and tails disposed on a main structure of the fuselage; the main structure of the machine body comprises a top beam, a bottom beam and a first supporting beam; the bottom beam comprises a machine head bottom beam and a machine body bottom beam, the rear end of the machine head bottom beam is fixedly connected with the front end of the machine body bottom beam, and the included angle between the machine head bottom beam and the machine body bottom beam is an obtuse angle; the front end of the top beam is bent downwards and fixedly connected with the front end of the machine head bottom beam, and the rear end of the top beam is fixedly connected with the rear end of the machine body bottom beam; the top end of the first supporting beam is fixedly connected with the top beam, and the bottom end of the first supporting beam is fixedly connected with the rear end of the machine head bottom beam; the machine head bottom beam is sequentially provided with pedals, an operating rod and a seat from the front end to the rear end of the machine head bottom beam; the operating rod is connected with the aileron of the wing through a transmission mechanism; the bottom side of aircraft nose floorpan is provided with the aircraft nose skid, the fuselage floorpan is provided with the take-off and landing wheel.
Further, a cross bar is arranged at the front end of the machine body bottom beam, and the front end of the machine body bottom beam, the bottom end of the first support beam and the rear end of the machine head bottom beam are fixedly connected with the cross bar; the bottom side of the cross rod is provided with a leaf spring along the length direction of the cross rod; the lifting wheel comprises a main machine wheel rotatably arranged at two ends of the leaf spring and a tail wheel arranged at the rear end of the bottom beam of the machine body; the nose skid, the host wheel and the tail wheel form a four-point landing gear system.
Further, the machine head bottom beam is provided with a first inclined supporting beam and a second inclined supporting beam; the first inclined supporting beam is positioned in front of the pedals, the top end of the first inclined supporting beam is fixedly connected with the arc-shaped section of the front end of the top beam, and the bottom end of the first inclined supporting beam is fixedly connected with the machine head bottom beam; the second diagonal bracing beam is positioned at the rear of the seat, the top end of the second diagonal bracing beam is fixedly connected with the first supporting beam, and the bottom end of the second diagonal bracing beam is fixedly connected with the machine head bottom beam.
Further, the fuselage sill is provided with a second supporting beam and a third supporting beam in sequence along the length direction of the fuselage sill, the top ends of the second supporting beam and the third supporting beam are respectively fixedly connected with the top beam, and the bottom ends of the second supporting beam and the third supporting beam are respectively fixedly connected with the fuselage sill.
Further, a third diagonal bracing beam and a fourth diagonal bracing beam are arranged between the first supporting beam and the second supporting beam; the top end of the third inclined supporting beam is fixedly connected with the top beam, and the bottom end of the third inclined supporting beam is fixedly connected with the first supporting beam; the top end of the fourth inclined supporting beam is fixedly connected with the first supporting beam, and the bottom end of the fourth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the fixed connection end of the third inclined supporting beam and the top beam is positioned at the fixed connection end of the second supporting beam and the top beam, and the fixed connection end of the fourth inclined supporting beam and the bottom beam of the machine body is positioned at the fixed connection end of the second supporting beam and the bottom beam of the machine body; the fixed connection ends of the third diagonal bracing beam and the first supporting beam are adjacent to the fixed connection ends of the fourth diagonal bracing beam and the first supporting beam, and are V-shaped.
Further, a fifth diagonal bracing beam is arranged between the second supporting beam and the third supporting beam; the top end of the fifth inclined supporting beam is fixedly connected with the top beam, and the bottom end of the fifth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the fixed connection ends of the fifth inclined supporting beam and the top beam are positioned at the fixed connection ends of the second supporting beam and the top beam, and the fixed connection ends of the fifth inclined supporting beam and the bottom beam of the machine body are positioned at the fixed connection ends of the third supporting beam and the bottom beam of the machine body;
a sixth diagonal bracing beam and a seventh diagonal bracing beam are arranged between the rear ends of the third support beam and the bottom beam of the machine body; the top end of the sixth inclined supporting beam is fixedly connected with the top beam, and the bottom end of the sixth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the top end of the seventh inclined supporting beam is fixedly connected with the top beam, and the bottom end of the seventh inclined supporting beam is fixedly connected with the rear end of the bottom beam of the machine body; the fixed connection end of the sixth inclined supporting beam and the machine body bottom beam is positioned at the fixed connection end of the third supporting beam and the machine body bottom beam; the fixed connection ends of the sixth diagonal bracing beam and the top beam are adjacent to the fixed connection ends of the seventh diagonal bracing beam and the top beam, and are V-shaped.
Further, the left side and the right side of each fixed connection end of the main structure of the machine body are fixedly provided with fixed reinforcing splints; the fixed reinforcing clamp plates are connected with the beams at the corresponding fixed connection ends through fastening bolts.
Further, wing diagonal braces are respectively arranged at two ends of the cross rod, and the wing diagonal braces are connected with the wings at the same side.
Further, the flight experience/primary training glider further comprises a traction system; the traction system comprises a winch, a pulley block, a circulating rope and a traction lock; the winch drives the circulating cable; the circulating rope forms a closed structure without a free end and is sleeved on the pulley block and the winch; the circulating cable is at least connected with a traction cable connecting piece, the traction cable connecting piece is connected with the traction cable, and the traction cable is connected with a traction hook at the front end of the machine head bottom beam; the pulley block is fixedly arranged on the bottom surface.
Based on the traction system matched with the glider, the time for each flying of the glider can be shortened through the circulating rope, and continuous, efficient and convenient flying of the glider can be realized; meanwhile, compared with the existing mode of only adopting traction wires, the mode of the circulating cable and the traction cable greatly shortens the length of the traction cable, so that the problems of long traction cable, long recovery time and high recovery effort are solved; in addition, the limited length of the traction rope enables the flying height of the glider to be controllable, and the traction ropes with different lengths are selected according to the requirements, so that potential safety hazards are solved; therefore, the flight experience/primary training glider enables the low-cost, high-reliability and high-usability implementation of the glider-based flight experience and primary training by combining the glider with a traction system.
Further, the pulley block is composed of three groups of pulleys fixed on the ground and is of a 7-shaped transverse folding structure; the winch is arranged at the transverse starting end of the transverse folding structure, two pulleys are arranged at the transverse ending end of the transverse folding structure, and one pulley is arranged at the folding ending end of the quick search transverse folding structure.
Further, the power system of the winch is an oil-driven engine or an electric engine; the circulating cable is a steel cable, does not contact the ground and can rotate around the pulley block; the traction rope connecting piece is movably connected with the traction rope.
The invention has the beneficial effects that:
the flight experience/primary training glider provided by the invention has the advantages of simple structure, light weight and the like, improves the stability and flexibility of the glider in flight, and is beneficial to the flight experience of a driver; meanwhile, the flight experience/primary training glider is combined with the traction system through the glider, so that the flight experience and primary training based on the glider are realized with low cost, high reliability and high usability.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view of a glider described in embodiment 1;
fig. 2 is a side view of the glider described in example 1;
fig. 3 is a schematic structural view of the leaf spring described in embodiment 1;
fig. 4 is a front view of the glider described in embodiment 1 (seat omitted);
FIG. 5 is a schematic diagram of the traction system described in example 2;
fig. 6 is a schematic structural view of the traction system described in embodiment 3.
The reference numerals in the figures are:
the main structure 101 of the fuselage, wings 102, tail wings 103, host wheels 104, tail wheels 105, top beams 106, nose bottom beams 107, fuselage bottom beams 108, first support beams 109, second support beams 110, third support beams 111, pedals 112, operating levers 113, seats 114, first diagonal braces 115, nose skids 116, wing diagonal braces 117, cross bars 118, leaf springs 119, gliders 120, winch trucks 121, circulation cables 122, pulleys 123, traction cables 124, traction cable connectors 125.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, based on the examples herein, which are within the scope of the invention as defined by the claims, will be within the scope of the invention as defined by the claims.
Example 1
As shown in fig. 1 and 2, the present embodiment provides a flight experience/primary training glider including a fuselage and wings and tails provided on a main structure of the fuselage; the main structure of the machine body comprises a top beam, a bottom beam and a first supporting beam; the bottom beam comprises a machine head bottom beam and a machine body bottom beam, the rear end of the machine head bottom beam is fixedly connected with the front end of the machine body bottom beam, and the included angle between the machine head bottom beam and the machine body bottom beam is an obtuse angle; the front end of the top beam is bent downwards and fixedly connected with the front end of the machine head bottom beam, and the rear end of the top beam is fixedly connected with the rear end of the machine body bottom beam; the top end of the first supporting beam is fixedly connected with the top beam, and the bottom end of the first supporting beam is fixedly connected with the rear end of the machine head bottom beam; the machine head bottom beam is sequentially provided with pedals, an operating rod and a seat from the front end to the rear end of the machine head bottom beam; the operating rod is connected with the aileron of the wing through a traditional transmission mechanism; the machine head bottom beam is provided with a machine head skid, and the machine body bottom beam is provided with a lifting wheel.
The flight experience glider based on the structure has the advantages that the main structure of the glider body is formed by the top beam, the bottom beam and the first support beam, so that the glider has the advantages of simple structure, light weight and the like, the stability and the flexibility of the flight of the glider are improved, and the flight experience of a driver is facilitated; the foot pedal is convenient for a driver to place feet, and the foot pedal is sequentially arranged along the length direction of the machine head bottom beam together with the operating rod and the seat, so that the driver can conveniently operate the flying experience glider through the operating rod in action; meanwhile, the front end of the top beam is bent downwards to form a bent section which is convenient for a driver to hold.
Specifically, as shown in fig. 3, a cross bar is arranged at the front end of the machine body bottom beam, and the front end of the machine body bottom beam, the bottom end of the first support beam and the rear end of the machine head bottom beam are fixedly connected with the cross bar; the bottom side of the cross rod is provided with a leaf spring along the length direction of the cross rod; the roller comprises a main machine wheel which is rotatably arranged at two ends of the leaf spring and a tail wheel which is arranged at the rear end of the bottom beam of the machine body; therefore, the machine head skid, the main machine wheel and the tail wheel form a four-point landing gear system together, so that the operability and the safety are enhanced in the aspects of take-off and landing control of the glider.
Moreover, through the above-mentioned horizontal pole structure, not only be convenient for be connected between fuselage floorbar, first supporting beam and the aircraft nose floorbar, but also made things convenient for leaf spring's setting to play shock attenuation, cushioning effect, improve the security through leaf spring.
Preferably, the two ends of the cross rod are respectively provided with a fixed seat, and the fixed seats are provided with U-shaped locking pieces, so that the steel plate spring lock catch is fixed on the bottom side of the cross rod through the U-shaped locking pieces; the fixing seat is provided with threaded holes matched with two ends of the U-shaped locking fastener; external threads are arranged at two ends of the U-shaped locking piece and penetrate through corresponding threaded holes to be locked and fixed through locking nuts.
In order to better improve the mechanism strength of the cross rod, preferably, the two opposite sides of the first supporting beam are respectively provided with an inclined supporting rod, the top ends of the inclined supporting rods are fixedly connected with the first supporting beam, and the bottom ends of the inclined supporting rods are fixedly connected with the cross rod, so that the structural strength of the cross rod is improved through the supporting and fixing effect of the inclined supporting rods, and the safety of taking off and landing of the glider is more facilitated.
In order to better improve the structural strength of the nose part of the main structure of the fuselage, the nose bottom beam is preferably provided with a first diagonal bracing and a second diagonal bracing; the first inclined supporting beam is positioned in front of the pedals, the top end of the first inclined supporting beam is fixedly connected with the arc-shaped section of the front end of the top beam, and the bottom end of the first inclined supporting beam is fixedly connected with the machine head bottom beam; the second diagonal bracing beam is positioned at the rear of the seat, the top end of the second diagonal bracing beam is fixedly connected with the first supporting beam, and the bottom end of the second diagonal bracing beam is fixedly connected with the machine head bottom beam, so that the structural strength of the machine head part of the main structure of the machine body is improved through the supporting action of the first diagonal bracing beam and the second diagonal bracing beam; meanwhile, the backrest of the seat can be connected through the second inclined bracing beam, so that the seat is fixed and reinforced.
In order to better improve the structural strength of the main body part of the main structure of the fuselage, preferably, the fuselage bottom beam is sequentially provided with a second supporting beam and a third supporting beam along the length direction of the fuselage bottom beam, the top ends of the second supporting beam and the third supporting beam are respectively and fixedly connected with the top beam, and the bottom ends of the second supporting beam and the third supporting beam are respectively and fixedly connected with the fuselage bottom beam.
More preferably, a third diagonal bracing beam and a fourth diagonal bracing beam are arranged between the first supporting beam and the second supporting beam; the top end of the third inclined strut beam is fixedly connected with the top beam, and the bottom end of the third inclined strut beam is fixedly connected with the first supporting beam; the top end of the fourth inclined supporting beam is fixedly connected with the first supporting beam, and the bottom end of the fourth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the fixed connection end of the third diagonal bracing beam and the top beam is positioned at the fixed connection end of the second supporting beam and the top beam, and the fixed connection end of the fourth diagonal bracing beam and the bottom beam of the machine body is positioned at the fixed connection end of the second supporting beam and the bottom beam of the machine body; the fixed connection end of the third diagonal bracing beam and the first supporting beam is adjacent to the fixed connection end of the fourth diagonal bracing beam and the first supporting beam and is in a V shape.
More preferably, a fifth diagonal bracing beam is arranged between the second supporting beam and the third supporting beam; the top end of the fifth inclined supporting beam is fixedly connected with the top beam, and the bottom end of the fifth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the fixed connection end of the fifth inclined supporting beam and the top beam is positioned at the fixed connection end of the second supporting beam and the top beam, and the fixed connection end of the fifth inclined supporting beam and the bottom beam of the machine body is positioned at the fixed connection end of the third supporting beam and the bottom beam of the machine body; a sixth diagonal bracing beam and a seventh diagonal bracing beam are arranged between the rear ends of the third support beam and the bottom beam of the machine body; the top end of the sixth inclined supporting beam is fixedly connected with the top beam, and the bottom end of the sixth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the top end of the seventh inclined supporting beam is fixedly connected with the top beam, and the bottom end of the seventh inclined supporting beam is fixedly connected with the rear end of the bottom beam of the machine body; the fixed connection end of the sixth inclined strut beam and the machine body bottom beam is positioned at the fixed connection end of the third support beam and the machine body bottom beam; the fixed connection end of the sixth diagonal bracing beam and the top beam is adjacent to the fixed connection end of the seventh diagonal bracing beam and the top beam and is in a V shape.
Meanwhile, in order to better improve the connection strength at each fixed connection end, preferably, fixed reinforcing splints are fixedly arranged on the left side and the right side of each fixed connection end of the main structure of the machine body; the fixed reinforcing clamping plates are connected with the beams at the corresponding fixed connection ends through fastening bolts in a fastening mode, so that the limiting reinforcing fixing effect is achieved through the fixed reinforcing clamping plates, and the structural strength of the main structure of the whole machine body is improved better.
In the embodiment, each beam and each rod are preferably made of aviation aluminum alloy pipe materials, and the fixed reinforcing clamping plates are preferably made of aviation aluminum alloy plates; the operating rod can be connected with the aileron of the wing, the elevator of the tail wing and the rudder through a traditional transmission mechanism, so that the operability of the glider is improved.
As shown in fig. 4, preferably, the wing adopts an upper single wing layout, and the wing root of the wing is connected with the main structure of the fuselage; the two ends of the cross rod are respectively provided with the wing diagonal brace, and the wing diagonal brace is connected with the middle section of the wing at the same side, so that the wing is supported, and the structural strength and stability of the wing are better improved.
Example 2
As shown in fig. 5, the flight experience/primary training glider provided in embodiment 1 further comprises a traction system; the traction system includes: winch, pulley block, circulating rope and traction rope; the winch drives the circulating rope; the circulating rope forms a closed structure without a free end and is sleeved on the pulley block and the winch; the circulating cable is at least connected with a traction cable connecting piece, the traction cable connecting piece is connected with a traction cable, and the pulley block is fixed on the ground.
Wherein, the power system of the winch adopts an oil engine or an electric engine; wherein, electric motor adopts the commercial power as the power to be connected with emergency power source, thereby can prevent that the glider from being at the in-process that lifts off because of the potential safety hazard that causes of outage, and the glider cuts off the power supply at the in-process that lifts off, then can rely on the outstanding gliding performance of glider, very safe landing.
In the embodiment, the circulating rope is a steel rope and rotates close to the bottom surface and is not contacted with the bottom surface; the traction rope connecting piece is movably connected with the traction rope; preferably, the traction rope connecting piece is made of flexible materials; the front end of the machine head bottom beam is provided with a traction hook, and the traction rope is connected to the front end of the machine head through the traction hook.
Example 3
As shown in fig. 6, the flight experience/primary training glider provided in embodiment 1 further comprises a traction system; the traction system includes: winch, pulley block, circulating rope and traction rope; the winch of the (2) is used as a power unit of the whole system to provide power for the whole system; the power system of the winch is an electric engine and adopts commercial power as a power supply.
The winch drives the circulating rope; the circulating rope forms a closed structure without a free end and is sleeved on the pulley block and the winch; the pulley block and the circulating rope form a transmission system and are driven by a winch.
A plurality of traction rope connecting pieces are uniformly arranged on the circulation rope, and the traction rope connecting pieces are made of flexible materials; the pulley block is composed of three groups of pulleys 3 fixed on the ground, and is of a transverse folding structure in a shape of 7, a winch is arranged at the transverse starting end of the transverse folding structure, two pulleys are arranged at the transverse ending end of the transverse folding structure, and one pulley 3 is arranged at the folding ending end of the transverse folding structure, so that the parallel circulating ropes 2 can be prevented from being disturbed; in addition, part of the field can be saved.
The circulating rope is made of a high-strength steel wire rope so as to ensure that the circulating rope can provide enough tension; the traction rope is connected with the traction hook at the front end of the machine head bottom beam, and the traction rope connecting piece is movably connected with the traction rope.
When the winch is used, the winch, the circulating rope and the pulley block form a system in which the circulating rope can rotate between the winch and the pulley block; one end of the traction rope is connected to a traction rope connecting piece arranged on the circulation rope, and the other end of the traction rope is connected to the glider.
Starting a winch, wherein the winch drives a circulating rope, and the circulating rope drives a traction rope connecting piece connected with the circulating rope, so that a traction rope connected with the traction rope connecting piece drives a glider; as the winch is continuously accelerated, the speed of the glider is increased more and more, and as aerodynamic knowledge is obtained, after the glider reaches a certain speed, the glider is lifted under the action of air lifting force.
After the limit height is reached, the winch is decelerated, and the glider is automatically separated from the traction rope to form a gliding state; because the length of the traction rope is fixed, the flying height of the glider is fixed, and the glider is not too high and is safer; the length of the traction rope is short, and the recovery is convenient.
The circulating rope close to the bending part is connected with another traction rope, so that the take-off preparation work of the next glider can be completed, and the like.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present invention should be included in the present invention.
Claims (8)
1. A flight experience/primary training glider, comprising a fuselage and wings and tails disposed on a main structure of the fuselage; the main structure of the machine body comprises a top beam, a bottom beam and a first supporting beam; the bottom beam comprises a machine head bottom beam and a machine body bottom beam, the rear end of the machine head bottom beam is fixedly connected with the front end of the machine body bottom beam, and the included angle between the machine head bottom beam and the machine body bottom beam is an obtuse angle; the front end of the top beam is bent downwards and fixedly connected with the front end of the machine head bottom beam, and the rear end of the top beam is fixedly connected with the rear end of the machine body bottom beam; the top end of the first supporting beam is fixedly connected with the top beam, and the bottom end of the first supporting beam is fixedly connected with the rear end of the machine head bottom beam; the machine head bottom beam is sequentially provided with pedals, an operating rod and a seat from the front end to the rear end of the machine head bottom beam; the operating rod is connected with the aileron of the wing through a transmission mechanism; the machine head bottom beam is provided with a machine head skid, and the machine body bottom beam is provided with a lifting wheel;
the front end of the machine body bottom beam is provided with a cross rod, and the front end of the machine body bottom beam, the bottom end of the first support beam and the rear end of the machine head bottom beam are fixedly connected with the cross rod; the bottom side of the cross rod is provided with a leaf spring along the length direction of the cross rod; the lifting wheel comprises a main machine wheel rotatably arranged at two ends of the leaf spring and a tail wheel arranged at the rear end of the bottom beam of the machine body; the machine head skid, the main machine wheel and the tail wheel form a four-point lifting frame system;
the machine head bottom beam is provided with a first inclined supporting beam and a second inclined supporting beam; the first inclined supporting beam is positioned in front of the pedals, the top end of the first inclined supporting beam is fixedly connected with the arc-shaped section of the front end of the top beam, and the bottom end of the first inclined supporting beam is fixedly connected with the machine head bottom beam; the second diagonal bracing beam is positioned at the rear of the seat, the top end of the second diagonal bracing beam is fixedly connected with the first supporting beam, and the bottom end of the second diagonal bracing beam is fixedly connected with the machine head bottom beam.
2. The experience/primary training glider according to claim 1, wherein the fuselage bottom beam is provided with a second support beam and a third support beam in sequence along the length direction of the fuselage bottom beam, the top ends of the second support beam and the third support beam are respectively fixedly connected with the top beam, and the bottom ends of the second support beam and the third support beam are respectively fixedly connected with the fuselage bottom beam.
3. The flying experience/primary training glider according to claim 2, wherein a third diagonal beam and a fourth diagonal beam are provided between the first support beam and the second support beam; the top end of the third inclined supporting beam is fixedly connected with the top beam, and the bottom end of the third inclined supporting beam is fixedly connected with the first supporting beam; the top end of the fourth inclined supporting beam is fixedly connected with the first supporting beam, and the bottom end of the fourth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the fixed connection end of the third inclined supporting beam and the top beam is positioned at the fixed connection end of the second supporting beam and the top beam, and the fixed connection end of the fourth inclined supporting beam and the bottom beam of the machine body is positioned at the fixed connection end of the second supporting beam and the bottom beam of the machine body; the fixed connection ends of the third diagonal bracing beam and the first supporting beam are adjacent to the fixed connection ends of the fourth diagonal bracing beam and the first supporting beam, and are V-shaped.
4. A flying experience/primary training glider according to claim 3, wherein a fifth diagonal bracing is provided between the second and third support beams; the top end of the fifth inclined supporting beam is fixedly connected with the top beam, and the bottom end of the fifth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the fixed connection ends of the fifth inclined supporting beam and the top beam are positioned at the fixed connection ends of the second supporting beam and the top beam, and the fixed connection ends of the fifth inclined supporting beam and the bottom beam of the machine body are positioned at the fixed connection ends of the third supporting beam and the bottom beam of the machine body;
a sixth diagonal bracing beam and a seventh diagonal bracing beam are arranged between the rear ends of the third support beam and the bottom beam of the machine body; the top end of the sixth inclined supporting beam is fixedly connected with the top beam, and the bottom end of the sixth inclined supporting beam is fixedly connected with the bottom beam of the machine body; the top end of the seventh inclined supporting beam is fixedly connected with the top beam, and the bottom end of the seventh inclined supporting beam is fixedly connected with the rear end of the bottom beam of the machine body; the fixed connection end of the sixth inclined supporting beam and the machine body bottom beam is positioned at the fixed connection end of the third supporting beam and the machine body bottom beam; the fixed connection ends of the sixth diagonal bracing beam and the top beam are adjacent to the fixed connection ends of the seventh diagonal bracing beam and the top beam, and are V-shaped.
5. The flying experience/primary training glider according to claim 4, wherein the left and right sides of each fixed connection end of the main structure of the fuselage are fixedly provided with fixed reinforcing cleats; the fixed reinforcing clamp plates are connected with the beams at the corresponding fixed connection ends through fastening bolts.
6. The flying experience/primary training glider according to any one of claims 1-4, further comprising a traction system; the traction system comprises a winch, a pulley block, a circulating rope and a traction lock; the winch drives the circulating cable; the circulating rope forms a closed structure without a free end and is sleeved on the pulley block and the winch; the circulating cable is at least connected with a traction cable connecting piece, the traction cable connecting piece is connected with the traction cable, and the traction cable is connected with a traction hook at the front end of the machine head bottom beam; the pulley block is fixedly arranged on the bottom surface.
7. The flying experience/primary training glider according to claim 6, wherein said pulley block is made up of three sets of pulleys fixed on the ground and is in a "7" shaped cross-folded configuration; the winch is arranged at the transverse starting end of the transverse folding structure, two pulleys are arranged at the transverse ending end of the transverse folding structure, and one pulley is arranged at the folding ending end of the transverse folding structure.
8. The flying experience/primary training glider of claim 7, wherein the power system of the winch is an oil motor or an electric motor; the circulating cable is a steel cable, does not contact the ground and can rotate around the pulley block; the traction rope connecting piece is movably connected with the traction rope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711183069.2A CN107776887B (en) | 2017-11-23 | 2017-11-23 | Flight experience/primary training glider |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711183069.2A CN107776887B (en) | 2017-11-23 | 2017-11-23 | Flight experience/primary training glider |
Publications (2)
| Publication Number | Publication Date |
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| CN107776887A CN107776887A (en) | 2018-03-09 |
| CN107776887B true CN107776887B (en) | 2024-02-06 |
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| RU2104223C1 (en) * | 1993-05-05 | 1998-02-10 | Юрий Васильевич Макаров | Invalid microaircraft |
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| GB455067A (en) * | 1935-12-30 | 1936-10-13 | Arthur Hubert Trevor | Aeroplane kite |
| DD107233A1 (en) * | 1973-09-13 | 1974-07-20 | ||
| US4372506A (en) * | 1980-06-05 | 1983-02-08 | David Cronk | Landing gear for ultralight aircraft |
| CA1144134A (en) * | 1980-10-28 | 1983-04-05 | Dale C. Kramer | Lightweight aircraft |
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| RU2104223C1 (en) * | 1993-05-05 | 1998-02-10 | Юрий Васильевич Макаров | Invalid microaircraft |
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| Publication number | Publication date |
|---|---|
| CN107776887A (en) | 2018-03-09 |
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