A pressure measuring device for aircraft test flights

Abstract

The utility model relates to the field of aerospace technology, concretely relates to a pressure measuring device for airplane test flight, including pressure sensor, the outer wall left side fixed connection of pressure sensor has the joint, the outer wall left side of joint of the joint is provided with the joint, the joint and joint are engaged, the outer wall left side mounting of joint has the cable, the outer wall left side mounting of pressure sensor has the fixed mechanism, the fixed mechanism is used for stabilizing joint, the bottom of pressure sensor is provided with the mounting mechanism, the mounting mechanism is used for fixing pressure sensor on the airplane, in the utility model, through the compression spring of pull rod, then the joint is inserted into the joint of pressure sensor, loosens the pull ring, and the spring makes the clamping block clamping limit block, and the connection of stable joint and joint, and the pull ring is convenient for operation, has guaranteed the stability of connection and the convenience of operation, has guaranteed the reliability and efficiency of signal transmission in the process of test flight simultaneously.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a pressure measuring device for aircraft flight testing. Background Technology

[0002] Aircraft test flights are conducted before an aircraft is delivered for use. They involve flight testing to collect flight data and ensure that the aircraft is in the most stable flight condition before delivery. This ensures that the flight results are accurate and scientific. The core purpose of aircraft test flights is to verify the safety, reliability, performance indicators, and practical applicability of the aircraft.

[0003] Air pressure measurement devices used for aircraft flight testing are a type of equipment specifically designed to measure air pressure parameters of an aircraft during flight. These parameters are crucial for analyzing the aircraft's aerodynamic performance, flight status, and structural stress. Their accuracy and reliability directly affect the validity of flight test data and drive aircraft design towards a safer and more efficient direction.

[0004] Existing pressure measurement devices are mainly used to measure air pressure parameters during flight. Their working principle is based on Bernoulli's principle in fluid mechanics and pressure sensing technology. They consist of an elastic element and a strain gauge. Pressure is applied to the elastic element, causing it to deform. The strain gauge attached to the elastic element changes its resistance value with the deformation. The change in resistance is measured by a Wheatstone bridge, and a voltage signal proportional to the pressure is output. However, wired sensors require a large number of cables to transmit signals. Vibration during flight testing can cause cable breakage, loosening of connectors, and poor contact. Existing technology uses the threaded engagement of nuts and bolts to connect the cable connectors, providing mechanical support against vibration and impact. However, disassembly requires turning the nuts one turn at a time, which is time-consuming and difficult to operate in confined spaces. Utility Model Content

[0005] The purpose of this invention is to provide a pressure measuring device for aircraft test flights, which solves the problems of having to tighten the nut one turn at a time during disassembly, which is time-consuming and difficult to operate in a confined space.

[0006] To achieve the above objectives, this utility model provides a pressure measuring device for aircraft flight testing. (The pressure measuring device for aircraft flight testing includes a pressure sensor. A connector is fixedly connected to the left side of the outer wall of the pressure sensor. A connector is provided on the left side of the outer wall of the connector. The connector engages with the connector. A cable is installed on the left side of the outer wall of the connector. A fixing mechanism is installed on the left side of the outer wall of the pressure sensor. The fixing mechanism is used to stabilize the connector. An installation mechanism is provided at the bottom of the pressure sensor. The installation mechanism is used to fix the pressure sensor to the aircraft. The fixing mechanism includes two fixing blocks, each fixedly connected to the front and rear ends of the left side of the outer wall of the pressure sensor. A pull rod passes through the outer wall of the fixing block. A spring is provided on the outer wall of the pull rod. A clamping block is fixedly connected to one adjacent end of the outer wall of each of the two pull rods. A limit block is fixedly connected to the right side of the outer wall of the connector. The limit block engages with the clamping block. An auxiliary component is provided on the left side of the outer wall of the pressure sensor.)

[0007] (The auxiliary component includes pull rings, and two pull rings are fixedly connected to the outer walls of the two pull rods at opposite ends. The outer walls of the pull rings are fitted with rubber sleeves.)

[0008] The mounting mechanism includes a second fixing block, which is fixedly connected to the right side of the bottom wall of the pressure sensor. A hollow block is fixedly connected to the right side of the outer wall of the second fixing block. A connecting rod is slidably connected to the inner wall of the hollow block. A U-shaped locking block is fixedly connected to the left end of the outer wall of the connecting rod. A base plate is provided at the bottom of the pressure sensor. A slot block is fixedly connected to the front and rear ends of the left side of the top wall of the base plate. A driving assembly is provided at the bottom of the pressure sensor.

[0009] The drive assembly includes an eccentric wheel, which is rotatably connected to the right end of the outer wall of the connecting rod. A threaded hole is provided on the front side of the outer wall of the eccentric wheel, and a handle is threadedly connected to the inner wall of the threaded hole.

[0010] (The pull rod is slidably connected to the fixed block, and the two springs are both set on the adjacent side of the outer wall of the fixed block).

[0011] (The connecting rod passes through the right side of the outer wall of the second fixing block, and the slot block engages with the U-shaped card block).

[0012] (The pressure sensor has an adhesive layer at its bottom, which is installed on the bottom wall of the base plate).

[0013] Among them, (the pressure sensor has unlocking holes at both the front and rear ends of the left side of its outer wall, fixing holes at both the front and rear ends of the left side of its outer wall, and pins at both the front and rear ends of the left side of its outer wall, the unlocking holes engaging with the pins, and the fixing holes engaging with the pins).

[0014] This utility model discloses a pressure measuring device for aircraft flight testing.

[0015] In this invention, the pull ring is first pulled to compress the spring through the pull rod, and then the connector is inserted into the connection hole of the pressure sensor. After the pull ring is released, the spring causes the clamping block to clamp the limiting block, stabilizing the connection between the connector and the connection hole. The pull ring is easy to operate, ensuring the stability of the connection and the convenience of operation, while also ensuring the reliability and efficiency of signal transmission during flight testing.

[0016] In this invention, the base plate is first installed on the aircraft, then the pressure sensor is placed on the base plate, fixed to the eccentric wheel by the handle and rotated. The eccentric wheel pulls the connecting rod to slide inside the hollow block, so that the U-shaped block and the slot block are engaged, and the pressure sensor is quickly installed. Finally, the handle is removed to reduce wind resistance during flight testing and avoid affecting data accuracy or increasing energy consumption. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0018] Figure 1 This is a front view of a pressure measuring device for aircraft flight testing proposed in this utility model;

[0019] Figure 2 This is a perspective view of a pressure measuring device for aircraft flight testing proposed in this utility model;

[0020] Figure 3 This is a partial structural exploded view of a pressure measuring device for aircraft flight testing proposed in this utility model;

[0021] Figure 4 This is a partial structural schematic diagram of a pressure measuring device for aircraft flight testing proposed in this utility model;

[0022] Figure 5 This is a partial exploded view of a pressure measuring device for aircraft flight testing proposed in this utility model.

[0023] 1. Pressure sensor; 2. Connecting hole; 3. Connector; 4. Cable; 5. Fixing mechanism; 501. Fixing block one; 502. Pull rod; 503. Spring; 504. Clamping block; 505. Limiting block; 506. Auxiliary component; 5061. Pull ring; 5062. Rubber sleeve; 6. Mounting mechanism; 601. Fixing block two; 602. Hollow block; 603. Connecting rod; 604. U-shaped locking block; 605. Base plate; 606. Slot block; 607. Drive component; 6071. Eccentric wheel; 6072. Threaded hole; 6073. Handle; 7. Adhesive layer; 8. Unlocking hole; 9. Fixing hole; 10. Pin. Detailed Implementation

[0024] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0025] Please see Figure 1 , Figure 2 and Figure 4 This utility model provides an embodiment of a pressure measuring device for aircraft test flights, comprising a pressure sensor 1. A connector 2 is fixedly connected to the left side of the outer wall of the pressure sensor 1. A connector 3 is provided on the left side of the outer wall of the connector 2, and the connector 2 engages with the connector 3. A cable 4 is installed on the left side of the outer wall of the connector 3. The pressure sensor 1 transmits pressure signals through the engagement of the connector 2 and the connector 3. The connector 3 connects to the cable 4 to output data. A fixing mechanism 5 is installed on the left side of the outer wall of the pressure sensor 1 to stabilize the connector 3. A mounting mechanism 6 is provided at the bottom of the pressure sensor 1 to fix the pressure sensor 1 to the aircraft. The fixing mechanism 5 includes two fixing blocks 501, both fixedly connected to the front and rear ends of the left side of the outer wall of the pressure sensor 1. A pull rod 502 passes through the outer wall of the fixing block 501, and a spring is provided on the outer wall of the pull rod 502. 503, spring 503 is used to rebound so that clamping block 504 clamps limiting block 505. Clamping block 504 is fixedly connected to the adjacent ends of the outer walls of the two pull rods 502. Pull rod 502 drives clamping block 504 to compress spring 503. Limiting block 505 is fixedly connected to the right side of the outer wall of connector 3. Limiting block 505 is engaged with clamping block 504. An auxiliary component 506 is provided on the left side of the outer wall of pressure sensor 1. The auxiliary component 506 includes pull ring 5061. Two pull rings 5061 are fixedly connected to the opposite ends of the outer walls of the two pull rods 502. Pull ring 5061 is used to facilitate the operation of pull rod 502 to separate clamping block 504. Rubber sleeve 5062 is installed on the outer wall of pull ring 5061. Rubber sleeve 5062 is used to enhance anti-slip and operation comfort. Pull rod 502 is slidably connected to fixed block 501. Two springs 503 are set on the adjacent side of the outer wall of fixed block 501.

[0026] Specifically, the fixing mechanism 5 is used to stabilize the connector 3, and the mounting mechanism 6 is used to fix the pressure sensor 1 on the aircraft. Pulling the pull rings 5061 on both sides outward causes the clamping block 504 to compress the spring 503 through the action of the pull rod 502. Then, the connector 3 is inserted into the receiving hole 2 on the left side of the pressure sensor 1. After releasing the pull ring 5061, the rebound force of the spring 503 will fasten the clamping block 504 to the limiting block 505, thereby ensuring the stable connection between the connector 3 and the receiving hole 2. The design of the pull ring 5061 makes it easy for the operator to separate the pull rod 502 and the clamping block 504, realizing the stability of the connection and the convenience of operation, and ensuring the reliability and efficiency of signal transmission between the pressure sensor 1 and the connector 3 during the test flight. The rubber sleeve 5062 is used to enhance the anti-slip properties and operating comfort.

[0027] Please see Figure 3 and Figure 5 The mounting mechanism 6 includes a second fixing block 601, which is fixedly connected to the right side of the bottom wall of the pressure sensor 1. A hollow block 602 is fixedly connected to the right side of the outer wall of the second fixing block 601. The second fixing block 601 supports the hollow block 602 and provides sliding guidance for the connecting rod 603. The connecting rod 603 is slidably connected to the inner wall of the hollow block 602. A U-shaped locking block 604 is fixedly connected to the left end of the outer wall of the connecting rod 603. A base plate 605 is provided at the bottom of the pressure sensor 1. A slot block 606 is fixedly connected to the front and rear ends of the left side of the top wall of the base plate 605. A driving assembly 607 is provided at the bottom of the pressure sensor 1. The driving assembly 607 includes an eccentric wheel 6071. The eccentric wheel 6071 pulls the connecting rod 603 to slide inside the hollow block 602. A threaded hole 6072 is provided on the front side of the outer wall of the eccentric wheel 6071. A handle 6073 is threadedly connected to the inner wall of the threaded hole 6072. The handle 6073 is fixed to the eccentric wheel 6071 through the threaded hole 6072. The handle 6073 drives the eccentric wheel 6071 to rotate. The connecting rod 603 passes through the right side of the outer wall of the fixed block 601. The slot block 606 engages with the U-shaped slot block 604. The U-shaped slot block 604 on the connecting rod 603 engages with the slot block 606 on the base plate 605, realizing the quick installation of the pressure sensor 1 and the aircraft base plate 605.

[0028] Specifically, first, the base plate 605 is installed on the aircraft. Next, the pressure sensor 1 is placed on the base plate 605. Then, the handle 6073 is fixed to the eccentric wheel 6071 through the threaded hole 6072. Rotating the handle 6073 causes the eccentric wheel 6071 to rotate, which in turn pulls the connecting rod 603 to slide within the hollow block 602. This allows the U-shaped locking block 604 on the connecting rod 603 to engage with the locking slot block 606 on the base plate 605, thus achieving rapid installation of the pressure sensor 1 on the aircraft base plate 605. Finally, the handle 6073 is removed from the eccentric wheel 6071 to reduce wind resistance during flight testing and prevent it from affecting the accuracy of flight test data or increasing flight energy consumption.

[0029] Please see Figure 3 and Figure 4 The bottom of the pressure sensor 1 is provided with an adhesive layer 7, which is installed on the bottom wall of the base plate 605. The adhesive layer 7 is used to fix the base plate 605 to the aircraft. The front and rear ends of the left side of the outer wall of the pressure sensor 1 are provided with unlocking holes 8 and fixing holes 9. The front and rear ends of the left side of the outer wall of the pressure sensor 1 are provided with pins 10. The unlocking holes 8 and the pins 10 are engaged. Pulling the pull ring 5061 will pass the pins 10 through the pull ring 5061 and insert them into the unlocking holes 8. The clamping block 504 cannot rebound under the action of the spring 503, avoiding interference between the clamping block 504 and the connector 3, and facilitating the smooth insertion of the connector 3 into the middle of the connector hole 2. The fixing holes 9 and the pins 10 are engaged. By passing the pins 10 through the pull ring 5061 and inserting them into the fixing holes 9, the pull rod 502 on the pull ring 5061 can be prevented from loosening.

[0030] Specifically, the adhesive layer 7 is used to fix the base plate 605 to the aircraft. Pulling the pull ring 5061 will insert the pin 10 through the pull ring 5061 into the unlocking hole 8. The clamp 504 cannot rebound under the action of the spring 503, thus avoiding interference between the clamp 504 and the connector 3, and facilitating the smooth insertion of the connector 3 into the middle of the connector hole 2. By inserting the pin 10 through the pull ring 5061 into the fixing hole 9, the pull rod 502 on the pull ring 5061 can be prevented from loosening.

[0031] Working principle: First, pull the two pull rings 5061 outward. The pull rings 5061 drive the clamping block 504 to compress the spring 503 through the pull rod 502. Then, insert the connector 3 into the connection hole 2 on the left side of the pressure sensor 1. Release the pull rings 5061. The spring 503 rebounds and clamps the limit block 505 with the clamping block 504, thereby stabilizing the connection between the connector 3 and the connection hole 2. The pull rings 5061 facilitate the operation of the pull rod 502 to separate the clamping block 504, realizing connection stability and operation convenience, and ensuring the reliability and efficiency of signal transmission between the pressure sensor 1 and the connector 3 during the test flight.

[0032] First, install the base plate 605 on the aircraft. Then, place the pressure sensor 1 on the base plate 605. Fix the handle 6073 to the eccentric wheel 6071 through the threaded hole 6072. Rotate the handle 6073 to drive the eccentric wheel 6071 to rotate. The eccentric wheel 6071 pulls the connecting rod 603 to slide in the hollow block 602, so that the U-shaped locking block 604 on the connecting rod 603 engages with the locking slot block 606 on the base plate 605, realizing the quick installation of the pressure sensor 1 to the aircraft base plate 605. Finally, rotate the handle 6073 off the upper eccentric wheel 6071 to reduce wind resistance during the test flight and prevent it from affecting the accuracy of the test flight data or increasing flight energy consumption.

[0033] The above-disclosed embodiments are merely one or more preferred embodiments of this application and should not be construed as limiting the scope of this application. Those skilled in the art can understand that all or part of the processes for implementing the above embodiments and equivalent changes made in accordance with the claims of this application still fall within the scope of this application.

Claims

1. A pressure measuring device for use in flight testing of an aircraft, comprising a pressure sensor, characterised in that: The pressure sensor has a fixed connection hole on the left side of its outer wall, and a connector is provided on the left side of the outer wall of the connection hole. The connection hole and the connector engage. A cable is installed on the left side of the outer wall of the connector. A fixing mechanism is installed on the left side of the outer wall of the pressure sensor. The fixing mechanism is used to stabilize the connector. An installation mechanism is provided at the bottom of the pressure sensor. The installation mechanism is used to fix the pressure sensor on the aircraft. The fixing mechanism includes a fixing block 1. Two fixing blocks 1 are fixedly connected to the front and rear ends of the left side of the outer wall of the pressure sensor. A pull rod passes through the outer wall of the fixing block 1. A spring is provided on the outer wall of the pull rod. A clamping block is fixedly connected to one adjacent end of the outer wall of the two pull rods. A limit block is fixedly connected to the right side of the outer wall of the connector. The limit block engages with the clamping block. An auxiliary component is provided on the left side of the outer wall of the pressure sensor.

2. A pressure measuring device for use in flight testing of an aircraft as claimed in claim 1, wherein: The auxiliary component includes pull rings, two of which are fixedly connected to the outer walls of the two pull rods at opposite ends, and the outer walls of the pull rings are fitted with rubber sleeves.

3. The pressure-measuring device for flight testing of an aircraft according to claim 1, characterized in that The installation mechanism includes a second fixing block, which is fixedly connected to the right side of the bottom wall of the pressure sensor. A hollow block is fixedly connected to the right side of the outer wall of the second fixing block. A connecting rod is slidably connected to the inner wall of the hollow block. A U-shaped locking block is fixedly connected to the left end of the outer wall of the connecting rod. A base plate is provided at the bottom of the pressure sensor. A slot block is fixedly connected to the front and rear ends of the left side of the top wall of the base plate. A driving assembly is provided at the bottom of the pressure sensor.

4. A pressure-measuring device for use in flight testing of an aircraft according to claim 3, characterized in that: The drive assembly includes an eccentric wheel, which is rotatably connected to the right end of the outer wall of the connecting rod. A threaded hole is provided on the front side of the outer wall of the eccentric wheel, and a handle is threadedly connected to the inner wall of the threaded hole.

5. The pressure-measuring device for flight testing of an aircraft according to claim 1, characterized in that The pull rod is slidably connected to the fixed block, and the two springs are both located on adjacent sides of the outer wall of the fixed block.

6. A pressure-measuring device for use in flight testing of an aircraft as defined in claim 3, characterized in that: The connecting rod passes through the right side of the outer wall of the second fixing block, and the slot block engages with the U-shaped card block.

7. A pressure-measuring device for use in flight testing of an aircraft as defined in claim 3, characterized in that: An adhesive layer is provided at the bottom of the pressure sensor, and the adhesive layer is installed on the bottom wall of the base plate.

8. The pressure-measuring device for flight testing of an aircraft according to claim 1, characterized in that: The pressure sensor has unlocking holes at both the front and rear ends of the left side of its outer wall, fixing holes at both the front and rear ends of the left side of its outer wall, and pins at both the front and rear ends of the left side of its outer wall. The unlocking holes engage with the pins, and the fixing holes engage with the pins.

Images